基于Kriging代理模型的单边膨胀喷管尾缘切角优化

魏仁敏; 杜刚; 金捷

doi:10.13224/j.cnki.jasp.2018.04.013

基于Kriging代理模型的单边膨胀喷管尾缘切角优化

doi: 10.13224/j.cnki.jasp.2018.04.013

北京航空航天大学能源与动力工程学院，北京 100191

计量
- 文章访问数: 972
- HTML浏览量: 2
- PDF量: 584
- 被引次数: 0
出版历程
- 收稿日期: 2016-09-12
- 刊出日期: 2018-04-28

Optimization of trailing edge angles of single expansion ramp nozzle based on Kriging method

摘要

摘要: 在设计点落压比25和非设计点落压比15条件下，对单边膨胀喷管（SERN）不同尾缘切角模型进行了三维数值模拟，并采用Kriging代理模型以SERN轴向推力系数为目标，对尾缘切角进行多目标优化。研究结果表明：尾缘切角会影响SERN后气体的膨胀，增强流动的三维效应，恰当的尾缘切角会使SERN后气体更充分膨胀，有利于提高SERN的轴向推力系数，改善SERN的性能；通过优化，SERN的轴向推力系数由0.94达到了0.975以上，比优化之前提高了约5%，基于Kriging代理模型的SERN优化方法是有效的。
- 单边膨胀喷管 /
- 尾缘切角 /
- 优化设计 /
- 轴向推力系数 /
- 三维数值模拟
Abstract: Based on three-dimensional numerical simulation, different trailing edge angles of single expansion ramp nozzle (SERN) were studied under the condition of nozzle pressure ratio of 25 as the design point, and nozzle pressure ratio of 15 as the undesign point. The trailing edge angles were optimized to get a higher axial thrust coefficient under the nozzle pressure ratio of both 25 and 15 by the Kriging method. Results showed that the trailing edge angles made plume expanding better and the three-dimensional effect of fluid was enhanced. This was propitious to improve the axial thrust coefficient. Whats more, within the design range, the axial thrust coefficient increased from 0.94 to 0.975, about 5% after optimization. So the optimization based on Kriging method is effective.
- single expansion ramp nozzle /
- trailing edge angles /
- optimization design /
- axial thrust coefficient /
- three-dimensional numerical simulation

HTML

参考文献(21)

