JP4731156B2 - タービンシュラウドの非対称冷却要素 - Google Patents
タービンシュラウドの非対称冷却要素 Download PDFInfo
- Publication number
- JP4731156B2 JP4731156B2 JP2004337529A JP2004337529A JP4731156B2 JP 4731156 B2 JP4731156 B2 JP 4731156B2 JP 2004337529 A JP2004337529 A JP 2004337529A JP 2004337529 A JP2004337529 A JP 2004337529A JP 4731156 B2 JP4731156 B2 JP 4731156B2
- Authority
- JP
- Japan
- Prior art keywords
- cooling
- opening
- shroud
- symmetrical
- impingement
- 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
Links
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S165/00—Heat exchange
- Y10S165/908—Fluid jets
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
9 エンジン中心軸線
10 タービンシュラウド組立体
12 タービンブレード
14 タービンノズル
16 ベーン
18 外側バンド
22 円弧形シュラウドセグメント
24 円弧形ハンガセグメント
25 タービンシュラウド組立体非対称冷却要素
26 外側ケーシング
44 シュラウドセグメントの基体
52 シュラウドセグメント空洞
68 バッフル
72 バッフルプレナム
74 ノズルプレナム
76 調量孔
78 インピンジメント冷却開口
80 対流冷却開口
81 シュラウドセグメント基体の半径方向外側背面
89 シュラウドセグメント基体の半径方向内側正面
102 回転軸線
120 開口入口
137 開口出口
138 シュラウドチャンバ
Claims (8)
- 回転軸線(102)の周りを囲みかつ軸方向に間隔を置いて配置された対向する前端部及び後端部(104及び106)を有する円弧形パネル(100)と、
前記パネル(100)を貫通する複数の冷却開口(78及び80)と、
前記回転軸線(102)と平行な、前記パネル(100)の軸方向中線(112)と、
前記軸方向中線(112)に対して対称である対称密度の開口入口(120)を有する、前記冷却開口(78及び80)の対称部分(110)と、
前記軸方向中線(112)に対して非対称である非対称密度の開口入口(120)を有する、前記冷却開口(78及び80)の非対称部分(116)と、
前記円弧形パネル(100)の上流側のタービンノズルからの圧力ウェイクにより形成される、該円弧形パネルにおけるウェイク領域(134)内に設置された前記冷却開口(78及び80)の高い密度区域(130)と
を含むことを特徴とする、タービンシュラウド組立体冷却要素(25)。 - 前記冷却開口(78及び80)の非対称部分(116)内に冷却開口(78及び80)の高い密度区域(130)をさらに含み、前記高い密度区域(130)が、前記冷却開口(78及び80)の対称部分(110)におけるよりも高い密度の開口入口(120)を有する、請求項1記載の冷却要素(25)。
- 前記冷却開口(78及び80)の非対称部分(116)内に冷却開口(78及び80)の低い密度区域(132)をさらに含み、前記低い密度区域(132)が、前記冷却開口(78及び80)の対称部分(110)におけるよりも低い密度の開口入口(120)を有する、請求項2記載の冷却要素(25)。
- 前記冷却要素(25)がバッフル(68)であり、また前記冷却開口がインピンジメント開口(78)である、請求項1ないし請求項3のいずれか一項記載の冷却要素(25)。
- 前記冷却要素(25)がシュラウドセグメント(22)であり、前記円弧形パネル(100)が基体(44)であり、また前記冷却開口が対流冷却開口(80)である、請求項1記載の冷却要素(25)。
- エンジン中心軸線(9)の周りに円周方向に配置され、その各々が半径方向外側背面(81)と半径方向内側正面(89)と軸方向に間隔を置いて配置された対向する上流及び下流端部(104及び106)とを有する基体(44)を含む、複数の円弧形シュラウドセグメント(22)と、
前記背面(81)に対流開口入口(120)を備えまた前記半径方向内側正面(89)に開口出口(137)を備えた状態で前記基体(44)を貫通する複数の傾斜した細長い対流冷却開口(80)と、
前記シュラウドセグメント(22)を支持し、かつガスタービンエンジン外側ケーシング(26)に固定された複数の円弧形ハンガセグメント(24)と、
前記ハンガセグメント(24)及び基体(44)の各々の半径方向間に配置されたシュラウドチャンバ(138)と、
前記ハンガセグメント(24)及び基体(44)の各々の半径方向間で前記シュラウドチャンバ(138)内に配置され、かつ前記シュラウドチャンバ(138)内でその半径方向外側にバッフルプレナム(72)を画成した鍋形状バッフル(68)と、
前記ハンガセグメント(24)の各々を貫通して配置され、前記バッフルプレナム(72)に至る少なくとも1つの調量孔(76)と、
前記基体(44)とほぼ同心に該基体から半径方向に間隔を置いて配置された前記バッフル(68)のパネル(100)を貫通しかつほぼ前記基体(44)に向けて配向されたインピンジメント開口入口(120)を有する、複数のインピンジメント開口(78)と、
前記エンジン中心軸線(9)と平行になっている、前記パネル(100)及び基体(44)の平行な軸方向中線(112)と、
前記軸方向中線(112)に対して対称である対称密度の開口入口(120)を有する、前記冷却開口(78及び80)の対称部分(110)と、
前記軸方向中線(112)に対して非対称である非対称密度の開口入口(120)を有する、前記冷却開口(78及び80)の非対称部分(116)と、
前記円弧形パネル(100)の上流側のタービンノズルからの圧力ウェイクにより形成される、該円弧形パネルのウェイク領域(134)内に設置された前記冷却開口(78及び80)の高い密度区域(130)と
を含むことを特徴とする、タービンシュラウド組立体(10)。 - 前記インピンジメント開口(78)の非対称部分(116)内にインピンジメント開口(78)の高い密度区域(130)をさらに含み、前記高い密度区域(130)が、前記インピンジメント開口(78)の対称部分(110)におけるよりも高い密度の開口入口(120)を有する、請求項6記載の組立体(10)。
- 前記インピンジメント開口(78)の非対称部分(116)内にインピンジメント開口(78)の低い密度区域(132)をさらに含み、前記低い密度区域(132)が、前記インピンジメント開口(78)の対称部分(110)におけるよりも低い密度の開口入口(120)を有する、請求項7記載の組立体(10)。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/720,430 | 2003-11-24 | ||
