JP2011074803A5 - - Google Patents
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- JP2011074803A5 JP2011074803A5 JP2009225900A JP2009225900A JP2011074803A5 JP 2011074803 A5 JP2011074803 A5 JP 2011074803A5 JP 2009225900 A JP2009225900 A JP 2009225900A JP 2009225900 A JP2009225900 A JP 2009225900A JP 2011074803 A5 JP2011074803 A5 JP 2011074803A5
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- JP
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- Prior art keywords
- fuel
- gas
- gas turbine
- turbine system
- heat exchanger
- Prior art date
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Claims (10)
第一のガス燃料と、第一のガス燃料よりも発熱量の多い第二のガス燃料との混合燃料を昇圧するガス圧縮機と、
前記空気圧縮機で圧縮された圧縮空気と前記ガス圧縮機で昇圧された前記混合燃料とを燃焼させ燃焼ガスを生成する燃焼器と、
前記燃焼器で生成された燃焼ガスで駆動するガスタービンと、
第一のガス燃料を燃焼させるフレアスタックとを有するガスタービンシステムにおいて、
前記フレアスタックは、前記第二のガス燃料よりも発熱量の多いパイロットバーナ用燃料を燃焼させるパイロットバーナを有し、前記パイロットバーナよりも下流側に、前記第一の燃料を噴射する第一燃料噴射手段を有することを特徴とするガスタービンシステム。 An air compressor for compressing air;
A gas compressor that pressurizes a mixed fuel of the first gas fuel and the second gas fuel having a larger calorific value than the first gas fuel;
A combustor that generates combustion gas by burning the compressed air compressed by the air compressor and the mixed fuel pressurized by the gas compressor;
A gas turbine driven by combustion gas generated in the combustor;
A gas turbine system having a flare stack for burning a first gas fuel;
The flare stack includes a pilot burner that burns fuel for a pilot burner that generates a larger amount of heat than the second gas fuel, and the first fuel that injects the first fuel downstream of the pilot burner. A gas turbine system having injection means.
前記パイロットバーナの外周側に、第一のガス燃料と第二のガス燃料との混合燃料を供給する混合燃料供給手段を備えたことを特徴とするガスタービンシステム。 The gas turbine system according to claim 1.
A gas turbine system comprising a mixed fuel supply means for supplying a mixed fuel of a first gas fuel and a second gas fuel on an outer peripheral side of the pilot burner.
前記第一燃料噴射手段は、前記パイロットバーナ用燃料の噴射方向に直交する方向に前記第一のガス燃料を噴射することを特徴とするガスタービンシステム。 The gas turbine system according to claim 1 or 2,
The gas turbine system according to claim 1, wherein the first fuel injection means injects the first gas fuel in a direction orthogonal to an injection direction of the pilot burner fuel.
前記フレアスタック内に設けられた熱交換器と、
前記熱交換器に空気を供給する空気供給系統と、
前記熱交換器で加熱された空気を、前記第一燃料供給手段の外周側から噴射する空気噴射手段とを備えたことを特徴とするガスタービンシステム。 The gas turbine system according to any one of claims 1 to 3,
A heat exchanger provided in the flare stack;
An air supply system for supplying air to the heat exchanger;
A gas turbine system comprising: air injection means for injecting air heated by the heat exchanger from an outer peripheral side of the first fuel supply means.
前記フレアスタック内に設けられ、第一のガス燃料を加熱する熱交換器を備え、
前記熱交換器で加熱された第一のガス燃料を、前記第一燃料噴射手段に供給することを特徴とするガスタービンシステム。 The gas turbine system according to any one of claims 1 to 3,
A heat exchanger provided in the flare stack for heating the first gas fuel;
A gas turbine system, wherein the first gas fuel heated by the heat exchanger is supplied to the first fuel injection means.
前記フレアスタック内に設けられた熱交換器と、
前記熱交換器に前記空気圧縮機から抽気した空気を供給する抽気空気供給系統と、
前記熱交換器に第一のガス燃料を供給する系統と、
窒素を供給する窒素供給手段と、
前記熱交換器に前記窒素供給手段からの窒素を供給する窒素供給系統とを有することを特徴とするガスタービンシステム。 The gas turbine system according to any one of claims 1 to 3,
A heat exchanger provided in the flare stack;
An extraction air supply system for supplying air extracted from the air compressor to the heat exchanger;
A system for supplying a first gas fuel to the heat exchanger;
Nitrogen supply means for supplying nitrogen;
A gas turbine system comprising: a nitrogen supply system that supplies nitrogen from the nitrogen supply means to the heat exchanger.
