INVESTIGATION OF THE SUPERSONIC THROUGH-FLOW COMPRESSOR CONCEPT. VOLUME I. PERFORMANCE POTENTIAL AND MECHANICAL DESIGN STUDY OF THE SUPERSONIC INFLOW ENGINE.
Abstract
An investigation was conducted to evaluate the performance potential of the supersonic inflow turbojet engine (SSIFE) utilizing a supersonic through-flow compressor. The engines considered in this study were designed to operate as accelerators at flight Mach numbers up to 3.5 in the 1980 time period. During the preliminary phases of this study, both cruise and the accelerator engines were considered. The program consisted of a preliminary study of compressor and engine configurations, followed by detailed compressor and engine performance investigations. Experimental investigations of supersonic cascade and diffuser performance were also conducted to provide experimental information required to evaluate this concept. Concurrent with this funded program a corporate-sponsored program was also conducted to evaluate the performance potential of supersonic combustion in the SSIFE and to generate a practical mechanical design for this engine. This report is intended to serve as a summary of all of the work performed on the supersonic inflow engine concept. Comparisons were made between the performance and mechanical design of both the SSIFE and an advanced turbojet sized to produce the same transonic thrust. The SSIFE evolved during the design study was 42 percent shorter, had the same frontal area, and approximately 15 percent greater installed weight than the advanced turbojet. The results obtained from component tests of supersonic cascades and the downstream supersonic diffuser were in general agreement with the level of compression system performance estimated for the engine analyses. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1967
- Accession Number
- AD0382020
Entities
People
- Robert L. O'brien
Organizations
- United Aircraft Corporation