Authors : Rohit Kumar

Volume/Issue : Volume 9 - 2024, Issue 1 - January

Google Scholar : http://tinyurl.com/mvfdfzf5

Scribd : http://tinyurl.com/hjtznth7

DOI : https://doi.org/10.5281/zenodo.10565920

Abstract : This paper presents the design and analysis of a high-speed centrifugal compressor for aircraft engine applications. The compressor was designed to operate at a pressure ratio of 6.5 and a design speed of 70,000 RPM. The design process involved the selection of suitable impeller and diffuser geometries, as well as the determination of the optimal blade angles and chord lengths. The aerodynamic performance of the compressor was analyzed using computational fluid dynamics (CFD) simulations, and the structural integrity was evaluated using finite element analysis (FEA) simulations. The results of the simulations showed that the compressor met the design requirements for both aerodynamic performance and structural integrity.This research paper presents the design, analysis, and testing of a high-speed centrifugal compressor for use in aircraft engines. The compressor was designed using a combination of theoretical calculations and optimization techniques to achieve high efficiency and performance. Computational Fluid Dynamics (CFD) simulations were used to analyze the flow characteristics and performance of the compressor under various operating conditions. The compressor was manufactured using advanced materials and manufacturing techniques, and was tested under various operating conditions to evaluate its performance. The results of the testing showed that the compressor achieved high efficiency and performance, meeting the stringent requirements of aircraft engine applications. The paper concludes by highlighting the importance of high-speed centrifugal compressors in aircraft engine applications, and the need for continued research in this area to develop more efficient and high-performance compressors.