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Low Aspect Ratio Axial Flow Compressors: Why and What It Means
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Abstract
One of the more visible changes which has occured in fans and compressors for aircraft turbine engines which have entered development since about 1970 has been a significant reduction in the aspect ratio of the blading. This has brought with it a greatly reduced engine parts count and improved ruggedness and aeroelastic stability. This paper traces the evolution of thinking concerning appropriate aspect ratios for axial flow compressors since the early years of the aircraft turbine engine. In the 1950s, moderate aspect ratios were favored for reasons of mechanical design. As mechanical design capability became more sophisticated, several attempts were made, primarily in the 1960s, to employ very high aspect ratios to reduce engine size and weight. Four of these programs are described which were largely unsuccesful for both mechanical and aerodynamic reasons. After 1970, the pendulum swung strongly in the other direction and designs of very low aspect ratio began to emerge. This has had a significant impact on compressor design systems, and a number of the ways in which design systems have been affected are discussed. Some concluding remarks are made concerning the author's opinion of trends in the near future in aerodynamic design technology.
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Citation
Wennerstrom, A., "Low Aspect Ratio Axial Flow Compressors: Why and What It Means," SAE Technical Paper 861837, 1986, https://doi.org/10.4271/861837.Also In
Low Aspect Ratio Axial Flow Compressors-Why and What It Means
Number: SP-0683; Published: 1986-10-01
Number: SP-0683; Published: 1986-10-01
References
- Novak, R. A. “Streamline Curvature Computing Procedures for Fluid-Flow Problems,” Journal of Engineering for Power 89 1967 478 490
- Wright, L. C. Novak, R. A. “Aerodynamic Design and Development of the General Electric CJ805-23 Aft Fan Component,” ASME Paper 60-WA-270 1960
- Jansen, W. “The Application of End-Wall Boundary Layer Effects in the Performance Analysis of Axial Compressors,” ASME Paper 67-WA/GT-ll 1967
- Stratford, B. S. “The Use of Boundary Layer Techniques to Calculate the Blockage from the Annulus Boundary Layers in a Compressor,” ASME Paper 67-WA/GT-7 1967
- Lieblein, S. Schwenk, F. C. Broderick, R. L. “Diffusion Factor for Estimating Losses and Limiting Blade Loadings in Axial-Flow-Compressor Blade Elements,” NACA RM E53D01 1953
- Miller, G. R., Lewis, G. W., Jr. Hartmann, M. J. “Shock Losses in Transonic Compressor Blade Rows,” Journal of Engineering for Power 83 1961 235 242
- Sherstyuk, A. N. “Design of Compressors, Aerodynamic Calculations.” Translation of Osevyye Kompressory. Aerodinamicheskiy Raschet 1955 Foreign Technology Division Wright-Patterson Air Force Base OH 231 232
- Standahar, R. M. Geye, R. P. “Investigation of a High-Pressure-Ratio Eight-Stage Axial-Flow Research Compressor With Two Transonic Inlet Stages, V-Preliminary Analysis of Over-All Performance of Modified Compressor,” NACA RM E55A03 1955
- Sievers, G. K. Geye, R. P. Lucas, J. G. “Preliminary Analysis of Over-All Performance of an Eight-Stage Axial-Flow Research Compressor With Two Long-Chord Transonic Inlet Stages,” NACA RM E57H14 1958
- Kussoy, M. I. Bachkin, D. “Comparison of Performance of Two Aerodynamically Similar 14-Inch-Diameter Single Stage Compressor Rotors of Different Chord Length,” NACA RM E57I03 1958
- Lewis, G. W., Jr. Schwenk, F. C. Serovy, G. K. “Experimental Investigation of a Transonic Axial-Flow-Compressor Rotor with Double-Circular-Arc Airfoil Blade Sections, I-Design, Over-All Performance, and Stall Characteristics,” NACA RM E53L21a 1954
- Tysl, E. R. Schwenk, F. C. Watkins, T. B. “Experimental Investigation of a Transonic Compressor Rotor with a 1.5-Inch Chord Length and an Aspect Ratio of 3.0, I-Design, Over-All Performance, and Rotating Stall Characteristics,” NACA RM E54L31 1955
- Lieblein, S. Johnsen, I. A. “Resume of Transonic-Compressor Research at NACA Lewis Laboratory,” Journal of Engineering for Power 83 1961 219 234
- Page, R. J. “The Study and Design of a Research Inlet Stage Transonic Compressor with an Average Pressure Ratio of 2.0 and a Mass Flow per Frontal Area of 70% of the Theoretical Maximum,” Technical Report 55-8 Wright Air Development Center, Air Research and Development Command Wright-Patterson Air Force Base March 1956
- Young, W. H. “The Experimental Investigation of a Research Transonic Inlet Stage Compressor,” Technical Report 57-207 Wright Air Development Center, Air Research and Development Command Wright-Patterson Air Force Base May 1957
