JP2009513924A - 低排出燃焼器に対する改善された空気流分布 - Google Patents
低排出燃焼器に対する改善された空気流分布 Download PDFInfo
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- JP2009513924A JP2009513924A JP2008537797A JP2008537797A JP2009513924A JP 2009513924 A JP2009513924 A JP 2009513924A JP 2008537797 A JP2008537797 A JP 2008537797A JP 2008537797 A JP2008537797 A JP 2008537797A JP 2009513924 A JP2009513924 A JP 2009513924A
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- Prior art keywords
- gas turbine
- flow
- flow sleeve
- turbine combustor
- holes
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/54—Reverse-flow combustion chambers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gas Burners (AREA)
Abstract
Description
Claims (20)
- より高い燃焼安定性を持つガス・タービン燃焼器であって、
第1の端部、第2の端部、及び前記第2の端部に近接して設けられた複数の第1の穴を持つ流れスリーブと、
前記流れスリーブ内に径方向に設けられ、それによって前記流れスリーブとの間に第1の流路を形成する燃焼ライナと、
前記燃焼ライナ内で空気と混合する燃料を噴射するための少なくとも1つの燃料ノズルと、
前記複数の第1の穴に近接して前記流れスリーブに固定され、前記燃焼ライナに向けて前記第1の流路内に径方向内側に延びて、前記複数の第1の穴を通して前記第1の流路に入る空気から接線方向速度成分を顕著に取り除き、それによって前記空気を前記流れスリーブの第1の端部に向けてほぼ軸方向に導く複数の翼と、
を備えるガス・タービン燃焼器。 - 前記複数の翼が前記流れスリーブの周りに円周方向に等間隔で設けられている請求項1に記載のガス・タービン燃焼器。
- 前記翼が軸方向長さ、第1の壁及び第2の壁を持ち、それによって翼の厚さを画定しており、前記第1の壁及び第2の壁が前記流れスリーブと反対の縁で終わる請求項1に記載のガス・タービン燃焼器。
- 前記翼の縁に丸みが与えられている請求項3に記載のガス・タービン燃焼器。
- 前記翼の縁が前記燃焼ライナとの間に径方向の距離の間隔をあけられている請求項3に記載のガス・タービン燃焼器。
- 前記径方向の距離が最大で0.889cm(0.350インチ)である請求項5に記載のガス・タービン燃焼器。
- 前記複数の第1の穴が前記流れスリーブの周りに円周方向の列をなして軸方向に間隔をあけられている請求項1に記載のガス・タービン燃焼器。
- 前記複数の翼の数量が前記円周方向の列のそれぞれにおける前記複数の第1の穴の数量に等しい請求項7に記載のガス・タービン燃焼器。
- 前記複数の第1の穴が最大で5.08cm(2.00インチ)の直径を持つ請求項7に記載のガス・タービン燃焼器。
- ガス・タービン燃焼器全体を通しての圧力低下を軽減するための方法であって、
第1の端部、第2の端部、及び前記第2の端部に近接して設けられた複数の第1の穴を持つ流れスリーブと、前記流れスリーブ内に径方向に設けられ、それによって前記流れスリーブとの間に第1の流路を形成する燃焼ライナと、前記燃焼ライナ内で空気と混合する燃料を噴射するための少なくとも1つの燃料ノズルと、前記複数の第1の穴に近接して前記流れスリーブに固定され、前記第1の流路内に前記燃焼ライナに向けて径方向内側に延びる複数の翼とを備えるガス・タービン燃焼器を提供するステップと、
圧縮空気の流れを前記複数の第1の穴を通して前記第1の流路へ、さらに前記複数の翼の間へと導くステップと、
前記圧縮空気の流れを前記複数の翼によって整流して前記圧縮空気の流れから接線方向速度成分を顕著に取り除き、その上で、前記圧縮空気の流れを前記流れスリーブの第1の端部に向けてほぼ軸方向に導くステップであって、前記複数の翼によって前記圧縮空気の流れを機械的に整流することによって、前記流れスリーブの第2の端部から前記流れスリーブの第1の端部までの前記燃焼器全体を通しての圧力低下が軽減されるステップと、
を含む方法。 - 前記複数の翼が前記流れスリーブの周りに円周方向に等間隔で設けられている請求項10に記載の方法。
- 前記翼が軸方向長さ、第1の壁及び第2の壁を持ち、それによって翼の厚さを画定しており、前記第1の壁及び第2の壁が前記流れスリーブと反対の縁で終わる請求項10に記載の方法。
- 前記翼の縁に丸みが与えられている請求項12に記載の方法。
- 前記翼の縁が前記燃焼ライナとの間に径方向の距離の間隔をあけられている請求項12に記載の方法。
- 前記径方向の距離が最大で0.889cm(0.350インチ)である請求項14に記載の方法。
- より一様な円周方向の空気流分布を持つガス・タービン燃焼器であって、
第1の端部、第2の端部、及び前記第2の端部に近接して設けられた複数の第1の穴を持つ流れスリーブと、
前記流れスリーブ内に径方向に設けられ、それによって前記流れスリーブとの間に第1の流路を形成する燃焼ライナと、
前記燃焼ライナ内で空気と混合する燃料を噴射するための少なくとも1つの燃料ノズルと、
前記複数の第1の穴に近接して前記流れスリーブに固定され、前記第1の流路内に前記燃焼ライナに向けて径方向内側に延びて前記燃焼ライナからの径方向の距離を終える複数の翼であって、前記複数の第1の穴を通して前記第1の流路に入る空気から接線方向速度成分を顕著に取り除き、それによって前記空気を前記流れスリーブの第1の端部に向けてほぼ軸方向に導いて、より一様な円周方向の空気流パターンを前記燃焼器に対して提供する複数の翼と、
を備えるガス・タービン燃焼器。 - 前記複数の翼が前記流れスリーブの周りに円周方向に等間隔で設けられている請求項16に記載のガス・タービン燃焼器。
- 前記翼が軸方向長さ、第1の壁及び第2の壁を持ち、それによって翼の厚さを画定しており、前記第1の壁及び第2の壁が前記流れスリーブと反対の縁で終わる請求項17に記載のガス・タービン燃焼器。
- 前記翼の縁に丸みが与えられている請求項18に記載のガス・タービン燃焼器。
- 前記径方向の距離が最大で0.889cm(0.350インチ)である請求項16に記載のガス・タービン燃焼器。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/262,447 US7685823B2 (en) | 2005-10-28 | 2005-10-28 | Airflow distribution to a low emissions combustor |
US11/262,447 | 2005-10-28 | ||
