大涵道比涡扇发动机总压进气畸变数值模拟

郭晋; 胡骏; 屠宝锋

doi:10.13224/j.cnki.jasp.2020.05.015

大涵道比涡扇发动机总压进气畸变数值模拟

doi: 10.13224/j.cnki.jasp.2020.05.015

郭晋^1,2,
胡骏^1,2,
屠宝锋^1,2

基金项目: 国家科技重大专项(2017-Ⅱ-0004-0017)

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- 被引次数: 0
出版历程
- 收稿日期: 2019-11-16
- 刊出日期: 2020-05-28

Numerical simulation of high bypass ratio turbofan engine with total pressure inlet distortion

GUO Jin^1,2,
HU Jun^1,2,
TU Baofeng^1,2

1.
Jiangsu Province Key Laboratory of Aerospace Power System,College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
2.
Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China

摘要

摘要: 基于数值缩放理念,以一台大涵道比涡扇发动机为研究载体,将三维彻体力模型与二维多子平行发动机模型进行有机结合,初步搭建了适用于分析复杂进气畸变对航空发动机整机流场特性影响的多维耦合计算模型。利用该多维耦合模型定量分析了稳态周向总压畸变及插板式总压畸变进气下发动机内部的流场特性。计算结果表明即便是进口单纯的方波周向总压畸变进气,在经过大涵道比风扇转子作用后在下游内外涵进口的畸变流场特征也将具有显著差异;在内涵进口形成的总压/总温复合畸变在四级增压级中均得到不同程度的衰减;插板式总压畸变进气下风扇转子进口近轮毂处受周向静压梯度驱动将产生一定程度旋流,并导致风扇转子出口轮毂处形成低压区。
- 大涵道比涡扇发动机 /
- 总压畸变 /
- 多维耦合 /
- 三维彻体力模型 /
- 多子平行发动机模型
Abstract: Based on the concept of numerical zooming and taking a high bypass ratio turbofan engine as the research carrier, a mixed-dimension computational model to investigate the effect of complex inlet distortion on the characteristics of flow field in aero engines was preliminarily established by integrating a three-dimensional body force model and a two-dimensional multiple segment parallel engine model. The mixed-dimension model was utilized to analyze the characteristics of flow field in the engine under different forms of total pressure distortion, including steady circumferential total pressure distortion and flat baffle total pressure distortion. Results revealed that even if the total circumferential pressure distortion of the square wave at the inlet was simple, there were significant differences in the distortion flow field characteristics at the core and bypass inlet after the action of the fan rotor with high bypass ratio. The combined total pressure/total temperature distortion formed at the core inlet was attenuated under different degrees in the four-stage booster compressor. A certain degree of swirl was induced by the circumferential static pressure gradient near the hub region of the fan rotor inlet under the flat baffle total pressure distortion. Thus, the low pressure area was formed near the hub of the fan rotor outlet.
- high bypass ratio turbofan engine /
- total pressure distortion /
- mixed-dimension /
- three-dimensional body force model /
- multiple segment parallel engine model

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参考文献(25)

