JP2005054793A - 燃焼器の断熱シールドパネルおよび断熱シールドパネルとシェルとの組み合わせ - Google Patents
燃焼器の断熱シールドパネルおよび断熱シールドパネルとシェルとの組み合わせ Download PDFInfo
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- JP2005054793A JP2005054793A JP2004223416A JP2004223416A JP2005054793A JP 2005054793 A JP2005054793 A JP 2005054793A JP 2004223416 A JP2004223416 A JP 2004223416A JP 2004223416 A JP2004223416 A JP 2004223416A JP 2005054793 A JP2005054793 A JP 2005054793A
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- shell
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- combustor
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- 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
- F23R3/60—Support structures; Attaching or mounting means
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- 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
- F23R3/002—Wall structures
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03042—Film cooled combustion chamber walls or domes
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- 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
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
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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)
- Mounting Of Bearings Or Others (AREA)
Abstract
【解決手段】 燃焼器の断熱シールド(24)が燃焼器シェル(22)に対して固定されており、断熱シールドの主要領域にわたって該断熱シールドの外側面(34)がシェルの内側面(36)に面するとともにこれから離間される。断熱シールドの外側面とシェルの内側面との間には、断熱シールドの周縁の少なくとも主要部分に沿って間隙(80)が形成される。
【選択図】 図1
Description
24…内側断熱シールド
34…断熱シールドの外側面
36…シェルの内側面
80…間隙
Claims (10)
- 内側面と、
外側面と、
前記外側面に設けられた入口と、前記内側面に設けられた出口と、を有する複数の冷却ガス通路と、
前記外側面から延在するとともに、遠位のねじ付部分を備える複数のスタッドと、
取付面と接触する遠位の面を有するとともに、パネルの周縁の長さの少なくとも20%にわたって延在する周縁レールの突出部よりも少なくとも0.2mm長い距離で突出する複数のスタンドオフと、を有することを特徴とする燃焼器の断熱シールドパネル。 - 各々のスタンドオフは、関連する1つのスタッドの一部を囲むカラーまたはピンの列として形成されることを特徴とする請求項1記載の燃焼器の断熱シールドパネル。
- 前記距離は、前記周縁レールの突出部よりも少なくとも0.4mm長いことを特徴とする請求項1記載の燃焼器の断熱シールドパネル。
- 燃焼器の断熱シールドパネルとシェルとの組み合わせであって、
前記断熱シールドパネルは、
内側面と、
外側面と、
周縁と、
前記パネルの外側面に設けられた入口と、前記パネルの内側面に設けられた出口と、を備える複数の冷却ガス通路と、を有し、
前記シェルは、
内側面と、
外側面と、
前記シェルの外側面に設けられた入口と、前記シェルの内側面に設けられた出口と、を備える複数の冷却ガス通路と、を有し、
さらに、前記パネルの外側面の主要領域にわたって該パネルの外側面が前記シェルの内側面に面するとともにこの内側面から離間された状態に維持され、かつ前記周縁の少なくとも主要部分に沿って前記パネルの外側面と前記シェルの内側面との間に間隙が形成されるように、前記パネルを前記シェルに固定する手段を有することを特徴とする燃焼器の断熱シールドパネルとシェルとの組み合わせ。 - 前記間隙は、前記周縁の全体にわたって延びていることを特徴とする請求項4記載の燃焼器の断熱シールドパネルとシェルとの組み合わせ。
- 前記パネルの外側面は、前記間隙の主要部分に沿って、前記周縁の12.7mm以内において前記シェルに向かって延在するレールを有することを特徴とする請求項4記載の燃焼器の断熱シールドパネルとシェルとの組み合わせ。
- 前記レールは、前記周縁の全体にわたって延在していることを特徴とする請求項6記載の燃焼器の断熱シールドパネルとシェルとの組み合わせ。
- 前記パネルの外側面は、前記間隙の主要部分に沿って前記シェルに向かって延在するレールを含まないことを特徴とする請求項4記載の燃焼器の断熱シールドパネルとシェルとの組み合わせ。
- 前記間隙は、前記周縁の大部分に沿って少なくとも0.2mmの高さを有することを特徴とする請求項4記載の燃焼器の断熱シールドパネルとシェルとの組み合わせ。
- 前記手段は、複数のスタッドを含み、前記断熱シールドと前記シェルとは、前記スタッドの軸から12.7mmを超える領域では接触していないことを特徴とする請求項4記載の燃焼器の断熱シールドパネルとシェルとの組み合わせ。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
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US10/632,046 US7146815B2 (en) | 2003-07-31 | 2003-07-31 | Combustor |
Publications (2)
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JP2005054793A true JP2005054793A (ja) | 2005-03-03 |
JP4083717B2 JP4083717B2 (ja) | 2008-04-30 |
