JP2007155170A5 - - Google Patents
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- JP2007155170A5 JP2007155170A5 JP2005348619A JP2005348619A JP2007155170A5 JP 2007155170 A5 JP2007155170 A5 JP 2007155170A5 JP 2005348619 A JP2005348619 A JP 2005348619A JP 2005348619 A JP2005348619 A JP 2005348619A JP 2007155170 A5 JP2007155170 A5 JP 2007155170A5
- Authority
- JP
- Japan
- Prior art keywords
- nozzle
- fuel
- main
- pilot
- gas turbine
- 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 44
- 238000002347 injection Methods 0.000 claims 9
- 239000007924 injection Substances 0.000 claims 9
- 238000000034 method Methods 0.000 claims 4
- 230000002093 peripheral effect Effects 0.000 claims 4
- 239000007788 liquid Substances 0.000 claims 2
- 238000007634 remodeling Methods 0.000 claims 2
- 238000011144 upstream manufacturing Methods 0.000 claims 2
Claims (8)
該ノズルキャップの内部に収納され、メイン燃料に旋回を付与するためのメイン旋回器及びパイロット燃料を噴出するためのパイロット噴孔を有し、前記ノズルキャップ内周壁との環状流路でメイン噴孔を形成するノズルチップと、
該ノズルチップ内に収納されパイロット燃料に旋回を付与するためのパイロット旋回器を有するパイロットチップからなるガスタービン燃焼器の燃料ノズルにおいて、
メイン燃料を噴出する前記メイン噴孔を燃料ノズルの軸線に対し平行な環状流路であって、該環状流路の流路断面積が変化しない直線部を有する構造としたことを特徴とするガスタービン燃焼器の燃料ノズル。 A nozzle cap that forms a main nozzle hole channel for ejecting main fuel;
A main swirler housed inside the nozzle cap and having a main swirler for imparting swirling to the main fuel and a pilot nozzle hole for ejecting pilot fuel, and the main nozzle hole in an annular flow path with the inner peripheral wall of the nozzle cap A nozzle tip to form,
In a fuel nozzle of a gas turbine combustor comprising a pilot tip housed in the nozzle tip and having a pilot swirler for imparting swirl to the pilot fuel,
Said main injection hole for injecting a main fuel a parallel annular channel against the axis of the fuel nozzle, wherein the flow path cross-sectional area of the annular flow path is a structure having a straight portion unchanged Fuel nozzle for gas turbine combustor.
前記メイン旋回器は前記旋回室の接線方向に複数の旋回流路を有する構成としたことを特徴とするガスタービン燃焼器の燃料ノズル。 The fuel nozzle of a gas turbine combustor according to claim 1 ,
Before SL main swirler fuel nozzle of a gas turbine combustor characterized by being configured to include a plurality of swirl channel in the tangential direction of the swirl chamber.
該ノズルキャップの内部に収納され、メイン燃料に旋回を付与するためのメイン旋回器及びパイロット燃料を噴出するためのパイロット噴孔を有し、前記ノズルキャップ内周壁との環状流路でメイン噴孔を形成するノズルチップと、A main swirler housed inside the nozzle cap and having a main swirler for imparting swirling to the main fuel and a pilot nozzle hole for ejecting pilot fuel, and the main nozzle hole in an annular flow path with the inner peripheral wall of the nozzle cap A nozzle tip to form,
該ノズルチップ内に収納されパイロット燃料に旋回を付与するためのパイロット旋回器を有するパイロットチップからなるガスタービン燃焼器の燃料ノズルにおいて、In a fuel nozzle of a gas turbine combustor comprising a pilot tip housed in the nozzle tip and having a pilot swirler for imparting swirl to the pilot fuel,
前記メイン噴孔は、前記ノズルチップが形成する前記パイロット流路の最下流部でメイン系統の中で最も流路断面積が小さくなる構造としたことを特徴とする燃料ノズル。The fuel nozzle according to claim 1, wherein the main nozzle hole has a structure in which a channel cross-sectional area is the smallest in the main system at a most downstream portion of the pilot channel formed by the nozzle tip.
前記パイロット噴孔の噴孔端の軸方向位置を前記メイン噴孔の噴孔端位置と同等、若しくは下流側に位置したことを特徴とするガスタービン燃焼器の燃料ノズル。 The fuel nozzle of a gas turbine combustor according to claim 1,
A fuel nozzle for a gas turbine combustor, wherein an axial position of an injection hole end of the pilot injection hole is located at a position equal to or downstream of the injection hole end position of the main injection hole.
