Performance of a Turbojet Combustor Using Natural Gas Fuel Heated to 1200 Degrees F (922 K)
Author : James S. Fear
Publisher :
Page : 20 pages
File Size : 42,34 MB
Release : 1970
Category :
ISBN :
Author : James S. Fear
Publisher :
Page : 20 pages
File Size : 42,34 MB
Release : 1970
Category :
ISBN :
Author : James S. Fear
Publisher :
Page : 28 pages
File Size : 24,16 MB
Release : 1970
Category : Airplanes
ISBN :
Combustion efficiency was determined using natural gas fuel over a range of injection temperatures from ambient to 1200' F (922 K). The combustor was comprised of three U-gutter flameholders mounted downstream of a trumpet-shaped diffuser in a rectangulai housing. A simple film-cooled liner was used. Tests were conducted at ambient pressure over a range of fuel-air ratios and combustor reference velocities. Increases in efficiency of more than 40 percentage points were achieved at the higher fuel temperatures. The results are applicable to natural gas afterburner design and to the design of advanced low-pressure-loss primary combustors.
Author : James S. Fear
Publisher :
Page : 19 pages
File Size : 38,30 MB
Release : 1970
Category :
ISBN :
Author :
Publisher :
Page : 776 pages
File Size : 21,87 MB
Release : 1971
Category : Mechanics, Applied
ISBN :
Author : Nicholas R. Marchionna
Publisher :
Page : 44 pages
File Size : 39,38 MB
Release : 1970
Category : Airplanes
ISBN :
Author :
Publisher :
Page : 370 pages
File Size : 26,26 MB
Release : 1970
Category : Aeronautics
ISBN :
Author : Helmut F. Butze
Publisher :
Page : 50 pages
File Size : 33,8 MB
Release : 1979
Category : Airplanes
ISBN :
Author : Nicholas R. Marchionna
Publisher :
Page : 19 pages
File Size : 35,92 MB
Release : 1973
Category :
ISBN :
Author : David N. Bowditch
Publisher :
Page : 34 pages
File Size : 28,29 MB
Release : 1960
Category : Aerodynamics, Supersonic
ISBN :
Author : Richard W. Niedzwiecki
Publisher :
Page : 44 pages
File Size : 22,61 MB
Release : 1971
Category : Aircraft gas-turbines
ISBN :
A 27-inch (68.6-cm) long rectangular combustor segment consisting of an array of 48 combustor modules was tested to determine its performance. Each module mixed and swirled fuel with air and stabilized combustion. Test conditions were inlet temperatures of 600 [degree] and 1150 [degree] F (589 and 894 K), a pressure of 3 atmospheres, and reference velocities to 160 ft/sec (48.8 m/sec). Results were combustion efficiencies of 100 percent, a pressure loss of 5.4 percent for an inlet Mach number of 0.25, a heat release rate of 11.86x10 [power of six] Btu/(hr)(ft [power of three] )(atm) for a temperature ratio of 2.5, and pattern factor spans of 0.30 to 0.37 and 0.22 to 0.28 with 600 [degree] and 1150 [degree] F (589 and 894 K) inlet air temperatures, respectively. Altitude blowout and relight data, as well as a comparison of results with a longer combustor, are also included.