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JP2004223416A Expired - Fee Related JP4083717B2 (ja) | 2003-07-31 | 2004-07-30 | 燃焼器の断熱シールドパネルおよび断熱シールドパネルとシェルとの組み合わせ |
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Country | Link |
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US (1) | US7146815B2 (ja) |
EP (1) | EP1503144B1 (ja) |
JP (1) | JP4083717B2 (ja) |
CN (1) | CN1580640A (ja) |
DE (1) | DE602004024478D1 (ja) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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JP2012047443A (ja) * | 2010-08-27 | 2012-03-08 | Alstom Technology Ltd | バーナ装置を稼働させる方法及びこの方法を実施するバーナ装置 |
Families Citing this family (102)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1423645B1 (de) * | 2001-09-07 | 2008-10-08 | Alstom Technology Ltd | Dämpfungsanordnung zur reduzierung von brennkammerpulsationen in einer gasturbinenanlage |
EP1398569A1 (de) * | 2002-09-13 | 2004-03-17 | Siemens Aktiengesellschaft | Gasturbine |
DE10341515A1 (de) * | 2003-09-04 | 2005-03-31 | Rolls-Royce Deutschland Ltd & Co Kg | Anordnung zur Kühlung hoch wärmebelasteter Bauteile |
US7363763B2 (en) * | 2003-10-23 | 2008-04-29 | United Technologies Corporation | Combustor |
US7140185B2 (en) * | 2004-07-12 | 2006-11-28 | United Technologies Corporation | Heatshielded article |
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US7219498B2 (en) * | 2004-09-10 | 2007-05-22 | Honeywell International, Inc. | Waffled impingement effusion method |
EP1650503A1 (en) * | 2004-10-25 | 2006-04-26 | Siemens Aktiengesellschaft | Method for cooling a heat shield element and a heat shield element |
US7574865B2 (en) * | 2004-11-18 | 2009-08-18 | Siemens Energy, Inc. | Combustor flow sleeve with optimized cooling and airflow distribution |
US7581385B2 (en) * | 2005-11-03 | 2009-09-01 | United Technologies Corporation | Metering sheet and iso-grid arrangement for a non axi-symmetric shaped cooling liner within a gas turbine engine exhaust duct |
US7954325B2 (en) * | 2005-12-06 | 2011-06-07 | United Technologies Corporation | Gas turbine combustor |
EP1832812A3 (de) * | 2006-03-10 | 2012-01-04 | Rolls-Royce Deutschland Ltd & Co KG | Gasturbinenbrennkammerwand mit Dämpfung von Brennkammerschwingungen |
US7726131B2 (en) * | 2006-12-19 | 2010-06-01 | Pratt & Whitney Canada Corp. | Floatwall dilution hole cooling |
DE102007018061A1 (de) * | 2007-04-17 | 2008-10-23 | Rolls-Royce Deutschland Ltd & Co Kg | Gasturbinenbrennkammerwand |
US8800293B2 (en) * | 2007-07-10 | 2014-08-12 | United Technologies Corporation | Floatwell panel assemblies and related systems |
JP4969384B2 (ja) * | 2007-09-25 | 2012-07-04 | 三菱重工業株式会社 | ガスタービン燃焼器の冷却構造 |
US20100037620A1 (en) * | 2008-08-15 | 2010-02-18 | General Electric Company, Schenectady | Impingement and effusion cooled combustor component |
US20100095680A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
US20100095679A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
US8435007B2 (en) * | 2008-12-29 | 2013-05-07 | Rolls-Royce Corporation | Hybrid turbomachinery component for a gas turbine engine |
US8438856B2 (en) | 2009-03-02 | 2013-05-14 | General Electric Company | Effusion cooled one-piece can combustor |
