An Experimental Study of a Catalytic Combustor for an Expendable Turbojet Engine
Abstract
A catalytic combustor was designed, an existing one modified, and both were tested on a small turbojet engine. The existing catalytic combustor, combustor A, used straight through flow and was modified by adding a flame arrestor to the combustor inlet. Combustor B was designed to use reverse flow with a preburner and air dilution zones. Combustors A and B were designed for an air capacity up to 0.75 lbm/sec and outlet temperatures of 1800 F. Combustor B did prove successful. Cold flow total pressure loss in combustor B was two percent, while the total pressure loss during heat addition was a maximum of seven percent. The flame arrestors tested on combustor A did not prove to be successful. Hydrogen was used as fuel for both combustors. Temperatures across the catalyst face varied by 290 F at a turbine inlet temperature of 1070 F, 370 F at 1450 F. Turbine inlet temperatures varied by 55 F at an average 1045 F, 190 F at an average 1475 F. The maximum temperature rise across the combustor during testing was 1565 F and the maximum turbine inlet temperature tested was 1855 F.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1978
- Accession Number
- ADA056512
Entities
People
- Larry E. Taylor
Organizations
- Air Force Institute of Technology