[1]	NICHOLS L D,CHAMIS C C.Numerical propulsion system simulation:an interdisciplinary approach［R］.AIAA 91-3554,1991.
[2]	CLAUS R W,EVANS A L,LYLTE J K,et al.Numerical propulsion system simulation［J］.Computing Systems in Engineering,1991,2(4):357-364.
[3]	LYTLE J,FOLLEN G,NAIMAN C,et al.2000 numerical propulsion system simulation review［R］.NASA/CP-2001-210673,2001.
[4]	BALA A.Poly-dimensional gas turbine system modeling and simulation［D］.Bedfordshire,England:Cranfield University,2007.
[5]	曹建国.航空发动机仿真技术研究现状、挑战和展望［J］.推进技术,2018,39(5):961-970. CAO Jianguo.Status,challenges and perspectives of aero-engine simulation technology［J］.Journal of Propulsion Technology,2018,39(5):961-970.(in Chinese)
[6]	MEDIC G,KALITZIN G,YOU D,et al.Integrated RANS/LES computations of an entire gas turbine jet engine［R］.AIAA 2007-1117,2007.
[7]	严伟.航空发动机气动稳定性分析数学模型研究与应用［D］.南京:南京航空航天大学,2016. YAN Wei.Research and application of mathematic model for aerodynamic stability analysis on aviation engine［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2016.(in Chinese)
[8]	PETERS A,SPAKOVSZKY Z S,LORD W K,et al.Ultrashort nacelles for low fan pressure ratio propulsors［J］.Journal of Turbomachinery,2015,137(2):021001.1-021001.14.
[9]	CAO T,VADLAMANI N R,TUCKER P G,et al.Fan-intake interaction under high incidence［J］.Journal of Engineering for Gas Turbines and Power,2017,139(4):041204.1-041204.10.
[10]	曹志鹏,刘大响,桂幸民,等.某小型涡喷发动机二维数值仿真［J］.航空动力学报,2009,24(2):439-444. CAO Zhipeng,LIU Daxiang,GUI Xingmin,et al.Two dimensional numerical simulation of small turbojet engine［J］.Journal of Aerospace Power,2009,24(2):439-444.(in Chinese)
[11]	金东海,桂幸民.某涡扇发动机考虑级间引气的二维数值模拟［J］.航空动力学报,2011,26(6):1346-1351. JIN Donghai,GUI Xingmin.Two-dimensional numerical simulation of a turbofan engine with air bleeding in compressor［J］.Journal of Aerospace Power,2011,26(6):1346-1351.(in Chinese)
[12]	杨晨,吴虎,杨金广,等.基于时间推进的涡扇发动机整机通流数值模拟［J］.推进技术,2019,40(10):2190-2197. YANG Chen,WU Hu,YANG Jinguang,et al.Numerical investigation of turbofan engine based on time-marching throughflow method［J］.Journal of Propulsion Technology,2019,40(10):2190-2197.(in Chinese)
[13]	刘晓恒,周成华,宋满祥,等.基于通流方法的某涡喷发动机整机数值仿真［J］.航空学报,2020,41(1):123199.1-123199.11. LIU Xiaoheng,ZHOU Chenghua,SONG Manxiang,et al.Overall simulation of a turbojet engine based on throughflow method［J］.Acta Aeronautica et Astronautica Sinica,2020,41(1):123199.1-123199.11.(in Chinese)
[14]	王占学,宋甫,周莉,等.航空发动机数值缩放技术的研究进展［J］.推进技术,2018,39(7):1441-1454. WANG Zhanxue,SONG Fu,ZHOU Li,et al.Research progress in numerical zooming technology of aero-engine［J］.Journal of Propulsion Technology,2018,39(7):1441-1454.(in Chinese)
[15]	TURNER M,REED J,RYDER R,et al.Multi-fidelity simulation of a turbofan engine with results zoomed into mini-maps for a zero-d cycle simulation［R］.ASME Paper GT2004-53956,2004.
[16]	PACHIDIS V,PILIDIS P,GUINDEUIL G,et al.A partially integrated approach to component zooming using computational fluid dynamics［R］.ASME Paper GT2005-68457,2005.
[17]	PACHIDIS V,PILIDIS P,TALHOUARN F,et al.A fully integrated approach to component zooming using computational fluid dynamics［R］.ASME Paper GT2005-68458,2005.
[18]	PACHIDIS V,PILIDIS P,TEMPLALEXIS I,et al.Prediction of engine performance under compressor inlet flow distortion using streamline curvature［J］.Journal of Engineering for Gas Turbines and Power,2007,129(1):97-103.
[19]	郭晋,胡骏,屠宝锋.多级轴流压气机彻体力模型:理论方法及简化应用［J］.航空动力学报,2018,33(8):1954-1963. GUO Jin,HU Jun,TU Baofeng.Body force model for multistage axial compressor-theoretical method and simplified application［J］.Journal of Aerospace Power,2018,33(8):1954-1963.(in Chinese)
[20]	郭晋,胡骏,屠宝锋.多级轴流压气机彻体力模型:三维应用［J］.航空动力学报,2018,33(9):2161-2169. GUO Jin,HU Jun,TU Baofeng.Body force model for multistage axial compressor-three-dimensional application［J］.Journal of Aerospace Power,2018,33(9):2161-2169.(in Chinese)
[21]	KOCH C C.Stalling pressure rise capability of axial flow compressor stages［J］.Journal of Engineering for Gas Turbines and Power,1981,103(4):645-656.
[22]	MARBLE F E.Three-dimensional flow in turbomachines,aerodynamics of turbines and compressors［M］.Princeton,US:Princeton University Press,1964.
[23]	BOSMAN C,MARSH H.An improved method for calculating the flow in turbo-machines,including a consistent loss model［J］.Journal of Mechanical Engineering Science,1974,16(1):25-31.
[24]	SOEDER R H,BOBULA G A.Effect of steady-state pressure distortion on inlet flow to a high-bypass-ratio turbofan engine［R］.NASA-TM-82964,1982.
[25]	丁宁.大涵道比涡扇发动机进气总压畸变摸拟及稳定性计算分析［D］.南京:南京航空航天大学,2014. DING Ning.Inlet total pressure distortion modeling and stability analysis of high bypass ratio turbofan engine［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2014.(in Chinese)