US20100257863A1 (en) * | 2009-04-13 | 2010-10-14 | General Electric Company | Combined convection/effusion cooled one-piece can combustor |
US20100263386A1 (en) * | 2009-04-16 | 2010-10-21 | General Electric Company | Turbine engine having a liner |
US8495881B2 (en) * | 2009-06-02 | 2013-07-30 | General Electric Company | System and method for thermal control in a cap of a gas turbine combustor |
EP2261564A1 (de) * | 2009-06-09 | 2010-12-15 | Siemens Aktiengesellschaft | Hitzeschildelementanordnung mit Schraubeneinfädelmittel und Verfahren zur Montage eines Hitzeschildelementes |
US8739546B2 (en) * | 2009-08-31 | 2014-06-03 | United Technologies Corporation | Gas turbine combustor with quench wake control |
US8443610B2 (en) | 2009-11-25 | 2013-05-21 | United Technologies Corporation | Low emission gas turbine combustor |
US9068751B2 (en) * | 2010-01-29 | 2015-06-30 | United Technologies Corporation | Gas turbine combustor with staged combustion |
US8966877B2 (en) | 2010-01-29 | 2015-03-03 | United Technologies Corporation | Gas turbine combustor with variable airflow |
US9151171B2 (en) | 2010-08-27 | 2015-10-06 | Siemens Energy, Inc. | Stepped inlet ring for a transition downstream from combustor basket in a combustion turbine engine |
US9038393B2 (en) | 2010-08-27 | 2015-05-26 | Siemens Energy, Inc. | Fuel gas cooling system for combustion basket spring clip seal support |
US8479521B2 (en) | 2011-01-24 | 2013-07-09 | United Technologies Corporation | Gas turbine combustor with liner air admission holes associated with interspersed main and pilot swirler assemblies |
US9068748B2 (en) | 2011-01-24 | 2015-06-30 | United Technologies Corporation | Axial stage combustor for gas turbine engines |
US9958162B2 (en) | 2011-01-24 | 2018-05-01 | United Technologies Corporation | Combustor assembly for a turbine engine |
US8667682B2 (en) | 2011-04-27 | 2014-03-11 | Siemens Energy, Inc. | Method of fabricating a nearwall nozzle impingement cooled component for an internal combustion engine |
US9534783B2 (en) * | 2011-07-21 | 2017-01-03 | United Technologies Corporation | Insert adjacent to a heat shield element for a gas turbine engine combustor |
US20130074471A1 (en) * | 2011-09-22 | 2013-03-28 | General Electric Company | Turbine combustor and method for temperature control and damping a portion of a combustor |
JP5821550B2 (ja) * | 2011-11-10 | 2015-11-24 | 株式会社Ihi | 燃焼器ライナ |
US9239165B2 (en) * | 2012-06-07 | 2016-01-19 | United Technologies Corporation | Combustor liner with convergent cooling channel |
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 |
US9052111B2 (en) | 2012-06-22 | 2015-06-09 | United Technologies Corporation | Turbine engine combustor wall with non-uniform distribution of effusion apertures |
US9181813B2 (en) * | 2012-07-05 | 2015-11-10 | Siemens Aktiengesellschaft | Air regulation for film cooling and emission control of combustion gas structure |
US9291123B2 (en) | 2012-07-26 | 2016-03-22 | United Technologies Corporation | Gas turbine engine exhaust duct |
DE102012213637A1 (de) * | 2012-08-02 | 2014-02-06 | Siemens Aktiengesellschaft | Brennkammerkühlung |
