Turbine assembly having a rotor system lock

Patent metadata

Field	Value
Publication number	US-10267177-B2
Application number	US-201615016813-A
Country	US
Kind code	B2
Filing date	Feb 5, 2016
Priority date	Feb 9, 2015
Publication date	Apr 23, 2019
Grant date	Apr 23, 2019

Abstract

A rotor system lock for a gas turbine engine is described which blocks movement of rotating wheel assemblies relative to static vane assemblies in a gas turbine engine in order to block unintended rotation (or windmilling) of the gas turbine engine when it is exposed to high winds while at rest or to ram air during pre-launch flight and thereby avoid damage to components of the engine.

First claim

What is claimed is:

1. A turbine assembly for use in a gas turbine engine, the assembly comprising
a case including a support housing and a plurality of vanes coupled to the support housing,
a rotor mounted in the case to rotate relative to the case, the rotor including a wheel and a plurality of blades coupled to the wheel, and
a fuse that extends from at least one vane of the plurality of vanes included in the case to at least one blade of the plurality of blades included in the rotor to block rotation of the rotor relative to the case and that is configured to disintegrate in response to the application of a predetermined current so that the rotor is allowed to rotate relative to the case.

2. The turbine assembly of claim 1 , wherein the fuse includes a first wrap that extends around the at least one vane of the plurality of vanes included in the case and the at least one blade of the plurality of blades included in the rotor.

3. The turbine assembly of claim 2 , wherein the fuse includes a second wrap spaced circumferentially from the first wrap, the second wrap extending around a second vane of the plurality of vanes spaced circumferentially from the at least one vane of the plurality of vanes included in the case and a second blade of the plurality of blades spaced circumferentially from the at least one blade of the plurality of blades included in the rotor.

4. The turbine assembly of claim 1 , wherein the fuse includes a metallic wire.

5. The turbine assembly of claim 4 , wherein the metallic wire includes a tin-based alloy.

6. The turbine assembly of claim 1 , wherein the fuse includes a textile band.

7. The turbine assembly of claim 6 , wherein the textile band includes carbon fiber.

8. The turbine assembly of claim 1 , wherein the predetermined current is less than 20 amps.

9. An assembly for use in a gas turbine engine, the assembly comprising
a case,
a rotor mounted in the case to rotate relative to the case, and
a fuse that extends from the case to the rotor to block rotation of the rotor relative to the case and that is configured to disintegrate in response to the application of a predetermined current so that the rotor is allowed to rotate relative to the case.

10. The assembly of claim 9 , further comprising an electrical power source coupled to the fuse to provide the predetermined current to the fuse.

11. The assembly of claim 10 , wherein the electrical power source is selected from one of a generator, a capacitor, and a battery.

12. The assembly of claim 9 , wherein the fuse includes a first wrap that extends around at least one vane included in the case and at least one blade included in the rotor.

13. The assembly of claim 12 , wherein the fuse includes a second wrap spaced circumferentially from the first wrap, the second wrap extending around a second vane of the plurality of vanes spaced apart circumferentially from the at least one vane included in the case and a second blade of the plurality of blades spaced apart circumferentially from the at least one blade included in the rotor.

14. The assembly of claim 13 , wherein the fuse includes a metallic wire that extends around a first vane included in the at least one vane of the case and a first blade included in the at least one blade of the rotor to provide the first wrap and a second metallic wire that extends around the second vane of the plurality of vanes spaced apart circumferentially from the at least one vane of the case and the second blade of the plurality of blades spaced apart circumferentially from the at least one blade of the rotor to provide the second wrap.

15. The assembly of claim 13 , wherein the fuse includes a textile band that extends around a first vane included in the at least one vane of the case and a first blade included in the at least one blade of the rotor to provide the first wrap and a second textile band that extends around the second vane of the plurality of vanes spaced apart circumferentially from the at least one vane of the case and the second blade of the plurality of blades spaced apart circumferentially from the at least one blade of the rotor to provide the second wrap.

16. The assembly of claim 9 , wherein the predetermined current is less than 20 amps.

17. A method of making a turbine assembly, the method comprising
mounting a rotor in a case for rotation relative to the case, and
fashioning a fuse between the rotor and the case to block rotation of the rotor relative to the case,
wherein the fuse is made from a material that disintegrates in response to the application of a predetermined current so that the rotor is allowed to rotate relative to the case.

18. The method of claim 17 , further comprising coupling an electrical power source to the fuse to provide the predetermined current to the fuse.

19. The method of claim 17 , wherein the predetermined current is less than 20 amps.

20. The method of claim 17 , wherein the fuse includes a first wrap extending from the case to the rotor and a second wrap spaced circumferentially from the first wrap, the second wrap extending from the case to the rotor.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Watts Iii Oran A
• Junod Larry A

Classifications

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F42B15/00

  Self-propelled projectiles or missiles, e.g. rockets; Guided missiles (F42B10/00, F42B12/00, F42B14/00 take precedence; for practice or training F42B8/12; rocket torpedoes F42B17/00; marine torpedoes F42B19/00; cosmonautic vehicles B64G; jet-propulsion plants F02K) · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F01D19/00 Primary

  Starting of machines or engines; Regulating, controlling, or safety means in connection therewith (warming-up before starting F01D25/10; turning or inching gear F01D25/34) · CPC title