[1]	林左鸣.战斗机发动机的研制现状和发展趋势［J］.航空发动机,2006,32(1):1-8.LIN Zuoming.Development and future trends of aircraft engine［J］.Aeroengine,2006,32(1):1-8.(in Chinese)
[2]	CAPONE F J,RE R J,BAREE A.Parametric investigation of single-expansion-ramp nozzles at Mach numbers from 0.60 to 1.20［R］.NASA TP-3240,1992.
[3]	RUFFIN S M,VENKATAPATHY E,KEENERE R,et al.Hypersonic single expansion ramp nozzle simulations［J］.Journal of Spacecraft and Rockets,1992,29(2):749-755.
[4]	WATANABE S.Scramjet nozzle experiment with hypersonic external flow［J］.Journal of Propulsion and Power,1993,9(4):521-528.
[5]	SPAID F W,KEENER E R.Hypersonic nozzle-afterbody experiment:flowfield surveys［J］.Journal of Spacecraft and Rockets,1996,33(3):333-338.
[6]	KEENER E R,SPAIDF W.Hypersonic nozzle-afterbody experiment:flow visualization and boundary-layer measurements［J］.Journal of Spacecraft and Rockets,1996,33(3):326-332.
[7]	谭杰,金捷,杜刚,等.过膨胀单边膨胀喷管试验和数值模拟［J］.推进技术,2009,30(3):292-296.TAN Jie,JIN Jie,DU Gang,et al.Experimental and computational investigation of an over-expanded single-expansion-ramp-nozzle［J］.Journal of Propulsion Technology,2009,30(3):292-296.(in Chinese)
[8]	谭杰,金捷,杜刚，等.单边膨胀喷管试验和数值模拟［J］.航空动力学报,2011,26(6):1223-1230.TAN Jie,JIN Jie,DU Gang,et al.Experiment and computational investigation of single-expansion-ramp-nozzle［J］.Journal of Aerospace Power,2011,26(6):1223-1230.(in Chinese)
[9]	谭杰,金捷,杜刚,等.下腹板长度对单边膨胀喷管性能的影响［J］.航空动力学报,2012,27(4):726-734.TAN Jie,JIN Jie,DU Gang,et al.Effect of flap length on the performance of single-expansion-ramp-nozzle［J］.Journal of Aerospace Power,2012,27(4):726-734.(in Chinese)
[10]	谭杰,金捷.单边膨胀喷管几何参数对内特性和流场的影响［J］.推进技术,2013,34(2):152-160.TAN Jie,JIN Jie.Effects of geometric parameters on internal performance and flowfield of single expansion ramp nozzles［J］.Journal of Propulsion Technology,2013,34(2):152-160.(in Chinese)
[11]	马伟.发动机尾喷管气动特性数值模拟研究［D］.北京:北京航空航天大学,2015.MA Wei.Numerical study of aerodynamic performance of exhaust nozzle［D］.Beijing:Beijing University of Aeronautics and Astronautics,2015.(in Chinese)
[12]	李翔宇.单边膨胀喷管气动和红外性能的数值模拟研究［D］.北京:北京航空航天大学,2016.LI Xiangyu.Numerical investigation on the aerodynamic and infrared performance of single expansion ramp nozzle［D］.Beijing:Beijing University of Aeronautics and Astronautics,2016.(in Chinese)
[13]	LI Xiangyu,JIN Jie,DU Gang.Experimental and numerical investigation on the performance of single expansion ramp nozzle of different flap length［R］.Keynes,Australia,APISAT2015,2015.
[14]	汪维娜,王占学,乔渭阳.单斜面膨胀喷管几何参数对流场和性能的影响［J］.航空动力学报,2006,21(2):280-284.WANG Weina,WANG Zhanxue,QIAO Weiyang.Investigation of the influence of single expansion ramp nozzle geometric parameters on the flow field and performance［J］.Journal of Aerospace Power,2006,21(2):280-284.(in Chinese)
[15]	陈兵,徐旭.基于遗传算法和空间推进方法的单壁扩张优化设计研究［J］.航空学报,2007,28(4):827-832.CHEN Bing,XU Xu.Optimization design of single expansion ramp nozzles using genetic algorithms based on a parabolized navier stokes solver［J］.Acta Aeronautica et Astronautica Sinica,2007,28(4):827-832.(in Chinese)
[16]	庞丽娜,徐惊雷,范志鹏.单边膨胀尾喷管下壁面型线优化设计及实验研究［J］.推进技术,2014,35(10):1297-1302.PANG Lina,XU Jinglei,FAN Zhipeng.Optimization design and experimental study of cowl configuration of SERN［J］.Journal of Propulsion Technology,2014,35(10):1297-1302.(in Chinese)
[17]	苗萌,曾鹏,阎超.基于替代模型的三维后体尾喷管优化设计［J］.空气动力学学报,2013,31(5):641-646.MIAO Meng,ZENG Peng,YAN Chao.Surrogate-based optimization of 3D afterbody nozzle［J］.Acta Aerodynamica Sinica,2013,31(5):641-646.(in Chinese)
[18]	施小娟,吉洪湖.基于代理模型的二元收扩喷管流道型面优化设计［J］.航空动力学报,2016,31(9):2124-2131.SHI Xiaojuan,JI Honghu.Optimization design of two dimensional convergent and divergent nozzles profile based on surrogate models［J］.Journal of Aerospace Power,31(9):2124-2131.(in Chinese)
[19]	成沉,鲍福廷,刘旸,等.基于响应面法的喉栓式喷管型面优化设计［J］.固体火箭技术,2014,37(1):47-51.CHENG Chen,BAO Futing,LIU Yang,et al.Optimization design for contour of pintle nozzle based on response surface method［J］.Journal of Solid Rocket Technology,2014,37(1):47-51.(in Chinese)
[20]	BURLEY J R,CARLSON J R.Circular-to-rectangular transition ducts for high-aspect-ratio nonaxisymmetric nozzles［R］.AIAA 85-1346,1985.
[21]	TIMOTHY W S.A concept exploration method for product family design［D］.Atlanta，US:Georgia Institute of Technology,1998.