GB201303057D0 (en) * | 2013-02-21 | 2013-04-03 | Rolls Royce Plc | A combustion chamber |
WO2014137428A1 (en) | 2013-03-05 | 2014-09-12 | Rolls-Royce Corporation | Dual-wall impingement, convection, effusion combustor tile |
US10634351B2 (en) | 2013-04-12 | 2020-04-28 | United Technologies Corporation | Combustor panel T-junction cooling |
US9303871B2 (en) * | 2013-06-26 | 2016-04-05 | Siemens Aktiengesellschaft | Combustor assembly including a transition inlet cone in a gas turbine engine |
GB201315871D0 (en) * | 2013-09-06 | 2013-10-23 | Rolls Royce Plc | A combustion chamber arrangement |
US10808928B2 (en) * | 2013-09-12 | 2020-10-20 | Raytheon Technologies Corporation | Boss for combustor panel |
EP3047127B1 (en) | 2013-09-16 | 2021-06-23 | Raytheon Technologies Corporation | Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor |
WO2015039074A1 (en) | 2013-09-16 | 2015-03-19 | United Technologies Corporation | Controlled variation of pressure drop through effusion cooling in a double walled combustor of a gas turbine engine |
EP3052786B1 (en) | 2013-10-04 | 2019-05-15 | United Technologies Corporation | Heat shield panels with overlap joints for a turbine engine combustor |
WO2015054115A1 (en) * | 2013-10-07 | 2015-04-16 | United Technologies Corporation | Combustor wall with tapered cooling cavity |
EP3055530B1 (en) | 2013-10-07 | 2020-08-12 | United Technologies Corporation | Bonded combustor wall for a turbine engine |
EP3060847B1 (en) | 2013-10-24 | 2019-09-18 | United Technologies Corporation | Passage geometry for gas turbine engine combustor |
US10240790B2 (en) | 2013-11-04 | 2019-03-26 | United Technologies Corporation | Turbine engine combustor heat shield with multi-height rails |
EP3066390B1 (en) * | 2013-11-04 | 2020-10-21 | United Technologies Corporation | Gas turbine engine wall assembly with offset rail |
US10753608B2 (en) | 2013-11-21 | 2020-08-25 | Raytheon Technologies Corporation | Turbine engine multi-walled structure with internal cooling element(s) |
EP3071816B1 (en) | 2013-11-21 | 2019-09-18 | United Technologies Corporation | Cooling a multi-walled structure of a turbine engine |
EP3071887B1 (en) | 2013-11-22 | 2020-03-11 | United Technologies Corporation | Turbine engine multi-walled structure with cooling elements |
WO2015077755A1 (en) | 2013-11-25 | 2015-05-28 | United Technologies Corporation | Film cooled multi-walled structure with one or more indentations |
WO2015085065A1 (en) | 2013-12-05 | 2015-06-11 | United Technologies Corporation | Cooling a quench aperture body of a combustor wall |
US10697636B2 (en) | 2013-12-06 | 2020-06-30 | Raytheon Technologies Corporation | Cooling a combustor heat shield proximate a quench aperture |
WO2015084963A1 (en) | 2013-12-06 | 2015-06-11 | United Technologies Corporation | Cooling a quench aperture body of a combustor wall |
EP3077640B1 (en) | 2013-12-06 | 2021-06-02 | Raytheon Technologies Corporation | Combustor quench aperture cooling |
US10968829B2 (en) | 2013-12-06 | 2021-04-06 | Raytheon Technologies Corporation | Cooling an igniter body of a combustor wall |
