Exploratory Development of Reduced Length Turbo-Propulsion Combustion Systems. Part 1. Preliminary 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. To attain this goal, two concepts based on maximum combustor dome airflow are being developed. The first is an integration of the diffuser and combustor to achieve minimum length and maximum efficiency with smoke free operation. The second is to achieve improved fuel injection using a high density premix fuel injection technique to obtain acceptable exit temperature patterns in a high temperature rise combustor. The fuel injection technique is the development of single modules for premixing of low pressure fuel and high density air ahead of the combustor dome. These modules are capable of accepting contaminated fuels and can be combined to permit testing as sectors of a full annular combustor. Initial testing of the various fuel injection premix modules and different designs of the integrated diffuser-combustor under Phase I of this program has verified the soundness of the concepts being developed. Based upon these results, the most promising premix modules and the best diffuser-combustor design will be combined as sectors of a full annular combustor for further evaluation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1968
- Accession Number
- AD0393661
Entities
People
- Donald A. Macnaughton
- J. T. Wyrobek
- Jack J. Simon
- Richard J. Stettler
Organizations
- General Motors