Gas turbine engine assembly and methods of assembling same
AssigneeGeneral Electric Company
InventorsRobert Joseph Orlando, Thomas Ory Moniz
Life of this patent
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Abstract
A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor to the low-pressure turbine such that the booster compressor rotates in the first direction.
Claims20
A method for assembling a gas turbine engine, said method comprising:
- coupling a low-pressure turbine to a core turbine engine;
- coupling a single low-pressure turbine shaft to the low-pressure turbine;
- coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine via the single low-pressure turbine shaft such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction;
- and
- coupling a booster compressor directly to the single low-pressure turbine shaft such that the booster compressor rotates in the first direction.
A counter-rotating fan assembly comprising:
- a forward fan assembly coupled to a low-pressure turbine via a single low-pressure turbine shaft, said forward fan assembly comprising a disk and a plurality of rotor blades coupled to said disk and configured to rotate in a first rotational direction;
- an aft fan assembly coupled to the low-pressure turbine via the single low-pressure turbine shaft, said aft fan assembly comprising a disk and a plurality of rotor blades coupled to said disk, said aft fan assembly configured to rotate in a second rotational direction;
- and
- a booster compressor coupled directly to the single low-pressure turbine shaft such that said booster compressor rotates in the first direction.
A turbine engine assembly comprising:
- a core gas turbine engine;
- a low-pressure turbine coupled to said core gas turbine engine;
- a single low-pressure turbine shaft coupled to said low-pressure turbine;
- a counter-rotating fan assembly coupled to said core gas turbine engine comprising:
- a forward fan assembly coupled to said low-pressure turbine via said single low-pressure turbine shaft, said forward fan assembly comprising a disk and a plurality of rotor blades coupled to said disk and configured to rotate in a first rotational direction;
- and
- an aft fan assembly coupled to the low-pressure turbine via said single low-pressure-turbine shaft, said aft fan assembly comprising a disk and a plurality of rotor blades coupled to said disk, said aft fan assembly configured to rotate in a second rotational direction;
- and
- a booster compressor coupled directly to said single low-pressure-turbine shaft such that said booster compressor rotates in the first direction.
Dependencies are inferred from the claim text.