DE102013226490A1 (de) * | 2013-12-18 | 2015-06-18 | Rolls-Royce Deutschland Ltd & Co Kg | Gekühlte Flanschverbindung eines Gasturbinentriebwerks |
EP3084310A4 (en) | 2013-12-19 | 2017-01-04 | United Technologies Corporation | Gas turbine engine wall assembly with circumferential rail stud architecture |
EP3099976B1 (en) * | 2014-01-30 | 2019-03-13 | United Technologies Corporation | Cooling flow for leading panel in a gas turbine engine combustor |
WO2015117137A1 (en) | 2014-02-03 | 2015-08-06 | United Technologies Corporation | Film cooling a combustor wall of a turbine engine |
WO2015117139A1 (en) | 2014-02-03 | 2015-08-06 | United Technologies Corporation | Stepped heat shield for a turbine engine combustor |
CN103968418B (zh) * | 2014-05-26 | 2015-12-30 | 西北工业大学 | 一种用于加力燃烧室的双层壁隔热屏 |
US10041675B2 (en) * | 2014-06-04 | 2018-08-07 | Pratt & Whitney Canada Corp. | Multiple ventilated rails for sealing of combustor heat shields |
EP2977679B1 (en) | 2014-07-22 | 2019-08-28 | United Technologies Corporation | Combustor wall for a gas turbine engine and method of acoustic dampening |
EP3189277B1 (en) | 2014-09-05 | 2020-04-15 | Siemens Aktiengesellschaft | Cross ignition flame duct |
US10478920B2 (en) | 2014-09-29 | 2019-11-19 | Rolls-Royce Corporation | Dual wall components for gas turbine engines |
US10077903B2 (en) * | 2014-10-20 | 2018-09-18 | United Technologies Corporation | Hybrid through holes and angled holes for combustor grommet cooling |
EP3061557B1 (en) | 2015-02-26 | 2018-04-18 | Rolls-Royce Corporation | Repair of dual walled metallic components using directed energy deposition material addition |
US10766105B2 (en) | 2015-02-26 | 2020-09-08 | Rolls-Royce Corporation | Repair of dual walled metallic components using braze material |
US10935240B2 (en) | 2015-04-23 | 2021-03-02 | Raytheon Technologies Corporation | Additive manufactured combustor heat shield |
CN104896514A (zh) * | 2015-05-13 | 2015-09-09 | 广东电网有限责任公司电力科学研究院 | 燃气轮机主燃烧室防振隔热壁 |
GB201518345D0 (en) * | 2015-10-16 | 2015-12-02 | Rolls Royce | Combustor for a gas turbine engine |
US9810434B2 (en) * | 2016-01-21 | 2017-11-07 | Siemens Energy, Inc. | Transition duct system with arcuate ceramic liner for delivering hot-temperature gases in a combustion turbine engine |
GB201603166D0 (en) * | 2016-02-24 | 2016-04-06 | Rolls Royce Plc | A combustion chamber |
US10215411B2 (en) * | 2016-03-07 | 2019-02-26 | United Technologies Corporation | Combustor panels having recessed rail |
GB201610122D0 (en) * | 2016-06-10 | 2016-07-27 | Rolls Royce Plc | A combustion chamber |
US20180073390A1 (en) * | 2016-09-13 | 2018-03-15 | Rolls-Royce Corporation | Additively deposited gas turbine engine cooling component |
US10619854B2 (en) * | 2016-11-30 | 2020-04-14 | United Technologies Corporation | Systems and methods for combustor panel |
US20180299126A1 (en) * | 2017-04-18 | 2018-10-18 | United Technologies Corporation | Combustor liner panel end rail |
US20180306113A1 (en) * | 2017-04-19 | 2018-10-25 | United Technologies Corporation | Combustor liner panel end rail matching heat transfer features |
US10830435B2 (en) | 2018-02-06 | 2020-11-10 | Raytheon Technologies Corporation | Diffusing hole for rail effusion |
