NASA Technical Paper 1510 Aerodynamic Performance of Axial-Flow Fan Stage Operated at Nine Inlet Guide Vane Angles Royce D. Moore and Lonnie Reid SEPTEMBER 1979 fVI/NSA UNIVERSITY OF ILLINOIS-URBANA 3 0112 106725762 NASA Technical Paper 1510 Aerodynamic Performance of Axial-Flow Fan Stage Operated at Nine Inlet Guide Vane Angles Royce D. Moore and Lonnie Reid Lewis Research Center Cleveland, Ohio NASA National Aeronautics and Space Administration Scientific and Technical Information Branch 1979 Digitized by the Internet Archive in 2012 with funding from University of Illinois Urbana-Champaign http://archive.org/details/aerodynamicperfoOOmoor SUMMARY The overall performance of a fan stage suitable for vertical-lift aircraft is pre- sented for nine inlet guide vane angle settings. Data were obtained over the stable flow range at speeds from 60 to 120 percent of design for vane setting angles from -25° to 42.5°. At design speed and design inlet guide vane angle, the stage had a peak effi- ciency of 0.892 at a pressure ratio of 1.322 and a flow of 25. 31 kilograms per second. The stall margin based on flow and pressure ratio at peak efficiency and stall was 20 percent. Based on an operating line passing through the peak efficiency point at the design setting angle, the useful operating range of the stage at design speed is limited by stall at the positive setting angles (32.5 ) and by choke at the negative angles (-17.5 ). The calculated static thrust along the operating line varied from 68 to 114 percent of that ob- tained at the design setting angle. INTRODUCTION The research program on axial-flow fans and compressors for advanced air breath- ing engines being conducted at the NASA Lewis Research Center is primarily directed toward improving the performance and reducing the size, weight, and cost of these components. As a part of this program, experimental studies have been conducted on fan stages with variable-pitch-rotor-blades suitable for use in engines for powered-lift aircraft (refs. 1 to 7). The results from these investigations indicated that some of the various flight requirements could be achieved using engines with such fan stages. The Lewis Research Center is studying various engine concepts for vertical-lift aircraft. Not only are the cruise requirements more demanding than those for powered- lift aircraft, there is also a takeoff and landing requirement that the thrust for each en- gine be varied to provide aircraft stability control. Two of the methods being consid- ered for varying the thrust are the use of variable-pitch rotor blades and the use of var- iable inlet guide vanes. The performance of a fan stage with variable-pitch rotor blades operating over a range of angle settings is presented in reference 8. The performance of the same fan stage with the rotor blades at a fixed setting angle is presented in the report for nine inlet guide vane angles. The variable inlet guide vanes were designed and fabricated by Hamilton Standard Division of the United Technologies Corporation to be added to the 1. 38-pressure-ratio variable-pitch- rotor fan stage previously tested. The stage with the inlet guide vanes was tested by Lewis at speeds from 60 to 120 percent of design and inlet guide vane angles from -25 to 42.5 . It was anticipated that this angle variation would give a sig- nificant range in fan thrust at design speed. This report presents the overall perform- ance of the stage operated at nine inlet guide vane setting angles. TEST STAGE The test stage (figs. 1 and 2), designated stage 57M2, was designed and fabricated by the Hamilton Standard Division of the United Technologies Corporation. The rotor and stator are those described in reference 8. The inlet guide vanes (IGV's) were designed to be added to that stage. From the previous tests on the fan stage (ref. 8), it appears that the efficiency would be optimum at a rotor setting angle of 6° (closed) . Thus the rotor-blade setting angle for stage 57M2 was set at 6°. The casing diameter above the rotor tip was constant, and the rotor was machined to have a constant clearance from blade leading to trailing edge. The 20 inlet guide vanes were of NACA 63-009 series profiles. In their design position the vanes are alined to the axial direction. As shown in figure 3, the front portion of the blades was stationary, and the rear portion was movable. The stage was tested with the inlet guide vanes set at nine angles. Listed below are the stage designations for each setting angle: Stage Inlet guide vane setting angle, deg from design 57M2A 57M2B -10.0 57M2C -17.5 57M2D -25.0 57M2E 10.0 57M2F 17.5 57M2G 25.0 57M2H 32.5 57M2I 42.5 APPARATUS AND PROCEDURE Test Facility The fan stage was tested in the Lewis single-stage compressor test facility, which is diagramed in figure 4. Atmospheric air enters the test facility at a inlet located on the roof of the building, and flows through the flow measuring orifice into the plenum chamber upstream of the test stage. The air then passes through the experimental fan stage into the collector and is exhausted to the facility exhaust system. Instrumentation The fan flow was determined from the measurements on a calibrated thin-plate ori- fice that was 38.9 centimeters in diameter. The orifice temperature was determined from an average of two Chromel-Constantan thermocouples. Orifice pressures were measured by calibrated transducers. Radial surveys of the flow were made upstream of the IGV's, between the IGV's and the rotor, between the rotor and the stator, and downstream of the stator (see fig. 1 for axial locations). Photographs of the survey instrumentation are shown in figure 5. At stations and 2 total pressure, total temperature, and flow angle were measured with the combination probe (fig. 5(a)), and the static pressure was measured with an 18° wedge probe (fig. 5(b)). At stations 1 and 3 total pressure and total temperature were measured with the nine-element radial rake (figs. 5(c) and (d)) . The static pressure and flow angle were determined from the wedge probe. Each probe was positioned with a null-balancing stream-direction-sensitive control system that automatically alined the probe to the direction of flow. At station 3 the rakes were set straight ahead. At station 1 the rakes were set to match the IGV angle. The thermocouples were Chromel- Constantan for both the combination probe and the rake. Inner- and outer-wall static-pressure taps were located at approximately the same axial stations as the survey instrumentation. The circumferential locations of the sur- vey instrumentation along with the inner- and outer-wall static-pressure taps are shown in figure 6. An electronic speed counter, in conjunction with a magnetic pickup, was used to measure rotative speed (rpm). The estimated errors of the data based on inherent accuracies of the instrumenta- tion and recording system are as follows: Airflow, kg/sec ±0.3 Rotative speed, rpm ±30 Flow angle, deg ±1.0 3 Temperature, K ±0.6 o Rotor-inlet total pressure, N/cm ±0.04 o Rotor-outlet total pressure, N/cm ±0.10 2 Stator-outlet total pressure, N/cm ±0.10 2 Rotor-inlet static pressure, N/cm ±0.04 2 Rotor-outlet static pressure, N/cm ±0.10 2 Stator-outlet static pressure, N/cm ±0.10 2 IGV inlet total pressure, N/cm ±0.01 2 IGV inlet static pressure, N/cm ±0.04 Test Procedure The stage survey data for each configuration were taken over a range of speeds from 60 to 120 percent of design speed and a range of flows from maximum to near- stall conditions. The data were recorded at nine radial positions for each speed and weight flow. The combination probes at stations and 2 and the wedge probes at all stations were traversed radially at the same time the nine-element rakes at stations 1 and 3 were traversed circumferentially. The wedge probes were set at midgap because previous studies showed that the static pressure across the stator gap was constant. The probes and rakes were set at their initial position and values of pressure, temper- ature, and flow angle were recorded. The instruments are then traversed to their next scheduled position, and data were again recorded. When the rakes are at their last circumferential position, the probes are at their last radial position. Calculation Procedure Measured values of total pressure, static pressure, and total temperature were corrected for Mach number and streamline slope. These corrections were based on an average calibration for the type of instrument used. Orifice airflow, rotative speed, static and total pressures, and total temperatures were all corrected to standard-day conditions based on the IGV inlet condition. For the data reduction program the circumferential distributions of static pressure and flow angle downstream of the inlet guide vane (station 1) and stator (station 3) were assumed to be constant for each radial position and equal to the measured midgap val- ues. The nine values of total temperature were mass-averaged to obtain the stator- outlet temperature. The nine values of total pressure were converted to their enthalpy equivalents and then mass averaged. To obtain the overall performance, the radial values of total temperature were mass averaged, and the values of total pressure were converted to their enthalpy equiv- alent and then mass averaged as before. The sea-level static thrust is composed of both the momentum thrust and the pres- sure thrust. The momentum thrust is a product of the flow rate and the outlet velocity. The pressure thrust consists of a product of the outlet area and the difference between outlet static pressure and inlet total pressure. The symbols and equations are defined in appendixes A and B. The weight flow at stall was obtained in the following manner: during operation at the near-stall condition, the collector valve was slowly closed in small increments. At each increment the air flow was obtained. The air flow obtained just before stall oc- curred is defined as the stall air flow. The pressure ratio at stall was obtained by ex- trapolating the total pressure obtained from the survey data to the stall air flow. RESULTS AND DISCUSSION The results from this investigation are presented in three sections. The overall performance of the rotor and stage for the design inlet guide vane angle are presented first. (The rotor is the same as that presented in ref. 8, but the blades are set at 6° closed.) The effects of vane angle on the overall performance are then presented. Finally, the effects of vane angle on calculated static thrust are discussed. The overall performances for all nine inlet guide vane angles are presented in tables I to K. Performance with IGV at Design Angle The overall performance for the rotor and stage are presented in figures 7 and 8, respectively. Pressure ratio and adiabatic efficiency are presented at several flows for speeds of 60, 70, 80, 90, 100, 110, and 120 percent of design. The stall line is also shown for the overall stage performance (fig. 8). At design speed the rotor had a peak efficiency of 0.905. It occurred at a flow of 24.06 kilograms per second and a pressure ratio of 1. 361. The stage peak efficiency of 0.892 occurred at a pressure ratio of 1. 322 and a flow of 25. 