JP2013217267A5 - - Google Patents
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- JP2013217267A5 JP2013217267A5 JP2012087893A JP2012087893A JP2013217267A5 JP 2013217267 A5 JP2013217267 A5 JP 2013217267A5 JP 2012087893 A JP2012087893 A JP 2012087893A JP 2012087893 A JP2012087893 A JP 2012087893A JP 2013217267 A5 JP2013217267 A5 JP 2013217267A5
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- JP
- Japan
- Prior art keywords
- compressed air
- fuel
- combustion burner
- line
- supply line
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Description
実施形態３において、抽気ラインＰＡに供給される圧縮空気Ａｉｎは、車室４８の圧縮空気Ａｉｎの一部であって、圧縮機１１の出口の下流に位置する燃焼器尾筒４７の周囲の車室４８から抽出される。このため、抽気ラインＰＡは、車室４８の圧縮空気Ａｉｎの中で最も高い圧力の圧縮空気Ａｉｎを抽出できる。圧縮空気Ａｉｎの圧力は、高くなっているため、抽気ラインＰＡがパイロットノズル燃料ラインＦＰまたはメインノズル燃料ラインＦＭａに供給する圧縮空気Ａｉｎの圧力も高い。このため、パイロット燃料供給ラインＦＰまたはメイン燃料供給ラインＦＭの燃料ガスと、抽気ラインＰＡの圧縮空気Ａｉｎとが混合することにより、パイロット燃焼バーナ４４またはメイン燃焼バーナ４５がパイロット燃料またはメイン燃料を噴射する燃料ノズル差圧を増加することができる。そして、ガスタービン燃焼器１２は、大きな出力の圧縮機を備えなくても燃料ノズル差圧を増加することができ、上述した燃料供給ラインの大きさを抑制できる。その結果、パイロット燃料またはメイン燃料を噴射する軌跡が安定し、燃焼振動と呼ばれる不安定燃焼が助長される可能性を抑制できる。 In the third embodiment, the compressed air Ain supplied to the bleed line PA is a part of the compressed air Ain in the casing 48 and around the combustor tail cylinder 47 located downstream of the outlet of the compressor 11. Extracted from the cabin 48. For this reason, the extraction line PA can extract the compressed air Ain having the highest pressure among the compressed air Ain in the passenger compartment 48. Since the pressure of the compressed air Ain is high, the pressure of the compressed air Ain supplied from the extraction line PA to the pilot nozzle fuel line FP or the main nozzle fuel line FMa is also high. Therefore, the fuel gas in the pilot fuel supply line FP or the main fuel supply line FM and the compressed air Ain in the extraction line PA are mixed, so that the pilot combustion burner 44 or the main combustion burner 45 injects the pilot fuel or the main fuel. The fuel nozzle differential pressure can be increased. And the gas turbine combustor 12 can increase a fuel nozzle differential pressure, even if it does not have a high output compressor, and can suppress the magnitude | size of the fuel supply line mentioned above. As a result, the trajectory for injecting the pilot fuel or the main fuel is stabilized, and the possibility that unstable combustion called combustion oscillation is promoted can be suppressed.
Claims (6)
前記圧縮空気と燃料とが内部で燃焼して燃焼ガスを発生させる燃焼器内筒と、
前記燃焼器内筒の中央部に配置されるパイロット燃焼バーナと、
前記パイロット燃焼バーナを取り囲むように配置される複数のメイン燃焼バーナと、
前記パイロット燃焼バーナまたは前記メイン燃焼バーナに前記燃料を供給する燃料供給ラインと、
前記車室に流入する圧縮空気または前記車室の圧縮空気の少なくとも一方の一部を抽出し、前記燃料供給ラインに供給して前記燃料供給ラインの燃料に混合させる抽気ラインと、を含み、
前記抽気ラインに供給される圧縮空気は、前記車室に流入する圧縮空気の一部であって、前記圧縮機からの圧縮空気を整流するストラットから抽出されることを特徴とするガスタービン燃焼器。 A cabin into which compressed air from the compressor flows,
A combustor inner cylinder in which the compressed air and fuel are burned to generate combustion gas;
A pilot combustion burner disposed in a central portion of the combustor inner cylinder;
A plurality of main combustion burners arranged to surround the pilot combustion burner;
A fuel supply line for supplying the fuel to the pilot combustion burner or the main combustion burner;
Extracting at least one of a portion of the compressed air in the compressed air or the casing flows into the casing, see containing and a bleed line to be mixed with the fuel in the fuel supply line is supplied to the fuel supply line,
Compressed air supplied to the bleed line is a part of compressed air flowing into the passenger compartment, and is extracted from a strut that rectifies compressed air from the compressor . .
