SEGMENTED CERAMIC MATRIX COMPOSITE TURBINE AIRFOIL COMPONENT

• US 20100189556A1
• Filed: 01/28/2009
• Published: 07/29/2010
• Est. Priority Date: 01/28/2009
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Propheter-Hinckley, Tracy A., Shi, Jun
• Granted Patent: US 8,251,651 B2
• Time in Patent Office: Days
• 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 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. In one embodiment, the gas path portion comprises an airfoil for a turbine blade. In another embodiment, the gas path portion comprises a removable platform for a turbine blade. In another embodiment, the gas path portion comprises an airfoil for a turbine vane.

Claims

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

a gas path portion for interacting with gas flow from the gas turbine engine;

wherein 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 plurality of middle segments comprising radially elongate ceramic matrix composite material plates.

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 to reduce porosity within the component.

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 wherein the forward segment and the aft segment are comprised of an alloy material.

6. The segmented component of claim 1 wherein the segmented component further comprises a root portion extending radially inwardly from the gas path portion, the root portion having a geometry for providing radial retention with a rotor of the gas turbine engine.

7. The segmented component of claim 6 wherein each of the segments is comprised of a ceramic matrix composite plate having fibers extending continuously through the root portion and the gas path portion.

8. The segmented component of claim 7 wherein the root portion further includes an axial retention bore for receiving a retention bolt.

9. The segmented component of claim 8 wherein the geometry of the root portion comprises a dovetail or fir-tree configuration.

10. The segmented component of claim 6 wherein the forward segment or the aft segment of the root portion includes a tangentially extending flange for axially restraining a root portion of an adjacent rotor component connected to an outer periphery of the rotor.

11. The segmented component of claim 6 wherein the gas path portion comprises:

a forward platform segment having contours configured to flushly abut leading edge portions of adjacent airfoils;

an aft platform segment having contours configured to flushly abut trailing edge portions of adjacent airfoils; and

a plurality of middle platform segments having contours configured to abut a suction side and a pressure side of adjacent airfoils.

12. The segmented component of claim 11 wherein the forward and the aft platform segments are comprised of plates of ceramic matrix composite material having a bend to form a radially extending portion forming the root portion and an axially extending portion forming the gas path portion.

13. The segmented component of claim 11 wherein the forward and aft platform segments each further include an axial extending retention tab for abutting one of the plurality of middle segments.

14. The segmented component of claim 6 wherein the gas path portion comprises:

a forward portion forming a leading edge of an airfoil;

an aft portion forming a trailing edge of an airfoil; and

a plurality of middle portions forming a pressure side and a suction side of an airfoil.

15. The segmented component of claim 1 wherein 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.

16. The segmented component of claim 15 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.

17. The segmented component of claim 16 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.

18. The segmented component of claim 16 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.

19. 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; and

a root portion extending from the gas path portion and configured to fit within a radial retention slot of a rotor;

wherein 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, 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 and the root portion, and stacked axially to a thickness that permits uniform infiltration of a ceramic matrix liquid.

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 and the root portion, and stacked axially to a thickness that permits uniform infiltration of a ceramic matrix liquid.