前記第二のガス燃料よりも発熱量の多いパイロットバーナ用燃料を燃焼させるパイロットバーナを有し、第一のガス燃料を燃焼させるフレアスタックと、
を有するガスタービンシステムの運転方法において、
前記ガスタービンの運転停止時には、前記燃焼器への前記混合燃料の供給を停止させ、前記混合燃料を前記フレアスタックに供給する一方、
第一のガス燃料を前記フレアスタック内のパイロットバーナの下流に供給することを特徴とするガスタービンシステムの運転方法。 An air compressor that compresses air, a gas compressor that pressurizes a mixed fuel of the first gas fuel, and a second gas fuel that generates more heat than the first gas fuel, and is compressed by the air compressor A gas turbine having a combustor that generates a combustion gas by burning the compressed air and the mixed fuel that has been pressurized by the gas compressor, and a gas turbine that is driven by the combustion gas generated by the combustor;
A flare stack that has a pilot burner that burns a fuel for a pilot burner that generates more heat than the second gas fuel, and that burns the first gas fuel;
In a method of operating a gas turbine system having
When the operation of the gas turbine is stopped, the supply of the mixed fuel to the combustor is stopped and the mixed fuel is supplied to the flare stack,
A method for operating a gas turbine system, wherein the first gas fuel is supplied downstream of a pilot burner in the flare stack.
前記ガスタービンの運転時には、前記フレアスタックに設けられた熱交換器に、前記空気圧縮機からの抽気空気を供給し、
前記ガスタービンの運転停止時には、前記熱交換器に不活性媒体を供給した後、前記熱交換器に第一のガス燃料を供給し、前記熱交換器で加熱した第一のガス燃料を前記フレアスタック内のパイロットバーナの下流に供給することを特徴とするガスタービンシステムの運転方法。 The operation method of the gas turbine system according to claim 7,
During operation of the gas turbine, the extracted air from the air compressor is supplied to a heat exchanger provided in the flare stack,
When the operation of the gas turbine is stopped, an inert medium is supplied to the heat exchanger, a first gas fuel is supplied to the heat exchanger, and the first gas fuel heated by the heat exchanger is supplied to the flare. A method for operating a gas turbine system, wherein the gas turbine system is supplied downstream of a pilot burner in a stack.
前記第一のガス燃料が、ＢＦＧであることを特徴とするガスタービンシステム。 The gas turbine system according to any one of claims 1 to 6,
The gas turbine system, wherein the first gas fuel is BFG.
前記第二のガス燃料が、ＣＯＧであることを特徴とするガスタービンシステム。 The gas turbine system according to claim 9, wherein
The gas turbine system, wherein the second gas fuel is COG.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2009225900A JP5183605B2 (en) | 2009-09-30 | 2009-09-30 | Low calorie gas fired gas turbine system and method of operating the system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2009225900A JP5183605B2 (en) | 2009-09-30 | 2009-09-30 | Low calorie gas fired gas turbine system and method of operating the system |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| JP2011074803A JP2011074803A (en) | 2011-04-14 |
| JP2011074803A5 true JP2011074803A5 (en) | 2011-09-22 |
| JP5183605B2 JP5183605B2 (en) | 2013-04-17 |
Family
ID=44019043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2009225900A Active JP5183605B2 (en) | 2009-09-30 | 2009-09-30 | Low calorie gas fired gas turbine system and method of operating the system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP5183605B2 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE112013005578B4 (en) | 2012-11-21 | 2022-05-05 | Mitsubishi Heavy Industries, Ltd. | Power generation system, drive method for power generation system |
| JP6004913B2 (en) * | 2012-11-21 | 2016-10-12 | 三菱日立パワーシステムズ株式会社 | Power generation system, power generation system driving method, and combustor |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH11324714A (en) * | 1998-05-11 | 1999-11-26 | Toshiba Corp | Gas turbine plant and its operating method |
| JP4898594B2 (en) * | 2007-08-10 | 2012-03-14 | 三菱重工業株式会社 | Gas turbine equipment |
-
2009
- 2009-09-30 JP JP2009225900A patent/JP5183605B2/en active Active
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