US10/720,430 US7147432B2 (en) | 2003-11-24 | 2003-11-24 | Turbine shroud asymmetrical cooling elements |
Publications (3)
Publication Number | Publication Date |
---|---|
JP2005155626A JP2005155626A (ja) | 2005-06-16 |
JP2005155626A5 JP2005155626A5 (ja) | 2010-10-07 |
JP4731156B2 true JP4731156B2 (ja) | 2011-07-20 |
Family
ID=34435822
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2004337529A Expired - Fee Related JP4731156B2 (ja) | 2003-11-24 | 2004-11-22 | タービンシュラウドの非対称冷却要素 |
Country Status (4)
Country | Link |
---|---|
US (1) | US7147432B2 (ja) |
EP (1) | EP1533478A3 (ja) |
JP (1) | JP4731156B2 (ja) |
CN (1) | CN100507234C (ja) |
Families Citing this family (78)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7296966B2 (en) * | 2004-12-20 | 2007-11-20 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
US7438520B2 (en) * | 2005-08-06 | 2008-10-21 | General Electric Company | Thermally compliant turbine shroud mounting assembly |
US7296967B2 (en) * | 2005-09-13 | 2007-11-20 | General Electric Company | Counterflow film cooled wall |
FR2891862B1 (fr) * | 2005-10-12 | 2011-02-25 | Snecma | Plaque perforee a disposer dans une cavite de refroidissement d'anneau de turbine |
US7607885B2 (en) * | 2006-07-31 | 2009-10-27 | General Electric Company | Methods and apparatus for operating gas turbine engines |
FR2907841B1 (fr) * | 2006-10-30 | 2011-04-15 | Snecma | Secteur d'anneau de turbine de turbomachine |
US7611324B2 (en) * | 2006-11-30 | 2009-11-03 | General Electric Company | Method and system to facilitate enhanced local cooling of turbine engines |
US7740442B2 (en) * | 2006-11-30 | 2010-06-22 | General Electric Company | Methods and system for cooling integral turbine nozzle and shroud assemblies |
US7665953B2 (en) * | 2006-11-30 | 2010-02-23 | General Electric Company | Methods and system for recuperated cooling of integral turbine nozzle and shroud assemblies |
US7722315B2 (en) * | 2006-11-30 | 2010-05-25 | General Electric Company | Method and system to facilitate preferentially distributed recuperated film cooling of turbine shroud assembly |
GB2444501B (en) * | 2006-12-06 | 2009-01-28 | Siemens Ag | A gas turbine |
US7836703B2 (en) * | 2007-06-20 | 2010-11-23 | General Electric Company | Reciprocal cooled turbine nozzle |
US8393855B2 (en) * | 2007-06-29 | 2013-03-12 | General Electric Company | Flange with axially curved impingement surface for gas turbine engine clearance control |
US8197186B2 (en) * | 2007-06-29 | 2012-06-12 | General Electric Company | Flange with axially extending holes for gas turbine engine clearance control |
US20090053045A1 (en) * | 2007-08-22 | 2009-02-26 | General Electric Company | Turbine Shroud for Gas Turbine Assemblies and Processes for Forming the Shroud |
US8281604B2 (en) * | 2007-12-17 | 2012-10-09 | General Electric Company | Divergent turbine nozzle |
US8104292B2 (en) * | 2007-12-17 | 2012-01-31 | General Electric Company | Duplex turbine shroud |
US8205458B2 (en) * | 2007-12-31 | 2012-06-26 | General Electric Company | Duplex turbine nozzle |
US8439639B2 (en) | 2008-02-24 | 2013-05-14 | United Technologies Corporation | Filter system for blade outer air seal |
US8147192B2 (en) * | 2008-09-19 | 2012-04-03 | General Electric Company | Dual stage turbine shroud |
