Patent ID: 8763405
Filing Date: 2014-07-01
Classification: F01D,F02C,F05D,Y02T

Abstract:
1. A method of operating a gas turbine engine, comprising: a. injecting at least a first portion of fuel into a combustion chamber from at least one arm of a rotary injector, wherein said at least one arm extends from a rotatable portion of the gas turbine engine that when in operation rotates with said gas turbine engine, said first portion of said fuel is injected from at least one location on said at least one arm that is at a radial offset with respect to said rotatable portion of said gas turbine engine, and said radial offset provides for substantially separating an associated combustion zone from said rotatable portion of said gas turbine engine; b. injecting a first portion of air into said combustion chamber from at least one first location upstream of said rotary injector, wherein said gas turbine engine is adapted so that at least a portion of said first portion of air flows across said rotary injector, and a radial extent by which said at least one arm extends from said rotatable portion is at least as great as a corresponding radial extent, relative to said rotatable portion, of at least one first location of said at least one first location; and c. injecting a second portion of said air into said combustion chamber from at least one second location downstream of said rotary injector, wherein said second portion of said air is supplied to said at least one second location from a second plenum, and said rotary injector is adapted so that a pressure in said combustion chamber proximate to said at least one second location is less than an associated pressure within said second plenum, so as to provide for said second portion of said air to flow from said second plenum into said combustion chamber from said at least one second location.