US4257735A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine seal and method for making same
Assignee: General Electric Co
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Filing: 1978-12-15
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Granted: 1981-03-24
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Expires: 1998-12-15
Abstract
Abstract A seal and method for making same is provided for use in a gas turbine engine. The seal includes a composite article having a substrate of sintered metallic fibers with an apparent density within the range of 14.0% to 22.5%. The substrate comprises a network of interconnected pores and metallic bonds at points of contact between fibers. The substrate further includes an external face having surface pores communicating with the network of pores. A thin film barrier surface layer, impervious to the passage of fluid, is disposed on the external face of the substrate and fills the surface pores.
Inventors
- 👤 John S. Bradley
- 👤 Alan W. Dix
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 13:46
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/02; B; B22; B22F; B22F3/00; B22F3/002; F16; F16J; F16J15/00; F16J15/44; F16J15/445; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S277/00; Y10S277/935; Y10S277/936
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
123 words
A composite article for use in a seal in a gas turbine engine, said seal including a face seal adapted to cooperate with a rotating edge to prevent the passage of fluid from a first zone to a second zone in said engine, said composite article comprising: a substrate of sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate including a network of interconnected pores and metallic bonds at points of contact between said fibers, said substrate further including an external face having surface pores in communication with said network; and a thin film barrier surface layer impervious to the passage of fluid, said layer disposed on said external face and filling said surface pores.
Claim 2
Dependent Claim
123 words
A composite article for use in a seal in a gas turbine engine, said seal including a face seal adapted to cooperate with a rotating edge to prevent the passage of fluid from a first zone to a second zone in said engine, said composite article comprising: a substrate of sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate including a network of interconnected pores and metallic bonds at points of contact between said fibers, said substrate further including an external face having surface pores in communication with said network; and a thin film barrier surface layer impervious to the passage of fluid, said layer disposed on said external face and filling said surface pores.
Claim 3
Dependent Claim
22 words
The invention as set forth in claim 1 wherein said thin film barrier surface layer is comprised of a silicone base resin.
Claim 4
Dependent Claim
119 words
A seal for preventing the flow of fluid between zones in a gas turbine engine, said seal comprising: a composite face seal having a porous substrate formed by sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate further including a network of interconnected pores and an external face having surface pores in communication with said network, said composite face seal further including a thin film surface layer disposed on said substrate and filling said surface pores, said layer comprising a barrier impervious to the passage of fluid; and a rotating edge disposed immediately proximate to said face seal and adapted to form a groove in said face seal during engine operation.
Claim 5
Dependent Claim
119 words
A seal for preventing the flow of fluid between zones in a gas turbine engine, said seal comprising: a composite face seal having a porous substrate formed by sintered metallic fibers and having an apparent density within the range of 14.0% to 22.5%, said substrate further including a network of interconnected pores and an external face having surface pores in communication with said network, said composite face seal further including a thin film surface layer disposed on said substrate and filling said surface pores, said layer comprising a barrier impervious to the passage of fluid; and a rotating edge disposed immediately proximate to said face seal and adapted to form a groove in said face seal during engine operation.
Claim 6
Dependent Claim
17 words
The invention as set forth in claim 3 wherein said surface layer is comprised of silicone resin.
Claim 7
Dependent Claim
19 words
The invention as set forth in claim 4 wherein said surface layer is further comprised of a metallic filler.
Claim 8
Dependent Claim
17 words
The invention as set forth in claim 5 wherein said surface layer is comprised of aluminum silicone.
Claim 9
Dependent Claim
46 words
The invention as set forth in claim 3 wherein said thin film surface layer is comprised of a first chemical state and said groove is formed in said face seal by said edge during initial engine operation while said layer is in said first chemical state.
Claim 10
Dependent Claim
24 words
The invention as set forth in claim 7 wherein said surface layer transforms to a second chemical state while said engine accumulates running time.
Claim 11
Dependent Claim
25 words
The invention as set forth in claim 8 wherein said transformation occurs in response to a temperature in said engine during said accumulated running time.
Claim 12
Independent Claim
131 words
A method of providing a seal for preventing the flow of fluid between zones in a gas turbine engine, said method comprising the steps of: constructing a substrate formed of sintered metallic fibers and having an apparent density within the range 14.0% to 22.5%; disposing a thin film surface layer on said substrate to form a composite face seal, said surface layer impervious to the passage of fluid; initially curing said surface layer; installing said face seal in said engine immediately proximate a rotating edge; operating the engine on an initial cycle to cause said rotating edge to form a groove in said surface layer; and transforming said surface layer during engine accumulated running time from a first chemical state to a second chemical state in response to an engine temperature.
Claim 13
Independent Claim
131 words
A method of providing a seal for preventing the flow of fluid between zones in a gas turbine engine, said method comprising the steps of: constructing a substrate formed of sintered metallic fibers and having an apparent density within the range 14.0% to 22.5%; disposing a thin film surface layer on said substrate to form a composite face seal, said surface layer impervious to the passage of fluid; initially curing said surface layer; installing said face seal in said engine immediately proximate a rotating edge; operating the engine on an initial cycle to cause said rotating edge to form a groove in said surface layer; and transforming said surface layer during engine accumulated running time from a first chemical state to a second chemical state in response to an engine temperature.
Claim 14
Dependent Claim
25 words
The invention as set forth in claim 10 wherein said disposing step includes disposing a thin film surface layer comprised of a silicone based resin.
Claim 15
Dependent Claim
30 words
The invention as set forth in claim 11 wherein said transforming step includes transforming said surface layer to a second chemical state wherein said surface layer is comprised of silica.
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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) | 1984-03-23 | 1984-09-22 | 1985-03-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-03-23 | 1988-09-22 | 1989-03-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-03-23 | 1992-09-22 | 1993-03-24 | $7700.00 | Window Closed / Lapsed |