Patent US5121597A successfully refreshed from Google Patents.
US5121597A
Expired / Lapsed
US
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Gas turbine combustor and methodd of operating the same
Assignee: Hitachi Ltd
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Filing: 1990-01-26
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Granted: 1992-06-16
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Expires: 2010-01-26
Abstract
Abstract A gas turbine combustor and a method of operating the gas turbine combustor, with the gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of the combustion sleeve and having an air and fuel supply system, and a combustion main chamber disposed on a downstream side of the sub-chamber and having an air and fuel supply system. The combustion sub-chamber and combustion main chamber are formed in such a manner that the start-up of the gas turbine is effected by the hot combustion gas generated in the sub-chamber. The combustion sub-chamber is provided with an inner sleeve protruding from a side wall of the sub-chamber such that a tip of the inner sleeve is located in the vicinity of a downstream end of the sub-chamber, and a fuel nozzle is provided in a tip of the inner sleeve for increasing the fuel-to-air ratio during an initiating period of an increase in the gas turbine rotation speed.
Inventors
- 👤 Haruo Urushidani
- 👤 Seiichi Kirikami
- 👤 Isao Sato
- 👤 Nobuo Shimizu
- 👤 Osamu Arai
- 👤 Akira Shimura
- 👤 Michio Kuroda
- 👤 Tsuguaki Koga
- 👤 Tadashi Kurokawa
- 👤 Yoji Ishibashi
- 👤 Katsukuni Hisano
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-25 16:34
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C9/32; F02C9/34; F02C7/00; F02C7/26; F23; F23R; F23R3/00; F23R3/02; F23R3/16; F23R3/26; F23R3/28; F23R3/34; F05; F05D; F05D2270/00; F05D2270/30; F05D2270/31
Claims Analysis
Total Claims: 19
Claim 1
Independent Claim
139 words
A method of operating a gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system, a combustion main chamber disposed on a downstream side of said sub-chamber and having a second air and fuel supply system, the method comprising the steps of: driving and accelerating the gas turbine during a start-up by hot combustion gas generated in said sub-chamber by a first fuel nozzle connected to the first air and fuel supply system and during a load operation of the gas turbine by hot combustion gas generated in said main chamber, and supplying fuel to a downstream side of said sub-chamber during the start-up of the gas turbine by a second fuel nozzle having a second air and fuel supply system.
Claim 2
Independent Claim
139 words
A method of operating a gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system, a combustion main chamber disposed on a downstream side of said sub-chamber and having a second air and fuel supply system, the method comprising the steps of: driving and accelerating the gas turbine during a start-up by hot combustion gas generated in said sub-chamber by a first fuel nozzle connected to the first air and fuel supply system and during a load operation of the gas turbine by hot combustion gas generated in said main chamber, and supplying fuel to a downstream side of said sub-chamber during the start-up of the gas turbine by a second fuel nozzle having a second air and fuel supply system.
Claim 3
Independent Claim
171 words
A method of operating a gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle, a combustion main chamber disposed in a downstream side of said sub-chamber and having a second air and fuel supply system, the method comprising the steps of: driving and accelerating the gas turbine during the start-up of the gas turbine by hot combustion gas generated in said sub-chamber by the first fuel nozzle connected to the first air and fuel supply system and during a load operation of the gas turbine by hot combustion gas generated in said main chamber; and injecting a predetermined amount of fuel by a second fuel nozzle having a third air and fuel supply system toward a zone in a vicinity of a downstream end of said sub-chamber during acceleration of the gas turbine so as to maintain a fuel-to-air ratio in said sub-chamber at a predetermined value.
Claim 4
Independent Claim
171 words
A method of operating a gas turbine combustor comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle, a combustion main chamber disposed in a downstream side of said sub-chamber and having a second air and fuel supply system, the method comprising the steps of: driving and accelerating the gas turbine during the start-up of the gas turbine by hot combustion gas generated in said sub-chamber by the first fuel nozzle connected to the first air and fuel supply system and during a load operation of the gas turbine by hot combustion gas generated in said main chamber; and injecting a predetermined amount of fuel by a second fuel nozzle having a third air and fuel supply system toward a zone in a vicinity of a downstream end of said sub-chamber during acceleration of the gas turbine so as to maintain a fuel-to-air ratio in said sub-chamber at a predetermined value.
