Gas turbine part having an electrical system embedded in composite material

Patent metadata

Field	Value
Publication number	US-9713202-B2
Application number	US-201213716503-A
Country	US
Kind code	B2
Filing date	Dec 17, 2012
Priority date	Dec 22, 2011
Publication date	Jul 18, 2017
Grant date	Jul 18, 2017

Abstract

The present invention provides a gas turbine engine part which has a primary purpose in the engine which is structural and/or aerodynamic. The part is formed of rigid composite material, and has an electrical system comprising electrical conductors permanently embedded in the composite material. This provides advantages in terms of weight, complexity, and build time.

First claim

We claim:

1. A gas turbine engine part, comprising:
a composite material entirely composed from resin and reinforcing fibers, and
an electrical system comprising metallic electrical conductors permanently embedded in the composite material forming the gas engine turbine part so as to be surrounded by and fixed in position by the composite material, wherein
the composite material that surrounds and fixes the electrical conductors is the same as the composite material of the rest of the gas turbine engine part,
the gas turbine engine part includes at least one surface that (i) forms a part of an outer surface of a turbofan gas turbine engine, or (ii) is in contact with a bypass flow of the turbofan gas turbine engine in use, and
the electrical system forms part of an electrical harness of the turbofan gas turbine.

2. The gas turbine engine part according to claim 1 , wherein the gas turbine engine part is a nacelle that provides a streamlined outer surface of the turbofan gas turbine engine.

3. The gas turbine engine part according to claim 1 , wherein the gas turbine engine part is a core engine casing that surrounds a core engine.

4. The gas turbine engine part according to claim 1 , wherein the gas turbine engine part is a fan casing that forms an outer surface of a bypass duct in the turbofan gas turbine engine and contains an engine fan blade in case of a blade off event.

5. The gas turbine engine part according to claim 1 , wherein the gas turbine engine part is an aerodynamic, radially extending splitter that in use extends across a bypass flow duct of the turbofan gas turbine engine.

6. The gas turbine engine part according to claim 1 , wherein the gas turbine engine part is an A-frame that in use extends between a fan casing and a core casing of the turbofan gas turbine engine to provide the turbofan gas turbine engine with structural rigidity.

7. The gas turbine engine part according to claim 1 , further comprising a fluid system permanently embedded in the composite material.

8. The gas turbine engine part according to claim 1 , further comprising an electrical connector permanently embedded therein that is in electrical contact with at least one of the electrical conductors, and is connectable to a corresponding connector of an electrical component of the turbofan gas turbine engine.

9. A gas turbine engine or gas turbine engine installation including the gas turbine engine part according to claim 1 .

10. The gas turbine engine or gas turbine engine installation according to claim 9 , wherein a flexible cable electrically connects between the electrical conductors and an electrical component of the gas turbine engine.

11. A method of producing a gas turbine engine part according to claim 1 , the method including:
layering layers of the reinforcing fibers and resin for forming the composite material;
sandwiching the metallic electrical conductors between at least some successive layers of the reinforcing fibers and resin; and
consolidating the layers to form the gas turbine engine part.

12. The gas turbine engine part according to claim 1 , wherein:
the composite material is a fibre reinforced polymer matrix material; and
the metallic electrical conductors are embedded by being sandwiched between successive layers of the fibre reinforced polymer matrix material.

13. The gas turbine engine part according to claim 1 , wherein the metallic electrical conductors include electrically conductive wires and/or electrically conductive tracks formed in a flexible printed circuit.

14. The method of producing a gas turbine engine part according to claim 11 , wherein the metallic electrical conductors include electrically conductive wires and/or electrically conductive tracks formed in a flexible printed circuit.

Assignees

• Rolls Royce Plc

Inventors

• Broughton Paul
• Peace Richard
• Skinner Gary Alan
• Kennea Robin Charles

Classifications

• F02C7/32 Primary

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• Y10T156/10

  Methods of surface bonding and/or assembly therefor · CPC title

• Y10T29/49238

  Repairing, converting, servicing or salvaging · CPC title

• H02G3/32

  using mounting clamps · CPC title

• H05B1/0236

  for vehicles · CPC title