前記旋回流路の上流側に位置し、複数の該旋回流路に液体燃料を分配するための環状空間を有する構造で、該環状空間の上流には前記環状空間に液体燃料を供給するためのメイン燃料供給孔が旋回流路と同数有する構造であって、該メイン燃料供給孔と前記旋回流路の入口端との相対位置を周方向に所望の角度だけ異ならしめる位置に前記旋回流路を形成したことを特徴とするガスタービン燃焼器の燃料ノズル。 The fuel nozzle of a gas turbine combustor according to claim 2 ,
Positioned upstream of the front Symbol swirl channel, in the structure having an annular space for distributing liquid fuel to a plurality of revolving whirling path, upstream of the annular space for supplying the liquid fuel to the annular space The main fuel supply holes have the same number as the swirl flow paths, and the swirl flow paths are positioned at positions where the relative positions of the main fuel supply holes and the swivel flow path inlets are different by a desired angle in the circumferential direction. A fuel nozzle for a gas turbine combustor, characterized by comprising:
前記メイン旋回器は、前記軸線と垂直な平面内でメイン燃料が旋回するよう構成されていることを特徴とするガスタービン燃焼器の燃料ノズル。The fuel nozzle of a gas turbine combustor, wherein the main swirler is configured to swirl main fuel in a plane perpendicular to the axis.
メイン燃料に旋回を与えた後、燃料ノズルの軸線における前記パイロット燃料の噴射部位置において流路断面積を最も絞ることで流量を調整した前記メイン燃料を、前記パイロット燃料の軸線に垂直な平面における外周側から噴射することを特徴とする燃料ノズルの燃料噴射方法。After turning the main fuel, the main fuel whose flow rate is adjusted by narrowing the flow passage cross-sectional area at the pilot fuel injection position in the axis of the fuel nozzle in the plane perpendicular to the axis of the pilot fuel. A fuel injection method for a fuel nozzle, characterized by injection from the outer peripheral side.
前記ノズルキャップを取り外す第１の工程と、
パイロット燃料に旋回を付与するためのパイロット旋回器を有するパイロットチップを取り付ける第２の工程と、
メイン燃料に旋回を付与するためのメイン旋回器及びパイロット燃料を噴出するためのパイロット噴孔を有し、前記ノズルキャップ内周壁との環状流路でメイン噴孔を形成するノズルチップを取り付ける第３の工程と、
メイン燃料を噴出する前記メイン噴孔を燃料ノズルの軸線に対し平行な環状流路であって、該環状流路の流路断面積が変化しない直線部を有するように形成したノズルキャップを前記ノズルボディに取り付ける第４の工程を備えたことを特徴とするガスタービン燃焼器の改造方法。 A nozzle body having a flow path for main fuel and pilot fuel, a nozzle cap in which the nozzle body is housed, and a fixing screw provided to each of the nozzle body and the nozzle cap are fixed from the nozzle body. A gas turbine combustor remodeling method for ejecting the supplied main fuel and pilot fuel from the nozzle cap nozzle hole,
A first step of removing the nozzle cap;
A second step of attaching a pilot tip having a pilot swirler for imparting swirl to the pilot fuel;
A main swirler for imparting swirl to the main fuel and a pilot nozzle hole for ejecting pilot fuel, and a third nozzle tip for attaching the nozzle tip forming the main nozzle hole in an annular flow path with the inner peripheral wall of the nozzle cap And the process of
Said main injection hole for injecting a main fuel a parallel annular channel against the axis of the fuel nozzle, wherein the formed nozzle cap so as to have a straight portion which flow path cross-sectional area of the annular flow path is not changed A method for remodeling a gas turbine combustor comprising a fourth step of attaching to a nozzle body.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2005348619A JP2007155170A (en) | 2005-12-02 | 2005-12-02 | Fuel nozzle, gas turbine combustor, fuel nozzle for gas turbine combustor, and modification method for gas turbine combustor |
| EP11162240A EP2385299A3 (en) | 2005-12-02 | 2006-12-01 | Liquid fuel nozzle of gas turbine combustor and method of rebuilding a gas turbine combustor |
| EP06024947A EP1793165A3 (en) | 2005-12-02 | 2006-12-01 | Liquid fuel nozzle, gas turbine combustor, and method of rebuilding gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2005348619A JP2007155170A (en) | 2005-12-02 | 2005-12-02 | Fuel nozzle, gas turbine combustor, fuel nozzle for gas turbine combustor, and modification method for gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JP2007155170A JP2007155170A (en) | 2007-06-21 |
| JP2007155170A5 true JP2007155170A5 (en) | 2009-09-10 |
Family
ID=37757160
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2005348619A Pending JP2007155170A (en) | 2005-12-02 | 2005-12-02 | Fuel nozzle, gas turbine combustor, fuel nozzle for gas turbine combustor, and modification method for gas turbine combustor |
Country Status (2)
| Country | Link |
|---|---|
| EP (2) | EP1793165A3 (en) |
| JP (1) | JP2007155170A (en) |