31 kilograms per sec- ond. The stall margin was 20 percent based on flow and pressure ratio at stall and peak efficiency. Performance Over Range of IGV Setting Angles Performance curves for the inlet guide vanes set at nine vane setting angles for the 100 and 120 percent of design speeds are shown in figure 9. The stall lines are shown in each figure. The operating line, which passes through the design-speed peak- efficiency point at the 0° vane angle, was obtained by setting a constant throttle valve position and varying the IGV setting angle during tests. At both the 100 and 120 percent of design speeds, the pressure ratio and flow in- crease as the inlet guide vane setting angle is changed from 42.5° to -17.5°. However, a change in the flow characteristics is apparent as the setting angle is further changed to -25°. At design speed the flow -pressure ratio curve for -25° is essentially the same as that for -17.5° except near the stall line. The data presented were corrected to standard-day conditions at the IGV inlet. Had the data been corrected to rotor-inlet conditions, the flow-pressure ratio curve for -25° would not have been the same as that for -17.5°. At a setting angle of -25° the pressure losses across the IGV are consider- ably greater than those at -17.5°. For equivalent IGV inlet flows, the rotor will be op- erating at a higher corrected airflow at an angle of -25° than at -17.5°. At 120 percent design speed the flow-pressure ratio curve for -25° has dropped and is between those at the 0° and -10° angles. Preliminary survey data at 120 percent design speed (not presented in this report) indicate that the rotor tip element is choked even at a setting angle of 0°. Turning the inlet guide vanes to more negative angles caused this choked region to move further down the rotor blades. There is a considerable variation in peak efficiency over the range of vane setting angles. At 42.5° the design speed peak efficiency is 0.676. It continues to increase to a maximum of 0.892 at 0° and then decreases to 0.795 at -25°. There is a similar change in peak efficiency at 120 percent of design speed; however, the maximum value occurs at an angle of 10 . Based on the operating line presented, the useful range of inlet-guide-vane setting angle is limited: At the high negative angles, the stage choked; at the high positive angles, the stage stalled. Calculated Thrust The primary purpose of the variable inlet guide vane in this fan stage is to provide thrust modulation capability at constant blade speed. The effect of vane-angle variation on the calculated static thrust is presented in figure 10. Maximum calculated static thrust and operating line static thrust are presented for both the 100 and 120 percent of design speeds. At 100 percent of design speed (fig. 10(a)) the operating-line static thrust is nearly equal to maximum values except at the higher negative vane setting angles. At 120 per- cent of design speed the differences are more significant over the setting angle range. At design speed the operating line calculated static thrust varied from 3900 to 6500 new- tons, which corresponds to 68 to 114 percent of that obtained at as the inlet guide vane angle was changed from 32.5° to -17.5°. The lower limit was due to the operating line crossing the stall line and the upper limit was set by choking. In the application of this stage in an engine, a variable area exit nozzle would probably be required to achieve a wider range of thrust. At the more negative angles, more thrust could be realized by reducing the area (and flow); while at the more positive angles, increasing the area would move the operating line away from stall and would allow for further re- ductions in thrust. SUMMARY OF RESULTS The overall performance of a fan stage suitable for vertical-lift aircraft and incor- porating variable inlet guide vanes was determined for nine vane setting angles. Data were obtained over the stable flow range at rotative speeds from 60 to 120 percent of design. The vane angle was varied from 42. 5° to -25°. The following were the prin- cipal results of the investigation: 1. At the design speed and the design inlet guide vane angle, the stage had a peak efficiency of 0.892 at a pressure ratio of 1.322 and a flow of 25. 31 kilograms per sec- ond. The stall margin based on peak efficiency and stall was 20 percent. 2. Based on an operating line passing through the peak efficient point at the design vane setting angle, the useful operating range of the stage at design speed is limited by stall at the high positive setting angles (32.5°) and by choke at high negative setting angles (-17.5°). 3. At design speed the calculated static thrust along an operating line varied from 68 to 114 percent of that obtained at a vane angle of 0° as the inlet guide vanes were changed from 32.5° to -17.5°. Lewis Research Center, National Aeronautics and Space Administration, Cleveland, Ohio, May 9, 1979, 505-04. APPENDIX A SYMBOLS A 2 area, m 2 A annulus area at inlet guide vane leading edge, m 2 A f frontal area at inlet guide vane leading edge, m C specific heat at constant pressure, 1004 J /kg K N rotative speed, rpm 2 P total pressure, N/cm 2 p static pressure, N/cm SM stall margin T total temperature, K U wheel speed, m/sec V air speed, m/sec W airflow, kg/sec y ratio of specific heats 5 ratio of inlet guide vane inlet total pressure to standard pressure of 10.13 N/cm 2 r\ efficiency 6 ratio of inlet guide vane inlet total temperature to standard temperature at 288.2 K p density, kg /sec Subscripts: ad adiabatic LE blade leading edge mom momentum-rise TE blade trailing edge z axial direction 6 tangential direction Definitions and Units Used in Tables: 2 AREA area, m AIRFLOW equivalent airflow, kg/sec ROTATIVE SPEED rotative speed, rpm APPENDIX B EQUATIONS Adiabatic (temperature rise) efficiency - v(r-D/r TE , P LE "ad T TE j t le" Momentum- rise efficiency / P \(7-i)/y "mom ( uv e ) TE - ( uv 9 ) LE T LE C p Equivalent airflow Equivalent rotative speed Airflow per unit annulus area wVe _N_ wVe \ a„_ 10 Airflow per unit frontal area A f (B6) Head -rise coefficient C p T LE U Up \(y-D/y *TE LE (B7) Flow coefficient Static thrust - U tip/LE (B8) Stall margin SM \ P LE /stall v \j /ref W TE P LE/ref V 6 /sta11 V£ - 1 xlOO (B9) pV z A TE + (p TE - P LE )A TE (BIO) 11 REFERENCES 1. Kovich, George; and Steinke, Ronald J.: Performance of a Low-Pressure-Ratio Low- Tip Speed Fan Stage with Blade Tip Solidity of 0.65. NASA TM X-3341, 1976. 2. Kovich, George; Tysl, Edward R.; and Moore, Royce D.: Performance of a Low- Pressure Ratio Fan Stage at Two Off- Design Blade Setting Angles. NASA TM X-3447, 1977. 