US4392656A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Air-cooled sealing rings for the wheels of gas turbines
Assignee: Safran Aircraft Engines SAS
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Filing: 1980-10-23
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Granted: 1983-07-12
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Expires: 2000-10-23
Abstract
Abstract Sealing ring for the wheel of a gas turbine comprising successively from the periphery toward the axis, an annular support surrounding the wheel, an annular cooling layer attached to the annular support and made of a material permeable by air, and an annular wear layer. The sealing ring further contains a separating layer inserted between the cooling layer and the wear layer.
Inventors
- 👤 Jacques P. H. Tirole
- 👤 Claude M. Mons
- 👤 Roland R. Spinat
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 20:57
CPC Classifications
F; F01; F01D; F01D11/00; F01D11/08; F01D11/12; F01D11/122; F05; F05D; F05D2260/00; F05D2260/20; F05D2260/203; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10S; Y10S277/00; Y10S277/93
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
157 words
An assembly including a cooled sealing ring for the bladed wheel of a gas turbine of the type comprising successively from the periphery toward the axis: an annular support surrounding the wheel, a first annular layer designated the "cooling layer" attached to the inner surface of said annular support and made of a material permeable to air, cooling air inlet means at the upstream region of said cooling layer, downstream exhaust means and deflectors in said cooling layer, said cooling layer being of a material whereby it serves as a reserve wear layer; a thin, separating layer radially inwardly of said cooling layer, said separating layer being permeable to air with its permeability decreasing from upstream to downstream; and a wear layer adjacent the ends of the wheel blades and made of a material capable of being abraded by said blades and being traversed radially by the air from the cooling layer passing through the separating layer.
Claim 2
Dependent Claim
157 words
An assembly including a cooled sealing ring for the bladed wheel of a gas turbine of the type comprising successively from the periphery toward the axis: an annular support surrounding the wheel, a first annular layer designated the "cooling layer" attached to the inner surface of said annular support and made of a material permeable to air, cooling air inlet means at the upstream region of said cooling layer, downstream exhaust means and deflectors in said cooling layer, said cooling layer being of a material whereby it serves as a reserve wear layer; a thin, separating layer radially inwardly of said cooling layer, said separating layer being permeable to air with its permeability decreasing from upstream to downstream; and a wear layer adjacent the ends of the wheel blades and made of a material capable of being abraded by said blades and being traversed radially by the air from the cooling layer passing through the separating layer.
Claim 3
Dependent Claim
17 words
A sealing ring according to claim 1 wherein the separating layer is made of perforated foil .
Claim 4
Dependent Claim
22 words
A sealing ring according to claim 2 wherein the separating layer is a deposit obtained by plasma spraying onto the cooling layer.
Claim 5
Dependent Claim
27 words
A sealing ring according to claim 1 wherein the separating layer is appreciably thinner than the wear layer which itself is appreciably thinner than the cooling layer.
Claim 6
Dependent Claim
33 words
A sealing ring according to claim 4 wherein the thicknesses of the three layers are such that in normal operation the ends of said blades are out of contact with the separating layer.
Claim 7
Dependent Claim
43 words
A sealing ring according to claim 5 wherein the thickness of the cooling layer is between 3 and 10 mm, the thickness of the separating layer between 0.1 and 0.5 mm and the thickness of the wear layer between 0.5 and 3 mm.
Claim 8
Dependent Claim
43 words
A sealing ring according to claim 6 wherein the thickness of the cooling layer is between 5 and 6 mm, the thickness of the separating layer between 0.1 and 0.2 mm and the thickness of the wear layer between 1 and 1.5 mm.
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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) | 1986-07-11 | 1987-01-10 | 1987-07-12 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1990-07-11 | 1991-01-10 | 1991-07-12 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1994-07-11 | 1995-01-10 | 1995-07-12 | $7700.00 | Window Closed / Lapsed |