JP5374031B2 - タービンエンジンにおけるNOxエミッションを低減するのを可能にするための装置及びガスタービンエンジン - Google Patents
タービンエンジンにおけるNOxエミッションを低減するのを可能にするための装置及びガスタービンエンジン Download PDFInfo
- Publication number
- JP5374031B2 JP5374031B2 JP2007180473A JP2007180473A JP5374031B2 JP 5374031 B2 JP5374031 B2 JP 5374031B2 JP 2007180473 A JP2007180473 A JP 2007180473A JP 2007180473 A JP2007180473 A JP 2007180473A JP 5374031 B2 JP5374031 B2 JP 5374031B2
- Authority
- JP
- Japan
- Prior art keywords
- panel
- dilution
- holes
- dilution holes
- group
- 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.)
- Expired - Fee Related
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Classifications
-
- 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
- F23R3/06—Arrangement of apertures along the flame tube
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Description
12 低圧圧縮機
14 高圧圧縮機
16 燃焼器
18 高圧タービン
20 低圧タービン
21 第1のシャフト
22 第2のシャフト
52 外側ライナ
54 内側ライナ
56 外側ケーシング
58 内側ケーシング
60 燃焼室
62 外側通路
64 内側通路
66 カウル組立体
68 開口
70 ドームプレート
72 スワーラ組立体
74 燃料噴射器
75 長手方向軸線
76 前方端部
78 後方端部
80 パネル
82 第1のパネル
84 一次燃焼ゾーン
86 第2のパネル
88 中間燃焼ゾーン
90 第3のパネル
92 第4のパネル
94 下流希薄燃焼ゾーン
96 希釈孔
98 一次希釈孔
100 二次希釈孔
101 下流端部
102 希釈孔
140 長手方向軸線
150 希釈孔のグループ
152 希釈孔のグループ
160 冷却孔のグループ
170 第2のパネル上流端縁部
172 第1のグループ
174 第2のグループ
176 第3のグループ
Claims (5)
- 燃焼器ライナであって、
その上流端部に配置された第1のパネル(82)と前記第1のパネルの下流にかつ該第1のパネルに隣接して配置された第2のパネル(86)とを備えた複数の円周方向に延びるオーバーラップパネル(80)を含む環状シェルを含み、
前記第1のパネル(82)の下流部分が前記第2のパネル(86)の上流部分とオーバーラップし、
燃焼器ライナは、
前記第1のパネル(82)内に形成された複数の一次希釈孔(98)と、
前記第2のパネル(86)内に形成された、互いに均等に間隔を置いて配置された複数の二次希釈孔(100)と、を含み、
前記複数の二次希釈孔(100)は、前記一次希釈孔(98)に対し周方向にずらされて配置された二次希釈孔(100)を含み、前記一次及び二次希釈孔が、前記シェル内に希釈空気を吐出するように構成され、
前記二次希釈孔(100)が、前記一次希釈孔(98)から、該二次希釈孔の直径の2倍から該二次希釈孔の直径の4倍の範囲内にある距離だけ間隔を置いて配置され、
前記一次希釈孔(98)が、第1のグループの希釈孔(150)と第2のグループの希釈孔(152)とを含み、
前記第1のグループが、前記第2のグループの直径よりも大きい直径を有し、
前記第1のグループの各希釈孔が、前記第2のグループの隣接する希釈孔間に配置され、
前記二次希釈孔(100)が、前記第2のパネル(86)の下流に位置し該第2のパネルに隣接して配置された第3のパネル(90)から、該二次希釈孔の直径の二分の一である距離だけ間隔を置いて配置され、
前記第2のパネル及び第3のパネルのみに冷却孔(160)が設けられ、
前記冷却孔(160)は、前記二次希釈孔(100)のうちの2つの間に且つ該二次希釈孔(100)の下流に設けられる
ことを特徴とする、燃焼器ライナ。 - 前記一次希釈孔(98)が、前記二次希釈孔(100)の直径よりも大きい直径を有する、請求項1記載の燃焼器ライナ。
- 前記二次希釈孔(100)が、前記シェル内に燃料/空気混合気を吐出するように構成されたスワーラと整列する、請求項1記載の燃焼器ライナ。
- 前記希釈孔(98,100)が、ガスタービンエンジン(10)におけるNOxエミッションを低減するのを可能にする、請求項1記載の燃焼器ライナ。
- 圧縮機(12、14)と
燃焼器ライナを備えた燃焼器(16)と、
を含み、
前記燃焼器ライナが、
その上流端部に配置された第1のパネル(82)と前記第1のパネルの下流にかつ該第1のパネルに隣接して配置された第2のパネル(86)とを備えた複数の円周方向に延びるオーバーラップパネル(80)を含む環状シェルを含み、
前記第1のパネル(82)の下流部分が前記第2のパネル(86)の上流部分とオーバーラップし、
前記燃焼器ライナは、
前記第1のパネル内に形成された複数の一次希釈孔(98)と、
前記第2のパネル内に形成された、互いに均等に間隔を置いて配置された複数の二次希釈孔(100)と、を含み、
前記複数の二次希釈孔(100)は、前記一次希釈孔(98)に対し周方向にずらされて配置された二次希釈孔(100)を含み、前記一次及び二次希釈孔が、前記圧縮機から前記燃焼器内に希釈空気を吐出するように構成され、前記一次及び二次希釈孔が、ガスタービンエンジンにおけるNOxエミッションを低減するのを可能にするようにさらに構成され、
前記二次希釈孔(100)が、前記一次希釈孔(98)から、該二次希釈孔の直径の2倍から該二次希釈孔の直径の4倍の範囲内にある距離だけ間隔を置いて配置され、
前記一次希釈孔(98)が、第1のグループの希釈孔(150)と第2のグループの希釈孔(152)とを含み、
前記第1のグループが、前記第2のグループの直径よりも大きい直径を有し、
前記第1のグループの各希釈孔が、前記第2のグループの隣接する希釈孔間に配置され、
前記燃焼器ライナが、前記第2のパネルの下流にかつ該第2のパネルに隣接して配置された第3のパネル(90)を更に備え、