Claim 5
Dependent Claim
47 words
A method of operating a gas turbine combustor according to claim 2, wherein the step of injection of the fuel is effected during a time period in which a rotational speed of the gas turbine is within a range of 20 to 60% of a rated speed.
Claim 6
Dependent Claim
161 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having an air and fuel supply system and a first fuel nozzle, and a combustion main chamber disposed at a downstream side of said sub-chamber and having an air and fuel supply system and a second fuel nozzle, said combustion sub-chamber and said combustion main chamber being arranged in such a manner that a start-up of the gas turbine is effected by the hot combustion gas generated in said sub-chamber, an inner sleeve provided in said combustion sub-chamber and protruding from a side wall of said sub-chamber such that a tip of said sleeve is located in a vicinity of a downstream end of said sub-chamber, and a third fuel nozzle provided in the tip of said sleeve for increasing a fuel-to-air ratio during an initiating period of an increase in a rotational speed of the gas turbine.
Claim 7
Dependent Claim
161 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having an air and fuel supply system and a first fuel nozzle, and a combustion main chamber disposed at a downstream side of said sub-chamber and having an air and fuel supply system and a second fuel nozzle, said combustion sub-chamber and said combustion main chamber being arranged in such a manner that a start-up of the gas turbine is effected by the hot combustion gas generated in said sub-chamber, an inner sleeve provided in said combustion sub-chamber and protruding from a side wall of said sub-chamber such that a tip of said sleeve is located in a vicinity of a downstream end of said sub-chamber, and a third fuel nozzle provided in the tip of said sleeve for increasing a fuel-to-air ratio during an initiating period of an increase in a rotational speed of the gas turbine.
Claim 8
Dependent Claim
36 words
A combustor for a gas turbine according to claim 4, wherein means are provided for controlling a fuel flow rate of said third fuel nozzle as a function of the rotational speed of the gas turbine.
Claim 9
Dependent Claim
58 words
A combustor for a gas turbine according to one of claims 4 or 5, wherein said third fuel nozzle is adapted to inject the fuel in a downstream direction, and wherein a baffle sleeve is provided on a periphery of said nozzle so as to protrude in the downstream direction from an end face of said fuel nozzle.
Claim 10
Dependent Claim
133 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel system, and a combustion main chamber disposed at a downstream side of said sub-chamber for combusting therein any uncombusted combustible gas remaining in said sub-chamber and having a second fuel nozzle, an inner sleeve is provided in said sub-chamber and extending from an upstream end wall of said sub-chamber toward a downstream side thereof, and a third fuel nozzle provided in a downstream tip of said inner sleeve for injecting fuel during a change in rotational speed of the gas turbine and having a second air and fuel supply system.
Claim 11
Dependent Claim
133 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel system, and a combustion main chamber disposed at a downstream side of said sub-chamber for combusting therein any uncombusted combustible gas remaining in said sub-chamber and having a second fuel nozzle, an inner sleeve is provided in said sub-chamber and extending from an upstream end wall of said sub-chamber toward a downstream side thereof, and a third fuel nozzle provided in a downstream tip of said inner sleeve for injecting fuel during a change in rotational speed of the gas turbine and having a second air and fuel supply system.
Claim 12
Dependent Claim
131 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber for combusting therein any uncombusted combustible gas remaining in said sub-chamber and having a second fuel nozzle, an inner sleeve is provided in said sub-chamber and extending into a combustion space of said sub-chamber, and a third fuel nozzle provided at a downstream end face of said inner sleeve for injecting fuel during a change in a load of the gas turbine, said third fuel nozzle having a second air and fuel supply system.
