Seal assembly

• US 7,445,425 B2
• Filed: 03/03/2005
• Issued: 11/04/2008
• Est. Priority Date: 03/31/2004
• Status: Expired due to Fees

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Scanlon, Timothy John, Ferra, Paul William
• Primary Examiner(s): Kershteyn; Igor
• Application Number:
  US11/070,006
• Publication Number:
  US 20050249588A1
• Time in Patent Office: 1,342 Days
• Field of Search: 415/134, 415/136, 415/137, 415/138, 415/139
• US Class Current: 415/134
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 9/042 fixing blades to stators fixing stator-rings in the casing or to each other F01D25/246
• CPC Class Codes: F05D 2240/55 Seals

Abstract

A seal arrangement 32 between a turbine shroud seal segments 38,40 in a gas turbine engine. The arrangement 32 comprises facing slots 34, 36 provided respectively in the segments 38,40 with offset spaces 42, 44 provided between the segments 38,40. A strip 46 is cemented into the slot 36 such that the flow path 50 passes through the space 42, around the free end of the strip 46, and out through the offset space 44, thereby providing a longer flow path.

Claims

1. A seal assembly between components in a gas turbine engine, which assembly permits limited relative movement between the components, the assembly including cooperable formations on each component which together define a slot extending between and into each of the components, with respective spaces between the components on either side of the slot, a baffle member extending into the slot from one of the components such that the fluid flow path between the components extends through one of said spaces, into the slot, around the free end of the baffle member, and out through the other of said spaces, such that the fluid flow path is longer than the distance through said one space, around the free end of the baffle member, and out through a further space opposite said one space, each of said one space and the further space opposite said one space having a central longitudinal axis, the central longitudinal axis of each of said spaces being substantially parallel, and laterally offset, relative to the other.

2. An assembly according to claim 1, wherein the components comprise respective components of a segmented annular assembly.

3. An assembly according to claim 2, wherein the components comprise a turbine shroud seal segments.

4. An assembly according to claim 2, wherein the components comprise nozzle guide vanes.

5. An assembly according to claim 1, wherein the spaces between the components are radially offset relative to each other.

6. An assembly according to claim 1, wherein the baffle member comprises a separate element.

7. An assembly according to claim 6, wherein the baffle member is bonded to the respective one component.

8. An assembly according to claim 7, wherein the bonding is provided by a material, which material substantially fills the cooperable formation in said one component.

9. An assembly according to claim 6, wherein the separate element comprises a strip of material.

10. An assembly according to claim 1, wherein the baffle member is integrally formed with one of the components.

11. An assembly according to claim 1, wherein the slots are profiled across the components, with the baffle members having a corresponding profile.

12. An assembly according to claim 1, wherein a plurality of baffle members are provided, with adjacent baffle members extending respectively from different components.

13. An assembly according to claim 9, wherein the strip of material is metal.