前記圧縮空気と燃料とが内部で燃焼して燃焼ガスを発生させる燃焼器内筒と、
前記燃焼器内筒の中央部に配置されるパイロット燃焼バーナと、
前記パイロット燃焼バーナを取り囲むように配置される複数のメイン燃焼バーナと、
前記パイロット燃焼バーナまたは前記メイン燃焼バーナに前記燃料を供給する燃料供給ラインと、
前記車室に流入する圧縮空気または前記車室の圧縮空気の少なくとも一方の一部を抽出し、前記燃料供給ラインに供給して前記燃料供給ラインの燃料に混合させる抽気ラインと、を含み、
前記車室から前記燃焼器内筒の内部に導入する圧縮空気を整流する整流板をさらに備え、
前記抽気ラインに供給される圧縮空気は、前記車室の圧縮空気の一部であって、前記整流板から抽出されることを特徴とするガスタービン燃焼器。 A cabin into which compressed air from the compressor flows,
A combustor inner cylinder in which the compressed air and fuel are burned to generate combustion gas;
A pilot combustion burner disposed in a central portion of the combustor inner cylinder;
A plurality of main combustion burners arranged to surround the pilot combustion burner;
A fuel supply line for supplying the fuel to the pilot combustion burner or the main combustion burner;
An extraction line for extracting a part of at least one of the compressed air flowing into the vehicle compartment or the compressed air of the vehicle compartment, supplying the fuel supply line to the fuel supply line,
A rectifying plate for rectifying compressed air introduced from the vehicle compartment into the combustor inner cylinder;
The compressed air supplied to the bleed line is a part of the compressed air in the passenger compartment, features and be Ruga turbines combustor to be extracted from the rectifier plate.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2012087893A JP5693514B2 (en) | 2012-04-06 | 2012-04-06 | Gas turbine combustor |
| PCT/JP2013/060500 WO2013151162A1 (en) | 2012-04-06 | 2013-04-05 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2012087893A JP5693514B2 (en) | 2012-04-06 | 2012-04-06 | Gas turbine combustor |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| JP2013217267A JP2013217267A (en) | 2013-10-24 |
| JP2013217267A5 true JP2013217267A5 (en) | 2014-04-17 |
| JP5693514B2 JP5693514B2 (en) | 2015-04-01 |
Family
ID=49300638
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2012087893A Expired - Fee Related JP5693514B2 (en) | 2012-04-06 | 2012-04-06 | Gas turbine combustor |
Country Status (2)
| Country | Link |
|---|---|
| JP (1) | JP5693514B2 (en) |
| WO (1) | WO2013151162A1 (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3050764B1 (en) * | 2016-04-28 | 2019-05-10 | Safran Aircraft Engines | SYSTEM AND METHOD FOR CONTROLLING THE INJECTORS OF A COMBUSTION CHAMBER |
| JP6841968B1 (en) * | 2020-09-04 | 2021-03-10 | 三菱パワー株式会社 | Perforated plate of gas turbine combustor, gas turbine combustor and gas turbine |
| US20240110519A1 (en) * | 2022-09-30 | 2024-04-04 | Raytheon Technologies Corporation | Centrifugally pumped fuel system |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5731538U (en) * | 1980-07-30 | 1982-02-19 | ||
| JPS57192728A (en) * | 1981-05-20 | 1982-11-26 | Hitachi Ltd | Fremixing combustion method of gas turbine and device thereof |
| JPH01139919A (en) * | 1987-11-27 | 1989-06-01 | Mitsubishi Heavy Ind Ltd | Method and device for gas turbine combustion |
| JP3196549B2 (en) * | 1995-01-09 | 2001-08-06 | 株式会社日立製作所 | Power generation system with fuel reformer |
| JP3578852B2 (en) * | 1995-12-05 | 2004-10-20 | 東京瓦斯株式会社 | Fuel supply system for multi-burner type combustor and gas turbine having the fuel supply system |
| US8381532B2 (en) * | 2010-01-27 | 2013-02-26 | General Electric Company | Bled diffuser fed secondary combustion system for gas turbines |
-
2012
- 2012-04-06 JP JP2012087893A patent/JP5693514B2/en not_active Expired - Fee Related
-
2013
- 2013-04-05 WO PCT/JP2013/060500 patent/WO2013151162A1/en active Application Filing
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