Design and examination of a turboprop inlet with scavenge duct  

作　　者：Gaojie ZHENG Zhenlong WU Huijun TAN Yue ZHANG Kun WANG 

机构地区：[1]College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

出　　处：《Chinese Journal of Aeronautics》2023年第8期32-42,共11页中国航空学报（英文版）

基　　金：co-supported by the Civil Airplane Technology Development Program,China(No.MJ-2020-F-10);the National Science and Technology Major Project,China(No.HT-J2019-V-0004-0095).

摘　　要：The inlet with scavenge duct is an important part of turboprop aircraft engine.This type of inlet normally has a complex shape,of which the design is challenging and directly affects the flow field quality of the engine entrance and thus the engine performance.In this paper,the parametric design method of a turboprop aircraft inlet with scavenge duct is established by extracting and controlling the transition law of the critical characteristic parameters.The inlet’s performance and internal flow characteristics are examined by wind-tunnel experiment and numerical simulation.The results indicate that a flow tendency of winding up on both sides is formed due to the induction of the inlet profile,as well as a vortex pair on the back side of the power output shaft.The vortex pair dominates the pressure distortion index on the Aerodynamic Interface Plane(AIP).In addition,with the increase of freestream angle of attack,the total-pressure recovery coefficient of the inlet increases gradually while the total pressure distortion index decreases slightly.On the basis of the experimental results under different working conditions,the parametric design method proposed in this paper is feasible.

关 键 词：Design methord Flowcharacteristics Inlet performance Scavengeduct Turbopropaircraft 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]