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| JP4959523B2 (en) * | 2007-11-29 | 2012-06-27 | 株式会社日立製作所 | Combustion device, method for modifying combustion device, and fuel injection method for combustion device |
| US9175606B2 (en) | 2008-06-09 | 2015-11-03 | Siemens Aktiengesellschaft | Method for rinsing a fuel system of a gas turbine and associated fuel system |
| FR2938048B1 (en) * | 2008-11-06 | 2015-03-06 | Ge Energy Products France Snc | SYSTEM AND METHOD FOR WASHING AND PURGING THE LIQUID COMBUSTIBLE CIRCUIT OF A TURBINE |
| US8161751B2 (en) * | 2009-04-30 | 2012-04-24 | General Electric Company | High volume fuel nozzles for a turbine engine |
| CH702598B1 (en) * | 2010-01-29 | 2013-12-13 | Alstom Technology Ltd | Injection nozzle and method for operating such an injection nozzle. |
| CN103109059B (en) * | 2010-10-28 | 2015-09-09 | 三菱日立电力系统株式会社 | Gas turbine and there is its gas-turbine plant |
| US9745936B2 (en) | 2012-02-16 | 2017-08-29 | Delavan Inc | Variable angle multi-point injection |
| JP5967974B2 (en) * | 2012-02-28 | 2016-08-10 | 三菱日立パワーシステムズ株式会社 | Pilot nozzle, gas turbine combustor including the same, and gas turbine |
| JP5618337B2 (en) | 2012-02-28 | 2014-11-05 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor |
| WO2013146624A1 (en) * | 2012-03-28 | 2013-10-03 | 藤崎電機株式会社 | Liquid jetting apparatus and liquid jetting method |
| EP2890499A4 (en) * | 2012-08-29 | 2016-05-25 | Snow Logic Inc | Modular dual vector fluid spray nozzles |
| WO2014062076A1 (en) * | 2012-10-17 | 2014-04-24 | Schlumberger Canada Limited | Multiphase burner |
| JP6086860B2 (en) | 2013-11-29 | 2017-03-01 | 三菱日立パワーシステムズ株式会社 | Nozzle, combustor, and gas turbine |
| JP6397511B2 (en) * | 2014-05-12 | 2018-09-26 | ゼネラル・エレクトリック・カンパニイ | Pre-film liquid fuel cartridge |
| US10107499B2 (en) | 2014-07-31 | 2018-10-23 | General Electric Company | Fuel plenum for a fuel nozzle and method of making same |
| JP6804755B2 (en) * | 2015-11-26 | 2020-12-23 | ウエムラ技研株式会社 | Swirl type injection nozzle |
| CN108731250B (en) * | 2018-06-08 | 2020-11-13 | 上海薄荷信息科技有限公司 | Liquid food heating equipment and heating method thereof |
| CN108981165A (en) * | 2018-06-08 | 2018-12-11 | 南通劲凌智能科技有限公司 | A kind of even thermal of supping and its method |
| US11149950B2 (en) * | 2018-06-11 | 2021-10-19 | Woodward, Inc. | Pre-swirl pressure atomizing tip |
| RU188999U1 (en) * | 2018-10-09 | 2019-05-06 | Федеральное государственное бюджетное образовательное Учреждение высшего образования "Воронежский государственный аграрный университет имени императора Петра 1" (ФГБОУ ВО Воронежский ГАУ) | Multi-fuel injector |
| RU189000U1 (en) * | 2018-10-09 | 2019-05-06 | Федеральное государственное бюджетное образовательное Учреждение высшего образования "Воронежский государственный аграрный университет имени императора Петра 1" (ФГБОУ ВО Воронежский ГАУ) | Centrifugal nozzle |
| US11378040B2 (en) * | 2018-11-15 | 2022-07-05 | Stratolaunch, Llc | Swirl preburner system and method |
| WO2021079657A1 (en) | 2019-10-23 | 2021-04-29 | 株式会社Ihi | Liquid fuel injector |
| RU2763964C1 (en) * | 2019-12-30 | 2022-01-11 | Публичное акционерное общество "ОДК-Кузнецов" (ПАО "ОДК-Кузнецов") | Double-circuit burner of low-emission combustion chamber of gas turbine engine |
| RU2744963C1 (en) * | 2020-06-09 | 2021-03-17 | Акционерное общество "Металлист-Самара" | Combustion chamber of gas-turbine plant with external flame tubes and low-emission burner device |
| US20230347359A1 (en) * | 2020-08-31 | 2023-11-02 | Chongqing Haier Drum Washing Machine Co., Ltd. | Nozzle structure, additive delivery device and washing machine |
| CN112780416A (en) * | 2021-01-29 | 2021-05-11 | 安徽应流航空科技有限公司 | Main fuel oil distribution structure |
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| US12092331B2 (en) | 2022-11-23 | 2024-09-17 | Woodward, Inc. | Tangential pressure atomizing tip without feed chamber |
| US20250092827A1 (en) * | 2023-09-14 | 2025-03-20 | Pratt & Whitney Canada Corp. | Fuel Nozzle for an Aircraft Engine |
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-
2005
- 2005-12-02 JP JP2005348619A patent/JP2007155170A/en active Pending
-
2006
- 2006-12-01 EP EP06024947A patent/EP1793165A3/en not_active Withdrawn
- 2006-12-01 EP EP11162240A patent/EP2385299A3/en not_active Withdrawn
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