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US 7,694,505 B2Granted
Gas turbine engine assembly and method of assembling same
AssigneeGeneral Electric Company
InventorJan Christopher Schilling
Life of this patent
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Abstract
A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a low-pressure turbine axially aft from the core gas turbine engine, coupling a fan assembly axially forward from the core gas turbine engine, and coupling a booster compressor to the low-pressure turbine such that the booster compressor and the low-pressure turbine rotate at a first rotational speed.
Claims16
A method of assembling a gas turbine engine assembly, said method comprising:
- providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine;
- coupling a low-pressure turbine axially aft of the core gas turbine engine;
- coupling a fan assembly axially forward of the core gas turbine engine;
- and
- coupling a booster compressor to the low-pressure turbine;
- and coupling the fan assembly to the booster compressor via a gearbox and a drive shaft such that, upon rotation of the drive shaft in a first rotational direction, the booster compressor and the low-pressure turbine rotate in the first rotational direction at a first rotational speed and the fan assembly rotates in a second rotational direction at a second rotational speed, the first rotational direction different than the second rotational direction, the first rotational speed greater than the second rotational speed.
3 more elements
A turbine engine assembly comprising:
- a core gas turbine engine comprising a high-pressure compressor, a combustor, and a high-pressure turbine;
- a low-pressure turbine coupled axially aft of said core gas turbine engine;
- a fan assembly coupled axially forward of said core gas turbine engine;
- and
- a booster compressor coupled to said low-pressure turbine;
- and a fan assembly coupled to a booster compressor via a gearbox and drive shaft such that, upon rotation of said drive shaft in a first rotational direction, said booster compressor and said low-pressure turbine rotate in the first rotational direction at a first rotational speed and said fan assembly rotates in a second rotational direction at a second rotational speed, the first rotational direction different than the second rotational direction, the first rotational speed greater than the second rotational speed.
3 more elements
Dependencies are inferred from the claim text.