JP2015034649A5 - - Google Patents
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- JP2015034649A5 JP2015034649A5 JP2013164440A JP2013164440A JP2015034649A5 JP 2015034649 A5 JP2015034649 A5 JP 2015034649A5 JP 2013164440 A JP2013164440 A JP 2013164440A JP 2013164440 A JP2013164440 A JP 2013164440A JP 2015034649 A5 JP2015034649 A5 JP 2015034649A5
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- turbine combustor
- gas turbine
- injection holes
- swirler
- 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.)
- Pending
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- 239000000446 fuel Substances 0.000 claims 22
- 238000002347 injection Methods 0.000 claims 11
- 239000007924 injection Substances 0.000 claims 11
- 238000002485 combustion reaction Methods 0.000 claims 3
- 230000020169 heat generation Effects 0.000 claims 3
- 230000033228 biological regulation Effects 0.000 claims 1
- 238000001514 detection method Methods 0.000 claims 1
- 230000002093 peripheral Effects 0.000 claims 1
- 238000011144 upstream manufacturing Methods 0.000 claims 1
Claims (5)
前記バーナは、複数の燃料噴孔と複数の空気噴孔とを有し、
前記複数の燃料噴孔は前記複数の空気噴孔よりも前記バーナの半径方向の内側に配置され、前記ガスタービン燃焼器の軸心に対する内向角を有し、前記バーナの半径中心方向に前記燃料を噴射する
ことを特徴とするガスタービン燃焼器。 A gas turbine combustor comprising a cylindrical combustion chamber for mixing and burning fuel and air, and a burner located upstream of the combustion chamber for injecting the fuel and air into the combustion chamber to hold a flame In
The burner has a plurality of fuel injection holes and a plurality of air injection holes,
The plurality of fuel injection holes are disposed radially inward of the burner with respect to the plurality of air injection holes, have an inward angle with respect to the axis of the gas turbine combustor, and the fuel in the radial center direction of the burner A gas turbine combustor characterized by injecting.
前記複数の燃料噴孔と前記複数の空気噴孔とはそれぞれ旋回角を有し、前記燃料および前記空気の旋回角度を同一方向とした
ことを特徴とするガスタービン燃焼器。 The gas turbine combustor according to claim 1.
The gas turbine combustor, wherein the plurality of fuel injection holes and the plurality of air injection holes each have a turning angle, and the turning angles of the fuel and the air are in the same direction.
前記バーナは、前記複数の空気噴孔と前記複数の燃料噴孔とを設けた第１スワラと、前記第１スワラの外周側であって前記燃料の一部を噴射する複数の第２燃料噴孔を設けた第２スワラとを備え、
前記第１スワラの前記複数の空気噴孔の旋回方向と前記第２スワラの前記複数の第２燃料噴孔の旋回方向とを同方向とした
ことを特徴とするガスタービン燃焼器。 The gas turbine combustor according to claim 1 or 2,
The burner includes a first swirler having the plurality of air injection holes and the plurality of fuel injection holes, and a plurality of second fuel injection nozzles that are disposed on an outer peripheral side of the first swirler and inject a part of the fuel. A second swirler provided with a hole,
The gas turbine combustor, wherein the swirling direction of the plurality of air injection holes of the first swirler and the swirling direction of the plurality of second fuel injection holes of the second swirler are the same direction.
前記第１スワラに燃料を供給する第１燃料系統と、前記第２スワラに燃料を供給する第２燃料系統と、前記第１燃料系統に設けた第１流量調整弁と、前記第２燃料系統に設けた第２流量調整弁と、前記燃料の発熱量変化検出手段とを有し、
前記発熱量変化検出手段の検出する発熱量の変化に応じて、前記第１流量調整弁の開度と前記第２流量調整弁の開度とを調整して前記第１及び第２スワラに供給する燃料流量比率を制御する
ことを特徴とするガスタービン燃焼器。 The gas turbine combustor according to claim 3.
A first fuel system for supplying fuel to the first swirler, and a second fuel system for supplying fuel to said second swirler, the first flow rate regulation valve provided in the first fuel system, the second A second flow rate adjustment valve provided in the fuel system; and a heat generation amount change detecting means of the fuel,
The opening of the first flow rate adjustment valve and the opening of the second flow rate adjustment valve are adjusted and supplied to the first and second swirlers according to the change in the heat generation amount detected by the heat generation amount change detection means. A gas turbine combustor characterized by controlling a fuel flow rate ratio.
前記第１スワラの燃料噴孔の半径方向内側に、起動用の油ノズルあるいはＬＮＧなどのガスノズルを配置し、起動用燃料とメインガス燃料とをそれぞれ独立に供給可能とした
ことを特徴とするガスタービン燃焼器。 The gas turbine combustor according to claim 3 or 4,
A gas nozzle, such as a starting oil nozzle or LNG, is arranged inside the fuel nozzle hole of the first swirler in the radial direction so that the starting fuel and the main gas fuel can be supplied independently. Turbine combustor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2013164440A JP2015034649A (en) | 2013-08-07 | 2013-08-07 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2013164440A JP2015034649A (en) | 2013-08-07 | 2013-08-07 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2015034649A JP2015034649A (en) | 2015-02-19 |
| JP2015034649A5 true JP2015034649A5 (en) | 2016-09-08 |
Family
ID=52543302
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2013164440A Pending JP2015034649A (en) | 2013-08-07 | 2013-08-07 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2015034649A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6484546B2 (en) | 2015-11-13 | 2019-03-13 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| CN109268147B (en) * | 2018-12-03 | 2023-05-09 | 刘慕华 | Ignition method and ignition device of gas turbine |
| JP2024067373A (en) * | 2022-11-04 | 2024-05-17 | 三菱重工業株式会社 | Gas turbine combustor control device, control method, and starting method |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5332217A (en) * | 1976-09-08 | 1978-03-27 | Kawasaki Heavy Ind Ltd | Fuel supply means for gas turbine |
| JPS581322A (en) * | 1982-04-30 | 1983-01-06 | Sharp Corp | Electronic device |
| JPS60170511U (en) * | 1984-04-16 | 1985-11-12 | 川崎重工業株式会社 | Fuel injection nozzle for gas turbine combustor |
| JPH05203146A (en) * | 1992-01-29 | 1993-08-10 | Hitachi Ltd | Gas turbine combustion apparatus and gas turbine power generator |
| JP2000130757A (en) * | 1998-10-23 | 2000-05-12 | Hitachi Ltd | Gas turbine combustor for gasification power plant |
| JP4728176B2 (en) * | 2005-06-24 | 2011-07-20 | 株式会社日立製作所 | Burner, gas turbine combustor and burner cooling method |
| JP5773342B2 (en) * | 2011-06-03 | 2015-09-02 | 川崎重工業株式会社 | Fuel injection device |
-
2013
- 2013-08-07 JP JP2013164440A patent/JP2015034649A/en active Pending
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