Design of A Small-Turbjojet Compressor Test Facility

Date of Award

2021

Degree Name

M.S. in Mechanical and Aerospace Engineering

Department

Department of Mechanical and Aerospace Engineering

Advisor/Chair

Markus P. Rumpfkeil

Abstract

Validation of compressor aerodynamic design can be obtained through in-engine testing with considerable investment of time and money, or in rig testing, wherein a range of interchangeable designs can be tested without exposure to effects of other engine components. To more rapidly explore centrifugal and mixed-flow compressor designs for small, thrust-producing aviation gas-turbine engines, called turbojets, the Air ForceResearch Laboratories (AFRL) initiated development of a test apparatus to be integrated into an existing test facility at Wright-Patterson Air Force Base (WPAFB). Design of the inlet flow conditioning and measuring system, mechanical systems, exhaust discharge valve, and exhaust collector is accomplished through sizing calculations, aerodynamic and mechanical analysis. This thesis project presents the final design of this small-turbojet compressor test facility, capable of testing virtually the entire operating map of compressors in the desired size range. Fabrication of the test rig is underway as of the conclusion of this thesis; component testing, assembly, and initial test article testing is planned thereafter.

Keywords

Aerospace Engineering, Engineering, Mechanical Engineering, turbojet, small turbojet, compressor, compressor testing, mechanical design

Rights Statement

Copyright © 2021, author

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