ADVANCED HIGH TEMPERATURE COMBUSTOR RESEARCH FOR SMALL GAS TURBINE ENGINES
Abstract
Design studies and an experimental test program were conducted to provide basic technology and preliminary flight-weight designs for a small (2-5 lb/sec total engine airflow) high temperature rise combustor with a 3000F exit temperature, as a first step towards demonstration in an advanced engine. Tests were conducted to evaluate the combustor design parameters developed in the initial design study phase of the program pertaining to liner cooling techniques, primary-diluent air mixing, fuel introduction and patronization, and primary zone performance. The preliminary designs optimize the technology developed in this program and comprise both annular and can end-mounted combustor configurations incorporating an annular vaporizer fuel introduction system and transpirationally cooled liners.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 01, 1968
- Accession Number
- AD0681948
Entities
People
- Richard H. Andersen