0
RESEARCH PAPERS

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by an Optimization Procedure

[+] Author and Article Information
Y. Tsujikawa, M. Nagaoka

Department of Aeronautical Engineering, University of Osaka Prefecture, Mozu-umemachi, Sakai 591 Japan

J. Eng. Gas Turbines Power 113(1), 100-105 (Jan 01, 1991) (6 pages) doi:10.1115/1.2906515 History: Received February 05, 1990; Online April 24, 2008

Abstract

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including the scramjet engine) to achieve maximum performance. The optimization of such criteria as thermal efficiency, specific output, and total performance for gas turbine engines, and overall efficiency, nondimensional thrust, and specific impulse for aero-engines has been performed by the optimization procedure with the multiplier method. Comparison of results with analytical solutions establishes the validity of the optimization procedure.

Copyright © 1991 by The American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In