边界层抽吸效应对分布式推进系统气动性能影响数值研究

崔容; 潘天宇; 李秋实; 张健

doi:10.13224/j.cnki.jasp.2018.05.007

边界层抽吸效应对分布式推进系统气动性能影响数值研究

doi: 10.13224/j.cnki.jasp.2018.05.007

1.
北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室，北京 100191；先进航空发动机协同创新中心，北京 100191
2.
中国航空发动机集团重大专项工程部，北京 100097

基金项目: 国家自然科学重点基金（51636001）；航空动力基金（6141B090315）

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出版历程
- 收稿日期: 2017-11-19
- 刊出日期: 2018-05-28

Numerical investigation on the effects of boundary layer ingestion on aerodynamic performance of distributed propulsion system

摘要

摘要: 为探究边界层抽吸（BLI）效应对飞机的气动性能影响，采用基于沿流线体积力模型的飞机/发动机一体化数值模拟方法对某分布式推进系统进行了计算和分析。结果显示，BLI效应主要影响飞机中心体部分及发动机外整流罩的气体流动，对翼身融合体（BWB）的融合段及外翼段的升阻力影响较小。保持飞行条件和飞行攻角不变，飞机的升、阻力系数均随着无量纲化的发动机流量增加而增大，存在最佳无量纲化的发动机流量对应最大升阻比。发动机的安装位置直接影响机身表面的局部超声区和整流罩外的激波分布，布局在机身尾缘处会获得更好的升阻比，最大升阻比对应的无量纲化的发动机流量为0.65。
- 分布式推进系统 /
- 翼身融合体 /
- 边界层抽吸 /
- 沿流线体积力模型 /
- 内/外流一体化计算
Abstract: To explore the effect of boundary layer ingestion (BLI) on the aerodynamic performance of aircraft, the aircraft/engine integrated simulation method based on the streamwise-body-force model was used to calculate a distributed propulsion system. Results show that BLI mainly affect the flow field of center body parts and cowling of engines, but yield small impact on lift and drag of the blending field and outer wing of BWB. Under the same flying conditions and constant angle of attack, the lift coefficient and drag coefficient increase with the increase of the non-dimensional mass flow rate of the engines. Therefore, a best non-dimensional mass flow rate of the engines corresponding to maximum lift-to-drag ra-tio exists. Engine installation location directly influences the localized supersonic flow of fuselage surface and the shock wave distribution of cowling. Layout of engines at the trailing edge could get better lift-to-drag ratio, where the non-dimensional mass flow rate of the engines corresponding to maximum lift-to-drag ratio is 0.65.
- distributed propulsion system /
- blended wing body /
- boundary layer ingestion /
- streamwise-body-force model /
- internal/external flow filed integrated simulations

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参考文献(18)

[1]	SMITH L H.Wake ingestion propulsion benefit［J］.Journal of Propulsion and Power,1993,9(1):74-82.
[2]	HILEMAN J I,SPAKOVSZKY Z S,DRELA M,et al.Airframe design for silent fuel-efficient aircraft［J］.Journal of Aircraft,2010,47(3):956-969.
[3]	LIEBECK R H.Design of the blended wing body subsonic transport［J］.Journal of Aircraft,2004,41(1):10-25.
[4]	HALL C A,CRICHTON D.Engine design studies for a silent aircraft［J］.Journal of Turbomachinery,2007,129(3):479-487.
[5]	GOHARDANI A S,DOULGERIS G,SINGH R.Challenges of future aircraft propulsion:a review of distributed propulsion technology and its potential application for the all electric commercial aircraft［J］.Progress in Aerospace Sciences,2011,47(5):369-391.
[6]	DRELA M.Power balance in aerodynamic flows［J］.AIAA Journal,2009,47(7):1761-1771.
[7]	PLAS A,SARGEANT M,MADANI V,et al.Performance of a boundary layer ingesting (BLI) propulsion system［R］.AIAA-2007-450,2007.
[8]	LEIFSSON L,KO A,MASON W H,et al.Multidisciplinary design optimization of blended-wing-body transport aircraft with distributed propulsion［J］.Aerospace Science and Technology,2013,25(1):16-28.
[9]	KIRNER R,RAFFAELLI L,ROLT A,et al.An assessment of distributed propulsion:advanced propulsion system architectures for conventional aircraft configurations［J］.Aerospace Science and Technology,2015,46(7):42-50.
[10]	段静瑶,袁巍,李秋实.分布式动力系统尾缘射流与边界层抽吸的数值分析［J］.航空动力学报,2015,30(3):571-579.DUAN Jingyao,YUAN Wei,LI Qiushi.Numerical investigation on trailing edge jet and boundary layer ingestion in distributed propulsion system［J］.Journal of Aerospace Power,2015,30(3):571-579.(in Chinese)
[11]	WEBSTER R S,SREENIVAS K,HYAMS D G,et al.Demonstration of sub-system level simulations:a coupled inlet and turbofan stage［R］.AIAA-2012-4282,2012.
[12]	MANTICˇ-LUGO V,DOULGERIS G,GOHARDANI A,et al,Computational analysis of the aerodynamic performance of a jet-flap airfoil in transonic flow［J］.Journal of Aerospace Engineering,2012,226(6):664-678.
[13]	MANTICˇ-LUGO V,DOULGERIS G,GOHARDANI A,et al.Computational analysis of the effects of a boundary layer ingesting propulsion system in transonic flow［J］.Journal of Aerospace Engineering,2013,227(8):1215-1232.
[14]	KIM H,LIOU M S.Flow simulation of N3-X hybrid wing-body configuration［R］.AIAA-2013-0221,2013.
[15]	KIM H,LIOU M S.Mail-slot nacelle shape design for N3-X hybrid wing-body configuration［R］.AIAA-2015-3805,2015.
[16]	GONG Y.A computational model for rotating stall inception and inlet distortion in multistage compressors［D］.Massachusetts,US:Massachusetts Institute of Technology,1999.
[17]	GONG Y,GREITZER E M.A computational model for short wavelength stall inception and development in multi-stage compressors［J］.Journal of Turbomachinery,1999,121(4):726-734.
[18]	CUI Rong,LI Qiushi,PAN Tianyu,et al.Streamwise-body-force-model for rapid simulation combining internal and external flow fields［J］.Chinese Journal of Aeronautics,2016,29(5):1205-1212.