DE102008052409A1 (de) * | 2008-10-21 | 2010-04-22 | Rolls-Royce Deutschland Ltd & Co Kg | Strömungsarbeitsmaschine mit saugseitennaher Randenergetisierung |
ES2398727T3 (es) * | 2009-03-09 | 2013-03-21 | Snecma | Conjunto de anillo de turbina |
US8677763B2 (en) * | 2009-03-10 | 2014-03-25 | General Electric Company | Method and apparatus for gas turbine engine temperature management |
FR2957093B1 (fr) | 2010-03-02 | 2012-03-23 | Snecma | Preforme fibreuse pour un secteur d'anneau de turbine et son procede de fabrication. |
US8371800B2 (en) * | 2010-03-03 | 2013-02-12 | General Electric Company | Cooling gas turbine components with seal slot channels |
US10337404B2 (en) * | 2010-03-08 | 2019-07-02 | General Electric Company | Preferential cooling of gas turbine nozzles |
US8550778B2 (en) * | 2010-04-20 | 2013-10-08 | Mitsubishi Heavy Industries, Ltd. | Cooling system of ring segment and gas turbine |
WO2011132217A1 (ja) * | 2010-04-20 | 2011-10-27 | 三菱重工業株式会社 | 分割環冷却構造およびガスタービン |
GB201014802D0 (en) * | 2010-09-07 | 2010-10-20 | Rolls Royce Plc | Turbine stage shroud segment |
US9458855B2 (en) * | 2010-12-30 | 2016-10-04 | Rolls-Royce North American Technologies Inc. | Compressor tip clearance control and gas turbine engine |
US8887508B2 (en) * | 2011-03-15 | 2014-11-18 | General Electric Company | Impingement sleeve and methods for designing and forming impingement sleeve |
US8826668B2 (en) * | 2011-08-02 | 2014-09-09 | Siemens Energy, Inc. | Two stage serial impingement cooling for isogrid structures |
US9726043B2 (en) | 2011-12-15 | 2017-08-08 | General Electric Company | Mounting apparatus for low-ductility turbine shroud |
US9039350B2 (en) * | 2012-01-09 | 2015-05-26 | General Electric Company | Impingement cooling system for use with contoured surfaces |
US9403600B2 (en) | 2012-05-01 | 2016-08-02 | Lockheed Martin Corporation | Integrated thermal protection and leakage reduction in a supersonic air intake system |
US20130340966A1 (en) | 2012-06-21 | 2013-12-26 | United Technologies Corporation | Blade outer air seal hybrid casting core |
EP2716787A1 (en) | 2012-10-05 | 2014-04-09 | Siemens Aktiengesellschaft | Method for manufacturing a turbine assembly |
US9422824B2 (en) * | 2012-10-18 | 2016-08-23 | General Electric Company | Gas turbine thermal control and related method |
JP5518235B2 (ja) * | 2013-05-10 | 2014-06-11 | 三菱重工業株式会社 | 分割環冷却構造およびガスタービン |
GB201308603D0 (en) * | 2013-05-14 | 2013-06-19 | Rolls Royce Plc | A Shroud Arrangement for a Gas Turbine Engine |
CN105612313B (zh) | 2013-05-17 | 2017-11-21 | 通用电气公司 | 燃气涡轮机的cmc护罩支撑系统 |
GB201311333D0 (en) | 2013-06-26 | 2013-08-14 | Rolls Royce Plc | Component for use in releasing a flow of material into an environment subject to periodic fluctuations in pressure |
JP6529013B2 (ja) | 2013-12-12 | 2019-06-12 | ゼネラル・エレクトリック・カンパニイ | Cmcシュラウド支持システム |
US9657642B2 (en) * | 2014-03-27 | 2017-05-23 | Honeywell International Inc. | Turbine sections of gas turbine engines with dual use of cooling air |
JP6466647B2 (ja) * | 2014-03-27 | 2019-02-06 | 三菱日立パワーシステムズ株式会社 | ガスタービンの分割環の冷却構造及びこれを有するガスタービン |
EP3155236A1 (en) | 2014-06-12 | 2017-04-19 | General Electric Company | Shroud hanger assembly |
