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US 10,119,475 B2Granted
Gas turbine engine geared architecture
AssigneeUnited Technologies Corporation
InventorGary D. Roberge
Life of this patent
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Abstract
A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan.
Claims17
A gas turbine engine assembly comprising:
- a geared architecture that rotatably couples a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan;
- wherein the turbine is a high pressure turbine, and the geared architecture is a first geared architecture;
- and
- a second geared architecture rotatably coupled to the fan to rotate the fan at a different speed than a spool that drives the fan.
1 more element
A gas turbine engine assembly comprising:
- a fan section;
- a turbine section including a high pressure turbine;
- a compressor section including a high pressure compressor and a first compressor upstream of the high pressure compressor;
- wherein the high pressure turbine rotatably drives the high pressure compressor;
- and
- a geared architecture rotatably coupling the first compressor and the high pressure turbine to drive the first compressor at a different rotational speed than the high pressure turbine;
- and
- wherein the geared architecture is a first geared architecture, and further including a second geared architecture rotatably coupled to the fan section to rotate the fan section at a different speed than a spool driving the fan section.
5 more elements
Dependencies are inferred from the claim text.