Composite airfoil for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10563522-B2
Application number	US-201514797916-A
Country	US
Kind code	B2
Filing date	Jul 13, 2015
Priority date	Sep 22, 2014
Publication date	Feb 18, 2020
Grant date	Feb 18, 2020

Abstract

Stationary vanes and rotating blades of a gas turbine engine are disclosed that include airfoils formed from ceramic matrix composite materials. The airfoils include at least one layer of ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the matrix material. A core of the airfoils is surrounded by the at least one layer of ceramic-containing fiber/matrix material.

First claim

What is claimed is:

1. An airfoil for a gas turbine engine, the airfoil comprising
an interior layer of ceramic matrix composite material having an exterior surface that faces away from a core of the airfoil and an interior surface that faces the core of the airfoil, the interior layer including a ceramic-containing matrix material and a single preform tube of ceramic-containing reinforcing fibers that are bound together and suspended in the ceramic-containing matrix material, and
an exterior wrap of ceramic matrix composite material bonded to the exterior surface of the interior layer, the exterior wrap including at least one sheet containing a ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the ceramic-containing matrix material,
wherein the core of the airfoil comprises a void that extends along an axis, the airfoil has a leading edge and a trailing edge and the exterior wrap forms a seam at the trailing edge of the airfoil that extends parallel to the axis, and the tube of ceramic-containing reinforcing fibers included in the interior layer extends along each of a pressure side and a suction side of the airfoil all the way around the axis without forming a seam that extends along the axis, and
wherein the tube of ceramic-containing reinforcing fibers extends along an entire length of the interior layer and defines a surface of the void of the core of the airfoil.

2. The airfoil of claim 1 , wherein the tube of ceramic-containing reinforcing fibers included in the interior layer includes reinforcing fibers that are woven together.

3. The airfoil of claim 1 , wherein the tube of ceramic-containing reinforcing fibers included in the interior layer includes reinforcing fibers that are braided together.

4. The airfoil of claim 1 , wherein the airfoil includes at least one reinforcing rib extending through the core between a first portion of the interior surface and a second portion of the interior surface.

5. The airfoil of claim 4 , wherein the at least one reinforcing rib includes ceramic reinforcing fibers suspended in a ceramic matrix material.

6. The airfoil of claim 1 , wherein the core of the airfoil is hollow.

7. The airfoil of claim 1 , wherein the core of the airfoil contains a ceramic foam material.

8. An airfoil for a gas turbine engine, the airfoil comprising
an exterior wrap of ceramic matrix composite material having an exterior surface that defines a shape of the airfoil and an interior surface that face a core of the airfoil, the exterior wrap including at least one sheet containing a ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the ceramic-containing matrix material, and
an interior layer of ceramic matrix composite material bonded to the interior surface of the exterior wrap, the interior layer including a ceramic-containing matrix material and a single preform tube of ceramic-containing reinforcing fibers that are bound together and suspended in the ceramic-containing matrix material,
wherein the core of the airfoil comprises a void that extends along an axis, the airfoil has a leading edge and a trailing edge and the exterior wrap forms a seam at the trailing edge of the airfoil that extends parallel to the axis, and the tube of ceramic-containing reinforcing fibers included in the interior layer extends along each of a pressure side and a suction side of the airfoil around the axis seamlessly, and
wherein the tube of ceramic-containing reinforcing fibers extends from adjacent the leading edge of the airfoil to adjacent the trailing edge of the airfoil and defines a surface of the void of the core of the airfoil.

9. The airfoil of claim 8 , wherein the tube of ceramic-containing reinforcing fibers included in the interior layer includes reinforcing fibers that are woven together.

10. The airfoil of claim 8 , wherein the tube of ceramic-containing reinforcing fibers included in the interior layer includes reinforcing fibers that are braided together.

11. The airfoil of claim 8 , wherein the interior layer is directly bonded to the exterior wrap opposite the trailing edge of the airfoil.

12. The airfoil of claim 11 , wherein the interior layer and the exterior wrap are directly bonded together around the axis.

13. The airfoil of claim 8 , wherein the core of the airfoil is hollow.

14. The airfoil of claim 8 , wherein the core of the airfoil includes a ceramic foam material.

15. The airfoil of claim 8 , wherein the tube of the interior layer includes at least one reinforcing rib extending through the core.

16. A method of producing an airfoil for a gas turbine engine, the method comprising
creating a single preform tube of ceramic reinforcing fibers that are bound together,
suspending the preform tube in ceramic-containing matrix material by (i) positioning the preform tube around an axis such that the preform tube extends along each of a pressure side and a suction side of the airfoil without forming a seam that extends along the axis and (ii) curing the ceramic-containing matrix material applied to the preform tube to form an interior layer,
wrapping at least one sheet of prepreg ceramic matrix composite material around the preform tube or the interior layer,
curing ceramic matrix material applied to the at least one sheet to form an exterior wrap and to bond the exterior wrap to the interior layer,
forming ribs and/or a formed reinforcement in a core defined by the interior layer,
wherein (i) curing the ceramic matrix material to form the exterior wrap includes forming a seam at a trailing edge of the airfoil that extends parallel to the axis and (ii) positioning the preform tube around the axis includes positioning the preform tube around the axis such that the preform tube extends along each of the pressure and suction sides of the airfoil without forming a seam that extends along the axis, and
extending the tube of ceramic-containing reinforcing fibers along an entire length of the interior layer to define a surface of a void of the core of the airfoil.

17. The method of claim 16 , wherein creating the preform tube of ceramic reinforcing fibers comprises creating the preform tube of ceramic reinforcing fibers by weaving, braiding, knitting, or knotting.

18. The method of claim 16 , comprising forming a ceramic foam material into the core.

Assignees

• Rolls Royce Corp
• Rolls Royce Nam Tech Inc

Inventors

• Thomas David J
• Freeman Ted J
• Walston Jeffrey A

Classifications

• F05D2300/20

  Oxide or non-oxide ceramics · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title