A Thermal Investigation of the AFAPL Turbine Engine Heat Transfer Test Facility.
Final rept. Mar-Dec 74,
AIR FORCE AERO PROPULSION LAB WRIGHT-PATTERSON AFB OHIO
Pagination or Media Count:
An experimental investigation of the Heat Transfer Test Facility at the Air Force Aero Propulsion Laboratory was conducted to determine gas temperature distributions in the facilitys combustion chamber. The combustor consists of an air-fed, water-cooled duct with a hydrogen fuel injector system. Gas temperatures in the range of 1000 F to 3000 F were studied. The combustion chamber pressure was 3.4 atm, and its air mass flow rate varied from 1.0-3.0 lbmsec. Configurations of type-K and type-R thermocouples were used to measure temperature profiles parallel and perpendicular to the gas stream flow in the combustion chamber. These measurements indicated that a fairly uniform turbulent temperature profile developes at gas temperatures above 2000 F. In addition, the gas temperature was determined by 1 a thermal calculation which was based on the temperature decrease of the gas from the adiabatic flame temperature as a result of heat loss, and 2 a transient type K thermocouple probe. The thermal calculation agreed with experimental data to within 6 at gas flow rates of 2.0 and 3.0 lbmsec. Author
- Test Facilities, Equipment and Methods
- Jet and Gas Turbine Engines