US11248791B2 (en) * | 2018-02-06 | 2022-02-15 | Raytheon Technologies Corporation | Pull-plane effusion combustor panel |
US11009230B2 (en) | 2018-02-06 | 2021-05-18 | Raytheon Technologies Corporation | Undercut combustor panel rail |
US11022307B2 (en) | 2018-02-22 | 2021-06-01 | Raytheon Technology Corporation | Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling |
US10830436B2 (en) * | 2018-03-20 | 2020-11-10 | Pratt & Whitney Canada Corp. | Combustor heat shield edge cooling |
US11090771B2 (en) | 2018-11-05 | 2021-08-17 | Rolls-Royce Corporation | Dual-walled components for a gas turbine engine |
US11305363B2 (en) | 2019-02-11 | 2022-04-19 | Rolls-Royce Corporation | Repair of through-hole damage using braze sintered preform |
US11959641B2 (en) * | 2020-01-31 | 2024-04-16 | Rtx Corporation | Combustor shell with shaped impingement holes |
CN115013841B (zh) * | 2022-05-12 | 2023-10-31 | 中国航发四川燃气涡轮研究院 | 加力燃烧室双层浮动密封圆转方隔热屏结构及后排气系统 |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4748806A (en) * | 1985-07-03 | 1988-06-07 | United Technologies Corporation | Attachment means |
EP0224817B1 (de) * | 1985-12-02 | 1989-07-12 | Siemens Aktiengesellschaft | Hitzeschildanordnung, insbesondere für Strukturteile von Gasturbinenanlagen |
DE8618859U1 (de) | 1986-07-14 | 1988-01-28 | Siemens AG, 1000 Berlin und 8000 München | Hitzeschild |
US5435139A (en) | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
US5289677A (en) * | 1992-12-16 | 1994-03-01 | United Technologies Corporation | Combined support and seal ring for a combustor |
US5758503A (en) | 1995-05-03 | 1998-06-02 | United Technologies Corporation | Gas turbine combustor |
US5782294A (en) | 1995-12-18 | 1998-07-21 | United Technologies Corporation | Cooled liner apparatus |
JP3518447B2 (ja) | 1999-11-05 | 2004-04-12 | 株式会社日立製作所 | ガスタービン,ガスタービン装置およびガスタービン動翼の冷媒回収方法 |
GB9926257D0 (en) * | 1999-11-06 | 2000-01-12 | Rolls Royce Plc | Wall elements for gas turbine engine combustors |
GB2361303B (en) * | 2000-04-14 | 2004-10-20 | Rolls Royce Plc | Wall structure for a gas turbine engine combustor |
GB2373319B (en) * | 2001-03-12 | 2005-03-30 | Rolls Royce Plc | Combustion apparatus |
-
2003
- 2003-07-31 US US10/632,046 patent/US7146815B2/en active Active
-
2004
- 2004-07-27 DE DE602004024478T patent/DE602004024478D1/de active Active
- 2004-07-27 EP EP04254478A patent/EP1503144B1/en not_active Expired - Fee Related
- 2004-07-30 JP JP2004223416A patent/JP4083717B2/ja not_active Expired - Fee Related
- 2004-07-30 CN CN200410058833.XA patent/CN1580640A/zh active Pending
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010091258A (ja) * | 2008-10-03 | 2010-04-22 | General Electric Co <Ge> | 予混合直接噴射ノズル |
JP2012047443A (ja) * | 2010-08-27 | 2012-03-08 | Alstom Technology Ltd | バーナ装置を稼働させる方法及びこの方法を実施するバーナ装置 |
Also Published As
Publication number | Publication date |
---|---|
US7146815B2 (en) | 2006-12-12 |
EP1503144B1 (en) | 2009-12-09 |
CN1580640A (zh) | 2005-02-16 |
DE602004024478D1 (de) | 2010-01-21 |
EP1503144A1 (en) | 2005-02-02 |
US20050022531A1 (en) | 2005-02-03 |
JP4083717B2 (ja) | 2008-04-30 |
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