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ATR动力飞行器的变几何进气道设计研究
《宇航学报》2017年第3期240-247,共8页崔鹏 李国曙 张军 谭慧俊 
针对飞行器总体和空气涡轮火箭(ATR)发动机的设计要求,提出一种中心半锥体可调节的变几何进气道方案,探索了Ma 0.6~3.0宽速域性能平衡、类航发需求的出口畸变控制等设计方法。通过中心体的平移进行喉道面积调节并兼顾流量需求,扩张段设...
关键词：进气道 变几何 方案设计 畸变控制 风洞试验 
Unsteady supercritical/critical dual flowpath inlet flow and its control methods被引量：3
《Chinese Journal of Aeronautics》2017年第6期1877-1884,共8页Jun LIU Huacheng YUAN Yunfei WANG Ning GE 
co-supported by the Funding for Outstanding Doctoral Dissertation in NUAA of China(No.BCXJ16-01);Funding of Jiangsu Innovation Program for Graduate Education(No.KYLX16_0393);Foundation of Graduate Innovation Center in NUAA of China(No.KFJJ20160204);the Fundamental Research Funds for the Central Universities and the Aerospace Science;Technology Innovation Fund of China Aerospace Science and Technology Corporation
The characteristics of unsteady flow in a dual-flowpath inlet, which was designed for a Turbine Based Combined Cycle（TBCC） propulsion system, and the control methods of unsteady flow were investigated experimentally...
关键词：Airbreathing hypersonic vehicle Dual flowpath inlet Terminal shock oscillation Turbine based combined CYCLE Unsteady flow 
基于激波形状控制的高超声速轴对称进气道设计
《应用能源技术》2018年第9期7-8,共2页程林 
文中主要针对基于二次流控制的高超声速轴对称可调进气道,给出了其具体的流道实现方案,完成了进气道设计工作。而后通过全流道仿真分析,检验了该可调进气道在非设计点的工作情况,获得了其工作特性,仿真说明文中设计的进气道具有良好的...
关键词：高超声速 进气道 可调 二次流 激波控制 
Unsteady flow characteristics in an over-under TBCC inlet during mode transition under unthrottled and throttled conditions
《Chinese Journal of Aeronautics》2024年第12期275-295,共21页Liang CHEN Yue ZHANG Hao ZHANG Huijun TAN Ziyun WANG Hang YU Hongchao XUE 
funded by the National Natural Science Foundation of China(Nos.12025202,U20A2070 and 12172175);the National Science and Technology Major Project,China(No.J2019-Ⅱ-0014-0035);the Postdoctoral Fellowship Program of CPSF,China(No.GZB20230970);the Science Center for Gas Turbine Project,China(Nos.P2022-C-Ⅱ-002-001 and P2022-A-Ⅱ-002-001);the Young Scientific and Technological Talents Project of Jiangsu Association for Science and Technology,China(No.TJ-2021-052).
The study presents an experimental exploration into the mode transition of an overunder TBCC(Turbine-Based Combined Cycle)inlet,with a specific emphasis on the flow characteristics at off-design transition Mach number...
关键词：Over-under TBCC inlet Mode transition Off-design condition Unsteady flows HYSTERESIS 
Design method with controllable velocity direction at throat for inward-turning inlets被引量：4
《Chinese Journal of Aeronautics》2019年第6期1403-1415,共13页Wenyou QIAO Anyuan YU Wei GAO Weixing WANG 
supported by the National Natural Science Foundation of China (Nos. 11702229, 11602207 and 91641103)
In the design of a hypersonic inward-turning inlet by applying the traditional basic flowfield, a reflected shock-wave is formed in the isolator due to the continuous reflection of the cowlreflected shock wave in the ...
关键词：HYPERSONIC Inverse design Inward-turning INLET Method of characteristic Shock wave 
Numerical assessment on improving multistage centrifugal impeller performance by changing inlet skew angle at impeller inlet被引量：2
《Journal of Central South University》2012年第4期953-961,共9页M.N.Labib Woo Ju-sik Choi Du-youl T.Utomo B.Fajar Chung Han-shik Jeong Hyo-min 
Project(NRF-2010-013-D00007) supported by the National Research Foundation of Korea;Work finacially supported by the 2010 Research Professor Fund of Gyeongsang National University,Korea
Multistage centrifugal impellers with four different skew angles were investigated by using computational fluid dynamics.The purpose of this work is to investigate the influences of lean angle at the blade tip of the ...
关键词：computational fluid dynamics secondary flow blade inlet skew angle multistage centrifugal compressor 
Numerical Analysis and Experimental Validation of a Submerged Inlet on the Plane Surface被引量：6
《Chinese Journal of Aeronautics》2005年第3期199-205,共7页孙姝 郭荣伟 
National973PlanofChina
In order to get a deep insight of a submerged inlet on the plane surface, the integrated flow field of the inlet and fuselage has been numerically studied. The investigation is mainly focused on the formation of the t...
关键词：submerged inlet on the plane surface CFD boundary layer counter-rotating vortices total pressure coefficient 
高超声速进气道起动特性数值研究被引量：14
《宇航学报》2007年第6期1482-1487,共6页丁海河 王发民 
国家自然科学重点基金(90505016)
进气道的起动能力决定着冲压发动机可能的工作范围,针对由于来流马赫数引起的进气道不起动现象,采用CFD技术开展了高超声速二维进气道起动与不起动过程的数值计算,并检验了一种改善进气道起动性能的边界层抽吸法。结果表明,进气道不起...
关键词：进气道 起动特性 边界层抽吸 
高超声速飞行器前体/进气道一体化气动设计回顾与展望
《空天技术》2024年第2期15-38,共24页许耀宇 黄河峡 谭慧俊 蔡佳 刘梦莹 王磊 满延进 李宏东 
国家自然科学基金(12272177,12025202,U20A2070);国家重大科技专项(J2019-II-0014-0035);青年托举人才项目(2021-JCJQ-QT-064);先进航空动力创新工作站资助项目(HKCX202-02-005);进排气技术教育部重点实验室基金(CEPE2020012)。
高超声速飞行器具有飞行速度快、突防能力强的优点,现已经成为世界各国军事战略及装备发展博弈的焦点之一,前体/进气道一体化气动设计是提升高超声速飞行器/推进系统性能的一个核心途径。综述了升力体/进气道、乘波前体/进气道以及轴对...
关键词：高超声速飞行器 升力体 乘波前体 轴对称前体 进气道 一体化 
Cervical inlet patch-optical coherence tomography imaging and clinical significance被引量：3
《World Journal of Gastroenterology》2012年第20期2502-2510,共9页Chao Zhou Tejas Kirtane Tsung-Han Tsai Hsiang-Chieh Lee Desmond C Adler Joseph M Schmitt Qin Huang James G Fujimoto Hiroshi Mashimo 
Supported by The VA Boston Healthcare System and NIH grants R01-CA75289-14,to Fujimoto JG and Mashimo H;K99-EB010071-01A1,to Zhou C;Air Force Office of Scientific Research contract FA9550-10-1-0063,to Fujimoto JG;Medical Free Electron Laser Program contract FA9550-10-1-0551,to Fujimoto JG;the MIT/CIMIT Medical Engineering Fellowship,to Tsai TH
AIM:To demonstrate the feasibility of optical coherence tomography(OCT)imaging in differentiating cervical inlet patch(CIP)from normal esophagus,Barrett'sesophagus(BE),normal stomach and duodenum. METHODS:This study w...
关键词：Cervical inlet patch Heterotopic gastric mucosa Optical coherence tomography Optical biopsy Barrett’s esophagus 
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