3. Lewis, George W., Jr.; Moore, Royce D.; and Kovich, George: Performance of a 1.20 Pressure- Ratio STOL Fan Stage at Three Rotor Blade Setting Angles. NASA TM X-2837, 1973. 4. Lewis, George W. , Jr.; and Tysl, Edward R.: Overall and Blade-Element Per- formance of a 1.20-Pressure-Ratio Fan Stage at Design Blade Setting Angle. NASA TM X-3101, 1974. 5. Lewis, George W. , Jr.; Osborn, Walter M.; and Moore, Royce D. : Overall and Blade- Element Performance of a 1. 20-Pressure Ratio Fan Stage with Rotor Blades Reset Minus 5°. NASA TM X-3338, 1976. 6. Lewis, George W. , Jr.; and Kovich, George: Overall and Blade-Element Perform- ance of a 1. 20-Pressure Ratio Fan Stage with Rotor Blades Reset Minus 7°. NASA TM X-3342, 1976. 7. Moore, Royce D. ; and Kovich, George: Aerodynamic Performance of Two Variable- Pitch Fan Stages. NASA TM X-73416, 1976. 8. Moore, Royce D. ; and Osborn, Walter M.: Aerodynamic Performance of a 1.38- Pres sure- Ratio Variable- Pitch Fan Stage. NASA TP-1502, 1979. 12 TABLE I. - OVERALL PERFORMANCE OF STAGE 57M2A (a) 120 Percent of design speed READING NUMBER 16V TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO ICV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOH COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0461 0460 0459 0458 0457 0.999 0.999 0.999 0.999 0.999 1.587 1.529 1.457 1.367 1.310 0.981 0.995 0.991 0.980 0.967 1.000 1.000 0.999 0.999 0.999 1.166 1.156 1.143 1.125 1.116 0.99S 0.99S 0.995 0.996 0.995 0.849 0.826 0.796 0.746 0.688 0.894 0.876 0.832 0.765 0.718 0.394 0.354 0.308 0.250 0.213 0.371 0.395 0.407 0.409 0.410 133.33 140.60 144.42 145.07 145.23 145.67 1S3.61 157.79 158.50 158.67 27.02 28.50 29.27 29.40 29.44 27.00 28.55 29.23 29.38 29.39 27.11 28.66 29.31 29.41 29.45 25.86 27.54 28.58 28.83 29.06 27.27 28.76 29.23 28.86 29.09 13079.7 13141.7 13133.1 13122.0 13097.1 120.2 120.7 120.6 120.5 120.3 1.555 1.520 1.442 1.338 1.265 1.160 1.149 1.136 1.121 1.110 0.842 0.851 0.811 0.718 0.634 (b) 110 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0456 0454 0453 0451 0450 0.999 0.999 0.999 0.999 0.999 1.489 1.453 1.412 1.323 1.266 0.980 0.989 0.990 0.984 0.970 1.000 1.000 1.000 1.000 1.000 1.138 1.130 1.123 1.105 1.097 0.996 0.993 0.995 0.997 0.995 0.876 0.863 0.844 0.791 0.720 0.920 0.931 0.902 0.811 0.752 0.390 0.364 0.332 0.263 0.219 0.362 0.399 0.416 0.427 0.429 120.99 131.09 136.19 139.69 139.84 132.19 143.23 148.80 152.62 152.79 24.52 26.57 27.60 28.31 28.34 24.49 26.58 27.61 28.22 28.27 24.55 26.63 27.62 28.28 28.33 23.74 25.81 26.92 2^.63 27.97 24.44 26.34 27.24 27.56 27.71 11987.7 11962.0 11973.7 11968.9 11956.4 110.1 109.9 110.0 109.9 109.8 1.458 1.435 1.396 1 .300 1.227 1.133 1.123 1.117 1.102 1.091 0.858 0.885 0.857 0.765 0.662 3 Percent of design speed 0449 0448 0447 0446 0445 0.999 0.999 0.999 0.999 0.999 1.380 1.361 1.338 1.302 1.226 0.986 0.989 0.989 0.982 0.972 1.000 1.000 0.999 0.999 1.000 1.111 1.104 1.098 1.090 1.079 0.996 0.996 0.996 0.996 0.996 0.869 0.885 0.883 0.874 0.761 0.920 0.945 0.940 0.905 0.791 0.371 0.353 0.330 0.295 5.223 0.358 0.392 0.415 0.445 0.453 109.70 118.65 124.87 132.90 13S.60 119.85 129.63 136.44 145.20 148.15 22.23 24.05 25.31 26.94 27.43 22.24 24.06 25.32 26.94 ?7.40 22.22 24.06 25.35 26.95 27.43 21.52 23.52 24.83 26.50 26.84 21.96 23.62 24.74 26.16 26.67 10868.6 10858.5 10863.8 10876.6 10893.9 99.8 99.7 99.8 99.9 100.1 1.359 1.344 1.322 1.277 1.191 1.106 1 .099 1.093 1.085 1 .074 0.862 0.891 0.892 0.851 0.693 13 Continued. OVKRALL PKIU-TJKM ANCK OF STAGE 57M2A READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO ICV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY (d) 90 Percent of design speed utt 046S 0464 0463 0462 0.99? 0.999 0.999 0.999 0.999 1.295 1.278 1 .256 1.235 1.189 0.989 0.992 0.992 0.988 0.976 1 .000 0.999 0.999 0.999 0.999 1.089 1.082 1 .075 1.069 1.063 0.997 0.998 0.998 0.998 0.997 0.865 0.888 0.899 0.898 0.810 0.924 0.945 0.952 0.939 0.854 0.360 0.339 0.312 0.286 0.232 0.347 0.383 0.417 0.446 0.478 96.44 105.44 114.03 121 .13 128.83 105.37 115.20 124.58 132.34 140.75 19.55 21.37 23.11 24.55 26.11 19. S7 21.36 23.11 24. S3 26.03 19.54 21.36 23.12 24.53 26.07 19.03 20.82 22.67 24.09 25.48 19.38 21.01 22.61 23.90 2S.3S 9749.3 9735.7 9740.1 9747.6 9736.0 89.6 89.4 89. S 89.5 89.4 1.280 1.268 1.245 1.218 1.159 1.085 1 .079 1.072 1.066 1.058 0.859 0.893 0.900 0.876 0.742 (e) 80 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0471 0470 0469 0468 0467 1.000 0.999 0.999 0.999 0.999 1.228 1.214 1.194 1.177 1.153 0.992 0.992 0.990 0.984 0.976 1.000 1.000 1.000 0.999 0.999 1.070 1.063 1.057 1.053 1.048 0.998 0.998 0.998 0.997 0.997 0.869 0.900 0.907 0.903 0.859 0.930 0.963 0.963 0.954 0.910 0.349 0.327 0.297 0.272 0.236 0.345 0.388 0.425 0.4S8 0.490 86.30 96.28 104.71 111.95 119.04 94.29 105.19 114.40 122.31 130.05 17.49 19.52 21.22 22.69 24.13 17.47 19.51 21.22 22.67 24.08 17.46 19.49 21.19 22.66 24.08 16.92 19.12 20.87 22.39 23.67 17.19 18.97 20.54 21.83 23.23 8701.3 8707.3 8706.8 8689.7 8691.4 79.9 80.0 80.0 79.8 79.8 1.217 1.204 1.182 1.157 1.124 1.067 1.061 1.055 1 .049 1 .044 0.866 0.893 0.893 0.862 0.766 Percent of design speed 0477 0476 0475 0474 0473 1.000 1.000 0.999 0.999 0.999 1.169 1.1S9 1.143 1.129 1.111 0.994 0.995 0.991 0.987 0.981 1.000 1.000 1. 