DRUM SEAL

• US 20140169953A1
• Filed: 12/03/2013
• Published: 06/19/2014
• Est. Priority Date: 12/13/2012
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: MAGUIRE, Alan Robert
• Granted Patent: US 9,777,576 B2
• Time in Patent Office: Days
• US Class Current: 415/173.1
• CPC Class Codes: F01D 5/06 Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections F01D5/022, F01D5/023 take precedence
• CPC Class Codes: F01D 5/066 Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
• CPC Class Codes: F05D 2260/60 Fluid transfer
• CPC Class Codes: F05D 2260/609 Deoiling or demisting
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine comprising at least one drum pack having two or more annular discs 62a-c. Adjacent discs 62a-c are connected by drive arms 68 the drum pack is provided with a tubular sealing body 84 positioned radially inwards of the drive arms 68 and extending from a first disc 62a to a last disc 62c in the drum pack. The first 62a and last 62c discs have the greatest axial separation of all discs 62a-c in the drum pack. The sealing body 84 engaging the first 62a and last 62c discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity 76 defined between the first 62a and last 62c discs, the drive arms 68 and the sealing body 84.

Claims

1. A gas turbine engine comprising at least one drum pack having two or more annular discs, where adjacent discs are connected by drive arms, and where further the drum pack is provided with a tubular sealing body positioned radially inwards of the drive arms and extending from a first disc to a last disc in the drum pack, the first and last discs having the greatest axial separation of all discs in the drum pack, the sealing body engaging the first and last discs and the engagement being arranged to limit or prevent the ingress of liquid into a drum cavity defined between the first and last discs, the drive arms and the sealing body.

2. A gas turbine engine according to claim 1 where the drive arms are not provided with liquid drainage passages.

3. A gas turbine engine according to claim 1 where the sealing body is a single piece.

4. A gas turbine engine according to claim 1 where at points adjacent each disc, the sealing body extends radially inwards of the minimum radial extent of the respective disc.

5. A gas turbine engine according to claim 1 where the engagement is arranged to direct the flow of liquid away from an interface region between the sealing body and the respective first or last disc when the engine is in use.

6. A gas turbine engine according to claim 1 where the sealing body comprises a radially outwardly extending rim at one or both of its ends adjacent the respective first or last disc.

7. A gas turbine engine according to claim 6 where the rim extends on the side of the adjacent disc opposite the drum cavity.

8. A gas turbine engine according to claim 7 where the rim is arranged such that the only access from the fluid passage to the interface region is from the radially inward direction.

9. A gas turbine engine according to claim 5 where the interface region of the first and/or last disc with the sealing body is provided with one or more passages arranged to permit the flow of gas there through.

10. A gas turbine engine according to claim 1 where the sealing body is provided with a sloping gradient in the axial direction.

11. A gas turbine engine according to claim 1 further provided with one or more fluid passages external to the drum pack to allow fluid to pass radially outwards and around the drum pack into a core flow annulus.

12. A gas turbine engine according to claim 1 where radial gas flow passages are provided at the joint between drive arms extending from adjacent discs.

13. A gas turbine engine according to claim 12 where the radial gas flow passages are provided in a seal ring positioned at the joint between drive arms extending from adjacent discs.

14. A gas turbine engine according to claim 11 where the fluid passages external to the drum pack supply gas flow to one or more inter-disc stage cavities via one or more blade root gas passages in one or more blade root fixings.

15. A gas turbine engine drum pack in accordance with any of claims 1.

16. A sealing body in accordance with any of claims 1.