[1] KANTROWITZ A. The supersonic axial-flow compressor:NACA-Report 974[R]. Washington, D.C.:NACA, 1946.
[2] ERWIN J R, WRIGHT L C, KANTROWITZ A. Investigation of an experimental supersonic axial-flow compressor:NACA-RM-L6J01b[R]. Washington, D.C.:NACA, 1947.
[3] RITTER W K, JOHNSEN I A. Performance of 24-inch supersonic axial-flow compressor in air I:Performance of compressor rotor at design tip speed of 1600 feet per second:NACA-RM-E7L10[R]. Washington, D.C.:NACA, 1948.
[4] ULLMAN G N. Experimental investigation of a 16-inch impulse-type supersonic compressor rotor:NACA-RM-E51G19[R]. Washington, D.C.:NACA, 1951.
[5] KLAPPROTH J F, ULLMAN G N, TYSL E R. Performance of an impulse-type supersonic compressor with stators:NACA-RM-52B22[R]. Washington, D.C.:NACA, 1952.
[6] KANTROWITZ A, DONALDSON C. Preliminary investigation of supersonic diffusers:NACA ACR-L5D20[R]. Washington, D.C.:NACA, 1945.
[7] 张林, 张堃元, 金志光, 等. 高超声速二元进气道顶板移动变几何方案数值模拟[J]. 航空学报, 2012, 33(10):1800-1808. ZHANG L, ZHANG K Y, JIN Z G, et al. Numerical simulation of a variable geometry hypersonic 2D inlet designed with compressible ramp movable[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(10):1800-1808(in Chinese).
[8] 范晓樯. 高超声速进气道的设计、计算与实验研究[D]. 长沙:国防科学技术大学, 2006. FAN X Q. Design method, numerical simulation and experimental research of hypersonic inlet[D]. Changsha:National University of Defense Technology, 2006(in Chinese).
[9] GRAGAM R C, KLAPPROTH J F, BARINA F J. Investigation of off-design performance of shock-in-rotor type supersonic blading:NACA-RM-E51C22[R]. Washington, D.C.:NACA, 1951.
[10] WENNERSTROM A J, FROST G R. Design of a 1500 ft/sec, transonic, high-through-flow, single-stage axial flow compressor with low hub/tip ratio:AFAPL-TR-76-59/ADB-016386[R]. Washington, D.C.:ARL, 1976.
[11] TWEEDT D L, SCHREIBER H A, STARKEN H. Experimental investigation of the performance of a supersonic compressor cascade:NACA-TM-100879[R]. Washington, D.C.:NACA, 1988.
[12] LIEBLEIN S, LEWIS G W, SANDERCOCK D M. Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach number I-Overall performance of stage with transonic rotor and subsonic stators up to rotor relative inlet mach number of 1.1:NACA-RM-E52A24[R]. Washington, D.C.:NACA, 1952.
[13] STRAZISAR A J, WOOD J R, HATHAWAY M D, et al. Laser anemometer measurements in a transonic axial-flow fan rotor:NASA-TP-2879[R]. Washington, D.C.:NASA, 1989.
[14] CALVERT W J, GINDER R B. Transonic fan and compressor design[J]. Proceedings of the Institution of Mechanical Engineers, Part C:Journal of Mechanical Science, 1999, 213(5):419-436.
[15] BIOLLO R, BENINI E. Recent advances in transonic axial compressor aerodynamics[J]. Progress in Aerospace Sciences, 2013, 56:1-18.
[16] MOORE R D, REID L. Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05:NASA-TP-1659[R]. Washington, D.C.:NASA, 1980.
[17] MOORE R D, REID L. Design and overall performance of four highly loaded, high-speed inlet stages for an advanced high-pressure-ratio core compressor:NASA-TP-1337[R]. Washington, D.C.:NASA, 1978.
[18] AGARD. CFD validation for propulsion system components:Agard-ar-355[R]. Neuilly-sur-Seine:North Atlantic Treaty Organization AGARD, 1998.
[19] LAWLOR S P, BALDWIN P. Conceptual design of a supersonic C02 compressor:ASME Paper GT2005-68349[R]. Reston:ASME, 2005.
[20] ROBERT S, PETER B, JAMES K. Insertion of shock wave compression technology into micro turbines for increased efficiency and reduced costs:ASME Paper GT2005-68203[R]. Reston:ASME, 2005.
[21] GROSVENOR A D, BROWN P M, BUCHER J R, et al. Measured and predictec performance of a high pressure ratio supersonic compressor rotor:ASME Paper GT2008-50150[R]. Reston:ASME, 2008.
[22] 肖翔. 对转冲压压气机冲压叶轮内部流动分析研究[D]. 北京:中国科学院研究生院, 2007. XIAO X. Investigation on counter-rotating ram-pressor impeller internal flow[D]. Beijing:Graduate University of Chinese Academy of Sciences, 2007(in Chinese).
[23] 邱名. 高级压比轴流压气机转子通道内激波组织研究[D]. 南京:南京航空航天大学, 2014. QIU M. Research the shock control law in high stage pressure-ratio compressor rotor channel[D]. Nanjing:Nanjing University of Aeronautics and Astronautics, 2014(in Chinese).
[24] 韩吉昂, 钟兢军, 严红明, 等. 旋转冲压压缩转子三维进气流道数值研究[J]. 航空动力学报, 2009, 24(5):1079-1088. HAN J A, ZHONG J J, YAN H M et al. Numerical research of three dimensional flow-path in a ram-rotor[J]. Journal of Aerospace Power, 2009, 24(5):1079-1088(in Chinese).
[25] 韩吉昂, 钟兢军, 严红明, 等. 旋转冲压压缩转子二维进气流道数值研究[J]. 航空动力学报, 2008, 23(6):1054-1060. HAN J A, ZHONG J J, YAN H M, et al. Numerical research of two-dimensional flow-path in ram-rotor[J]. Journal of Aerospace Power, 2008, 23(6):1054-1060(in Chinese).
[26] 杨凌, 钟兢军, 韩吉昂, 等. 关键几何参数对旋转冲压压缩转子流场及性能影响研究[J]. 工程热物理学报, 2012, 33(3):388-392. YANG L, ZHONG J J, HAN J A, et al. Influence of the two geometric parameters on ram-rotor flow field and performance[J]. Journal of Engineering Thermophysics, 2012, 33(3):388-392(in Chinese).
[27] FLEETER S, HOLTMAN R, MCCLURE R B. Experimental investigation of a supersonic compressor cascade:ARL-TR-75-0208[R]. Washington, D.C.:ARL, 1975.
[28] 邱名, 周正贵, 刘龙龙, 等. 超声叶型设计方法研究[J]. 航空学报, 2014, 35(4):975-985. QIU M, ZHOU Z G, LIU L L, et al. Investigation of supersonic compressor blade profile design method[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(4):975-985(in Chinese).
[29] LEVINE P. Two-dimensional inflow conditions for a supersonic compressor with curved blades[J]. Journal of Applied Mechanics, 1957, 24(2):165-169.
[30] YORK R E, WOODARD W S. Supersonic compressor cascades-an analysis of the entrance region flow field contain detached[J]. Journal of Engineering for Power, 1976, 98(2):247-257. |