000 1.000 0.999 1.052 1.048 1.043 1.039 1.036 0.998 0.999 0.998 0.998 0.998 0.875 0.901 0.916 0.901 0.858 0.941 0.970 0.979 0.963 0.927 0.339 0.318 0.287 0.259 0.224 0.343 0.383 0.429 0.464 0.500 75.35 83.83 93.17 100.18 107.60 82.33 91.59 101.79 109.46 117.56 15.27 16.99 18.88 20.31 21 .81 15.31 16.99 18.91 20.29 21.79 15.28 16.98 18.88 20.28 21.77 14.82 16.61 18.66 19.96 21.28 15.00 16.52 18.28 19. S2 21 .00 7611.1 7608.9 7603.2 7600.8 7607.8 69.9 69.9 69.8 69.8 69.9 1.161 1.152 1.132 1.113 1.090 1.050 1.046 1 .040 1.037 1 .033 0.866 0.895 0.892 0.850 0.748 14 Concluded. OVERALL PERFORMANCE OF STAGE 57M2A (g) 60 Percent of design speed READING NUMBER I6V TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO I6V TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT I6V INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0481 0480 0479 0478 1.000 1.000 0.999 0.999 1.122 1.109 1.095 1.078 0.995 0.995 0.991 0.984 1.000 1.000 1.000 1.000 1.038 1.033 1.129 1.025 0.999 0.999 0.999 0.999 0.877 0.914 0.915 0.867 0.948 1.000 0.993 0.955 0.332 0.298 0.2S9 0.213 0.336 0.404 0.457 0.513 63.68 76.15 85.79 95.35 69.57 83.20 93.73 104.17 12.91 15.43 17.39 19.33 12.94 15.46 17.40 19.31 12.91 15.42 17.37 19.27 12.50 15.23 17.11 18.84 12.67 14.96 16.73 18.59 6534.2 6522.9 6534.0 6514.1 60.0 59.9 60.0 59.8 1.116 1 .103 1.084 1.060 1.037 1 .031 1.027 1.023 0.860 0.902 0.859 0.714 15 TABLE II. - OVERALL PERFORMANCE OF STAGE 57M2H (a) 120 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOH PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0506 0.998 1 .582 0.990 1.000 1.173 0.996 0.811 0.837 0.394 0.396 140.12 153.09 28.40 28.45 28.68 27.85 28.96 13057.6 119.9 .S63 .168 0502 0.998 1 .572 0.991 1.000 I .170 0.996 0.810 0.838 0.387 0.404 142.54 155.73 28.89 28.91 29.16 28.43 29.38 13068.8 120.1 1.555 1 .165 0.813 C503 0.998 1.557 0.987 0.999 1.167 0.996 0.807 0.840 0.377 0.416 146.45 160.00 29.68 29.66 29.89 29.55 29.80 13077.2 120.1 1.533 1.162 0.802 0501 0.998 1.489 0.981 0.999 1 .156 0.996 . 773 0. 796 0. 332 0. 421 143 .33 \62 .06 30 .06 29 .96 30 .17 29 .89 29 .47 308 :.a 120.2 1. 458 1. ISO 0. 757 0500 0.998 1.419 0.970 0.999 1.144 0.995 0.731 0.748 0.288 0.423 148.66 162.42 30.13 30.04 30.25 30.07 29.17 13061.5 120.0 1.374 1.138 0.690 049) 0.998 1.350 0.943 0.999 1.134 0.993 0.667 0.703 0.243 0.424 148.94 162.72 30.15 30.11 30.30 30.35 30.35 13059. .< 120. 1.271 1 .125 0.565 (b) 110 Percent of design speed READING HUMBER 0498 0497 0496 049S 0494 IGV TOTAL PRESSURE RATIO 0.999 .1.998 0.998 0.998 0.998 ROTOR TOTAL PRESSURE RATIO 1.535 1.504 1.444 1.364 1.317 STATOR TOTAL PRESSURE RATIO 0.980 0.989 0.982 0.969 0.945 IGV TOTAL TEMPERATURE RATIO 1.000 1.000 1.000 0.999 0.999 ROTOR TOTAL TEMPERATURE RATIO 1.151 1.145 1.132 1.121 1.113 STATOR TOTAL TEHPERATURE RATIO 0.996 C.996 0.997 0.996 0.995 ROTOR ADIABATIC EFFICIENCY 0.865 0.855 0.835 0.768 0.728 ROTOR MOMENTUM-RISE EFFICIENCY 0.893 0.889 0.856 0.796 0.753 ROTOR HEAD-RISE COEFFICIENT 0.427 0.404 0.357 0.297 0.260 FLOW COEFFICIENT 0.381 0.416 0.438 ".445 0.446 AIRFLOW PER UIIIT FRONTAL AREA 126.57 136.15 142.47 H4.44 144.82 AIRFLOW PER UNIT ANNULUS AREA 138.29 148.74 155.66 157.81 158.22 AIRFLOW AT ORIFICE 25.65 27.59 28.88 29.28 29.35 AIRFLOW AT IGV INLET 25.62 27.57 28.83 29.17 29.25 AIRFLOW AT ROTOR INLET 25.83 27.77 29.01 29.36 29.44 AIRFLOW AT ROTOR OUTLET 25.44 27.14 28.61 28.97 29.74 AIRFLOW AT STATOR OUTLET 25.63 27.57 27.97 28.13 29.10 ROTATIVE SPEED 11980.8 11964.4 11987.6 11965.0 11979.2 PERCENT OF DESIGN SPFED 110.1 109.9 110.1 109.9 110.0 COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIC STAGE ADIABATIC EFFICIENCY 1.502 1.146 0.841 1.485 1.139 0.859 1.415 1.128 0.812 1.319 1.115 0.718 1.243 ! .106 0.608 (c) 100 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0492 0491 0490 0489 0488 0.999 0.999 0.998 0.998 0.998 1.413 1.412 1.383 1.322 1.271 0.989 0.987 0.985 0.976 0.951 1.000 0.999 0.999 0.999 0.999 1.119 1.116 1.109 1.101 1.093 0.998 0.997 0.998 0.997 0.996 0.873 0.896 0.894 0.819 0.762 0.898 0.930 0.918 0.846 0.778 0.400 0.398 0.371 0.315 0.266 0.379 0.416 0.445 0.466 0.469 115.71 125.67 133.34 138.66 139.60 126.42 137.31 145.68 151.49 152.51 23.45 25.47 27.03 28.10 28.29 23.43 25.42 26.9/ 28.03 28.21 23.53 2S.57 27.13 28.19 28.3' 22.91 25.23 26.76 27.64 28.47 23.16 25.04 26.15 27.04 27.64 10898.7 10895.4 10898.2 10886.0 10900.9 100.1 100.1 100.1 100.0 100.1 1 .396 1.392 1.360 1.238 1.206 1 117 1.112 1.106 1.097 1 .088 0.857 0.886 0.866 0.771 0.624 16 TABLE II. - Concluded. OVERALL PERFORMANCE OF STAGE 57M2B (d) 90 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO 16V TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOHEHTUH-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOH COEFFICIENT AIRFLOW PER UHIT FRONTAL AREA AIRFLOW PER UNIT AHNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 101 0507 0.999 1 .317 0.991 0.999 1 .096 0.998 0.854 0.898 .383 .364 .10 10.45 20.49 20.48 20.59 20.11 20.24 9779.5 89.8 1.304 1.093 0.849 (e) 80 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOHEHTUH-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT AHNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0508 0.999 1.246 0.991 1.000 1 .075 0.999 0.864 0.905 0.374 0.359 89.77 98.08 18.20 18.20 18.29 18.00 17.88 8733.8 80.2 1.234 1.073 0.84S (f) 7U Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEHPERATURE RATIO STATOR TOTAL TEHPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR HOHEMTUH-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOH PER UHIT AHNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR IHLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0513 0512 0511 0510 0509 0.999 0.999 0.999 0.999 0.999 1.181 1.173 1.160 1.150 1.139 0.993 0.993 0.991 0.981 0.968 1 .000 1.000 1.000 0.999 0.999 1 .056 1.052 1.049 1.046 1.043 0.999 0.999 0.999 0.998 0.999 0.870 0.895 0.892 0.892 0.882 0.918 0.952 0.960 0.960 0.946 0.363 0.347 0.321 0.299 0.278 0.363 0.405 0.448 0.488 0.525 79.72 88.63 97.22 105.42 112.73 87.09 96.83 106.22 115.17 123.16 16.16 17.96 19.71 21 .37 22.85 16.15 17.93 19.71 21.31 22.79 16.24 18.03 19.80 21.42 22.87 15.93 17.74 19.32 21.12 22.75 15.78 17.28 18.95 20.34 21.96 '614.4 7618.1 7624.1 7620.1 7613.7 69.9 70.0 70.0 70.0 69.9 1.172 1 .164 1.149 1.127 1 .102 1.054 1 .051 1.047 1.043 1 .041 0.855 0.879 0.865 0.800 0.685 (g) 60 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEHPERATURE RATIO ROTOR TOTAL TEHPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR r.OUENTUH-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOH PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANHULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COHPRESSOR PERFORHANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEHPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0514 1.000 1.130 0.995 1.000 1.040 0.999 0.880 0.926 0.349 0.369 70.34 76.85 14.26 14.28 14.38 14.03 13.81 6582.0 60.5 1.124 1 .040 0.860 17 OVKKAU, PERFORMANCE OF STAGE 57M2C (a) 12u Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR AOIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE AOIABATIC EFFICIENCT 0S54 0553 0552 0551 0550 0.992 0.989 0.988 0.988 0.988 1.402 1.572 1.514 1.443 1 .404 0.988 0.97S 0.958 0.943 0.929 0.999 0.999 0.998 0.998 0.999 1.187 1.178 1.149 1 .159 1.148 0.994 0.994 0.993 0.993 0.994 0.770 0.775 0.747 0.720 0.493 0.804 0.794 0.749 0.739 0.708 0.410 0.389 0.355 0.321 0.282 0.401 0.424 0.427 0.428 0.429 142.19 148.73 149.59 150.04 150.19 1SS.35 142.50 143.43 143.93 144.09 28.82 30.15 30.32 30.41 30.44 28.78 30.11 30.21 30.28 30.33 28.95 30.12 30.25 30.33 30.34 28.31 30.04 30.42 31.30 31.25 29.14 29.42 29.17 29.25 30.54 13042.3 13058.9 13017.5 13018.9 13035.4 120.0 120.0 119.4 119.4 119.7 1.570 1.515 1.433 1.344 1.291 1.181 1.172 1.159 1.150 1.142 0.741 0.733 0.482 0.420 5.532 (b) 110 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR AOIABATIC EFFICIENCT ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0S24 0.994 1.528 0.994 1.000 1.159 0.997 0.812 0.849 0.424 0.411 134.82 147.29 27.33 27.31 27.52 24.19 27.30 11973.7 110.0 1.510 1.155 0.805 0525 0.992 1.513 0.987 0.999 1.154 0.997 0.814 0.847 0.414 0.434 141.01 154.04 28.58 28.57 28.74 27.79 28.09 11971. 4 110.0 1.482 1.149 0.797 0524 0.991 1.474 0.975 0.999 1.148 0.995 0.795 0.829 0.384 0.449 145.32 158.77 29.44 29.34 29. SO 29.01 28.43 11948.3 109.9 1.424 1.141 0.753 0523 0.990 1.421 0.957 0.999 1.138 0.995 0.744 0.800 0.344 0.452 144.37 159.91 29.47 29.54 29.44 30.02 28.43 11951.3 109.8 1.347 1.131 0.477 0522 0.989 1.340 0.934 0.999 1.128 0.994 0.719 0.759 .294 .454 144.83 140.42 29.74 29.44 29.75 30.32 30.04 11944.9 109.9 1.240 1.122 0.559 (c) 100 Percent of design READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCT ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE AOIABATIC EFFICIENCT 0521 0520 0519 0518 0517 0.997 0.995 0.994 0.993 0.992 1.440 1.444 1.418 1.370 1.314 0.987 0.990 0.988 0.948 0.944 0.999 1.000 0.999 0.999 0.999 1.129 1.128 1.122 1.115 1.105 0.998 0.997 0.998 0.994 0.998 0.849 0.870 0.858 0.818 0.774 0.884 0.910 0.895 0.855 0.813 0.429 0.434 0.407 0.343 0.310 0.390 0.432 0.457 0.478 0.482 118.54 129.57 134.38 141.41 142.51 129.53 141.54 149.00 154.50 155.49 24.03 24.24 27.44 28.44 28.88 23.98 24.23 27.54 28.57 28.80 24.13 24.37 27.73 28.72 28.94 23.71 25.58 24.88 28.32 28.99 23.77 25.84 24.73 27.40 28.74 10848.8 10873.7 10874.0 10844.4 1088S.8 99.8 99.9 99.9 99.8 100.0 1.417 1.424 1.393 1.317 1.234 1.124 1 .123 1.119 1.110 1.101 0.833 0.844 0.833 0.742 0.411 18 TABLE III. - Continued. OVERALL PERFORMANCE OF STAGE 57M2C READING NUMBER I6V TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT percent of design speed 0547 0544 054S 0544 0543 0.997 0.997 0.995 0.994 0.994 1.338 1.343 1.324 1.302 1.264 0.990 0.987 0.983 0.964 0.945 0.999 0.999 0.999 0.999 0.999 1.103 1.099 1.094 1 .091 1.086 0.998 0.998 0.998 0.997 0.998 0.844 0.886 0.884 0.858 0.809 0.882 0.921 0.931 0.900 0.860 0.407 0.409 0.389 0.362 0.320 0.388 0.429 0.474 0.504 0.512 107.32 118.12 128.68 135.63 137.53 117.26 129.05 140.59 148.19 150.26 21.75 23.94 26.08 27.49 27.88 21.77 23.91 26.02 27.46 27.76 21.77 23.95 26.10 27.55 27.87 21.45 23.62 25.50 27.44 27.86 21.28 23.16 24.90 26.38 27.11 9811.3 9834.3 9800. S 9820.5 9792.0 90.1 90.3 90.0 90.2 90.0 1.321 1.321 1.295 1.248 1.188 1 .099 1 .096 1.091 1 .087 1.082 0.833 0.860 0.843 0.748 0.614 (e) 80 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCT ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0542 0541 0540 0539 0538 0.998 0.998 0.997 0.994 0.996 1.254 1.253 1.244 1.233 1.214 0.991 0.989 0.983 0.970 0.951 1.000 1.000 0.999 1.000 0.999 1.079 1.076 1.073 1.069 1.044 0.999 0.998 0.997 0.998 0.998 0.848 0.878 0.887 0.891 0.871 0.872 0.915 0.941 0.938 0.934 0.391 0.387 0.374 0.354 0.331 0.370 0.419 0.466 0.507 0.537 91.87 103.33 113.74 123.17 129.18 100.37 112.89 124.26 134.57 141.13 18.62 20.94 23.05 24.97 24.18 18.65 20.94 23.06 24.92 24.14 18.65 20.96 23.08 24.93 24.19 18.28 20.66 22.76 24.73 24.13 18.21 20.10 21.91 23.79 25.24 8687.5 8707.8 8703.0 8719.2 8698.7 79.8 80.0 79.9 80.1 79.9 1.241 1.237 1.219 1.190 1.151 1.077 1.073 1.069 1 .066 1 .063 0.821 0.853 0.841 0.769 0.647 (f) 70 percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCT ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PEkFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0537 0536 0535 0534 0533 0.999 0.998 0.998 0.997 0.997 1.191 1.189 1.180 1.171 1.161 0.993 0.991 0.985 0.975 0.960 1.000 1.000 0.999 0.999 0.999 1.061 1.058 1.054 1.052 1.049 0.999 0.998 0.999 0.999 0.999 0.844 0.870 0.889 0.894 0.887 0.864 0.913 0.946 0.951 0.960 0.382 0.377 0.358 0.341 0.321 0.359 0.413 0.471 0.509 0.545 78.87 90.12 101.84 109.80 116.77 84.17 98.44 111.27 119.96 127.57 15.99 18.27 20.64 22.25 23.47 14.00 18.29 20.66 22.22 23.40 15.99 18.27 20.65 22.25 23.43 15.65 17.99 20.39 22.05 23.52 15.66 17.50 19.69 21 .25 22.44 7620.5 7429.3 7631.8 7636.2 7630.4 70.0 70.1 70.1 70.1 70.1 1 .181 1 .174 1.159 1.139 1 -lit 1 .060 1.056 1 .052 1 .050 1.048 0.817 0.845 0.828 0.760 0.639 19 TABLE III. - Concluded. OVERALL PERFORMANCE OF STAGE 57M2C (g) 60 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUfl-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA A1RFL0M PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0530 0529 0528 0527 0.99? 