Patent US3918255A successfully refreshed from Google Patents.
US3918255A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Ceramic-lined combustion chamber and means for support of a liner with combustion air penetrations
Assignee: Westinghouse Electric Corp
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Filing: 1973-07-06
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Granted: 1975-11-11
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Expires: 1993-07-06
Abstract
Abstract A gas turbine power plant metal combustion chamber cylinder is lined on its inside with two layers of ceramic material. The radially innermost layer is an interlocking, tile-like structure of dense ceramic material providing good thermal shock resistance. The intermediate layer which is disposed between the metal cylinder and the innermost layer is a low density ceramic material providing high thermal insulation. The layers of ceramic material are supported by ceramic tubes extending from the outer metal cylinder of the combustor through the intermediate wall and the inner wall. The tubes are also used to direct cooling air into the combustion chamber and increase the turbulence of the burning fuel and air within the chamber.
Inventors
- 👤 Abe N Holden
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 15:20
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/045; F23R3/007
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
126 words
A combustion chamber for a gas turbine engine comprising; an outer cylindrical wall portion forming the outer casing of said combustion chamber, an intermediate generally cylindrical wall portion disposed radially inwardly of and adjacent said outer wall portion, an inner generally cylindrical wall portion disposed radially inwardly of and adjacent said intermediate wall portion, said inner wall portion comprising interlocking members, said interlocking members being stabilized within said chamber by a plurality of inlet air tube-like bushings, said bushings providing air passageways from the outside of said outer casing to the inside of said inner wall portions, said bushings having retaining means for keeping the inner wall portions in close relationship to the intermediate and external wall members, said bushing being constructed from a ceramic material.
Claim 2
Dependent Claim
126 words
A combustion chamber for a gas turbine engine comprising; an outer cylindrical wall portion forming the outer casing of said combustion chamber, an intermediate generally cylindrical wall portion disposed radially inwardly of and adjacent said outer wall portion, an inner generally cylindrical wall portion disposed radially inwardly of and adjacent said intermediate wall portion, said inner wall portion comprising interlocking members, said interlocking members being stabilized within said chamber by a plurality of inlet air tube-like bushings, said bushings providing air passageways from the outside of said outer casing to the inside of said inner wall portions, said bushings having retaining means for keeping the inner wall portions in close relationship to the intermediate and external wall members, said bushing being constructed from a ceramic material.
Claim 3
Dependent Claim
150 words
A combustion chamber for a gas turbine engine comprising; an outer cylindrical wall portion forming the outer casing of said combustion chamber, an intermediate generally cylindrical wall portion dispOsed radially inwardly of and adjacent said outer wall portion, an inner generally cylindrical wall portion disposed radially inwardly of and adjacent said intermediate wall portion, said inner wall portion comprising interlocking members, said interlocking members being stabilized within said chamber by a plurality of inlet air tube-like bushings, said bushings providing air passageways from the outside of said casing to the inside of said inner wall portions, said bushings having retaining means for keeping the inner wall portions in close relationship to the intermediate and external wall members, said intermediate wall comprises a honeycomb structure, said honeycomb structure being attached to the inner side of the outer wall member, said honeycomb structure being filled with a low density refractory insulator material.
Claim 4
Dependent Claim
150 words
A combustion chamber for a gas turbine engine comprising; an outer cylindrical wall portion forming the outer casing of said combustion chamber, an intermediate generally cylindrical wall portion dispOsed radially inwardly of and adjacent said outer wall portion, an inner generally cylindrical wall portion disposed radially inwardly of and adjacent said intermediate wall portion, said inner wall portion comprising interlocking members, said interlocking members being stabilized within said chamber by a plurality of inlet air tube-like bushings, said bushings providing air passageways from the outside of said casing to the inside of said inner wall portions, said bushings having retaining means for keeping the inner wall portions in close relationship to the intermediate and external wall members, said intermediate wall comprises a honeycomb structure, said honeycomb structure being attached to the inner side of the outer wall member, said honeycomb structure being filled with a low density refractory insulator material.
Claim 5
Dependent Claim
36 words
A combustion chamber for a gas turbine engine as recited in claim 2, wherein said retaining means on said bushings comprises a tapered outer diameter on said bushing, said taper supporting the inner refractory interlocking members.
Claim 6
Dependent Claim
59 words
A combustion chamber for a gas turbine engine as recited in claim 2, wherein said retaining means comprises a spider nut on each end of said bushing, each of said spider nuts being in supporting contact with said adjacent wall members, said spider nuts preventing damaging dislocation of the inner wall members with respect to the outer wall member.
Claim 7
Dependent Claim
57 words
A combustion chamber for a gas turbine engine as recited in claim 4, wherein the arms on said spider nut have an air foil configuration to give the air passing through said tube-like passageways in said bushing a swirling motion, which penetrates the innermost combustion gases and provides added turbulence to the gases within the combustion chamber.
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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) | 1978-11-10 | 1979-05-12 | 1979-11-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-11-10 | 1983-05-12 | 1983-11-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-11-10 | 1987-05-12 | 1987-11-11 | $7700.00 | Window Closed / Lapsed |