TURBINE APPARATUS

• US 20090129916A1
• Filed: 11/04/2008
• Published: 05/21/2009
• Est. Priority Date: 11/19/2007
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Gravett, Clive Peter, Ferra, Paul William, YOUNG, COLIN, Snowsill, Guy David
• Granted Patent: US 8,186,938 B2
• Time in Patent Office: Days
• US Class Current: 415/115
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 5/085 cooling fluid circulating inside the rotor
• CPC Class Codes: F05D 2240/126 Baffles or ribs

Abstract

A gas turbine engine comprising a rotor and a stator which define first, second and third cavities; the rotor and stator define a seal therebetween and which is located for sealing between the second and third cavities, the rotor comprises an aperture through which a gas flow passes from the first cavity to the second cavity characterized in that the seal comprises a deflector that extends axially over at least a portion of the aperture to deflect at least a part of the gas towards the rotor.

Claims

1. A gas turbine engine comprising:

a rotor and a stator which define first, second and third cavities;

the rotor having an aperture through which a gas flow passes from the first cavity to the second cavity;

a seal configured between said rotor and stator for providing a sealing between the second and third cavities; and

a seal flow control feature that extends axially over at least a portion of the aperture to deflect at least a part of the gas towards the rotor.

2. A gas turbine engine as claimed in claim 1 wherein the seal further comprises a rotating part and a static part.

3. A gas turbine engine as claimed in claim 2 wherein the rotating part comprises the flow control feature.

4. A gas turbine engine as claimed in claim 2 wherein the static part further comprises the flow control feature.

5. A gas turbine engine as claimed in claim 1 wherein the flow control feature is annular.

6. A gas turbine engine as claimed in claim 1 wherein the flow control feature further comprises an angled surface, relative to the axis, upon which the gas impinges.

7. A gas turbine engine as claimed in claim 6 wherein the angle of the surface is between 15 and 45 degrees.

8. A gas turbine engine as claimed in claim 6 wherein the angle of the surface is about 30 degrees.

9. A gas turbine engine as claimed in claim 1 wherein the surface is arcuate.

10. A gas turbine engine as claimed in claim 1 wherein the gas passes through the aperture in a radial direction and the flow control feature is arranged to impart an axial component of velocity to the gas flow.

11. A gas turbine engine as claimed in claim 1 wherein the rotor further comprises a seal plate to which the deflected gases flow is directed.

12. A gas turbine engine as claimed in claim 1 wherein the rotor further comprises a drive arm that defines an annular array of apertures.