COMBUSTOR DIFFUSER
Assignee
Filed
Nov 15, 1976
Granted
Jan 10, 1989
Location
Abstract
A combustor diffuser assembly for a gas turbine engine includes a prediffuser for receiving compressed air from a gasifier impeller of a gas turbine engine and for directing it into the inlet of a vortex controlled downstream diffuser and wherein the prediffuser and vortex controlled diffuser are spaced to form gaps for air bleed to form vortices to minimize bleed and main diffuser flow pressure drop and to minimize distortion in compressed air flow to plural passages leading to primary and secondary air openings in the inner and outer walls of an annular combustor assembly for the gas turbine engine.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Dec 18, 1981
Rescinded
Feb 2, 1988
Duration
6 years, 1 month
Record Details
- Patent number
- US 4796429
- Application
- 05742289
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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