Composite gas turbine engine component

Patent metadata

Field	Value
Publication number	US-9890647-B2
Application number	US-84760810-A
Country	US
Kind code	B2
Filing date	Jul 30, 2010
Priority date	Dec 29, 2009
Publication date	Feb 13, 2018
Grant date	Feb 13, 2018

Abstract

One embodiment of the present invention is a unique composite gas turbine engine component. In one form, the composite component is an airfoil. Another embodiment is a unique method for manufacturing a composite gas turbine engine component. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations composite gas turbine engine components. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

First claim

What is claimed is:

1. A gas turbine engine component, comprising:
a structure formed of a composite material, the structure including:
a flowpath surface operable in a hot gas flowpath of a gas turbine engine;
a cavity spaced apart from the flowpath surface by a thickness of the composite material; and
a cooling opening operative to discharge cooling air into the flowpath,
wherein the cooling opening extends through the structure from the flowpath surface to the cavity, the cooling opening being defined by a plurality of ultrasonically formed geometric shapes; and
wherein the composite gas turbine engine component is disposed at least partially in the flowpath and/or bounds the flowpath;
wherein the composite material is a ceramic matrix composite (CMC), a metal matrix composite (MMC), and/or a carbon-carbon composite.

2. The gas turbine engine component of claim 1 , wherein one of the ultrasonically formed geometric shapes is noncylindrical.

3. The gas turbine engine component of claim 2 , wherein one of the ultrasonically formed geometric shapes forms a diffuser for the cooling air.

4. The gas turbine engine component of claim 3 , wherein one of the ultrasonically formed geometric shapes is fan shaped.

5. The gas turbine engine component of claim 3 , wherein one of the ultrasonically formed geometric shapes is laid-back fan shaped.

6. The gas turbine engine component of claim 1 , wherein the composite gas turbine engine component is an airfoil.

7. The gas turbine engine component of claim 1 , wherein the composite material is a ceramic matrix composite (CMC).

8. A method for manufacturing a composite gas turbine engine component, comprising:
forming a composite structure that is operable in a gas turbine engine, the composite structure being defined by a composite material and having a surface and a cavity spaced apart from the surface, wherein the composite material is a ceramic matrix composite (CMC), a metal matrix composite (MMC), and/or a carbon-carbon composite; and
ultrasonic machining an opening into the surface and through the composite material from the surface to the cavity; and
wherein the opening is defined by a plurality of geometric shapes
wherein the step for ultrasonic machining the opening includes using a probe to simultaneously form a plurality of said openings in the composite structure, wherein the probe comprises a plurality of protrusions, each protrusion having a shape corresponding to the plurality of geometric shapes.

9. The method of claim 8 , wherein one of the machined geometric shapes is fan shaped.

10. The method of claim 8 , wherein one of the machined geometric shapes is laid-back fan shaped.

11. The method of claim 8 , wherein the composite gas turbine engine component is an airfoil.

12. The method of claim 8 , wherein the composite material is a ceramic matrix composite (CMC).

13. A method for manufacturing a composite airfoil, comprising:
forming a composite airfoil structure having a flowpath surface and a cavity spaced apart from the flowpath surface by a thickness of a composite material, wherein the composite material is a ceramic matrix composite (CMC), a metal matrix composite (MMC), and/or a carbon-carbon composite; and
a step for forming a cooling opening having a plurality of geometric shapes, the cooling opening extending from the flowpath surface through the composite material to the cavity of the composite airfoil;
wherein the step for forming the cooling opening includes forming the plurality of geometric shapes in the composite airfoil by ultrasonic machining;
wherein the step for forming is performed without the use of backstrike protection; and
wherein the step for forming the cooling opening includes using a probe to simultaneously form a plurality of said cooling openings in the composite airfoil structure, wherein the probe comprises a plurality of protrusions, each protrusion having a shape corresponding to the plurality of geometric shapes.

14. The method of claim 13 , wherein the step for forming includes using an ultrasonic probe that has a shape corresponding to the plurality of geometric shapes.

15. The method of claim 13 , wherein the flowpath surface has an environmental barrier coating; and wherein the step for forming the cooling opening is performed without using a masking material for protecting the environmental barrier coating.

Assignees

• Chamberlain Adam Lee
• Freeman Ted Joseph
• Rolls Royce Nam Tech Inc

Inventors

• Chamberlain Adam Lee
• Freeman Ted Joseph

Classifications

• Y10T29/49337

  Composite blade · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/284 Primary

  Selection of ceramic materials · CPC title

• F01D5/282

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

• F01D5/187

  Convection cooling · CPC title