Airfoil with sandwich composite flange

Patent metadata

Field	Value
Publication number	US-12392247-B2
Application number	US-202318328217-A
Country	US
Kind code	B2
Filing date	Jun 2, 2023
Priority date	Jun 2, 2023
Publication date	Aug 19, 2025
Grant date	Aug 19, 2025

Abstract

An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side, a flange that extends from the non-gaspath side, and a gaspath side from which the airfoil section extends. The flange is comprised of a sandwich composite that includes first and second ceramic matrix composite (CMC) skins that each have at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine comprising:
an airfoil section; and a platform having a non-gaspath side,
a flange extending from the non-gaspath side, and a gaspath side from which the airfoil section extends, the flange being comprised of a sandwich composite including first and second ceramic matrix composite (CMC) skins each including at least one 2-D ceramic fiber ply, and a cellular ceramic core disposed between the first and second CMC skins, and the cellular ceramic core is selected from the group consisting of a ceramic honeycomb, a ceramic foam, a ceramic felt, a monolithic ceramic grid, and combinations thereof;
wherein the first and second CMC skins include, respectively, first and second radially upturned tabs extending in the flange, the cellular core including a base portion extending in the platform adjacent the flange and a ridge radially protruding from the base portion and extending between the first and second radially upturned tabs, the base portion having a maximum axial length in the platform and the ridge having a maximum radial thickness at the flange, and the axial length is greater than the radial thickness by a factor of at least 2.

2. The airfoil as recited in claim 1 , wherein the sandwich composite includes a third CMC skin including at least one 2-D ceramic fiber ply on the gaspath side of the platform, with the cellular ceramic core being radially disposed between the third CMC skin and each of the first and second CMC skins.

3. The airfoil as recited in claim 1 , wherein the flange defines a radial flange face, and the ridge defines a radial ridge face proximate the radial flange face.

4. The airfoil as recited in claim 1 , wherein the first radially upturned tab is axially forward of the second radially upturned tab.

5. The airfoil as recited in claim 1 , wherein the cellular ceramic core is selected from the group consisting of the ceramic honeycomb, the ceramic foam, the monolithic ceramic grid, and combinations thereof.

6. The airfoil as recited in claim 1 , wherein the cellular ceramic core includes cells that are void.

7. The airfoil as recited in claim 1 , wherein the cellular ceramic core is the ceramic honeycomb including honeycomb side walls that define and circumscribe uniformly-shaped cells.

8. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and

a turbine section in fluid communication with the combustor, the turbine section having an airfoil including
an airfoil section, and
a platform having a non-gaspath side, a flange extending from the non-gaspath side, and a gaspath side from which the airfoil section extends, the flange being comprised of a sandwich composite including first and second ceramic matrix composite (CMC) skins each including at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins, the first and second CMC skins including, respectively, first and second radially upturned tabs extending in the flange, the cellular core including a base portion extending in the platform adjacent the flange and a ridge radially protruding from the base portion and extending between the first and second radially upturned tabs, the base portion having a maximum axial length in the platform and the ridge having a maximum radial thickness at the flange, and the axial length is greater than the radial thickness by a factor of at least 2.

9. The gas turbine engine as recited in claim 8 , wherein the sandwich composite includes a third CMC skin including at least one 2-D ceramic fiber ply on the gaspath side of the platform, with the cellular core being radially disposed between the third CMC skin and each of the first and second CMC skins.

10. The gas turbine as recited in claim 8 , wherein the cellular core is selected from the group consisting of a ceramic honeycomb, a ceramic foam, a ceramic felt, a monolithic ceramic grid, and combinations thereof.

11. The gas turbine as recited in claim 8 , wherein the flange defines a radial flange face, and the ridge defines a radial ridge face that has cells that open at the radial flange face.

12. The gas turbine as recited in claim 11 , wherein the radial ridge face is flush with the radial flange face.

13. A method for fabricating an airfoil for a gas turbine engine, the method comprising:
providing a core blank made of a cellular material;
shaping the core blank into a cellular ceramic core;
forming a fiber preform that has an airfoil section and a platform by laying-up first and second ceramic fiber ply skins on the cellular ceramic core such that in a flange on the platform the cellular ceramic core is sandwiched between the first and second ceramic fiber ply skins, the first and second ceramic fiber ply skins each include at least one 2-D ceramic fiber ply, the cellular ceramic core is selected from the group consisting of a ceramic honeycomb, a ceramic foam, a ceramic felt, a monolithic ceramic grid, and combinations thereof;
densifying the fiber preform with a ceramic matrix to make the first and second ceramic fiber ply skins into first and second ceramic matrix composite (CMC) skins; and
wherein the first and second CMC skins include, respectively, first and second radially upturned tabs extending in the flange, the cellular core including a base portion extending in the platform adjacent the flange and a ridge radially protruding from the base portion and extending between the first and second radially upturned tabs, the base portion having a maximum axial length in the platform and the ridge having a maximum radial thickness at the flange, and the axial length is greater than the radial thickness by a factor of at least 2.

14. The method as recited in claim 13 , wherein the shaping includes machining the core blank.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Kim Russell
• Surace Raymond
• Roach James T
• Banhos Jonas

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title

• F05D2300/612

  Foam · CPC title

• F05D2250/283

  honeycomb · CPC title

• F05D2250/20

  Three-dimensional · CPC title