0.999 0.998 0.998 1.138 1.133 1.124 1.113 .995 0.993 0.984 0.970 1.000 1.000 0.999 0.999 1.044 1.041 1.038 1.035 1.000 0.999 0.999 0.999 0.857 0.883 0.898 0.892 0.889 0.951 0.973 0.985 0.374 0.358 0.335 0.307 0.354 0.433 0.496 0.551 67.74 81.69 93.20 102.84 74.03 89.25 101.83 112.36 13.73 16.56 18.89 20.84 13.75 16.58 18.86 20.79 13.84 16.64 18.91 20.87 13.51 16.27 18.70 20.69 13.43 15.86 18.08 19.98 6559.6 6561.0 6562.0 6560.9 60.3 60.3 60.3 60.3 1.131 1.123 1.104 1.077 1 .044 1.040 1 .036 1.034 0.822 0.854 0.794 0.639 20 TABLE IV. - OVERALL PERFORMANCE OF STAGE 57M2D (a) 120 Percent of design speed READIH6 MUMBER ISV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOHEIiTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOM COEFFICIENT AIRFLOU PER UNIT FRONTAL AREA AIRFLOW PER UNIT AHNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0578 0577 0576 0575 0574 0.981 0.974 0.973 0.971 0.971 1.646 1.597 1.541 1.459 1.401 0.965 0.958 0.945 0.949 0.933 0.999 0.999 0.999 0.999 0.999 1.207 1.197 1.184 1.168 1.159 0.993 0.994 0.997 1.003 1.004 0.739 0.727 0.715 0.676 0.636 0.743 0.726 0.697 0.648 0.619 0.443 0.409 0.372 0.316 0.281 0.395 0.415 0.418 0.417 0.419 140.15 145.82 147.19 147.04 147.23 153.12 159.31 160.81 160.65 160.86 28.41 29.56 29.83 29.80 29.84 28.44 29.61 29.81 29.83 29.83 28.75 29.81 29.95 29.90 29.93 29.14 30.01 31.09 30.53 30.32 28.71 28.50 28.42 28.71 29.99 13065.5 13077.5 13084.0 13117.3 13061.9 120.0 120.1 120.2 120.5 120.0 1.557 1.49! 1 .417 1 .344 1 .270 1.198 1.191 1 .179 1 .171 1 .162 0.682 0.634 0.585 0.515 0.435 (b) 110 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEHPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 0573 0572 0571 0570 0569 0.985 0.979 0.977 0.976 0.976 1.558 1 .530 1.485 1.428 1.364 0.983 0.970 0.959 0.950 0.944 0.999 0.999 0.999 0.999 0.999 1.173 1 .165 1.158 1.149 1.139 0.996 .998 0.997 0.999 1.001 0.783 0.784 0.758 0.720 0.669 0.788 0.769 0.750 0.707 0.659 0.453 0.430 0.395 0.351 0.301 0.414 0.437 0.446 0.448 0.448 135.46 141 .56 144.18 144.73 145.08 147.99 154.66 157.52 158.12 158.51 27.45 28.69 29.22 29.33 29.41 27.46 28.71 29.20 29.33 29.37 27.80 29.02 29.46 29.54 29.59 26.78 29.04 29.73 30.04 29.70 27.33 27.49 27.69 28.08 29.18 11963.5 11961 .7 11969.9 11979.3 11983.9 109.9 109.9 110.0 110.0 110.1 1.508 1.452 1 .392 1.324 1 .256 1 .167 1 .161 1 .154 1.146 1.139 0.744 0.697 0.644 0.573 0.486 )0 Percent of design speed 0568 0566 0565 0564 0563 0.989 0.985 0.981 0.979 0.979 1.477 1.464 1.429 1.374 1.329 0.987 0.981 0.968 0.957 0.947 1.000 0.999 0.999 0.998 0.999 1.142 1.136 1.133 1.130 1.119 0.997 1 .000 0.998 0.994 0.999 0.829 0.847 0.806 0.733 0.709 0.832 0.837 0.799 0.757 0.726 0.466 0.455 0.418 0.348 0.326 0.416 0.453 0.470 0.478 0.479 125.09 134.22 139.39 141 .66 141.94 136.66 146.64 152.29 154.77 155.08 25.35 27.20 28. 2S 28.71 28.77 25.38 27.25 28.28 28.65 28.72 25.59 27.59 28.56 28.89 28.96 25.11 26.75 28.62 28.74 28.82 25.02 26.17 26.92 27.31 28.12 10870.5 10848.3 10910.5 10908.6 10901.5 99.9 99.7 100.2 100.2 100.1 1 .440 1 .414 1 .356 1.287 1.232 1 .138 1.135 1 .130 1.121 1.117 0.796 0.772 0.699 0.619 0.525 21 [•ABLE IV. - Concluded. OVERALL PERFORMANCE OF STACK 57M2D (d) oi design READING HUHDER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEHPERATURE RATIO ROTOR ADIA3ATIC EFFICIENCY ROTOR i:a;iCHTU!1-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOH COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT AHHULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCY 057? 0.992 1.354 0.991 0.999 1 .108 1.000 0.839 0.836 0.430 0.403 110.94 121.21 22.49 22.50 22.55 22.35 21.85 9787.8 89.9 1.332 1.108 0.793 (, , ii Percent of design spi ed READING NUMBER 0580 IGV TOTAL PRESSURE RATIO 0.994 ROTOR TOTAL PRESSURE RATIO 1.274 STATOR TOTAL PRESSURE RATIO 0.987 IGV TOTAL TEHPERATURE RATIO 999 ROTOR TOTAL TEMPERATURE RATIO t .086 STATOR TOTAL TEMPERATURE RATIO 0.999 ROTOR ADIABATIC EFFICIENCY 0.834 ROTOR MOMEHTUM-RISE EFFICIENCY 844 ROTOR HEAD-RISE COEFFICIENT 0.418 FLOW COEFFICIENT 0.389 AIRFLOW PER UNIT FRONTAL AREA 96 56 AIRFLOW PER UNIT ANNULUS AREA 105 50 AIRFLOW AT ORIFICE 19.57 AIRFLOW AT IGV INLET 19.59 AIRFLOW AT ROTOR INLET 19 61 AIRFLOW AT ROTOR OUTLET 19.53 AIRFLOW AT STATOR OUTLET 18.83 ROTATIVE SPEED 8721 .2 PERCENT OF DESIGN SPEED 80.1 COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO 1.24? STAGE TOTAL TEMPERATURE RATIO 1.084 STAGE ADIABATIC EFFICIENCY 0.784 (f) 70 Percent of design speed READING NUMBER 0587 0586 0585 0584 0583 IGV TOTAL PRESSURE RATIO 0.996 0.995 0.993 0.992 0.990 ROTOR TOTAL PRESSURE RATIO t .205 1.205 1.195 1.188 1.184 STATOR TOTAL PRESSURE RATIO 0.989 0.985 0.978 0.970 0.960 IGV TOTAL TEMPERATURE RATIO 1-000 0.999 0.99? 0.999 0.99? ROTOR TOTAL TEHPERATURE RATIO 1-065 1.062 1.05? 1.057 1.056 STATOR TOTAL TEMPERATURE RATIO 0.998 0.998 0.999 1.030 1.000 R0T03 ADIABATIC EFFICIENCY 0.841 0.878 0.889 0.884 0.875 ROTOR HOflEMTUH-RISE EFFICIENCY 0.858 0.908 0.921 0.921 0.925 ROTOR HEAD-RISE COEFFICIENT 0.407 0.405 0.386 0.373 0.365 FLOW COEFFICIENT 0.393 0.445 0.502 0.532 0.556 AIRFLOW PER UNIT FRONTAL AREA 86.36 97.68 108.58 114.48 118.93 AIRFLOH PER UNIT ANHULUS AREA 94.35 106.72 118.63 125.07 129.93 AIRFLOW AT ORIFICE 17.50 19.80 22.01 23.20 24.10 AIRFLOW AT IGV INLET 17.54 19.71 22.02 23.18 24.08 AIRFLOW AT ROTOR INLET 17.48 19.83 22.04 23.22 24.08 AIRFLOW AT ROTOR OUTLET 17.59 19.87 21.66 22.77 23.67 AIRFLOW AT STATOR OUTLET '.6.75 18.74 20.79 21.99 23.10 ROTATIVE SPEED 7666.3 7665.9 7663.3 7656.6 7646.7 PERCENT OF DESIGN SPEED 70.4 70.4 70.4 70.3 70.2 COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO 1-187 1.180 \ ,\6\ STAGE TOTAL TEHPERATURE RATIO 1-063 1.060 1.057 STAGE ADIABATIC EFFICIENCY 0.805 0.812 0.758 1.125 1.056 0.610 (g) 60 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEHPERATURE RATIO ROTOR ADIABATIC EFFICIENCT ROTOR MOHENTUM-RISE EFFICIENCY ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOH AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEHPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0588 0.997 1.147 0.992 1.000 1.048 0.998 0.835 0.854 0.397 0.381 72.08 78.75 14.61 14.68 14.65 14.63 14.02 6560.3 60.3 1.134 1.046 0.803 22 TABLE V. - OVERALL PERFORMANCE OF STAGE 57M2E (a) 120 