JP6574208B2 (ja) | 2014-06-12 | 2019-09-11 | ゼネラル・エレクトリック・カンパニイ | シュラウドハンガアセンブリ |
EP3155231B1 (en) | 2014-06-12 | 2019-07-03 | General Electric Company | Shroud hanger assembly |
JP5676040B1 (ja) * | 2014-06-30 | 2015-02-25 | 三菱日立パワーシステムズ株式会社 | 静翼、これを備えているガスタービン、静翼の製造方法、及び静翼の改造方法 |
FR3024884B1 (fr) * | 2014-08-14 | 2019-07-05 | Safran Aircraft Engines | Procede de realisation d'un anneau sectorise d'etancheite et d'une turbine de turbomachine |
WO2016028310A1 (en) | 2014-08-22 | 2016-02-25 | Siemens Aktiengesellschaft | Shroud cooling system for shrouds adjacent to airfoils within gas turbine engines |
GB201417150D0 (en) | 2014-09-29 | 2014-11-12 | Rolls Royce Plc | Carriers for turbine components |
EP3034803A1 (en) * | 2014-12-16 | 2016-06-22 | Rolls-Royce Corporation | Hanger system for a turbine engine component |
US10018068B2 (en) * | 2015-01-13 | 2018-07-10 | United Technologies Corporation | Blade outer air seal with cooling holes |
US9874104B2 (en) | 2015-02-27 | 2018-01-23 | General Electric Company | Method and system for a ceramic matrix composite shroud hanger assembly |
WO2016152573A1 (ja) | 2015-03-26 | 2016-09-29 | 三菱日立パワーシステムズ株式会社 | 翼、及びこれを備えているガスタービン |
US20170198602A1 (en) * | 2016-01-11 | 2017-07-13 | General Electric Company | Gas turbine engine with a cooled nozzle segment |
RU2706210C2 (ru) | 2016-01-25 | 2019-11-14 | Ансалдо Энерджиа Свитзерлэнд Аг | Тепловой экран статора для газовой турбины, газовая турбина с таким тепловым экраном статора и способ охлаждения теплового экрана статора |
EP3232002A1 (en) * | 2016-04-11 | 2017-10-18 | Rolls-Royce Corporation | Impingement plate with stress relief feature |
CN106246238A (zh) * | 2016-07-25 | 2016-12-21 | 西北工业大学 | 一种台阶型收缩气膜孔结构 |
GB2559739A (en) * | 2017-02-15 | 2018-08-22 | Rolls Royce Plc | Stator vane section |
US10677084B2 (en) * | 2017-06-16 | 2020-06-09 | Honeywell International Inc. | Turbine tip shroud assembly with plural shroud segments having inter-segment seal arrangement |
US10900378B2 (en) | 2017-06-16 | 2021-01-26 | Honeywell International Inc. | Turbine tip shroud assembly with plural shroud segments having internal cooling passages |
FR3072711B1 (fr) * | 2017-10-19 | 2021-07-16 | Safran Aircraft Engines | Element de repartition d'un fluide de refroidissement et ensemble d'anneau de turbine associe |
US10619504B2 (en) | 2017-10-31 | 2020-04-14 | United Technologies Corporation | Gas turbine engine blade outer air seal cooling hole configuration |
US10533454B2 (en) | 2017-12-13 | 2020-01-14 | Pratt & Whitney Canada Corp. | Turbine shroud cooling |
US10502093B2 (en) * | 2017-12-13 | 2019-12-10 | Pratt & Whitney Canada Corp. | Turbine shroud cooling |
US10570773B2 (en) | 2017-12-13 | 2020-02-25 | Pratt & Whitney Canada Corp. | Turbine shroud cooling |
US10738637B2 (en) | 2017-12-22 | 2020-08-11 | Raytheon Technologies Corporation | Airflow deflector and assembly |
JP7065941B2 (ja) * | 2018-03-07 | 2022-05-12 | 川崎重工業株式会社 | ガスタービンのシュラウド取付構造、シュラウド集合体及びシュラウド要素 |
US10941709B2 (en) * | 2018-09-28 | 2021-03-09 | Pratt & Whitney Canada Corp. | Gas turbine engine and cooling air configuration for turbine section thereof |
JP6508499B1 (ja) * | 2018-10-18 | 2019-05-08 | 三菱日立パワーシステムズ株式会社 | ガスタービン静翼、これを備えているガスタービン、及びガスタービン静翼の製造方法 |
