Ceramic matrix composite turbine engine

• US 8,262,345 B2
• Filed: 02/06/2009
• Issued: 09/11/2012
• Est. Priority Date: 02/06/2009
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Andrew, Philip L.
• Primary Examiner(s): Landau, Matthew C.
• Assistant Examiner(s): Nicely, Joseph C
• Application Number:
  US12/367,277
• Publication Number:
  US 20100202873A1
• Time in Patent Office: 1,313 Days
• Field of Search: 415/159, 415/200, 416/97.R
• US Class Current: 415/159
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 5/187 Convection cooling
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F04D 27/0207 by bleeding, bypassing or recycling fluids influencing the boundary layer by an uncontrolled bleeding of the working fluid F04D29/681
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

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.

Claims

1. 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.

2. The turbine engine of claim 1, wherein the ceramic matrix composite comprises a silicon carbide fiber-silicon carbide matrix.

3. The turbine engine of claim 1, wherein the ceramic matrix composite comprises a non-oxide ceramic matrix, an oxide ceramic matrix, or combinations thereof.

4. The turbine engine of claim 1, comprising:

a compressor; and

a passageway configured to direct a flow of cooling fluid from the compressor to the transition section.

5. The turbine engine of claim 1, wherein each variable airfoil of the plurality of variable airfoils is configured to rotate along its longitudinal axis.

6. 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.

7. The variable area turbine nozzle assembly of claim 6, wherein the at least one variable airfoil includes one or more cooling passages configured to direct a cooling fluid within the variable airfoil, and wherein the one or more cooling passages are disposed within the ceramic matrix composite.

8. The variable area turbine nozzle assembly of claim 7, wherein the one or more cooling passages include a plurality of outlet ports configured to direct the cooling fluid from the variable airfoil.

9. The variable area turbine nozzle assembly of claim 7, wherein the one or more cooling passages extend through the at least one variable airfoil in a relatively straight-line geometry and each comprise an angled outlet.

10. The variable area turbine nozzle assembly of claim 6, comprising one or more seals configured to impede entrainment of the cooling fluid into the transition duct.

11. The variable area turbine nozzle assembly of claim 6, wherein the at least one variable airfoil is configured to rotate along its longitudinal axis.

12. The variable area turbine nozzle assembly of claim 6, wherein the at least one trunnion is constructed of a ceramic matrix composite.

13. The variable area turbine nozzle assembly of claim 6, comprising a drive lever coupled to the at least one trunnions to rotate the at least one variable airfoil, wherein the drive lever is constructed of the ceramic matrix composite.

14. The variable area turbine nozzle assembly of claim 13, comprising a synchronization ring coupled to the drive lever, wherein the synchronization ring is constructed of the ceramic matrix composite.

15. 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.

16. The transition duct of claim 15, wherein the ceramic matrix composite comprises a non-oxide ceramic matrix, an oxide ceramic matrix, or combinations thereof.

17. 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.

18. The variable area turbine nozzle assembly of claim 17, wherein the variable area turbine nozzle is configured to synchronize the high-pressure turbine and the low-pressure turbine.

19. The variable area turbine nozzle assembly of claim 17, wherein each variable airfoil of the plurality of variable airfoils is rotatable along its longitudinal axis to modulate a flow of the combustion fluids.

20. The variable area turbine nozzle assembly of claim 17, wherein the ceramic matrix composite comprises a silicon carbide fiber-silicon carbide matrix.