BACK-UP FEATHERER

• US 20110171030A1
• Filed: 11/26/2010
• Published: 07/14/2011
• Est. Priority Date: 01/08/2010
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: MORGAN, Antony, SWIFT, Andrew
• Granted Patent: US 8,573,927 B2
• Time in Patent Office: Days
• US Class Current: 416/159
• CPC Class Codes: B64C 11/308 automatic
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: F01D 1/26 traversed by the working-fluid substantially axially
• CPC Class Codes: F01D 21/18 involving hydraulic means
• CPC Class Codes: F01D 7/00 Rotors with blades adjustable in operation; Control thereof for reversing F01D1/30
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02C 9/58 with control of a variable-pitch propeller
• CPC Class Codes: F02K 3/072 with counter-rotating , e.g. fan rotors
• CPC Class Codes: F05D 2220/324 to drive unshrouded, low solidity propeller
• CPC Class Codes: F05D 2250/44 by counter rotation
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A back-up featherer for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement, and fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator. The back-up featherer has a back-up actuator assembly for angular displacement of the propellers, the back-up actuator assembly rotating with the propeller assembly, a signal detector operatively connected to the back-up actuator assembly and rotates with the propeller assembly, and a back-up rotating coupling. A static side of the back-up rotating coupling is mounted to the static structure of the engine arrangement and communicates with a regulator located on a static structure of the engine arrangement. A rotating side of the back-up hydraulic rotating coupling rotates with the propeller assembly and communicates with the signal detector.

Claims

1. A back-up featherer for an engine arrangement having a main hydraulic actuator which angularly displaces propellers of a propeller assembly of the engine arrangement, the engine arrangement further having one or more fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator, the back-up featherer having:

a back-up actuator assembly for angular displacement of the propellers, the back-up actuator assembly rotating with the propeller assembly,

a signal detector that is operatively connected to the back-up actuator assembly and rotates with the propeller assembly, and

a back-up rotating coupling, a static side of the back-up rotating coupling being mounted to the static structure of the engine arrangement and communicating with a regulator located on a static structure of the engine arrangement, and a rotating side of the back-up rotating coupling rotating with the propeller assembly and communicating with the signal detector,

wherein the back-up actuator assembly angularly displaces the propellers when the signal detector detects a signal from the regulator to displace the propellers.

2. A back-up featherer according to claim 1, wherein the back-up actuator assembly is electrically-powered.

3. A back-up featherer according to claim 2, further having an electrical generator for electrically powering the back-up actuator assembly, the generator utilising the rotation of the propeller assembly to generate the electrical power.

4. A back-up featherer according to claim 1, further having a unison ring which is coaxial with the propeller assembly, the unison ring being movable by the main hydraulic actuator and by the back-up actuator assembly to drive mechanisms for angular displacement of respective propellers.

5. A back-up featherer according to claim 1, wherein the back-up rotating coupling is a hydraulic rotating coupling and the signal detector is a pressure signal detector, the static side of the back-up rotating coupling fluidly communicating with the hydraulic pressure power source.

6. A back-up featherer according to claim 1, wherein the back-up rotating coupling is an electro-magnetic rotating coupling and the signal detector is an electrical signal detector, the static side of the back-up rotating coupling electrically communicating with the regulator.

7. An engine arrangement having:

a propeller assembly,

a main hydraulic actuator for angular displacement of propellers of the propeller assembly, the main hydraulic actuator rotating with the propeller assembly, and

one or more fluid supply lines for transferring hydraulic fluid between a hydraulic pressure power source located on a static structure of the engine arrangement and the main hydraulic actuator;

wherein the engine arrangement further has a back-up featherer according to claim 1, the static side of the back-up rotating coupling communicating with a regulator located on a static structure of the engine arrangement, and the back-up actuator assembly being for angular displacement of the propellers of the propeller assembly.

8. An engine arrangement according to claim 7, further having a gear assembly that drives the propeller assembly, the gear assembly being driven by a power drive shaft that joins to the gear assembly at a first side thereof.

9. An engine arrangement according to claim 7, wherein the power drive shaft has a longitudinally extending internal cavity, and the engine arrangement further has:

a static conduit which extends along the internal cavity, the conduit penetrating the gear assembly such that a portion of the conduit projects from an opposing second side of the gear assembly, and the fluid supply lines being routed inside the static conduit, and

a main hydraulic rotating coupling mounted to the projecting portion of the static conduit, the fluid supply lines fluidly communicating with the main hydraulic actuator via the main hydraulic rotating coupling.

10. An engine arrangement according to claim 9, wherein the static side of the back-up rotating coupling is mounted to the projecting portion of the static conduit.

11. An engine arrangement according to claim 9, wherein the static side of the back-up rotating coupling communicates with the regulator over a communication line which is routed inside the static conduit.

12. An engine arrangement according to claim 9 which is for a contra-rotating engine, the propeller assembly, the main hydraulic actuator, the fluid supply lines and the main hydraulic rotating coupling being respectively a second propeller assembly, a second main hydraulic actuator, second fluid supply lines and a second hydraulic rotating coupling of the engine arrangement;

wherein the engine arrangement further has;

a first propeller assembly arranged to rotate in an opposite direction to the second propeller assembly, the gear assembly also driving the first propeller assembly

a first main hydraulic actuator for angular displacement of propellers of the first propeller assembly, the first hydraulic actuator rotating with the first propeller assembly,

one or more first fluid supply lines for transferring hydraulic fluid between the hydraulic pressure power source and the first main hydraulic actuator, the first fluid supply lines being routed inside the static conduit, and

a first main hydraulic rotating coupling which is mounted to the projecting portion of the static conduit, the first fluid supply lines fluidly communicating with the first main hydraulic actuator via the first main hydraulic rotating coupling.

13. A gas turbine engine having an engine arrangement according to claim 12, the engine comprising in flow series:

(i) a generator section which includes one or more turbine subsections, one or more respective generator drive shafts extending axially forwardly from the turbine subsections to one or more corresponding generator compressor subsections, and (ii) a power turbine section, the power drive shaft extending axially rearwardly from the power turbine section, wherein a forward mouth of the static conduit opens to a gap formed between the forwardly extending generator drive shafts and the rearwardly extending power drive shaft, the fluid supply lines from the hydraulic pressure power source and the communication line entering the static conduit at said mouth.

14. A gas turbine engine according to claim 11 wherein a row of nozzle guide vanes are located at said gap, the fluid supply lines and the communication line being routed through one or more of the nozzle guide vanes to arrive at said mouth.