US10830050B2 (en) | 2019-01-31 | 2020-11-10 | General Electric Company | Unitary body turbine shrouds including structural breakdown and collapsible features |
US10927694B2 (en) * | 2019-03-13 | 2021-02-23 | Raytheon Technologies Corporation | BOAS carrier with cooling supply |
US11047250B2 (en) * | 2019-04-05 | 2021-06-29 | Raytheon Technologies Corporation | CMC BOAS transverse hook arrangement |
FR3096395B1 (fr) * | 2019-05-21 | 2021-04-23 | Safran Aircraft Engines | Turbine pour une turbomachine, telle qu’un turboréacteur ou un turbopropulseur d’avion |
US11525401B2 (en) | 2021-01-11 | 2022-12-13 | Honeywell International Inc. | Impingement baffle for gas turbine engine |
KR102510535B1 (ko) * | 2021-02-23 | 2023-03-15 | 두산에너빌리티 주식회사 | 링 세그먼트 및 이를 포함하는 터보머신 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0587339A (ja) * | 1991-05-03 | 1993-04-06 | General Electric Co <Ge> | 燃焼器ライナ |
JPH05141270A (ja) * | 1991-05-20 | 1993-06-08 | General Electric Co <Ge> | シユラウド冷却集成体 |
JPH06173706A (ja) * | 1992-12-08 | 1994-06-21 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンエンジンのシュラウドハウジング構造 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4693667A (en) * | 1980-04-29 | 1987-09-15 | Teledyne Industries, Inc. | Turbine inlet nozzle with cooling means |
US5167487A (en) * | 1991-03-11 | 1992-12-01 | General Electric Company | Cooled shroud support |
US5165847A (en) * | 1991-05-20 | 1992-11-24 | General Electric Company | Tapered enlargement metering inlet channel for a shroud cooling assembly of gas turbine engines |
US5759012A (en) * | 1996-12-13 | 1998-06-02 | Caterpillar Inc. | Turbine disc ingress prevention method and apparatus |
US6205789B1 (en) * | 1998-11-13 | 2001-03-27 | General Electric Company | Multi-hole film cooled combuster liner |
US6155778A (en) * | 1998-12-30 | 2000-12-05 | General Electric Company | Recessed turbine shroud |
US6196792B1 (en) * | 1999-01-29 | 2001-03-06 | General Electric Company | Preferentially cooled turbine shroud |
US6354795B1 (en) * | 2000-07-27 | 2002-03-12 | General Electric Company | Shroud cooling segment and assembly |
FR2832178B1 (fr) * | 2001-11-15 | 2004-07-09 | Snecma Moteurs | Dispositif de refroidissement pour anneaux de turbine a gaz |
-
2003
- 2003-11-24 US US10/720,430 patent/US7147432B2/en active Active
-
2004
- 2004-11-22 JP JP2004337529A patent/JP4731156B2/ja not_active Expired - Fee Related
- 2004-11-24 CN CNB2004101023238A patent/CN100507234C/zh active Active
- 2004-11-24 EP EP04257275A patent/EP1533478A3/en not_active Withdrawn
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH0587339A (ja) * | 1991-05-03 | 1993-04-06 | General Electric Co <Ge> | 燃焼器ライナ |
JPH05141270A (ja) * | 1991-05-20 | 1993-06-08 | General Electric Co <Ge> | シユラウド冷却集成体 |
JPH06173706A (ja) * | 1992-12-08 | 1994-06-21 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンエンジンのシュラウドハウジング構造 |
Also Published As
Publication number | Publication date |
---|---|
JP2005155626A (ja) | 2005-06-16 |
US7147432B2 (en) | 2006-12-12 |
EP1533478A2 (en) | 2005-05-25 |
EP1533478A3 (en) | 2012-11-07 |
CN100507234C (zh) | 2009-07-01 |
US20050111965A1 (en) | 2005-05-26 |
CN1644891A (zh) | 2005-07-27 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
JP4731156B2 (ja) | タービンシュラウドの非対称冷却要素 | |
