US3751910A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Combustion liner
Assignee: Motors Liquidation Co
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Filing: 1972-02-25
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Granted: 1973-08-14
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Expires: 1992-02-25
Abstract
Abstract A gas turbine combustion liner has successive wall sections which define between them entrances for film cooling air which flows rearwardly along the inside of the liner in the same direction as the combustion products. The forward liner section is telescoped within the rearward one, and the rear portion of the forward liner section is tapered inwardly so that the gap between the two diverges radially in the direction of flow to diffuse the air flowing through the film cooling entrance. The overlapping portions of the liners are joined by a zigzag strip wbich is tapered to conform to the divergence of the passage walls, alternate lands of the strip being fixed by spot welding and brazing to the inner section and the lands between these having tabs extending from them which are spot welded and brazed to the outer liner section.
Inventors
- 👤 A Verdouw
- 👤 J Vaught
- 👤 R Sweeney
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 20:16
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/06; F23R3/08
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
145 words
A combustion liner for a gas turbine combustion apparatus or the like comprising two wall sections disposed successively in the direction of gas flow through the liner, with the adjacent marginal portions of the sections overlapping longitudinally of the liner and spaced radially of The liner to define an entrance for film cooling air into the liner between the said portions, the said marginal portions diverging radially of the liner in the direction of film cooling air flow to provide a diverging diffusing passage to reduce the velocity and increase the static pressure of the film cooling air as it flows through the entrance, and comprising a zigzag joining strip fixed to both adjacent wall sections having alternating inner and outer lands conforming to the surfaces of the respective marginal portions and having risers diverging in the direction of cooling air flow joining alternate lands.
Claim 2
Dependent Claim
145 words
A combustion liner for a gas turbine combustion apparatus or the like comprising two wall sections disposed successively in the direction of gas flow through the liner, with the adjacent marginal portions of the sections overlapping longitudinally of the liner and spaced radially of The liner to define an entrance for film cooling air into the liner between the said portions, the said marginal portions diverging radially of the liner in the direction of film cooling air flow to provide a diverging diffusing passage to reduce the velocity and increase the static pressure of the film cooling air as it flows through the entrance, and comprising a zigzag joining strip fixed to both adjacent wall sections having alternating inner and outer lands conforming to the surfaces of the respective marginal portions and having risers diverging in the direction of cooling air flow joining alternate lands.
Claim 3
Dependent Claim
158 words
A combustion liner for a gas turbine combustion apparatus or the like comprising two wall sections disposed successively in the direction of gas flow through the liner, with the adjacent marginal portions of the sections overlapping longitudinally of the liner and spaced radially of the liner to define an entrance for film cooling air into the liner between the said portions, the radially inner wall section converging radially toward its edge so that the said marginal portions diverge radially of the liner in the direction of film cooling air flow to provide a diverging diffusing passage to reduce the velocity and increase the static pressure of the film cooling air as it flows through the entrance, and comprising by a corrugated joining strip fixed to both adjacent wall sections having alternating inner and outer lands conforming to the surfaces of the respective marginal portions and having risers diverging in the direction of cooling air flow joining alternate lands.
Claim 4
Dependent Claim
158 words
A combustion liner for a gas turbine combustion apparatus or the like comprising two wall sections disposed successively in the direction of gas flow through the liner, with the adjacent marginal portions of the sections overlapping longitudinally of the liner and spaced radially of the liner to define an entrance for film cooling air into the liner between the said portions, the radially inner wall section converging radially toward its edge so that the said marginal portions diverge radially of the liner in the direction of film cooling air flow to provide a diverging diffusing passage to reduce the velocity and increase the static pressure of the film cooling air as it flows through the entrance, and comprising by a corrugated joining strip fixed to both adjacent wall sections having alternating inner and outer lands conforming to the surfaces of the respective marginal portions and having risers diverging in the direction of cooling air flow joining alternate lands.
Claim 5
Dependent Claim
190 words
A combustion liner for a gas turbine combustion apparatus or the like comprising two wall sections disposed successively in the direction of gas flow through the liner, with the adjacent marginal portions of the sections overlapping longitudinally of the liner and spaced radially of the liner to define an entrance for film cooling air into the liner between the said portions, the said marginal portions diverging radially of the liner in the direction of film cooling air flow to provide a diverging diffusing passage to reduce the velocity and increase the static pressure of the film cooling air as it flows through the entrance, and comprising by a zigzag joining strip fixed to both adjacent wall sections having alternating inner and outer lands conforming to the surfaces of the respective marginal portions and having risers diverging in the direction of cooling air flow joining alternate lands, the joining strip including tabs generally coplanarly extending from alternate lands so as to project beyond the overlapping marginal portions, the tabs being fixed to one of the wall sections, and the lands disposed between the tabs being fixed to the other wall section.
Claim 6
Dependent Claim
190 words
A combustion liner for a gas turbine combustion apparatus or the like comprising two wall sections disposed successively in the direction of gas flow through the liner, with the adjacent marginal portions of the sections overlapping longitudinally of the liner and spaced radially of the liner to define an entrance for film cooling air into the liner between the said portions, the said marginal portions diverging radially of the liner in the direction of film cooling air flow to provide a diverging diffusing passage to reduce the velocity and increase the static pressure of the film cooling air as it flows through the entrance, and comprising by a zigzag joining strip fixed to both adjacent wall sections having alternating inner and outer lands conforming to the surfaces of the respective marginal portions and having risers diverging in the direction of cooling air flow joining alternate lands, the joining strip including tabs generally coplanarly extending from alternate lands so as to project beyond the overlapping marginal portions, the tabs being fixed to one of the wall sections, and the lands disposed between the tabs being fixed to the other wall section.
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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) | 1976-08-13 | 1977-02-12 | 1977-08-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-08-13 | 1981-02-12 | 1981-08-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-08-13 | 1985-02-12 | 1985-08-14 | $7700.00 | Window Closed / Lapsed |