Ceramic matrix composite turbine engine components with unitary stiffening frame

• US 7,950,234 B2
• Filed: 10/13/2006
• Issued: 05/31/2011
• Est. Priority Date: 10/13/2006
• Status: Expired due to Fees

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Radonovich, David Charles, Keller, Douglas Allen, Morrison, Jay Alan, Gonzalez, Malberto Fernandez, Schiavo, Anthony L.
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): KIM, CRAIG SANG
• Application Number:
  US11/581,165
• Publication Number:
  US 20080087021A1
• Time in Patent Office: 1,691 Days
• Field of Search: 607/53, 415/173.1, 415/177, 415/178, 415/200, 415/116, 415/173.4
• US Class Current: 60/753
• CPC Class Codes: F01D 11/122 with erodable or abradable material blades having cutting or grinding tips F01D5/20
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2250/12 rectangular
• CPC Class Codes: F05D 2250/121 square
• CPC Class Codes: F05D 2300/21 Oxide ceramics
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced

Abstract

Aspects of the invention are directed to a ring seal segment having a base portion and a frame portion. The base portion and the frame portion are a unitary structure. The frame portion is made of four unitary side walls: a forward wall, an aft wall and a pair of transverse side walls. The side walls can be arranged in a rectangular configuration. At least a part of the base portion can be coated with a thermal insulating material. A ring seal segment according to aspects of the invention is well suited to withstand the expected operational loads in the turbine section. The transverse side walls can provide bending strength to the base and can strengthen the forward and aft side walls. Transition regions between the side walls and the base portion are strengthened by three perpendicular planes that cooperate to provide structural strength to the ring seal segment.

Claims

1. A turbine engine component comprising:

a ceramic matrix composite body having a base portion and frame portion, the base portion and the frame portion being unitary, the frame portion including at least three unitary side walls that enclose a space, wherein each side wall transitions at opposite ends into one of the other side walls, each side wall extending substantially radially outward from the base portion, and wherein each side wall transitions into the base portion such that the frame portion is closed on one side wherein the transition between two side walls occurs in a side wall transition region, wherein the ceramic matrix composite includes a ceramic matrix and a plurality of fibers therein, wherein at least some of the fibers span continuously across the side wall transition region and extend into a portion of each of the two side walls;

the turbine engine component further including a combustor liner, wherein the body is operative connected to the combustor liner, whereby the turbine engine component is a heat shield.

2. The turbine engine component of claim 1 wherein the base portion has a radially inner surface, wherein at least a portion of the radially inner surface of the base portion is coated with a thermal insulating material.

3. The turbine engine component of claim 1, wherein at least about 25% of the fibers in the side wall transition region span continuously across the side wall transition region and extend into a portion of each of the two side walls.

4. The turbine engine component of claim 1 wherein the fibers are provided in the form of a plurality of plies, wherein at least about 50% of the plies in the side wall transition region span continuously across the side wall transition region and extend into a portion of each of the two side walls.

5. The turbine engine component of claim 1 wherein the transition between at least one of the side walls and the base portion occurs in a transition region, wherein the ceramic matrix composite includes a ceramic matrix and a plurality of fibers therein, wherein with at least some of the fibers span continuously across the transition region and extend into a portion of each of the at least one side wall and the base portion.

6. The turbine engine component of claim 5, wherein at least about 25% of the fibers in the transition region span continuously across the transition region and extend into a portion of each of the at least one side wall and the base portion.

7. The turbine engine component of claim 5 wherein the fibers are provided in the form of a plurality of plies, wherein at least about 50% of the plies in the transition region span continuously across the transition region and extend into a portion of each of the at least one side wall and the base portion.

8. The turbine engine component of claim 1 further including at least one reinforcing wall enclosed by the at least three side walls, wherein the reinforcing wall is unitary with the base portion and at least one of the side walls of the frame portion.

9. The turbine engine component of claim 1 wherein the base portion has a radially inner surface, wherein a substantial majority of the fibers in the base portion extend substantially parallel to the radially inner surface.

10. A turbine engine component comprising:

a ceramic matrix composite body having a base portion and frame portion, the base portion and the frame portion being unitary, the frame portion including at least three unitary side walls that enclose a space, wherein each side wall transitions at opposite ends into one of the other side walls, each side wall extending substantially radially outward from the base portion, and wherein each side wall transitions into the base portion such that the frame portion is closed on one side wherein the transition between two side walls occurs in a side wall transition region, wherein the ceramic matrix composite includes a ceramic matrix and a plurality of fibers therein, wherein at least some of the fibers span continuously across the side wall transition region and extend into a portion of each of the two side walls;

the turbine engine component further including a stationary turbine support structure, wherein at least two of the side walls of the body are operatively connected to the stationary turbine support structure, whereby the turbine engine component is a ring seal segment.

11. A turbine engine ring seal segment comprising:

a ring seal segment body made of ceramic matrix composite, the ring seal body having a base portion and frame portion, the base portion and the frame portion being unitary,

the frame portion extending substantially radially outward from the base portion, the frame portion having a forward side wall and an opposite aft side wall, the frame portion further including a first transverse side wall and an opposite second transverse side wall, wherein the first and second transverse side walls are angled relative to the forward and aft side walls, wherein the forward side wall transitions into each of the first and second transverse side walls, and wherein the aft side wall transitions at opposite ends into the first and second transverse side walls, wherein the transition between at least one of the side walls and the base portion occurs in a transition region, and wherein the ceramic matrix composite includes a ceramic matrix and a plurality of fibers therein, a plurality of fibers spanning continuously across the transition region.

12. The ring seal segment of claim 11 wherein the forward and aft side walls are substantially parallel to each other, and wherein the first and second transverse side walls are substantially parallel to each other, whereby the frame portion is substantially parallelogrammatic.

13. The ring seal segment of claim 11 wherein the forward and aft side walls are substantially parallel to each other, and wherein the first and second transverse side walls are non-parallel to each other, whereby the frame portion is substantially trapezoidal.

14. The ring seal segment of claim 11 wherein the ceramic matrix composite is an oxide-based ceramic matrix composite.

15. The ring seal segment of claim 11 wherein the base portion has a radially inner surface, wherein at least a portion of the radially inner surface of the base portion is coated with a thermal insulating material.

16. The ring seal segment of claim 11 wherein the transition between two side walls occurs in a side wall transition region, wherein the ceramic matrix composite includes a ceramic matrix and a plurality of fibers therein, and wherein at least about 25% of the fibers in the side wall transition region span continuously across the side wall transition region and extend into a portion of each of the two side walls.

17. The ring seal segment of claim 11 wherein the transition between two side walls occurs in a side wall transition region, wherein the ceramic matrix composite includes a ceramic matrix and a plurality of fibers therein, wherein the fibers are provided in the form of a plurality of plies, and wherein at least about 50% of the plies in the side wall transition region span continuously across the side wall transition region and extend into a portion of each of the two side walls.

18. The ring seal segment of claim 11 wherein at least about 25% of the fibers in the transition region span continuously across the transition region and extend into a portion of each of the at least one side wall and the base portion.

19. The ring seal segment of claim 11 wherein the fibers are provided in the form of a plurality of plies, and wherein at least about 50% of the plies in the transition region span continuously across the transition region and extend into a portion of each of the at least one side wall and the base portion.