翼身融合背撑发动机布局的动力短舱设计

doi:10.7527/S1000-6893.2019.23047

Abstract

Abstract: To solve the problem of aircraft-engine flow interference of Blend-Wing-Body (BWB) configuration with podded engines, this paper presents the design principles for podded nacelles based on the BWB flow characteristics. The axisymmetric nacelles should be taken into account together with the fan cowl profile which could reduce the influence of nacelle external flow on the airframe and the intake profile which meets the requirements of intake efficiency. Based on the parameterization method and multipoint optimization design method for powered nacelles established in this paper, the nacelles optimization considering both internal and external flow is carried out. Finally, the flowfield of the installed engine nacelle is analyzed. The results show that the design method proposed in this paper can provide the design options with different internal and external aerodynamic characteristics and meet the multipoint design requirements of the power nacelle for BWB with podded engines. The peak Mach number at cruise and full thrust condition can be reduced by 8.35% and 11.81% respectively to the largest extent. The optimization results also have good intake performance at maximum thrust and crosswind takeoff condition. For the installed nacelle configuration, the strong shock wave between engine and airframe and the rear body separation at high speed cruise condition is eliminated, and the airframe external flow provides uniform and stable intake for the engine at low speed condition with high angle of attack, meanwhile, the intake total pressure recovery coefficient meets the design requirements.

Key words: blended-wing-body configuration, podded engines, nacelles, genetic algorithms, multiobjective optimization design

CLC Number:

V211.6

GU Wenting, ZHAO Zhenshan, ZHOU Hanwei, FENG Jian, TAN Zhaoguang, LI Dong. Powered-on nacelle design on blended-wing-body configuration with podded engines[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(9): 623047-623047.

