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US 7,409,819 B2Granted
Gas turbine engine and method of assembling same
AssigneeGeneral Electric Company
InventorJohn Leslie Henry
Life of this patent
Estimating the term…
Abstract
A method of assembling a gas turbine engine that includes rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine, rotatably coupling a second low pressure turbine rotor to the first low-pressure turbine rotor, and rotatably coupling the second low-pressure turbine rotor to a turbine rear-frame such that a weight of the high-pressure turbine is transmitted to the turbine rear-frame.
Claims18
A method of assembling a gas turbine engine, said method comprising:
- rotatably coupling a first low-pressure turbine rotor to a high-pressure turbine using a first differential bearing coupled between the first low-pressure turbine rotor and the high-pressure turbine, wherein the first low-pressure turbine rotor includes a first plurality of turbine blades, each of the first plurality of blades extending radially outwardly from a root end toward a low-pressure turbine casing;
- rotatably coupling a second low-pressure turbine rotor to the first low-pressure turbine rotor using a second differential bearing coupled between the first low-pressure turbine rotor and the second low-pressure turbine rotor, wherein the second low-pressure turbine rotor includes a second plurality of turbine blades, each of the second plurality of blades extending radially outwardly from a root end toward the low-pressure turbine casing;
- and
- rotatably coupling the second low-pressure turbine rotor to a turbine rear-frame such that the weight of the high-pressure turbine is transmitted to the turbine rear-frame.
1 more element
A gas turbine engine comprising:
- a high-pressure turbine;
- a first low-pressure turbine rotor rotatably coupled to said high-pressure turbine, wherein a first differential bearing is coupled between said first low-pressure turbine rotor and said high-pressure turbine, said first low-pressure turbine rotor comprises a first plurality of turbine blades, each of said first plurality of blades extending radially outwardly from a root end toward a low-pressure turbine easing;
- a second low-pressure turbine rotor rotatably coupled to said first low-pressure turbine rotor, wherein a second differential bearing is coupled between said first low-pressure turbine rotor and said second low-pressure turbine rotor, said second low-pressure turbine rotor comprises a second plurality of turbine blades, each of said second plurality of blades extending radially outwardly from a root end toward the low-pressure turbine casing;
- and
- a turbine rear-frame rotatably coupled to said second low-pressure turbine rotor such that the weight of said high-pressure turbine is transmitted to said turbine rear-frame.
2 more elements
Dependencies are inferred from the claim text.