高为民,任智博,王勤,王晓良.飞机进气道/ 发动机台架联合试验及匹配特性研究[J].航空发动机,2017,43(4):74-78
飞机进气道/ 发动机台架联合试验及匹配特性研究
Combination Test and Match Characteristics Research of an Aircraft Inlet / Engine Testbed
  
DOI:
中文关键词:  :动应力  测量试飞  风扇叶片  大涵道比  涡扇发动机
英文关键词:进发匹配  进气道试验  流动畸变  发动机台架
基金项目:航空动力基础研究项目资助
作者单位E-mail
高为民,任智博,王勤,王晓良 中国航发沈阳发动机研究所沈阳110015 Gao_weimin@hotmail.com。 
摘要点击次数: 401
全文下载次数: 274
中文摘要:
      为了确定发动机地面装机条件下的进气畸变大小,对1 种全尺寸进气道与发动机地面台架开展进发联合试验研究。试 验速度条件为飞机静止状态,对应飞机迎角为0毅,马赫数为0。参试进气道为2 元外压式超声速进气道,参试发动机为大推力双转 子带加力涡轮风扇发动机。采用地面台架联合试车的方法,获得了不同进气道条件下的进发匹配特性数据,包括在发动机不同工作 转速下进气道出口流场的稳态总压特性、动态畸变特性等参数,并与进气道缩比模型风洞试验结果进行了对比分析。结果表明:全 尺寸进气道的出口畸变随发动机空气流量增加而增大,与风洞试验结果一致,但防护网对于畸变的影响效果相反。
英文摘要:
      In order to determine the distortion under the engine installed conditions, a combination test were studied on a full scale inlet and an engine ground testbed. The speed condition of the test was simulated at the aircraft stationary state, the corresponding angle of attack was 0毅and mach was 0. The tested inlet was a two-dimensional external-compression supersonic inlet, the tested engine was a large thrust double spod turbofan with afterburer. Using the ground testbed combined test method袁the test got the inlet characteristic parameters including steady-state pressure distortion, time-variant distortion at the Aerodynamic Interface Plane (AIP) in various engine rotating speed, and test results were compared with the wind-tunnel. Results show that the distortion of full scale inlet increases with the engine air flow increases, which is consistent with the results of scale model test in the wind-tunnel, but the effect of the protective net on the distortion is opposite against the wind-tunnel.
查看全文  查看/发表评论  下载PDF阅读器