References 34

[1]	LIEBECK R H. Design of the blended wing body subsonic transport[J]. Journal of Aircraft, 2004, 41(1):10-25.
[2]	PAULUS D, SALMON T, MOHR B, et al. Configuration selection for a 450 passenger ultra-efficient 2020 aircraft[C]//4th European Conference for Aerospace Sciences (EUCASS) Proceedings, 2011:601-618.
[3]	GRAHAMN W R, HALL C A, MORALES M V. The potential of future aircraft technology for noise and pollutant emissions reduction[J]. Transport Policy, 2014, 34(1):36-51.
[4]	SHAW R J, PEDDIE C L. Overview of the Ultra Efficient Engine Technology (UEET) Program:NASA CP-2003-212458[R]. Washington, D.C.:NASA, 2003.
[5]	SUDER K L. Overview of the NASA environmentally responsible aviation project's propulsion technology portfolio:AIAA-2012-4038[R]. Reston, VA:AIAA, 2012.
[6]	HOOKER J R, WICK A, ZEUNE C, et al. Over wing nacelle installations for improved energy efficiency:AIAA-2013-2920[R]. Reston, VA:AIAA, 2013.
[7]	HOOKER J R, WICK A. Design of the hybrid wing body for fuel efficient air mobility operations:AIAA-2014-1285[R]. Reston, VA:AIAA, 2014.
[8]	TONG M T, JONES S M, HALLER W J, et al. Engine conceptual design studies for a hybrid wing body aircraft:NASA/TM-2009-215680[R]. Washington, D.C.:NASA, 2009.
[9]	RODRIGUEZ D L. Multidisciplinary optimization method for designing boundary-layer-ingesting inlets[J]. Journal of Aircraft, 2009, 46(3):883-894.
[10]	FERRAR A M, O'BRIEN W F. Progress in boundary layer ingesting embedded engine research:AIAA-2012-4283[R]. Reston,VA:AIAA, 2012.
[11]	GISSEN A N, VUKASINOVIC B, MCMILLAN M L, et al. Distortion management in a boundary layer ingestion inlet diffuser using hybrid flow control[J]. Journal of Propulsion and Power, 2013, 30(3):834-844.
[12]	FLAMM J D, JAMES K D, BONET J T. Overview of ERA Integrated Technology Demonstration (ITD) 51A Ultra-High Bypass (UHB) integration for Hybrid Wing Body (HWB):AIAA-2016-0007[R]. Reston,VA:AIAA, 2016.
[13]	DEERE K A, LUCKRING J M, MCMILLIN S N, et al. CFD predictions for transonic performance of the ERA hybrid wing-body configuration:AIAA-2016-0266[R]. Reston,VA:AIAA, 2016.
[14]	强旭浩, 王占学, 刘增文, 等. 涡扇发动机短舱设计方法研究[J]. 机械设计与制造, 2013(11):23-25, 28. QIANG X H, WANG Z X, LIU Z W, et al. Design method research of turbofan-engine nacelle[J]. Machinery Design and Manufacture, 2013(11):23-25, 28(in Chinese).
[15]	王修方. 涡扇发动机动力短舱的设计[J]. 民用飞机设计与研究, 1998(1):30-36. WANG X F. Turbofan engine dynamic nacelle design[J]. Journal of Civil Aircraft Design and Research, 1998(1):30-36(in Chinese).
[16]	MIAO Z S. Aircraft engine performance and integration in a flying wing aircraft conceptual design[D]. Cranfield:Cranfield University, 2012:55-62.
[17]	UENISHI K, PEARSON M S, LEHNIG T R, et al. CFD-based 3D turbofan nacelle design system:AIAA-1990-3081[R]. Reston, VA:AIAA, 1990.
[18]	WILHELM R. An inverse design method for designing isolated and wing-mounted engine nacelles:AIAA-2002-0104[R]. Reston, VA:AIAA, 2002.
[19]	MORITZ A, DIETER B. Aerodynamic design optimization of nacelle and intake:GT2013-94857[R]. New York:ASME, 2013:1-8.
[20]	FANG X M, ZHANG Y F, CHEN H X. Transonic nacelle aerodynamic optimization based on hybrid genetic algorithm:AIAA-2016-3833[R]. Reston, VA:AIAA, 2016.
[21]	RIEDEL H, HORSTMANN K H, RONZHEIMER A, et al. Aerodynamic design of a natural laminar flow nacelle and the design validation by flight testing[J]. Aerospace Science and Technology, 1998, 2(1):1-12.
[22]	RIEDEL H, RONZHEIMER A, SITZMANN M. Analysis of the static pressure distribution on a laminar flow nacelle based on Euler calculations and flight measurements[J]. Aerospace Science and Technology, 1998, 2(2):129-143.
[23]	MATTINGLY J D, HEISER W H, PRATT D T. Aircraft engine design[M]. 2nd ed. Reston, VA:AIAA, 2002:569-588.
[24]	KULFAN B M. A universal parametric geometry representation method-"CST":AIAA-2007-0062[R]. Reston, VA:AIAA, 2007.
[25]	KULFAN B M. Recent extensions and applications of the "CST" universal parametric geometry representation method:AIAA-2007-7709[R]. Reston, VA:AIAA, AIAA, 2007.
[26]	关晓辉, 李占科, 宋笔锋. CST气动外形参数化方法研究[J]. 航空学报, 2012, 33(4):625-633. GUAN X H, LI Z K, SONG B F. A study on CST aerodynamic shape parameterization method[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(4):625-633(in Chinese).
[27]	LEE C H, MAVRIS D N. Bayesian collaborative sampling for aero-propulsion design of an engine and nacelle:AIAA-2012-3997[R]. Reston, VA:AIAA, 2012.
[28]	刘李涛, 杨永, 李喜乐. 外吹式动力吹气襟翼N-S方程数值分析[J]. 航空计算技术, 2008, 38(3):61-64. LIU L T, YANG Y, LI X L. Numerical analysis of high-lift system with externally blown flap using N-S equations[J]. Aeronautical Computing Technique, 2008, 38(3):61-64(in Chinese).
[29]	谭兆光, 陈迎春, 李杰, 等. 机体/动力装置一体化分析中的动力影响效应数值模拟[J]. 航空动力学报, 2009, 24(8):1766-1772. TAN Z G, CHEN Y C, LI J, et al. Numerical simulation method for the powered effects in airframe/propulsion integration analysis[J]. Journal of Aerospace Power, 2009, 24(8):1766-1772(in Chinese).
[30]	HIROSE N, ASAI K, IKAWA K. Transonic 3-D Euler analysis of flows around fan-jet engine and TPS (Turbine Powered Simulator):NAL-TR-1045[R]. Tokyo:National Aerospace Laboratory of Japan, 1989.
[31]	JEONG S, MURAYAMA M, YAMAMOTO K. Efficient optimization design method using kriging model[J]. Journal of Aircraft, 2015, 42(2):413-420.
[32]	张彬乾,罗烈,陈真利, 等. 飞翼布局隐身翼型优化设计研究[J].航空学报, 2014, 35(4):957-967. ZHANG B Q, LUO L, CHEN Z L, et al. On stealth airfoil optimization design for flying wing configuration[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(4):957-967(in Chinese).
[33]	YU G, LI D, SHU Y, et al. The engine position effect on SWB airplane aerodynamic performance[C]//2018 Asia-Pacific International Symposium on Aerospace Technology, 2018.
[34]	刘凯礼, 孙一峰,钟园, 等. 民用飞机进气道的侧风畸变研究[J].航空动力学报, 2015, 30(2):289-296. LIU K L, SUN Y F, ZHONG Y, et al. Research on inlet distortion under crosswind for civil aircraft[J]. Journal of Aerospace Power, 2015, 30(2):289-296(in Chinese).

