US 2025/0093032 A1 · GAS TURBINE ENGINE AND FUEL NOZZLE THEREFOR

Gas turbine engine and fuel nozzle therefor

AssigneesGeneral Electric Company, GE Marmara Technology Center Muhendislik Hizmetleri Ltd, GE Aerospace Poland Sp. z o.o.

InventorsEmrah Deniz, Fatih Yasar, Katarzyna Anna Mikolajczyk, Michael T. Bucaro, Ahmet Kacar, Anquan Wang, Hejie Li, Craig Alan Gonyou, Aaron C. Brady

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Abstract

A gas turbine engine comprises a compressor section, a combustion section, and a turbine section in a serial flow arrangement and enshrouded by a casing, the combustion section comprising: an annular combustion chamber defined by at least a dome wall and an annular liner; a plurality of combustor cups circumferentially arranged on the dome wall; a fuel supply connected to the casing; and a fuel nozzle passing through the casing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two combustor cups of the plurality of combustor cups; wherein the fuel nozzle is fixed to the at least two combustor cups.

Claims23

Dependent claims

A gas turbine engine, comprising:

a combustion section enshrouded by a casing, the combustion section comprising:
an annular combustion chamber defined by at least a dome wall and an annular liner;
a plurality of combustor cups circumferentially arranged on the dome wall;
a fuel supply coupled to the casing;
and
a fuel nozzle passing through the casing and having a nozzle tube and a distribution manifold fluidly coupling the nozzle tube to at least two combustor cups of the plurality of combustor cups,
wherein the fuel nozzle is fixed to the at least two combustor cups;
and
wherein the fuel nozzle is rigidly fixed to an inner surface of the casing and is rigidly fixed to the at least two combustor cups.

6 more elements

Dependencies are inferred from the claim text.