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US 9,541,292 B2Granted
Combustor for gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorOleg Morenko
Life of this patent
Estimating the term…
Abstract
A gas turbine engine comprises a combustor. The combustor comprises an annular combustor chamber formed between an inner liner and an outer liner spaced apart from the inner liner. An annular fuel manifold has fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber.
Claims16
A combustor comprising:
- an annular combustion chamber formed between an inner liner and an outer liner spaced apart from the inner liner;
- an annular fuel manifold having fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber;
- and
- radial pins connected to at least one of the inner liner and the outer liner, each radial pin being completely solid with no conduits therethrough and connected directly to an annular body of the annular fuel manifold whereby the fuel manifold is supported by at least one of the inner liner and the outer liner of the combustor via the radial pins.
1 more element
A gas turbine engine comprising a combustor, the combustor comprising:
- an annular combustion chamber formed between an inner liner and an outer liner spaced apart from the inner liner;
- an annular fuel manifold having fuel nozzles distributed circumferentially on the fuel manifold, the fuel manifold and fuel nozzles positioned entirely inside the combustion chamber;
- and
- radial pins connected to at least one of the inner liner and the outer liner, each radial pin being completely solid with no conduits therethrough and connected directly to an annular body of the annular fuel manifold whereby the fuel manifold is supported by at least one of the inner liner and the outer liner of the combustor via the radial pins.
1 more element
Dependencies are inferred from the claim text.