JP2005155626A5 (ja) | ||
JP4486201B2 (ja) | 優先冷却タービンシュラウド | |
JP6266231B2 (ja) | タービンロータブレード先端における冷却構造 | |
US6183192B1 (en) | Durable turbine nozzle | |
US8087249B2 (en) | Turbine cooling air from a centrifugal compressor | |
CA2700019C (en) | Flange cooled turbine nozzle | |
JP5345310B2 (ja) | タービンエンジンの冷却を促進するシステム及びガスタービンエンジン | |
JP4975990B2 (ja) | ロータ組立体の先端間隙を維持するための方法及び装置 | |
JP4641916B2 (ja) | 隅部が冷却されるタービンノズル | |
JP6031116B2 (ja) | ガスタービンエンジン用の非対称半径方向スプラインシール | |
US7165937B2 (en) | Methods and apparatus for maintaining rotor assembly tip clearances | |
JP2004060656A (ja) | 低圧タービンケースの内部冷却 | |
US20120057968A1 (en) | Ring segment with serpentine cooling passages | |
JP5546148B2 (ja) | ハイブリッド衝突冷却式タービンノズル | |
CA2941225A1 (en) | Stator component cooling | |
JP2009156261A (ja) | マルチソース型ガスタービン冷却 | |
JP2004526893A (ja) | ガスタービンエンジンのブレード先端を冷却するための方法及び装置 | |
JP2012013080A (ja) | ガスタービンエンジンに用いるロータ組立体、およびそれを組み立てる方法 | |
JP2011522158A (ja) | 調量冷却空洞を備えたタービン翼形部 | |
US20180142564A1 (en) | Combined turbine nozzle and shroud deflection limiter | |
JP2009209936A (ja) | 一体型衝突ブランケットを備えたタービンノズル | |
EP3461995B1 (en) | Gas turbine blade | |
JP2010084766A (ja) | ガスタービンエンジン用タービンノズル | |
CA1183695A (en) | Efficiently cooled transition duct for a large plant combustion turbine |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20071121 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20100223 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20100511 |
|
RD02 | Notification of acceptance of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7422 Effective date: 20100511 |
|
RD04 | Notification of resignation of power of attorney |
Free format text: JAPANESE INTERMEDIATE CODE: A7424 Effective date: 20100511 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20100514 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20100622 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20100625 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20100722 |
|
A602 | Written permission of extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A602 Effective date: 20100727 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20100818 |
|
A524 | Written submission of copy of amendment under section 19 (pct) |
Free format text: JAPANESE INTERMEDIATE CODE: A524 Effective date: 20100818 |
|
A02 | Decision of refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A02 Effective date: 20101012 |
|
A521 | Written amendment |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20110210 |
|
A911 | Transfer of reconsideration by examiner before appeal (zenchi) |
Free format text: JAPANESE INTERMEDIATE CODE: A911 Effective date: 20110223 |
|
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20110322 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20110419 |
|
FPAY | Renewal fee payment (event date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20140428 Year of fee payment: 3 |
|
R150 | Certificate of patent or registration of utility model |
Free format text: JAPANESE INTERMEDIATE CODE: R150 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
R250 | Receipt of annual fees |
Free format text: JAPANESE INTERMEDIATE CODE: R250 |
|
LAPS | Cancellation because of no payment of annual fees |