Patent ID: 9068751
Filing Date: 2015-06-30
Classification: F23R

Abstract:
1. An annular combustor for a gas turbine engine, comprising: an inboard liner extending circumferentially and extending longitudinally fore to aft; an outboard liner extending circumferentially and extending longitudinally fore to aft and circumscribing the inboard liner; a bulkhead extending between a forward end of the inboard liner and a forward end of the outboard liner and in cooperation with the inboard liner and the outboard liner defining the annular combustion chamber; the outboard liner including a forward section defining a radially outward projecting substantially rectangular stabilization chamber extending aftward from the bulkhead and circumferentially about and in open relationship to the annular combustion chamber; the inboard liner including a forward section and an aft section, the forward section converges towards the outboard liner from fore to aft and the aft section converges towards the outboard liner from fore to aft more gradually than the forward section; a plurality of primary fuel injectors opening through the bulkhead admitting fuel directly into a central primary combustion zone of the annular combustion chamber, the plurality of the primary fuel injectors disposed at circumferentially spaced intervals in a ring radially intermediate the inboard liner and the outboard liner; a plurality of secondary fuel injectors opening through the bulkhead admitting fuel directly into a secondary combustion zone substantially located in the stabilization chamber of the outboard liner, the plurality of secondary fuel injectors being independently controllable relative to the plurality of primary fuel injectors, disposed at circumferentially spaced intervals in a ring coaxially radially outboard of the plurality of primary fuel injectors and arranged in circumferential alignment with the plurality of primary fuel injectors; a first plurality of tertiary fuel injectors opening through the bulkhead admitting fuel directly into a first tertiary combustion zone, the first plurality of tertiary fuel injectors being independently controllable relative to the plurality of primary fuel injectors and plurality of secondary fuel injectors, disposed at circumferentially spaced intervals in a ring coaxially radially outboard of the plurality of primary fuel injectors and coaxially radially inboard of the plurality of secondary fuel injectors, and arranged in an alternating relationship with the plurality of primary fuel injectors and plurality of secondary fuel injectors, the first tertiary combustion zone located coaxially radially outboard of the central primary combustion zone and coaxially radially inboard of the secondary combustion zone; and a second plurality of tertiary fuel injectors opening through the bulkhead admitting fuel into a second tertiary combustion zone of the annular combustion chamber, the second plurality of tertiary fuel injectors being independently controllable relative to the plurality of primary fuel injectors, plurality of secondary fuel injectors and first plurality of tertiary fuel injectors, disposed at circumferentially spaced intervals in a ring coaxially radially inboard of the plurality of primary fuel injectors, and arranged in an alternating relationship with the plurality of primary fuel injectors and plurality of secondary fuel injectors, the second tertiary combustion zone located radially inward of the central primary combustion zone.