Shroud seal

• US 5,088,888 A
• Filed: 12/03/1990
• Issued: 02/18/1992
• Est. Priority Date: 12/03/1990
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bobo, Melvin
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US07/621,149
• Time in Patent Office: 442 Days
• Field of Search: 415/170.1, 415/174.2, 415/134, 415/135, 415/136, 415/137, 415/138, 415/139, 415/229-231, 277/5, 277/160, 277/138, 220/437, 220/438
• US Class Current: 415/170.1
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: Y10S 277/93 Seal including heating or cooling feature

Abstract

To prevent overheating of the gaps between shroud segments circumferentially arranged about a high pressure turbine rotor, an improved seal is provided to block radial leakage flow of hot working gas through the gaps, as well as to restrict axial flow of working gas in the gaps. The seal includes a corrugated, axial fluid flow restricting element sandwiched between a pair of radially spaced, gap spanning shim sealing elements. Pressurized cooling air is admitted to the gap at locations between the shim sealing elements via passages through adjacent shroud segments to cool the gap and to further restrict working gas axial flow in the gap.

Claims

1. In a segmented annular shroud for confining the axial flow of hot working gas in a gas turbine engine, a seal for blocking radial leakage flow of working gas through a gap between adjacent shroud segments, and seal comprising, in combination:

A. a first axially elongated strip sealing element spanning the gap and having lateral edges received in opposed first slots formed in confronting, gap-defining, radial surfaces of adjacent shroud segments;

B. a second, axially elongated strip sealing element spanning the gap and having lateral edges received in opposed second slots formed in said confronting, gap-defining, radial surfaces of the adjacent shroud segments, said second sealing element being in radially spaced relation with said first sealing element; and

C. a flow restricting element disposed between said first and second sealing elements to restrict the axial flow of hot working gas in the gap between said first and second sealing elements.

2. The seal defined in claim 1, wherein said flow restricting element is axially elongated to extend over a substantial portion of the axial length of the shroud segments.

3. The seal defined in claim 2, wherein said flow restricting element is corrugated in the direction of axial elongation.

4. The seal defined in claim 3, wherein said corrugated flow restricting element includes corrugations with crests of alternating said corrugations engaging said confronting, gap-defining radial surfaces of the adjacent shroud segments.

5. The seal defined in claim 4, wherein said corrugated flow restricting element is formed of a material of sufficient resiliency to accommodate variations in the width of the gap.

6. The seal defined in claim 1, which further includes passages formed in at least one of the adjacent shroud segments for introducing pressurized cooling air into the gap between said first and second sealing elements.

7. The seal defined in claim 6, wherein said flow restricting element is axially elongated to extend over a substantial portion of the axial length of the shroud segments.

8. The seal defined in claim 7, wherein said flow restricting element is corrugated in the direction of axial elongation.

9. The seal defined in claim 8, wherein said corrugated flow restricting element includes corrugations with crests of alternating said corrugations engaging said confronting, gap-defining radial surfaces of the adjacent shroud segments.

10. The seal defined in claim 9, wherein said corrugated flow restricting element is formed of a material of sufficient resiliency to accommodate variations in the width of the gap.

11. The seal defined in claim 9, wherein said cooling passages are formed in both of the adjacent shroud segments and have exits at said confronting, gap-defining radial surfaces of the adjacent shroud segments.

12. The seal defined in claim 11, wherein said cooling passage exits are distributed over the axial length of said confronting, gap-defining radial surfaces of the adjacent shroud segments.

13. The seal defined in claim 12, wherein said cooling passage exits are axial located such as to avoid obstruction by said corrugation crests of said flow restricting element.