US5127793A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbine shroud clearance control assembly
Assignee: General Electric Co
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Filing: 1990-05-31
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Granted: 1992-07-07
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Expires: 2010-05-31
Abstract
Abstract The clearances between an array of high pressure turbine blades and its surrounding high pressure turbine shroud as well as the clearances between an array of low pressure turbine blades and its associated low pressure turbine shroud are carefully controlled by a support structure which provides for evenly controlled circumferential cooling of the shroud support structure. Radial loads on the shroud support structure are reduced by counterbalancing loads imposed on the support structure by the shroud with predetermined pressure loads controlled and set through a series of cooling air cavities. The high pressure turbine shroud and low pressure turbine shroud are formed as integral segments in a segmented shroud design. Forward and aft shroud hanger members interconnect the shroud with its support so as to facilitate assembly and disassembly of the shroud segments to and from their support structure.
Inventors
- 👤 Alan Walker
- 👤 Thomas G. Wakeman
- 👤 Dean T. Lenahan
- 👤 Larry W. Plemmons
- 👤 Andrew P. Elovic
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 09:55
CPC Classifications
F; F01; F01D; F01D25/00; F01D25/24; F01D25/246; F01D11/00; F01D11/08; F05; F05D; F05D2240/00; F05D2240/10; F05D2240/11
Claims Analysis
Total Claims: 21
Claim 1
Independent Claim
81 words
A segmented shroud assembly for a gas turbine engine having a plurality of high pressure turbine blades on a high pressure turbine rotor and a plurality of low pressure turbine blades on a low pressure turbine rotor, said shroud assembly comprising: a plurality of shroud segments arranged circumferentially to form a segment shroud, wherein said shroud segments are arranged within said gas turbine engine so as to axially span both said high pressure turbine blades and said low pressure turbine blades.
Claim 2
Dependent Claim
81 words
A segmented shroud assembly for a gas turbine engine having a plurality of high pressure turbine blades on a high pressure turbine rotor and a plurality of low pressure turbine blades on a low pressure turbine rotor, said shroud assembly comprising: a plurality of shroud segments arranged circumferentially to form a segment shroud, wherein said shroud segments are arranged within said gas turbine engine so as to axially span both said high pressure turbine blades and said low pressure turbine blades.
Claim 3
Dependent Claim
20 words
The assembly of claim 1, further comprising a one-piece annular shroud support connecting said segmented shroud to said turbine engine.
Claim 4
Dependent Claim
21 words
The assembly of claim 2, further comprising a plurality of segmented shroud hangers interconnecting said shroud segments with said shroud support.
Claim 5
Dependent Claim
27 words
The assembly of claim 3, wherein said annular shroud support comprises a forward position control ring, a mid position control ring and an aft position control ring.
Claim 6
Dependent Claim
39 words
The assembly of claim 4, wherein said plurality of segmented shroud hangers comprises a plurality of forward shroud hangers engaging said shroud support in radial planar alignment with said forward position control ring and said mid position control ring.
Claim 7
Dependent Claim
33 words
The assembly of claim 5, wherein said plurality of segmented shroud hangers comprises a plurality of aft shroud hangers engaging said shroud support in radial planar alignment with said aft position control ring.
Claim 8
Dependent Claim
118 words
A one-piece shroud segment for use in a segmented gas turbine engine shroud of a gas turbine engine having a plurality of high pressure turbine blades on a high pressure turbine rotor and a plurality of low pressure turbine blades on a low pressure turbine rotor, said shroud segment comprising: a one-piece shroud segment having a high pressure shroud portion integrally formed with a low pressure shroud portion; and a forward mounting member, a mid mounting member, and an aft mounting member for mounting said shroud segment to the gas turbine engine wherein said shroud segment is of sufficient axial length so as to axially span both the high pressure turbine blades and the low pressure turbine blades.
Claim 9
Dependent Claim
118 words
A one-piece shroud segment for use in a segmented gas turbine engine shroud of a gas turbine engine having a plurality of high pressure turbine blades on a high pressure turbine rotor and a plurality of low pressure turbine blades on a low pressure turbine rotor, said shroud segment comprising: a one-piece shroud segment having a high pressure shroud portion integrally formed with a low pressure shroud portion; and a forward mounting member, a mid mounting member, and an aft mounting member for mounting said shroud segment to the gas turbine engine wherein said shroud segment is of sufficient axial length so as to axially span both the high pressure turbine blades and the low pressure turbine blades.
Claim 10
Dependent Claim
19 words
The shroud segment of claim 7, wherein said mid mounting member comprises an axially forwardly projecting free end portion.
Claim 11
Dependent Claim
32 words
The shroud segment of claim 8, wherein said forward mounting member comprises an axially rearwardly projecting free end portion and said aft mounting member comprises an axially rearwardly projecting free end portion.
Claim 12
Dependent Claim
29 words
The shroud segment of claim 7, wherein said forward mounting member is formed with a radial recess for facilitating disassembly of said shroud segment from said gas turbine engine.
Claim 13
Dependent Claim
101 words
A shroud assembly for a gas turbine engine, comprising: a segmented tubine shroud; a shroud support for radially positioning said segmented turbine shroud within said gas turbine engine; a plurality of segmented forward hanger members interconnecting said segmented turbine shroud and said shroud support; and a plurality of segmented aft hanger members interconnecting said segmented turbine shroud and said shroud support such that a first cooling air cavity is formed between said forward hanger members and said shroud support and a second cooling air cavity is formed between said shroud support and said segmented turbine shroud and said aft hanger members.
Claim 14
Dependent Claim
101 words
A shroud assembly for a gas turbine engine, comprising: a segmented tubine shroud; a shroud support for radially positioning said segmented turbine shroud within said gas turbine engine; a plurality of segmented forward hanger members interconnecting said segmented turbine shroud and said shroud support; and a plurality of segmented aft hanger members interconnecting said segmented turbine shroud and said shroud support such that a first cooling air cavity is formed between said forward hanger members and said shroud support and a second cooling air cavity is formed between said shroud support and said segmented turbine shroud and said aft hanger members.
Claim 15
Dependent Claim
43 words
The assembly claim 11, wherein cooling air pressure on said first cavity is maintained at a first predetermined value and wherein cooling air pressure in said second cavity is maintained at a second predetermined value which is less than said first predetermined value.
Claim 16
Dependent Claim
32 words
The assembly of claim 12 wherein said first and second cooling air pressures in said first and second cavities are maintained at levels which counteract mechanical loads applied to said shroud assembly.
Claim 17
Dependent Claim
39 words
The assembly of claim 11, wherein said shroud support comprises a first position control ring and a second position control ring, said first and second position control rings being located on the exterior of said first and second cavities.
Claim 18
Dependent Claim
31 words
The assembly of claim 11, further comprising a combustor case encircling said shroud support and wherein a third cooling air cavity is formed between said combustor case and said shroud support.
Claim 19
Dependent Claim
31 words
The assembly of claim 12, further comprising a combustor case encircling said shroud support and wherein a third cooling air cavity is formed between said combustor case and said shroud support.
Claim 20
Dependent Claim
29 words
The assembly of claim 16 wherein cooling air pressure in said third cavity is maintained at a third predetermined value which is between said first and second predetermined values.
Claim 21
Dependent Claim
24 words
The assembly of claim 15 wherein said third cavity receives cooling air from said first cavity and directs cooling air into said second cavity.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-07-07 | 1996-01-06 | 1996-07-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-07-07 | 2000-01-06 | 2000-07-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-07-07 | 2004-01-06 | 2004-07-07 | $7700.00 | Window Closed / Lapsed |