前記第2のパネル及び第3のパネルのみに冷却孔(160)が設けられ、
前記冷却孔(160)は、前記二次希釈孔(100)のうちの2つの間に且つ該二次希釈孔(100)の下流に設けられる
ことを特徴とする、ガスタービンエンジン(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/486,757 US7895841B2 (en) | 2006-07-14 | 2006-07-14 | Method and apparatus to facilitate reducing NOx emissions in turbine engines |
US11/486,757 | 2006-07-14 |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2008020180A JP2008020180A (ja) | 2008-01-31 |
JP5374031B2 true JP5374031B2 (ja) | 2013-12-25 |
Family
ID=38650015
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2007180473A Expired - Fee Related JP5374031B2 (ja) | 2006-07-14 | 2007-07-10 | タービンエンジンにおけるNOxエミッションを低減するのを可能にするための装置及びガスタービンエンジン |
Country Status (7)
Country | Link |
---|---|
US (2) | US7895841B2 (ja) |
EP (1) | EP1878971A3 (ja) |
JP (1) | JP5374031B2 (ja) |
CN (2) | CN101105293B (ja) |
CA (1) | CA2593466C (ja) |
MY (1) | MY151124A (ja) |
SG (2) | SG158865A1 (ja) |
Families Citing this family (42)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7509809B2 (en) * | 2005-06-10 | 2009-03-31 | Pratt & Whitney Canada Corp. | Gas turbine engine combustor with improved cooling |
FR2892180B1 (fr) * | 2005-10-18 | 2008-02-01 | Snecma Sa | Amelioration des perfomances d'une chambre de combustion par multiperforation des parois |
US7762074B2 (en) * | 2006-04-04 | 2010-07-27 | Siemens Energy, Inc. | Air flow conditioner for a combustor can of a gas turbine engine |
US20090142548A1 (en) * | 2007-10-18 | 2009-06-04 | David Bruce Patterson | Air cooled gas turbine components and methods of manufacturing and repairing the same |
US8056342B2 (en) * | 2008-06-12 | 2011-11-15 | United Technologies Corporation | Hole pattern for gas turbine combustor |
US8091367B2 (en) * | 2008-09-26 | 2012-01-10 | Pratt & Whitney Canada Corp. | Combustor with improved cooling holes arrangement |
US20100242483A1 (en) * | 2009-03-30 | 2010-09-30 | United Technologies Corporation | Combustor for gas turbine engine |
US8910481B2 (en) * | 2009-05-15 | 2014-12-16 | United Technologies Corporation | Advanced quench pattern combustor |
US8397511B2 (en) * | 2009-05-19 | 2013-03-19 | General Electric Company | System and method for cooling a wall of a gas turbine combustor |
CN102116487B (zh) * | 2009-12-30 | 2012-07-11 | 中国科学院工程热物理研究所 | 一种航机改型生物燃料燃烧室降低co排放的方法 |
FR2972027B1 (fr) * | 2011-02-25 | 2013-03-29 | Snecma | Chambre annulaire de combustion de turbomachine comprenant des orifices de dilution ameliores |
US8984888B2 (en) | 2011-10-26 | 2015-03-24 | General Electric Company | Fuel injection assembly for use in turbine engines and method of assembling same |
US9134028B2 (en) | 2012-01-18 | 2015-09-15 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
US9217568B2 (en) | 2012-06-07 | 2015-12-22 | United Technologies Corporation | Combustor liner with decreased liner cooling |
US9243801B2 (en) | 2012-06-07 | 2016-01-26 | United Technologies Corporation | Combustor liner with improved film cooling |
