US3916619A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Burning method for gas turbine combustor and a construction thereof
Assignee: Hitachi Ltd
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Filing: 1973-10-26
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Granted: 1975-11-04
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Expires: 1993-10-26
Abstract
Abstract A gas turbine combustor comprising a conical liner cone formed at a liner head of an annular liner wall, a fuel nozzle for spraying fuel in a conical form provided in the central part of the liner cone, inwardly directed flow jet ports for discharging air arranged annularly in the part of the liner cone in the vicinity of said fuel nozzle, and air jet ports for forming annularly an outwardly directed flow or a turning flow provided outside said inwardly directed flow jet ports, and characterized in that fuel is sprayed by said fuel nozzle to form a central flame, and at the same time, an annular small flame is formed in the vicinity of the fuel nozzle.
Inventors
- 👤 Tadahisa Masai
- 👤 Isao Sato
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 03:29
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/02; F23R3/04; F23R3/10; F23R3/12; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 9
Claim 1
Independent Claim
197 words
A gas turbine combustor comprising a cylindrical liner wall; a conical liner cap located at one end of said cylindrical liner wall, whereby said cylindrical liner wall and said liner cap form a combustion chamber for the gas turbine; a fuel nozzle provided at said liner cap for spraying fuel in a conical manner into the combustion chamber; first air supply ports annularly arranged on said liner cap in the vicinity of said fuel nozzle in such manner that air flows along said liner cap toward said fuel nozzle; second air supply ports annularly arranged on said liner cap downstream of said first air supply ports with respect to the stream of fuel sprayed from said fuel nozzle in such manner that a turning air flow about the axis of the combustion chamber results and together with the air flow from said first air supply ports forms a first annular vortex stream along said liner cap in the vicinity of the fuel nozzle; and third air supply ports annularly arranged on said liner cap downstream of said second air supply ports in such manner that air flows toward the downstream side of the first annular vortex stream.
Claim 2
Dependent Claim
197 words
A gas turbine combustor comprising a cylindrical liner wall; a conical liner cap located at one end of said cylindrical liner wall, whereby said cylindrical liner wall and said liner cap form a combustion chamber for the gas turbine; a fuel nozzle provided at said liner cap for spraying fuel in a conical manner into the combustion chamber; first air supply ports annularly arranged on said liner cap in the vicinity of said fuel nozzle in such manner that air flows along said liner cap toward said fuel nozzle; second air supply ports annularly arranged on said liner cap downstream of said first air supply ports with respect to the stream of fuel sprayed from said fuel nozzle in such manner that a turning air flow about the axis of the combustion chamber results and together with the air flow from said first air supply ports forms a first annular vortex stream along said liner cap in the vicinity of the fuel nozzle; and third air supply ports annularly arranged on said liner cap downstream of said second air supply ports in such manner that air flows toward the downstream side of the first annular vortex stream.
Claim 3
Dependent Claim
108 words
A gas turbine combustor as set forth in claim 1, wherein said first air supply ports have a plurality of louvers opening toward the center of said liner cap for causing the air to flow along said liner cap toward said fuel nozzle; said second air supply ports have a plurality of louvers which open tangentially about a concentric circle of said liner cap; and said third air supply ports have a plurality of holes for directing the flow of air toward the downstream side of the first annular vortex stream in an amount greater than the flow of air from said first and second air supply ports.
Claim 4
Dependent Claim
58 words
A gas turbine combustor as set forth in claim 2, wherein said plurality of louvers comprising said first air supply ports are arranged along a plurality of concentric circles on said liner cap; and said second air supply ports are arranged downstream of said first air supply ports along a plurality of concentric circles on said liner cap.
Claim 5
Dependent Claim
100 words
A gas turbine combustor as set forth in claim 1, further comprising fourth air supply ports annularly arranged on the downstream side of said third air supply ports for spraying air along said liner cap toward said fuel nozzle; and fifth air supply ports annularly arranged downstream of said fourth air supply ports for spraying air in a turning flow about the axis of the combustion chamber so that the air flow from the fourth and fifth air supply ports forms a second annular vortex stream along said liner cap on the downstream side of said third air supply ports.
Claim 6
Dependent Claim
54 words
A gas turbine combuster as set forth in claim 1, wherein a radial line emanating from the fuel nozzle disposed along the axis of the combustion chamber and said first air supply ports have a crossing angle in a range of 0* to 45* as viewed in the axial direction of the combustion chamber.
Claim 7
Dependent Claim
47 words
A gas turbine combustor as set forth in claim 1, wherein said liner cap includes a cup-shaped cone in the vicinity of said fuel nozzle, and the axis of said third air supply ports are provided substantially at right angles to the axis of the combustion chamber.
Claim 8
Dependent Claim
52 words
A gas turbine combustor as set forth in claim 1, including an air chamber for regulating the speed and flow of air arranged on the surface of said liner cap opposite to the interior burning surface of said liner cap, said liner cap being cup-shaped in the vicinity of said fuel nozzle.
Claim 9
Dependent Claim
100 words
A gas turbine combustor as set forth in claim 1, including an air chamber for regulating the speed and flow of air discharged from said third air supply ports, fourth air supply ports annularly arranged on the downstream side of said third air supply ports, and fifth air supply ports annularly arranged downstream of said fourth air supply ports for spraying air in a turning flow about the axis of said combustion chamber, wherein said fourth and fifth air supply ports are arranged on a surface of said liner cap opposite to the interior burning surface of said liner cap.
References Cited (Backward Citations)
US2581999A
Cited
US2555965A
Cited
US2699648A
Cited
US2775094A
Cited
US2840989A
Cited
US2974485A
Cited
US3430443A
Cited
US3498055A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1978-11-03 | 1979-05-05 | 1979-11-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-11-03 | 1983-05-05 | 1983-11-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-11-03 | 1987-05-05 | 1987-11-04 | $7700.00 | Window Closed / Lapsed |