Design of a High Pressure Centrifugal Compressor Impeller of an Aviation Turboshaft Engine

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Sadr, Motahareh | 2019

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Type of Document: M.Sc. Thesis
Language: Farsi
Document No: 52293 (45)
University: Sharif University of Technology
Department: Aerospace Engineering
Advisor(s): Ghorbanian, Kaveh
Abstract:
The purpose of this study is developing the design means of a high pressure centrifugal compressor impeller for aviational applications i.e. turboshaft engines. The logic and constraints of designing a high pressure centrifugal impeller for a turboshaft engine is different from those of low pressure aerial or high speed industrial ones. This kind of impeller is deployed in a number of advanced generation of aero engines. In this study, the centrifugal impeller design tools are developed using two design methods. Then, the results are compared, validated and corrected with an existing high pressure impeller data. A number of impellers with pressure ratios ranging from 6 to 11 are designed and the effects of pressure ratio change on main design parameters are studied. This type of compressor which is used in helicopter turboshaft engines, has distinguished performance characteristics and is very popular. After one dimensional design is conducted, three dimensional flow simulation through impeller is carried out and its performance map is obtained
Keywords:
Centrifugal Compressor ; Impeller Design ; High Pressure ; Helicopter Turboshaft Engine ; Turboshaft