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEHPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCY ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOH COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0606 0605 0604 0603 0602 0.994 0.993 0.993 0.993 0.993 1.554 1.461 1.391 1.335 1.270 0.969 0.994 1.004 0.994 0.969 0.999 0.999 0.999 0.999 0.999 1.153 1.139 1.128 1.120 1.105 0.993 0.992 0.992 0.990 0.989 0.879 0.824 0.776 0.718 0.672 0.930 0.908 0.871 0.812 0.744 0.370 0.311 0.266 0.230 0.186 0.347 0.374 0.383 0.385 0.385 126.00 134.31 136.94 137.76 138.08 137.66 146.74 149.62 150.51 150.86 25.54 27.22 27.76 27.92 27.99 25.52 27.20 27.77 27.87 27.95 25.13 26.80 27.39 27.51 27.57 24.65 25.85 26.45 27.10 28.03 25.64 27.22 27.91 27.61 27.40 13082.1 13084.2 13106.6 13100.8 13116.9 120.2 120.2 120.4 120.3 120.5 1.497 1.444 1.387 1.318 1.223 1.143 1.128 1.118 1.107 1.093 0.854 0.864 0.831 0.764 0.640 (b) 110 Percent of design speed READING NUMBER IGV TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO IGV TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCT ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOH COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT READING NUMBER I6V TOTAL PRESSURE RATIO ROTOR TOTAL PRESSURE RATIO STATOR TOTAL PRESSURE RATIO I6V TOTAL TEMPERATURE RATIO ROTOR TOTAL TEMPERATURE RATIO STATOR TOTAL TEMPERATURE RATIO ROTOR ADIABATIC EFFICIENCT ROTOR MOMENTUM-RISE EFFICIENCT ROTOR HEAD-RISE COEFFICIENT FLOW COEFFICIENT AIRFLOW PER UNIT FRONTAL AREA AIRFLOW PER UNIT ANNULUS AREA AIRFLOW AT ORIFICE AIRFLOW AT IGV INLET AIRFLOW AT ROTOR INLET AIRFLOW AT ROTOR OUTLET AIRFLOW AT STATOR OUTLET ROTATIVE SPEED PERCENT OF DESIGN SPEED COMPRESSOR PERFORMANCE STAGE TOTAL PRESSURE RATIO STAGE TOTAL TEMPERATURE RATIO STAGE ADIABATIC EFFICIENCT 0601 0600 0596 0597 0599 0.996 0.995 0.994 0.994 0.994 1.446 1.390 1.355 1.299 1.234 0.975 0.991 0.991 0.990 0.973 1.000 0.999 0.999 0.999 0.999 1.126 1.114 1.107 1.100 1.087 0.994 0.993 0.992 0.990 0.990 0.884 0.865 0.848 0.774 0.709 0.943 0.949 0.935 0.877 0.805 0.358 0.314 0.288 0.245 0.193 0.338 0.373 0.392 0.405 0.407 113.55 123.99 129.34 132.94 133.72 124.06 135.47 141.31 145.25 146.10 23.02 25.13 26.22 26.95 27.10 22.99 25.08 26.20 26.92 27.06 22.61 24.73 25.78 26.51 26.65 22.31 24.13 25.49 26.41 26.85 23.01 24.87 2S.84 26.53 26.43 11963.2 11959.5 11950.2 11949.4 11943.3 109.9 109.9 109.8 109.8 109.7 1.404 1.370 1.335 1.278 1.193 1.119 1.105 1.098 1.089 1.076 0.859 0.897 0.881 0.820 0.685 Percent of design speed 0595 0594 0593 0592 0591 0.997 8.996 0.995 0.994 0.994 1.358 1.328 1.288 1.255 1.204 0.977 0.987 0.990 0.982 0.974 1.000 0.999 0.999 0.999 0.999 1.104 1.097 1.086 1 .081 1.073 0.995 0.993 0.995 0.990 0.990 0.883 0.871 0.869 0.823 0.746 0.938 0.950 0.953 0.933 0.858 0.350 0.321 0.282 0.251 0.202 0.330 0.359 0.391 0.419 0.428 101.78 109.94 118.59 126.34 128.76 111.20 120.12 129.57 138.04 140.67 20.63 22.28 24.04 25.61 26.10 20.64 22.28 24.05 25.58 26.04 20.25 21.85 23.63 25.16 25.64 20.13 21.53 23.41 25.39 25.71 20.59 21.97 23.34 25.02 25.33 10865.3 10870.4 10863.2 10870.9 0869.7 99.8 99.9 99.8 99.9 99.9 1.323 1.305 t.268 1.226 1.166 1.097 1 .089 1.080 1 .070 1.061 0.856 0.888 0.884 0.856 0.736 23 lAiUJ V. Concluded. OVERALL PERFORMANCE OF STAGE 57M2E ( to -S c Sg E -g |j = 37 16 20 24 28 Airflow, kg/sec Figure 8. - Overall performance of stage 57M2A (IGV angle, 0°). 38 IGV angle, (a) 100 Percent of design speed. (b) 120 Percent of design speed. Figure 9. - Effect of inlet -guide-vane angle on overall stage performance. 39 O Maximum D Operating line (constant throttle valve position) 30 20 10 -10 Inlet guide vane setting angle, deg (b) 120 Percent of design speed. Figure 10. - Effect of inlet guide vane angle on calculated static thrust. 40 Report No NASA TP -1510 Accession No. 3. Recipient's Catalog No Title and Subtitle AERODYNAMIC PERFORMANCE OF AXIAL-FLOW FAN STAGE OPERATED AT NINE INLET GUIDE VANE ANGLES 5. Report Date September 1979 6. Performing Organization Code 7. Author(s) Royce D. Moore and Lonnie Reid Performing Organization Report No E-9714 9. Performing Organization Name and Address National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 10. Work Unit No. 505-04 II. Contract or Grant No. 12. Sponsoring Agency Name and Address National Aeronautics and Space Administration Washington, D.C. 20546 13. Type of Report and Period Covered Technical Paper 14. Sponsoring Agency Code 15. Supplementary Notes Abstract The overall performance of a fan stage with nine inlet -guide -vane angle settings is presented. These data were obtained over the stable flow range at speeds from 60 to 120 percent of design for vane setting angles from -25° to 42. 5°. At design speed and design inlet guide vane angle, the stage had a peak efficiency of 0. 892 at a pressure ratio of 1. 322 and a flow of 25. 31 kilo- grams per second. The stall margin based on peak efficiency and stall was 20 percent. Based on an operating line passing through the peak efficiency point at the design setting angle, the use- ful operating range of the stage at design speed is limited by stall at the positive setting angles and by choke at the negative angles. At design speed the calculated static thrust along the oper- ating line varied from 68 to 114 percent of that obtained at design setting angle. 17. Key Words (Suggested by Author(s)) Turbomachinery Compressor VTOL STOL 18. Distribution Statement Unclassified - unlimited STAR Category 07 19. Security Classif. (of this report) Unclassified 20. Security Classif. (of this page) Unclassified 21. No. of Pages 42 22. Price A03 For sale by the National Technical Information Service, Springfield. Virginia 22161 NASA-Langley, 1979 National Aeronautics and Space Administration Washington, D.C. 20546 Official Business Penalty for Private Use, $300 THIRD-CLASS BULK RATE m Postage and Fees Paid National Aeronautics and Space Administration NASA-451 2 _ ***** **>, »°1S ° 9 17 ?9 s 00t, 6 l8 0l lX *X>x 8 <>*