Claim 13
Dependent Claim
131 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber for combusting therein any uncombusted combustible gas remaining in said sub-chamber and having a second fuel nozzle, an inner sleeve is provided in said sub-chamber and extending into a combustion space of said sub-chamber, and a third fuel nozzle provided at a downstream end face of said inner sleeve for injecting fuel during a change in a load of the gas turbine, said third fuel nozzle having a second air and fuel supply system.
Claim 14
Dependent Claim
125 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber for combusting therein any uncombusted combustible gas remaining in said sub-chamber and having a second fuel nozzle, an inner sleeve is provided in said sub-chamber and extending into a combustion space of said sub-chamber, and a third fuel nozzle is provided in a tip face of said inner sleeve for increasing a fuel-to-air ratio in said sub-chamber, said third nozzle having a second air and fuel supply system.
Claim 15
Dependent Claim
125 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber for combusting therein any uncombusted combustible gas remaining in said sub-chamber and having a second fuel nozzle, an inner sleeve is provided in said sub-chamber and extending into a combustion space of said sub-chamber, and a third fuel nozzle is provided in a tip face of said inner sleeve for increasing a fuel-to-air ratio in said sub-chamber, said third nozzle having a second air and fuel supply system.
Claim 16
Dependent Claim
147 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to said first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber and having a second air and fuel supply system and a second fuel nozzle connected to said second air and fuel supply system, said combustion sub-chamber and said combustion main chamber being arranged in such a manner that a start-up of the gas turbine is effected by hot combustion gas generated in said sub-chamber, and a third fuel nozzle is provided in said sub-chamber for injecting fuel during an increase in a rotational speed of the gas turbine, said third fuel nozzle having a third air and fuel supply system.
Claim 17
Dependent Claim
147 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to said first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber and having a second air and fuel supply system and a second fuel nozzle connected to said second air and fuel supply system, said combustion sub-chamber and said combustion main chamber being arranged in such a manner that a start-up of the gas turbine is effected by hot combustion gas generated in said sub-chamber, and a third fuel nozzle is provided in said sub-chamber for injecting fuel during an increase in a rotational speed of the gas turbine, said third fuel nozzle having a third air and fuel supply system.
Claim 18
Dependent Claim
158 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber and having a second air and fuel supply system and a second fuel nozzle connected to said second air and fuel supply system, said combustion sub-chamber and said combustion main-chamber being arranged in such a manner that a start-up of the gas turbine is effected by the hot combustion gas generated in said sub-chamber, a third fuel nozzle is provided in said sub-chamber for injecting fuel during a time period in which a rotational speed of the gas turbine, when accelerated, is 20 to 60% of a rated speed, said third fuel nozzle having a third air and fuel supply system.
Claim 19
Dependent Claim
158 words
A combustor for a gas turbine comprising a combustion sleeve, a combustion sub-chamber disposed at an upstream side of said combustion sleeve and having a first air and fuel supply system and a first fuel nozzle connected to the first air and fuel supply system, a combustion main chamber disposed at a downstream side of said sub-chamber and having a second air and fuel supply system and a second fuel nozzle connected to said second air and fuel supply system, said combustion sub-chamber and said combustion main-chamber being arranged in such a manner that a start-up of the gas turbine is effected by the hot combustion gas generated in said sub-chamber, a third fuel nozzle is provided in said sub-chamber for injecting fuel during a time period in which a rotational speed of the gas turbine, when accelerated, is 20 to 60% of a rated speed, said third fuel nozzle having a third air and fuel supply system.
References Cited (Backward Citations)
US4173118A
Cited
US4292801A
Cited
JPS59173633A
Cited
GB2146425A
Cited
JPS60147035A
Cited
JPS60185024A
Cited
EP0169431A1
Cited
EP0281961A1
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1995-06-16 | 1995-12-16 | 1996-06-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-06-16 | 1999-12-16 | 2000-06-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-06-16 | 2003-12-16 | 2004-06-16 | $7700.00 | Window Closed / Lapsed |