US9335049B2 (en) * | 2012-06-07 | 2016-05-10 | United Technologies Corporation | Combustor liner with reduced cooling dilution openings |
US9239165B2 (en) | 2012-06-07 | 2016-01-19 | United Technologies Corporation | Combustor liner with convergent cooling channel |
US10107497B2 (en) | 2012-10-04 | 2018-10-23 | United Technologies Corporation | Gas turbine engine combustor liner |
US9228747B2 (en) * | 2013-03-12 | 2016-01-05 | Pratt & Whitney Canada Corp. | Combustor for gas turbine engine |
US9879861B2 (en) * | 2013-03-15 | 2018-01-30 | Rolls-Royce Corporation | Gas turbine engine with improved combustion liner |
WO2014143209A1 (en) * | 2013-03-15 | 2014-09-18 | Rolls-Royce Corporation | Gas turbine engine combustor liner |
US9303871B2 (en) | 2013-06-26 | 2016-04-05 | Siemens Aktiengesellschaft | Combustor assembly including a transition inlet cone in a gas turbine engine |
US10816206B2 (en) | 2013-10-24 | 2020-10-27 | Raytheon Technologies Corporation | Gas turbine engine quench pattern for gas turbine engine combustor |
US10670267B2 (en) * | 2015-08-14 | 2020-06-02 | Raytheon Technologies Corporation | Combustor hole arrangement for gas turbine engine |
US10378444B2 (en) * | 2015-08-19 | 2019-08-13 | General Electric Company | Engine component for a gas turbine engine |
JP6722491B2 (ja) * | 2016-04-01 | 2020-07-15 | 川崎重工業株式会社 | ガスタービンの燃焼器 |
US11022313B2 (en) * | 2016-06-22 | 2021-06-01 | General Electric Company | Combustor assembly for a turbine engine |
US10337738B2 (en) * | 2016-06-22 | 2019-07-02 | General Electric Company | Combustor assembly for a turbine engine |
DE102016219424A1 (de) * | 2016-10-06 | 2018-04-12 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammeranordnung einer Gasturbine sowie Fluggasturbine |
US10830433B2 (en) | 2016-11-10 | 2020-11-10 | Raytheon Technologies Corporation | Axial non-linear interface for combustor liner panels in a gas turbine combustor |
US10935236B2 (en) | 2016-11-10 | 2021-03-02 | Raytheon Technologies Corporation | Non-planar combustor liner panel for a gas turbine engine combustor |
US10935235B2 (en) | 2016-11-10 | 2021-03-02 | Raytheon Technologies Corporation | Non-planar combustor liner panel for a gas turbine engine combustor |
US10655853B2 (en) | 2016-11-10 | 2020-05-19 | United Technologies Corporation | Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor |
GB201715366D0 (en) * | 2017-09-22 | 2017-11-08 | Rolls Royce Plc | A combustion chamber |
US10816202B2 (en) * | 2017-11-28 | 2020-10-27 | General Electric Company | Combustor liner for a gas turbine engine and an associated method thereof |
US11255543B2 (en) | 2018-08-07 | 2022-02-22 | General Electric Company | Dilution structure for gas turbine engine combustor |
US11181269B2 (en) | 2018-11-15 | 2021-11-23 | General Electric Company | Involute trapped vortex combustor assembly |
CN111006241B (zh) * | 2019-12-03 | 2022-01-21 | 哈尔滨工程大学 | 一种燃用低热值气体燃料的等离子点火与助燃燃烧室 |
