Advanced High Temperature Combustor Research for Small Gas Turbine Engines

Design studies and an experimental test program have been conducted to provide basic technology and preliminary flightweight designs for a small (2 lb/sec total engine airflow) high temperature rise combustor with a 3000 F exit temperature, as a first step towards demonstration in a research 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, fuel introduction, 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 transpiration cooled liners.