Research on Effects of Inlet Flow Rate on Flow Resistance Characteristics of Tubeless Vortex Reducer
Key Laboratory of Aero-Engine Thermal Environment and Structure,Ministry of Industry and Information Technology,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
XIA Zi-long1, WANG Suo-fang1. Research on Effects of Inlet Flow Rate on Flow Resistance Characteristics of Tubeless Vortex Reducer[J]. Journal of Propulsion Technology, 2020, 41(6): 1276-1285.
[1] Brown W M, Manente J C. Compressor Bleed System[P]. US： 4008977， 1977-02-22.
[2] Hide R. On Source-Sink Flows in a Rotating Fluid[J]. Journal of Fluid Mechanics， 1968， 32(4): 737-764.
[3] Chew J W， Owen J M， Pincombe J R. Numerical Predictions for Laminar Source-Sink Flow in a Rotating Cylindrical Cavity[J]. Journal of Fluid Mechanics， 1984， 143(1): 451-466.
[4] Firouzian M， Owen J M， Pincombe J R， et al. Flow and Heat Transfer in a Rotating Cavity with a Radial Inflow of Fluid， Part 1: The Flow Structure[J]. International Journal of Heat and Fluid Flow， 1985， 6(4): 228-234.
[5] Firouzian M， Owen J M， Pincombe J R， et al. Flow and Heat Transfer in a Rotating Cylindrical Cavity with a Radial Inflow of Fluid, Part 2: Velocity， Pressure and Heat Transfer Measurements[J]. International Journal of Heat and Fluid Flow， 1986， 7(1): 21-27.
[6] Chew J W， Snell R J. Prediction of the Pressure Distribution for Radial Inflow Between Co-Rotating Discs[R]. ASME 88-GT-61.
[7] Brillert D， Reichert A W， Simon H. Calculation of Flow Losses in Rotating Passages of Gas Turbine Cooling Systems[R]. ASME 99-GT-251.
[8] Brillert D， Lieser D， Reichert A W， et al. Total Pressure Losses in Rotor Systems with Radial Inflow[R]. ASME 2000-GT-0283.
[9] Kumar B G V， Chew J W， Hills N J. Rotating Flow and Heat Transfer in Cylindrical Cavities with Radial Inflow[J]. Journal of Engineering for Gas Turbines and Power， 2013， 135(2).
[10] Onori M， Amirante D， Hills N J， et al. LES Validation for a Rotating Cylindrical Cavity with Radial Inflow[R]. ASME GT 2016-56393.
[11] Amirante D， Sun Z， Chew J W， et al. Modeling of Compressor Drum Cavities with Radial Inflow[R]. ASME GT 2016-56505.
[12] Farthing P R， Chew J W， Owen J M. The Use of Deswirl Nozzles to Reduce the Pressure Drop in a Rotating Cavity with a Radial Inflow[J]. Journal of Turbomachinery， 1991， 113(1): 106-114.
[13] Farthing P R， Owen J M. De-Swirled Radial Inflow in a Rotating Cavity[J]. International Journal of Heat & Fluid Flow， 1991， 12(1): 63-70.
[14] Pfitzner M， Waschka W. Development of an Aeroengine Secondary Air System Employing Vortex Reducers[C]. Harrogate: 22nd ICAS Congress， 2000.
[15] Peitsch D， Stein M， Hein S， et al. Numerical Investigation of Vortex Reducer Flows in the High Pressure Compressor of Modern Aeroengines[R]. ASME 2002-GT-30674.
[16] Günther A， Uffrecht W， Kaiser E， et al. Experimental Analysis of Varied Vortex Reducer Configurations for the Internal Air System of Jet Engine Gas Turbines[R]. ASME GT 2008-50738.
[17] Negulescu D， Pfitzner M. Secondary Air Systems in Aeroengines Employing Vortex Reducers[R]. ASME 2001-GT-0198.
[18] May D， Chew J W， Scanlon T J. Prediction of Deswirled Radial Inflow in Rotating Cavities with Hysteresis[J]. Journal of Turbomachinery， 2013， 135(4).
[19] 黄爱霞， 王锁芳. 反旋进气盘腔内流动与换热的数值模拟[J]. 航空动力学报， 2008， 23(9): 1684-1688.
[20] 杨守辉， 王锁芳. 不同去旋角度进气共转盘腔内流动与换热研究[J]. 航空发动机， 2011， 37(6): 17-20.
[21] 张光宇， 王锁芳， 夏子龙， 等. 喷嘴结构对去旋系统减阻特性影响的数值研究[J]. 推进技术， 2018， 39(5): 979-985.
[22] Luo X， Feng A， Quan Y， et al. Experimental Analysis of Varied Vortex Reducers in Reducing the Pressure Drop in a Rotating Cavity with Radial Inflow[J]. Experimental Thermal and Fluid Science， 2016， 77: 159-166.
[23] Friedl W， Peitsch D， Negulescu D. Improvement of High Pressure Turbine Air Systems by De-Swirl Nozzles[C]. Montreal：ASME 2002 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference.
[24] 呼艳丽， 郭 文， 王 蕾， 等. 反旋喷嘴进气旋转盘腔压力损失特性[J]. 航空动力学报， 2016， 31(8): 1866-1873.
