Ceramic matrix composite turbine engine
AssigneeGeneral Electric Company
InventorPhilip L. Andrew
Life of this patent
Estimating the term…
Abstract
In one embodiment a transition section for a turbine engine is provided that includes one or more components constructed of a ceramic matrix composite. The transition section may fluidly connect a high-pressure turbine and a low-pressure turbine within the gas turbine engine. The transition section may include a transition duct and a variable area turbine nozzle. One or both of the transition duct and the variable area turbine nozzle may be constructed of the ceramic matrix composite.
Claims20
A turbine engine, comprising:
- a high-pressure turbine;
- a low-pressure turbine;
- and
- a transition section disposed between the high-pressure turbine and the low-pressure turbine and configured to direct combustion fluids from the high-pressure turbine to the low-pressure turbine, wherein at least one component of the transition section comprises a ceramic matrix composite;
- a variable area turbine nozzle annularly disposed within the transition section, wherein the variable area turbine nozzle comprises:
- a plurality of variable airfoils extending between first inner and outer surfaces, wherein the plurality of variable airfoils and the first inner and outer surfaces are each constructed of the ceramic matrix composite;
- and
- a plurality of fixed airfoils extending between second inner and outer surfaces, wherein the plurality of fixed airfoils and the second inner and outer surfaces are each constructed of the ceramic matrix composite;
- wherein the ceramic matrix composite of the plurality of variable airfoils, the first inner and outer surfaces, the plurality of fixed airfoils, and the second inner and outer surfaces is directly exposed to the combustion fluids.
A variable area turbine nozzle assembly comprising:
- at least one variable airfoil constructed of a ceramic matrix composite;
- and
- at least one trunnion configured to rotatably mount the at least one variable airfoil in a gas turbine engine;
- and
- at least one fixed airfoil constructed of the ceramic matrix composite;
- a first pair of opposing surfaces constructed of the ceramic matrix composite and disposed on opposite sides of the at least one variable airfoil;
- and
- a second pair of opposing surfaces constructed of the ceramic matrix composite and disposed on opposite sides of the at least one fixed airfoil;
- wherein the first pair of opposing surfaces and the second pair of opposing surfaces are configured to form a transition duct between a high-pressure turbine and a low-pressure turbine;
- and
- wherein the ceramic matrix composite of the at least one variable airfoil, the at least one fixed airfoil, the first pair of opposing surfaces, and the second pair of opposing surfaces is configured to be directly exposed to combustion fluids flowing through the gas turbine engine.
A transition duct comprising a ceramic matrix composite housing configured to direct combustion fluids from a high-pressure turbine to a low-pressure turbine, wherein the ceramic matrix composite housing constructed of a ceramic matrix composite;
- and wherein the ceramic matrix composite housing comprises:
- a first pair of inner and outer surfaces disposed on opposite sides of at least one variable airfoil and constructed of the ceramic matrix composite;
- and
- a second pair of inner and outer surfaces disposed on opposite sides of at least one fixed airfoil and constructed of the ceramic matrix composite;
- wherein the ceramic matrix composite of the first pair of inner and outer surfaces and the second pair of inner and outer surfaces is directly exposed to the combustion fluids.
A gas turbine engine, comprising:
- a high-pressure turbine;
- a low-pressure turbine;
- and
- a variable area turbine nozzle configured to direct combustion gases from the high-pressure turbine to the low-pressure turbine;
- wherein the variable area turbine nozzle comprises:
- a plurality of variable airfoils extending between first inner and outer surfaces, wherein the plurality of variable airfoils and the first inner and outer surfaces are each constructed of the ceramic matrix composite;
- and
- a plurality of fixed airfoils extending between second inner and outer surfaces, wherein the plurality of fixed airfoils and the second inner and outer surfaces are each constructed of the ceramic matrix composite;
- wherein the ceramic matrix composite of the plurality of variable airfoils, the first inner and outer surfaces, the plurality of fixed airfoils, and the second inner and outer surfaces is directly exposed to the combustion fluids.
Dependencies are inferred from the claim text.