US11560837B2 (en) * | 2021-04-19 | 2023-01-24 | General Electric Company | Combustor dilution hole |
US11572835B2 (en) * | 2021-05-11 | 2023-02-07 | General Electric Company | Combustor dilution hole |
US12078100B2 (en) | 2021-12-03 | 2024-09-03 | General Electric Company | Combustor size rating for a gas turbine engine using hydrogen fuel |
US11774100B2 (en) * | 2022-01-14 | 2023-10-03 | General Electric Company | Combustor fuel nozzle assembly |
Family Cites Families (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4733538A (en) * | 1978-10-02 | 1988-03-29 | General Electric Company | Combustion selective temperature dilution |
JPS56117273U (ja) * | 1980-02-01 | 1981-09-08 | ||
US4389848A (en) | 1981-01-12 | 1983-06-28 | United Technologies Corporation | Burner construction for gas turbines |
US4944149A (en) | 1988-12-14 | 1990-07-31 | General Electric Company | Combustor liner with air staging for NOx control |
US5117636A (en) * | 1990-02-05 | 1992-06-02 | General Electric Company | Low nox emission in gas turbine system |
IL110797A (en) | 1993-09-15 | 1997-09-30 | Electric Power Res Inst | Fluid atomizer |
JP3619626B2 (ja) * | 1996-11-29 | 2005-02-09 | 株式会社東芝 | ガスタービン燃焼器の運転方法 |
US6048510A (en) | 1997-09-30 | 2000-04-11 | Coal Tech Corporation | Method for reducing nitrogen oxides in combustion effluents |
US6192689B1 (en) | 1998-03-18 | 2001-02-27 | General Electric Company | Reduced emissions gas turbine combustor |
US6715292B1 (en) * | 1999-04-15 | 2004-04-06 | United Technologies Corporation | Coke resistant fuel injector for a low emissions combustor |
US6101814A (en) * | 1999-04-15 | 2000-08-15 | United Technologies Corporation | Low emissions can combustor with dilution hole arrangement for a turbine engine |
FI112526B (fi) | 1999-07-21 | 2003-12-15 | Waertsilae Finland Oy | Menetelmä nelitahtisen turboahdetun mäntämoottorin typpioksidipäästöjen (NOx) vähentämiseksi |
US6260359B1 (en) * | 1999-11-01 | 2001-07-17 | General Electric Company | Offset dilution combustor liner |
US6453658B1 (en) | 2000-02-24 | 2002-09-24 | Capstone Turbine Corporation | Multi-stage multi-plane combustion system for a gas turbine engine |
US6453830B1 (en) | 2000-02-29 | 2002-09-24 | Bert Zauderer | Reduction of nitrogen oxides by staged combustion in combustors, furnaces and boilers |
US6427446B1 (en) * | 2000-09-19 | 2002-08-06 | Power Systems Mfg., Llc | Low NOx emission combustion liner with circumferentially angled film cooling holes |
US20020104316A1 (en) | 2000-11-03 | 2002-08-08 | Capstone Turbine Corporation | Ultra low emissions gas turbine cycle using variable combustion primary zone airflow control |
US6543233B2 (en) | 2001-02-09 | 2003-04-08 | General Electric Company | Slot cooled combustor liner |
US6606861B2 (en) | 2001-02-26 | 2003-08-19 | United Technologies Corporation | Low emissions combustor for a gas turbine engine |
US6553767B2 (en) | 2001-06-11 | 2003-04-29 | General Electric Company | Gas turbine combustor liner with asymmetric dilution holes machined from a single piece form |
