A Mach 12, blowdown-type, storage heated, aerodynamic test facility, previously adapted to provide Mach 3.5 ramjet engine propulsion testing, has been further modified to provide high pressure, gas turbine combustor emission testing capability. Pressure control and temperature control systems have been incorporated into the original facility to provide constant flow properties for run times up to 30 minutes. An on-line gas sample system has also been designed and integrated with the facility to provide continuous combustor emission information.
These features now combine with the existing pebble bed storage heater, blowdown air supply and heated fuel supply systems to provide very high Mach number aerodynamic simulation, intermediate Mach number aeropropulsion testing and low Mach number, full scale, gas turbine combustor emission testing capability. Pressures of 1500 psia can be achieved with temperatures up to 2000 degrees Fahrenheit and flow rates up to 50 lb/sec.
This unique facility is described, with emphasis on the facility modifications necessary to provide the gas turbine combustor emission testing capability. To appreciate the modifications made, some of the differences between Mach 12 aerodynamic and low Mach number, gas turbine combustor emission testing are discussed. Results from some recent gas turbine emissions tests are also provided.
