A Study on Aerodynamic Design of a Transonic Mixed-Flow Compressor for UAV

Choi, Jae-Ho

Journal of the Korea Institute of Military Science and Technology 2008;11(2):152-160.

Jae-Ho Choi

Samsung Techwin

무인항공기용 천음속 사류형 압축기의 공력 설계

최재호

삼성테크윈 파워시스템연구소

Abstract

In the present paper, a transonic mixed-flow compressor that has relatively lower frontal area than that of centrifugal compressors is discussed, and aerodynamic design as well as performance prediction are performed. Main design constraints are compressor exit Mach number of 0.3 and flow angle of 30degrees at the design point, and maximum overall compressor diameter of 177mm, that is 7.0inch. The mass flow rate of design point and pressure ratio are 1.05kg/s and 5.2:1, respectively. The aerodynamic design results show that the transonic compressor designed with forward-swept inducer and curved diffuser can have the target performance with efficiency of 75% within the given constraints. And the compressor exit flow characteristics are discussed here.

Key Words: Mixed-Flow Compressor, Transonic Compressor, UAV(Unmanned Aerial Vehicle), Aerodynamic Design