Powered-on nacelle design on blended-wing-body configuration with podded engines

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

References 34

Related Articles 15

Recommended Articles

Metrics

Comments

[1]	ZHANG Minghui, CHEN Zhenli, GU Wenting, LI Dong, ZHANG Shuai, YUAN Changsheng, WANG Long, ZHANG Binqian. Tradeoff design of high and low speed performance for blended-wing-body civil aircraft [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(9): 623052-623052.
[2]	JIN Dongping, JI Bin. Topology optimization of flexible support structure for trailing edge [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(8): 2681-2687.
[3]	FENG Yan, ZHENG Xitao, WU Shuyi, LIU Zhendong. Layup optimization design and analysis of super lightweight composite wing [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1858-1866.
[4]	DAI Zhen, HE Feng, ZHANG Yujing, XIONG Huagang. Real-time path optimization algorithm of AFDX virtual link [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(6): 1924-1932.
[5]	ZHANG Zhi, LIN Shenglin, ZHU Qidan, WANG Kaiyu. Genetic collision avoidance planning algorithm for irregular shaped object with kinematics constraint [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(4): 1348-1358.
[6]	GONG Shufeng, BEN De, PAN Minghai, LONG Weijun. Pattern Synthesis for Opportunistic Array Radar Based on Fuzzy Chance-constrained Programming [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(9): 2615-2623.
[7]	GE Xiaokai, HU Jianbo, ZHANG Bofeng. Simulation Modeling for Condition Based Maintenance Optimization of Multi-component Systems with Dependencies [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2013, 34(8): 1854-1863.
[8]	XU Xiudong, HUANG Panfeng, MENG Zhongjie, WANG Dongke. Space Tethered Robot Optimal Trajectory Planning for Medium Approaching Range Based on Velocity Impulse [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(8): 1531-1539.
[9]	LIU Baosheng, LANG Lihui, YANG Xiying, DU Pingmei, CAI Gaocan. A Rate Dependent Constitutive Model Based on the Microstructure Evolution [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(7): 1329-1335.
[10]	Lu Zhong;Sun Youchao. Disassembly Sequence Planning of Civil Aircraft Products for Maintainability Design [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2010, 31(1): 143-150.
[11]	Wu Hao;Zuo Hongfu. Selective-disassembly Sequence Planning Based on Improved Genetic Algorithm [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(5): 952-958.
[12]	Li Xiong;Xu Xiaohao;Zhao Yifei;Wei Dongxuan. Flight Rerouting Path Planning in Dispersedly Distributed Severe Weather Areas [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(12): 2342-2347.
[13]	Sun Jie;Sun Zhigang;Song Yingdong;Gao Xiguang. Microstructure Topological Optimization Based on Highfidelity Generalized Method of Cell [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(11): 2106-2112.
[14]	Lu Feng;Huang Jinquan. Engine Component Performance Prognostics Based on Decision Fusion [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(10): 1795-1800.
[15]	Zhao Yifei. Time-route Assignment Model and Algorithm for Short-term Area Traffic Flow Management [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(1): 121-126.