Exploratory Development of Reduced Length Turbo-Propulsion Combustion Systems. Part II. Component Design and Development.
Abstract
Advanced design turbo-propulsion engines for future aircraft require a compact, high-performance combustion system for high thrust-to-weight ratios and an increased level of reliability. Two concepts are being incorporated to attain this goal. First, an integrated diffuser-combustor designed to achieve minimum length and maximum efficiency with smoke-free operation is being developed. Second, improved fuel injection using a high-density premix fuel injection technique to obtain acceptable combustor exit temperature patterns in a high-temperature-rise combustor is promising. Four diffuser designs were evaluated to establish length reduction techniques. Further, four premix module designs were evaluated for combustor performance values. Additionally, to complete the system design to meet the stated objectives, three liner cooling configurations were tested for system compatibility. Test data from the diffusers, premix modules, and liner cooling configurations resulted in a 60-degree sector design which attained program objectives. The technology developed on the 60-degree sector testing was used to design a scalable 120-degree sector and a full annular combustor. Combustors incorporating integrated diffuser-combustor and fuel and air premix techniques have definite application in future aircraft turbo-propulsion engines. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1971
- Accession Number
- AD0515005
Entities
People
- Richard J. Stettler
- Samuel B. Reider
Organizations
- General Motors