- Swan, W. C. “A Practical Engineering Solution to the Three-Dimensional Flow in Transonic Type Axial Flow Compressors,” Technical Report 58-57 Wright Air Development Center, Air Research and Development Command Wright-Patterson Air Force Base 1958
- Capiaux, R. Swan, W. C. “An Experiment Concerning the Extension of the Unstalled Range of a Transonic Axial Flow Compressor Inlet Stage,” Technial Report 58-337 Wright Air Development Center, Air Research and Development Command Wright-Patterson Air Force Base June 1958
- Swan, W. C. “An Experiment with Aspect Ratio as a Means of Extending the Useful Range of a Transonic Inlet Stage of an Axial Flow Compressor,” Journal of Engineering for Power 86 3 1964 243 246
- “J-93 Compressor Review,” September 6 1960
- “Compressor Development for a Lightweight Turbojet Engine,” Report PWA-1971 Pratt and Whitney Aircraft July 1961
- “History of Two Demonstrator Engine Programs,” Stibich, M. A. Technical Memorandum APTC-TM-67-17 Air Force Aero Propulsion Laboratory Wright-Patterson Air Force Base October 1967
- Carl, J. “Design and Component Evaluation of Lift Engine Demonstrators,” AFAPL-TR-66-124 I II III Air Force Aero Propulsion Laboratory Wright-Patterson Air Force Base March 1967
- Rawley, W. N. “Demonstration of a Gas Generator for V/STOL Application,” AFAPL-TR-67-65 I II Air Force Aero Propulsion Laboratory Wright-Patterson Air Force Base March 1967
- Fligg, J. “Test of a Low Speed, Three Stage Axial Flow Compressor with Aspect Ratios of 1, 2, and 4,” AIAA Paper 66-613 June 1966
- Horlock, J. H. Fahmi, G. J. “A Theoretical Investigation of the Effect of Aspect Ratio on Axial Flow Compressor Performance,” Current Paper No. 943 Aeronautical Research Council 1967
- Smith, L. H. Jr “Casing Boundary Layers in Multistage Axial-Flow Compressors,” Flow Research on Blading Dzung L. S. Elsevier Publishing Co. Amsterdam 1970 275 296
- “Jane's All the World's Aircraft 1984-85,” Jane's Publishing Company Ltd. London, England 1984 844 845
- Bettner, J. L. Alverson, R. F. “Turbine Engine High Flow Compressor,” AFAPL-TR-77-23 Air Force Aero Propulsion Laboratory Wright-Patterson Air Force Base May 1977
- Wennerstrom, A. J. “Experimental Study of a High-Throughflow Transonic Axial Compressor Stage,” Journal of Engineering for Gas Turbines and Power 106 3 July 1984 552 560
- Tipton, D. L. “Improved Techniques for Compressor Loss Calculation,” AGARD Conference Proceedings No. 34, Advanced Components for Turbojet Engines September 1968
- Hearsey, R. M. “A Revised Computer Program for Axial Compressor Design, Vol I,” ARL TR 75-0001 I Aerospace Research Laboratories Wright-Patterson Air Force Base January 1975
- Adkins, G. G., Jr. Smith, L. H., Jr. “Spanwise Mixing in Axial-Flow Turbomachines,” Journal of Engineering for Power 104 1 January 1982 104 110
- Gallimore, S. J. Cumpsty, N. A. “Spanwise Mixing in Multistage Axial Flow Compressors: Part I - Experimental Investigation,” Journal of Turbomachinery 108 1 July 1986
- Gallimore, S. J. “Spanwise Mixing in Multistage Axial Compressors: Part II - Throughflow Calculations Including Mixing,” Journal of Turbomachinery 108 1 July 1986
- Prince, D. C., Jr. “Three-Dimensional Shock Structures for Transonic/Supersonic Compressor Rotors,” Journal of Aircraft 17 1 January 1980
- Wennerstrom, A. J. Puterbaugh, S. L. “A Three-Dimensional Model for the Prediction of Shock Losses in Compressor Blade Rows,” Journal of Engineering for Gas Turbines and Power 106 2 April 1984 295 299
- Scott, J. N. Hankey, W. L. “Navier-Stokes Solutions of Unsteady Flow in a Compressor Rotor,” Journal of Turbomachinery 108 2 October 1986
- Ng, W. F. Epstein, A. H. “Unsteady Losses in Transonic Compressors,” Journal of Engineering for Gas Turbines and Power 107 2 April 1985 345 353
- Koch, C. C. “Stalling Pressure Rise Capability of Axial Flow Compressor Stages,” Journal of Engineering for Power 103 4 October 1981
- Schweitzer, J. K. Garberoglio, J. E. “Maximum Loading Capability of Axial Flow Compressors,” Journal of Aircraft 21 8 August 1984 593 600
- Kholschevnikov, K. V. “Theory and Design of Aircraft Turbomachines.” Translation of Teoriya i Raschet Aviatsionnokh Lopatocknykh Mashin Foreign Technology Division Wright-Patterson Air Force Base OH 1972 281
- Pickering, F. E. “A Decade of Progress in Turbomachinery Design and Development,” SAE Paper SP-637 1985
- Clemmons, D. R. Dodge, P. R. Blackmore, W. L. “The Impact of Three-Dimensional Analysis on Fan Design,” ASME Paper 83-GT-136 1983
- Denton, J. D. “The Calculation of Fully Three-Dimensional Flow Through Any Type of Turbomachine Blade Row,” 3-D Computation Techniques Applied to Internal Flows in Propulsion Systems June 1985