Aerodynamic Coupling Analysis of Counter⁃rotating Propfan and Inlet Flow Field  

作　　者：WANG Dingqi GAO Yang WANG Dingqi;GAO Yang(The Engine Department,Chinese Flight Test Establishment,Xi′an 710089,China)

机构地区：[1]The Engine Department,Chinese Flight Test Establishment,Xi'an 710089,China

出　　处：《International Journal of Plant Engineering and Management》2023年第2期65-85,共21页国际设备工程与管理（英文版）

摘　　要：Taking a propfan engine as the research object,the CFD method was used for 3D modeling and unsteady slip flow for numerical calculation.The propfan rotation domain and the nacelle outside flow domain were meshed by using the partition splicing grid technology.Used the Reynolds⁃averaged of N⁃S equation,the Reynolds stress term uses the RNG turbulence model;and based on the slip grid method,numerical calculation of the flow field with different Mach numbers,front and rear blade angles and engine state were carried out;and the change law of propeller fan characteristics and the influence of slip flow on the inlet flow field were analyzed.The blade angle was the key parameter of the propeller fan characteristic conditions.When the blade angle increases from 41°to 50°,the thrust coefficient increases by 31.2%,and the power coefficient increases by 33.4%;in the climbing state of the propeller fan,the maximum total pressure distortion at the inlet port of 6.8%;the cross section is less affected by the slip flow of the propfan;and the pressure distribution is relatively uniform,but the area of the flow channel is small.The research results can provide a solution for the matching of the counter⁃rotating propeller fan and the engine and the arrangement of the air inlet measuring rake.

关 键 词：counter rotor propfan numerical simulation patched⁃grid dynamic characteristic unsteady flow distortion of total pressure 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]