Segmented ceramic matrix composite turbine airfoil component

• US 8,511,980 B2
• Filed: 07/23/2012
• Issued: 08/20/2013
• Est. Priority Date: 01/28/2009
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Propheter-Hinckley, Tracy A., Shi, Jun
• Primary Examiner(s): Gilman, Alexander
• Application Number:
  US13/555,877
• Publication Number:
  US 20130004296A1
• Time in Patent Office: 393 Days
• Field of Search: 415/115, 415/200, 415/209.2, 415/135, 415/136, 415/189, 416/95, 416/97.R, 416/232
• US Class Current: 415/200
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 5/3015 with side plates
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A segmented component for use with a gas turbine engine comprises a radially extending gas path portion. The gas path portion is for interacting with gas flow from the gas turbine engine. The gas path portion comprises a forward portion forming a leading edge of a stationary vane, an aft portion forming a trailing edge of the stationary vane, and a plurality of middle portions forming a pressure side and a suction side of the stationary vane. The component is divided into axially aligned segments comprising a forward segment, an aft segment, and a plurality of middle segments disposed between the forward segment and the aft segment. The middle segments comprise radially elongate ceramic matrix composite material plates.

Claims

1. A segmented component for a gas turbine engine, the component comprising:

a gas path portion for interacting with gas flow in the gas turbine engine, the gas path portion comprising;

a forward portion forming a leading edge of a stationary vane;

an aft portion forming a trailing edge of the stationary vane; and

a plurality of middle portions forming a pressure side and a suction side of the stationary vane;

wherein the component is divided into axially aligned segments comprising;

a forward segment;

an aft segment; and

a plurality of middle segments axially stacked between the forward segment and the aft segment, the plurality of middle segments comprising radially elongate ceramic matrix composite material plates, each plate comprising;

planar forward and rear surfaces that are positioned between the forward segment and the aft segment; and

sides forming segments of the pressure side and suction side of the gas path portion.

2. The segmented component of claim 1 wherein each of the segments are comprised of ceramic fiber and have a thickness such that an entirety of the fiber can be nearly uniformly infiltrated with a ceramic matrix liquid.

3. The segmented component of claim 2 wherein each of the plurality of middle segments are comprised of ceramic matrix composite plates having an axial thickness up to approximately 0.25 inches (˜

0.635 cm).

4. The segmented component of claim 1 wherein each of the segments is comprised of a ceramic matrix composite plate having fabric mesh fibers extending in a radial and tangential plane with respect to a centerline of the gas turbine engine.

5. The segmented component of claim 1 and further comprising:

a non-integral outer diameter shroud disposed at an outer diameter end of the stationary vane; and

a non-integral inner diameter shroud disposed at an inner diameter end of the stationary vane.

6. The segmented component of claim 5 wherein:

the outer diameter shroud and the inner diameter shroud include a contoured surface configured to match a contour of either the pressure side or the suction side of the stationary vane, the contoured surfaces having a lip; and

the inner diameter end and the outer diameter end of the stationary vane each include a groove into which the lips on the contoured surface fit, respectively.

7. The segmented component of claim 5 and further comprising:

first and second retention tabs disposed against the outer diameter shroud and inner diameter shroud, respectively;

wherein;

the outer diameter shroud and the inner diameter shroud each include an opening extending radially through the shroud;

the inner diameter end and the outer diameter end of the stationary vane each include a flange extending into an opening, the flanges each having a channel; and

the first and second retention tabs are disposed within a channel.

8. The segmented component of claim 1 wherein the gas path portion further comprises:

a first diametric end;

a second diametric end; and

a retention lug disposed at the first diametric end.

9. The segmented component of claim 8 and further comprising a groove extending across the retention lug.

10. The segmented component of claim 8 and further comprising:

a shroud positioned at the first diametric end of the gas path portion; and

a retention tab coupled to the retention lug and joined to the shroud.

11. The segmented component of claim 10 wherein the shroud is comprised of an alloy material.

12. The segmented component of claim 11 wherein the retention tab is welded to the shroud.

13. The segmented component of claim 12 wherein the shroud comprises:

an opening through which the retention lug extends.

14. The segmented component of claim 13 wherein the shroud further comprises:

a notch disposed along the opening that traces a contour of the gas path portion.

15. The segmented component of claim 1 wherein the gas path portion further comprises:

a first diametric end;

a second diametric end; and

a groove circumscribing the gas path portion proximate the first diametric end.

16. The segmented component of claim 15 and further comprising:

a shroud coupled to the first diametric end of the gas path portion, the shroud comprising;

an opening through which the first diametric end of the gas path portion extends; and

a lip extending from the opening to engage the groove.

17. A segmented ceramic matrix composite turbine vane for a gas turbine engine, the turbine vane comprising:

a gas path portion for interacting with gas flow from the gas turbine engine, the gas path portion being divided into axially aligned segments comprising;

a forward segment forming a leading edge of a stationary vane;

an aft segment forming a trailing edge of the stationary vane; and

a plurality of middle segments forming a pressure side or a suction side of the stationary vane;

wherein each of the plurality of middle segments comprises a radially elongate ceramic matrix composite material plate having an axial thickness up to approximately 0.25 inches (˜

0.635 cm) and having fabric mesh fibers extending in a radial and tangential plane with respect to a centerline of the gas turbine engine to form segments of the pressure side or suction side.

18. The segmented ceramic matrix composite turbine vane of claim 17 and further comprising:

a retention lug disposed at a first diametric end of the gas path portion; and

a groove extending across the retention lug.

19. The segmented ceramic matrix composite turbine vane of claim 17 and further comprising a groove circumscribing the gas path portion proximate a first diametric end of the gas path portion.

20. A segmented component for a gas turbine engine, the component comprising:

a gas path portion for extending into a gas flow within a gas turbine engine, the gas path portion comprising a leading edge, a trailing edge, a pressure side and a suction side of an airfoil;

wherein the gas path portion is divided into axially aligned segments comprising;

a forward segment;

an aft segment; and

a plurality of middle segments disposed between the forward segment and the aft segment, each of the plurality of middle segments comprising a radially elongate ceramic matrix composite material plate having reinforcing fibers extending radially through the gas path portion to define a height and circumferentially across the gas path portion from the pressure side to the suction side to define a width, the plate having an axial thickness that is less than the height and width.