Composite component with hollow reinforcing pins

Patent metadata

Field	Value
Publication number	US-10578115-B2
Application number	US-201715496410-A
Country	US
Kind code	B2
Filing date	Apr 25, 2017
Priority date	May 19, 2016
Publication date	Mar 3, 2020
Grant date	Mar 3, 2020

Abstract

A composite component comprising fibres embedded in a matrix material. A plurality of pins extend through the matrix material. Each pin of the plurality of pins comprises a hollow bore such that the bore of each pin defines a plurality of holes in the composite component.

First claim

The invention claimed is:

1. A composite component that is a blade or a vane of a gas turbine engine exposed to a fluid flow during operation, the composite component comprising:
a plurality of stacked plies including fibres embedded in a matrix material; and
a plurality of pins extending into or within the matrix material in a direction transverse to the plurality of stacked plies, each pin of the plurality of pins including a hollow bore defining a hollow pathway in the composite component, the plurality of pins being arranged such that, during operation of the gas turbine engine, holes defined by the bores of the plurality of pins modify a boundary layer of flow over the composite component.

2. The composite component according to claim 1 , wherein the plurality of pins extend through the plurality of stacked plies in a direction such that an angle between the plurality of pins and a direction of the plurality of stacked plies is equal to or greater than 5 degrees and equal to or less than 90 degrees to the direction of the plurality of stacked plies.

3. The composite component according to claim 1 , wherein at least some of the plurality of pins extend through an entire thickness of the matrix material.

4. The composite component according claim 1 , wherein at least some of the plurality of pins partially extend through the matrix material.

5. The composite component according to claim 1 , wherein the plurality of pins are made from a fibre reinforced resin.

6. The composite component according to claim 1 , wherein the plurality of pins are made from a metallic material.

7. A gas turbine engine comprising the component according to claim 1 .

8. A composite component that is a vane, the composite component comprising:
a plurality of stacked plies including fibres embedded in a matrix material; and
a plurality of pins extending into or within the matrix material in a direction transverse to the plurality of stacked plies, each pin of the plurality of pins including a hollow bore defining a hollow pathway in the composite component, the bores of the plurality of pins define flow channels of a heat exchanger.

9. The composite component according to claim 8 , wherein the plurality of pins extend through the plurality of stacked plies in a direction such that an angle between the plurality of pins and a direction of the plurality of stacked plies is equal to or greater than 5 degrees and equal to or less than 90 degrees to the direction of the plurality of stacked plies.

10. The composite component according to claim 8 , wherein at least some of the plurality of pins extend through an entire thickness of the matrix material.

11. The composite component according claim 8 , wherein at least some of the plurality of pins partially extend through the matrix material.

12. The composite component according to claim 8 , wherein the plurality of pins are made from a fibre reinforced resin.

13. The composite component according to claim 8 , wherein the plurality of pins are made from a metallic material.

14. A gas turbine engine comprising the component according to claim 8 .

15. A method of repairing a composite component including (i) a plurality of stacked plies including fibres embedded in a matrix material, and (ii) a plurality of pins extending into or within the matrix material in a direction transverse to the plurality of stacked plies, each pin of the plurality of pins including a hollow bore defining a hollow pathway in the composite component, the bore of each pin of the plurality of pins defining cooling flow channels through the composite component, the method comprising:
injecting a material through the bores of the plurality of pins so as to deliver a repair material to a desired location of the composite component.

Assignees

• Rolls Royce Plc

Inventors

• Lander James K
• Backhouse Robert C

Classifications

• F04D29/663

  Sound attenuation · 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

• F04D29/324

  Blades · CPC title

• F04D29/388

  characterised by construction · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title