PCT/US2006/040903 WO2007053323A2 (en) | 2005-10-28 | 2006-10-19 | Improved airflow distribution to a low emission combustor |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2009513924A true JP2009513924A (ja) | 2009-04-02 |
JP5091869B2 JP5091869B2 (ja) | 2012-12-05 |
Family
ID=38006376
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2008537797A Active JP5091869B2 (ja) | 2005-10-28 | 2006-10-19 | 低排出燃焼器に対する改善された空気流分布 |
Country Status (12)
Country | Link |
---|---|
US (1) | US7685823B2 (ja) |
EP (1) | EP1960650B1 (ja) |
JP (1) | JP5091869B2 (ja) |
CN (1) | CN101351633A (ja) |
AU (1) | AU2006309151B2 (ja) |
BR (1) | BRPI0618012A8 (ja) |
CA (1) | CA2627511C (ja) |
CZ (1) | CZ2008257A3 (ja) |
HU (1) | HUP0800390A2 (ja) |
IL (1) | IL191006A (ja) |
RU (1) | RU2495263C2 (ja) |
WO (1) | WO2007053323A2 (ja) |
Cited By (1)
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CN102788367B (zh) * | 2011-05-18 | 2015-04-22 | 中国科学院工程热物理研究所 | 燃气轮机柔和燃烧室及实现方法 |
US20120297784A1 (en) * | 2011-05-24 | 2012-11-29 | General Electric Company | System and method for flow control in gas turbine engine |
US8601820B2 (en) | 2011-06-06 | 2013-12-10 | General Electric Company | Integrated late lean injection on a combustion liner and late lean injection sleeve assembly |
US8919137B2 (en) | 2011-08-05 | 2014-12-30 | General Electric Company | Assemblies and apparatus related to integrating late lean injection into combustion turbine engines |
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US10738704B2 (en) | 2016-10-03 | 2020-08-11 | Raytheon Technologies Corporation | Pilot/main fuel shifting in an axial staged combustor for a gas turbine engine |
CN108826357A (zh) * | 2018-07-27 | 2018-11-16 | 清华大学 | 发动机的环形燃烧室 |
CN108952821B (zh) * | 2018-09-25 | 2023-12-08 | 中国船舶重工集团公司第七0三研究所 | 一种固定船用汽轮机导流板结构 |
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- 2006-10-19 CN CNA2006800501371A patent/CN101351633A/zh active Pending
- 2006-10-19 WO PCT/US2006/040903 patent/WO2007053323A2/en active Application Filing
- 2006-10-19 AU AU2006309151A patent/AU2006309151B2/en not_active Ceased
- 2006-10-19 HU HU0800390A patent/HUP0800390A2/hu unknown
- 2006-10-19 CA CA2627511A patent/CA2627511C/en not_active Expired - Fee Related
- 2006-10-19 EP EP06826289.8A patent/EP1960650B1/en not_active Not-in-force
- 2006-10-19 CZ CZ20080257A patent/CZ2008257A3/cs unknown
- 2006-10-19 BR BRPI0618012A patent/BRPI0618012A8/pt not_active IP Right Cessation
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Also Published As
Publication number | Publication date |
---|---|
EP1960650B1 (en) | 2014-02-26 |
WO2007053323A3 (en) | 2007-08-02 |
CZ2008257A3 (cs) | 2008-10-22 |
RU2495263C2 (ru) | 2013-10-10 |
BRPI0618012A8 (pt) | 2017-07-25 |
US7685823B2 (en) | 2010-03-30 |
EP1960650A2 (en) | 2008-08-27 |
AU2006309151B2 (en) | 2012-04-05 |
CA2627511C (en) | 2014-07-08 |
US20090139238A1 (en) | 2009-06-04 |
WO2007053323A2 (en) | 2007-05-10 |
BRPI0618012A2 (pt) | 2011-08-16 |
JP5091869B2 (ja) | 2012-12-05 |
IL191006A (en) | 2013-07-31 |
EP1960650A4 (en) | 2012-01-25 |
RU2008121212A (ru) | 2009-12-10 |
CA2627511A1 (en) | 2007-05-10 |
CN101351633A (zh) | 2009-01-21 |
HUP0800390A2 (en) | 2008-11-28 |
AU2006309151A1 (en) | 2007-05-10 |
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