Evolution of Compression Processes in Aero-Engine Thermal Cycles
Y. Daren, T. Jingfeng*, B. Wen
Identifiers and Pagination:Year: 2008
First Page: 1
Last Page: 7
Publisher Id: TOAEJ-1-1
Article History:Received Date: 13/10/2007
Revision Received Date: 15/01/2008
Acceptance Date: 23/01/2008
Electronic publication date: 20/2/2008
Collection year: 2008
open-access license: This is an open access article distributed under the terms of the Creative Commons Attribution 4.0 International Public License (CC-BY 4.0), a copy of which is available at: https://creativecommons.org/licenses/by/4.0/legalcode. This license permits unrestricted use, distribution, and reproduction in any medium, provided the original author and source are credited.
In order to provide a basis for the establishment of an applicable strategy for the development of aero-engine thermal cycles, the evolution of compression processes in aero-engine thermal cycles is reviewed in this paper by analyzing the compression requirements for the injection or extraction of energy. It is therefore concluded that the injection of energy in the compression is required for applications in low speed ranges, for example, the injection of energy in turbojet compressors; the method of adiabatic compression is desirable for applications in intermediate speed ranges, for example, shock interactions for ramjets/scramjets; and the extraction of energy is needed for applications in high speed ranges, for example, the extraction of energy in ramjets with energy-bypass. The injection or extraction of energy in the compression heavily depends on the aero-engine performance required for applications in different speed ranges.