Author : J. Howard Childs
Publisher :
Page : 56 pages
File Size : 19,66 MB
Release : 1947
Category : Airplanes
ISBN :
The combustion performance and particularly the phenomenon of altitude operational limits was studied by operating the annular combustor of a turbojet engine over a range of conditions of air flow, inlet pressure, inlet temperature, and fuel flow. The combustor investigated was not the latest version of this combustor and the data are presented primarily because they are indicative of general trends and phenomena that apply to a large class of turbojet combustors.
Author : Eugene V. Zettle
Publisher :
Page : 24 pages
File Size : 24,87 MB
Release : 1955
Category : Airplanes
ISBN :
Author : RIchard J. McCafferty
Publisher :
Page : 96 pages
File Size : 16,33 MB
Release : 1948
Category : Aeronautics
ISBN :
Author : Helmut F. Butze
Publisher :
Page : 50 pages
File Size : 49,81 MB
Release : 1979
Category : Airplanes
ISBN :
Author : Suresh Ravi Vilayanur
Publisher :
Page : 370 pages
File Size : 15,64 MB
Release : 1998
Category : Combustion gases
ISBN :
Author : Donald F. Schultz
Publisher :
Page : 58 pages
File Size : 11,27 MB
Release : 1975
Category : Aircraft gas-turbines
ISBN :
Author : Jerrold D. Wear
Publisher :
Page : 60 pages
File Size : 44,80 MB
Release : 1972
Category : Airplanes
ISBN :
Tests of various fuel nozzles were conducted with natural gas fuel in a full-annulus combustor. The nozzles were designed to provide either axial, angled, or radial fuel injection. Each fuel nozzle was evaluated by measuring combustion efficiency at relatively severe combustor operating conditions. Combustor blowout and altitude ignition tests were also used to evaluate nozzle designs. Results indicate that angled injection gave higher combustion efficiency, less tendency toward combustion instability, and altitude relight characteristics equal to or superior to those of the other fuel nozzles that were tested.
Author : Nicholas R. Marchionna
Publisher :
Page : 44 pages
File Size : 44,39 MB
Release : 1970
Category : Airplanes
ISBN :
Author : Donald F. Schultz
Publisher :
Page : 52 pages
File Size : 13,18 MB
Release : 1972
Category : Aircraft gas-turbines
ISBN :
Inlet air velocity profile tests were conducted on a full-scale short-length 102-centimeter-diameter annual combustor designed for advanced gas turbine engine applications. The inlet profiles studied include radial distortions that were center peaked, and tip peaked, as well as a circumferential distortion which was center peaked for one-third of the circumference and flat for the other two-thirds. An increase in combustor pressure loss was the most significant effect of the radial air velocity distortions. With the circumferential distortion, exit temperature pattern factor doubled when compared to a flat velocity profile.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 472 pages
File Size : 21,37 MB
Release : 1955
Category : Aeronautics
ISBN :
