Sealing arrangement

• US 20060078421A1
• Filed: 10/03/2005
• Published: 04/13/2006
• Est. Priority Date: 10/11/2004
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Balsdon, Julian G.
• Granted Patent: US 7,347,662 B2
• Time in Patent Office: Days
• US Class Current: 415/170.100
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements

Abstract

A sealing arrangement between annular components 2, 4, for example in a gas turbine engine, comprises an L-shaped sealing ring 20. The sealing ring 20 has a first limb 24 received in a groove 28 in the first component 2, and a second limb 26 having a sealing face 30 which is maintained in contact with an abutment surface 32 on the second component 4 under the resilient action of the sealing ring 20. The second limb 26 is exposed to the pressure in a chamber 34 which assists the resilience of the sealing ring 20 in maintaining sealing contact between the sealing face 30 and the abutment surface 32. Bleed holes 38 are provided.

Claims

1. A sealing arrangement between first and second annular components (2, 4) having a common axis, the arrangement comprising a sealing ring (20) which, as viewed in cross-section, has a first limb (24) which is slidable within a circumferential groove the first limb (24) and which makes sealing contact with the second component (4), characterised in that the sealing ring (20) is radially resilient, the second limb (26) having a sealing face (30) which is biased by the resilience of the sealing ring (20) into contact with an abutment surface (32) of the second component (4).

2. A sealing arrangement as claimed in claim 1, characterised in that the sealing ring (20) is a split ring which is interrupted at one circumferential location.

3. A sealing arrangement as claimed in claim 1, characterised in that the first and second limbs (24, 26) are disposed perpendicular to each other, the first limb (24) extending radially with respect to the axis and the second limb (26) extending parallel to the axis.

4. A sealing arrangement as claimed in claim 1, in which the sealing face (30) is disposed on the side of the second limb (26) opposite the first limb (24).

5. A sealing arrangement as claimed in claim 1, in which the sealing face (30) is biased radially inwardly into contact with the abutment face (32).

6. A sealing arrangement as claimed in claim 1, in which the sealing ring (20) is provided with bleed holes (38) which permit flow across the sealing ring (20).

7. A sealing arrangement as claimed in claim 6, in which the bleed holes (38) are disposed at the junction between the first and second limbs (24, 26).

8. A sealing arrangement as claimed in claim 1, characterised in that the first and second components (2, 4) are components of a turbine casing of a gas turbine engine.

9. A sealing arrangement as claimed in claim 8, characterised in that the sealing ring (20) separates regions (34, 40) of high pressure and low pressure air.

10. A sealing arrangement as claimed in claim 9, characterised in that the second limb (26) is exposed to the pressure in the high pressure region (34) whereby the second limb (26) is pressed towards the abutment surface (32).

11. A sealing arrangement as claimed in claim 9, in which the sealing ring (20) is provided with bleed holes (38) which permit flow across the sealing ring (20), the bleed holes (38), which are disposed at the junction between the first and second limbs (24, 26), enabling flow from the high pressure region (34) to the low pressure region (40).

12. A gas turbine engine provided with a sealing arrangement in accordance with claim 1.