GAS TURBINE ENGINE COMBUSTION CHAMBER FUEL MANIFOLD Russian patent published in 2009 - IPC F02C7/22 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine production, particularly to design of gas turbine engine combustion chamber fuel manifold. Proposed fuel manifold comprises annular tube to feed fuel to jets arranged inside chamber housing, fuel feed pipeline and inlet union arranged outside said chamber and in outer bush attached to chamber housing to axially move therein. Aforesaid union is furnished with inner bush representing at least one link consisting of two fixed rings and moving ring arranged to move there between. Fixed rings are jointed to outer bush, while moving ring is arranged to contact inlet union.

EFFECT: compensation of thermal strains originating in outer bush and union due to different thermal expansion of combustion chamber and fuel manifold in axial and radial directions.

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