US6655146B2 (en) * | 2001-07-31 | 2003-12-02 | General Electric Company | Hybrid film cooled combustor liner |
US6513331B1 (en) | 2001-08-21 | 2003-02-04 | General Electric Company | Preferential multihole combustor liner |
KR100831772B1 (ko) * | 2001-11-30 | 2008-05-27 | 파워 시스템즈 엠에프지., 엘엘씨 | 질소산화물 저 배출 연소기용 연소 챔버/벤츄리 냉각장치및 방법 |
US7082753B2 (en) | 2001-12-03 | 2006-08-01 | Catalytica Energy Systems, Inc. | System and methods for improved emission control of internal combustion engines using pulsed fuel flow |
US6694900B2 (en) | 2001-12-14 | 2004-02-24 | General Electric Company | Integration of direct combustion with gasification for reduction of NOx emissions |
US6823852B2 (en) | 2002-02-19 | 2004-11-30 | Collier Technologies, Llc | Low-emission internal combustion engine |
US7086232B2 (en) | 2002-04-29 | 2006-08-08 | General Electric Company | Multihole patch for combustor liner of a gas turbine engine |
US6953558B2 (en) | 2002-09-06 | 2005-10-11 | Solutia, Inc. | Process for reducing nitrogen oxide emissions |
US6865881B2 (en) | 2002-11-18 | 2005-03-15 | Diesel & Combustion Technologies, Llc | System and method for reducing nitrogen oxides in combustion exhaust streams |
US7047748B2 (en) | 2002-12-02 | 2006-05-23 | Bert Zauderer | Injection methods to reduce nitrogen oxides emission from gas turbines combustors |
US6968693B2 (en) * | 2003-09-22 | 2005-11-29 | General Electric Company | Method and apparatus for reducing gas turbine engine emissions |
US7146802B2 (en) | 2004-10-07 | 2006-12-12 | General Motors Corporation | Reducing NOx emissions with a staged catalyst |
-
2006
- 2006-07-14 US US11/486,757 patent/US7895841B2/en active Active
- 2006-10-31 US US11/590,178 patent/US7900457B2/en active Active
-
2007
- 2007-07-09 MY MYPI20071090 patent/MY151124A/en unknown
- 2007-07-10 JP JP2007180473A patent/JP5374031B2/ja not_active Expired - Fee Related
- 2007-07-11 EP EP07112215.4A patent/EP1878971A3/en not_active Withdrawn
- 2007-07-12 CA CA2593466A patent/CA2593466C/en not_active Expired - Fee Related
- 2007-07-13 CN CN200710142192XA patent/CN101105293B/zh active Active
- 2007-07-16 CN CNA2007101364787A patent/CN101105292A/zh active Pending
- 2007-07-16 SG SG201000113-9A patent/SG158865A1/en unknown
- 2007-07-16 SG SG200705242-6A patent/SG139666A1/en unknown
Also Published As
Publication number | Publication date |
---|---|
CN101105293A (zh) | 2008-01-16 |
CA2593466A1 (en) | 2008-01-14 |
US7895841B2 (en) | 2011-03-01 |
SG158865A1 (en) | 2010-02-26 |
US20080010991A1 (en) | 2008-01-17 |
CN101105293B (zh) | 2011-06-08 |
CA2593466C (en) | 2014-11-04 |
JP2008020180A (ja) | 2008-01-31 |
CN101105292A (zh) | 2008-01-16 |
EP1878971A2 (en) | 2008-01-16 |
US20080010992A1 (en) | 2008-01-17 |
US7900457B2 (en) | 2011-03-08 |
SG139666A1 (en) | 2008-02-29 |
MY151124A (en) | 2014-04-30 |
EP1878971A3 (en) | 2014-02-26 |
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