A method and apparatus are provided for bleeding compressed air downstream from a diffuser outlet and upstream from a fuel injector in a gas turbine engine. A bleed manifold aft wall is disposed between the diffuser outlet and the fuel injectors and is configured for blocking recirculation flow of air discharged from the diffuser outlet to create a sheltered zone disposed in direct flow communication with the diffuser outlet. Bleed holes are disposed in the sheltered zone for channeling a portion of the diffuser discharge air directly therefrom as bleed air for use in an aircraft environmental system.
John M. Koshoffer - Forest Park OH Edward E. Ekstedt - Montgomery OH Billy P. Samuel - Madeira OH Edward I. Stamm - Madeira OH
Assignee:
General Electric Company - Cincinnati OH
International Classification:
F02C 722
US Classification:
60737
Abstract:
A carburetion assembly including flow control means is provided for controlling a discharge spray angle of a fuel and air mixture thereof. According to one embodiment of the present invention, the flow control means can comprise a plurality of circumferentially spaced apertures in a shroud member which are effective for providing a control portion of compressor airflow in a downstream, axial direction from a swirler stage of the swirler assembly. The apertures provide a predetermined amount of airflow circumferentially about the fuel and air mixture for constraining the mixture and controlling the discharge spray angle thereof.
