JP6567072B2 - 漏れ流調整装置を備えるシュラウド付きタービン翼 - Google Patents
漏れ流調整装置を備えるシュラウド付きタービン翼 Download PDFInfo
- Publication number
- JP6567072B2 JP6567072B2 JP2017548873A JP2017548873A JP6567072B2 JP 6567072 B2 JP6567072 B2 JP 6567072B2 JP 2017548873 A JP2017548873 A JP 2017548873A JP 2017548873 A JP2017548873 A JP 2017548873A JP 6567072 B2 JP6567072 B2 JP 6567072B2
- Authority
- JP
- Japan
- Prior art keywords
- downstream
- outer shroud
- leakage flow
- radially
- radially outer
- 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.)
- Active
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- 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
- F05D2260/60—Fluid transfer
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims (8)
- タービン翼(10)であって、
前縁(34)と、後縁(36)と、正圧面(38)と、該正圧面(38)と反対側の負圧面(40)と、第1の端部(44)における先端部(24)と、翼(32)を支持しかつ該翼(32)をディスクに結合するために前記第1の端部(44)と略反対側の第2の端部(48)において前記翼(32)に結合された根元部(46)とを有する、全体として細長い翼(32)と、
前記全体として細長い翼(32)の前記先端部(24)に結合された少なくとも1つの外側シュラウド(22)と、を備え、
前記少なくとも1つの外側シュラウド(22)は、ほぼ前記正圧面(38)から前記負圧面(40)に向かう方向に延びておりかつタービンエンジン内で周方向に延びており、
前記少なくとも1つの外側シュラウド(22)は、少なくとも部分的に、前記全体として細長い翼(32)の前記先端部(24)に結合された外側シュラウドベース(20)と、該外側シュラウドベース(20)から半径方向外方へ延びる外側シュラウドボディ(50)とによって形成されており、
前記外側シュラウドベース(20)は、前記外側シュラウドボディ(50)の上流に延びる上流セクション(52)と、前記外側シュラウドボディ(50)の下流に延びる下流セクション(54)とを有し、
前記外側シュラウドボディ(50)の下流に延びる前記下流セクション(54)に配置された下流漏れ流調整装置(58)を備え、
前記下流漏れ流調整装置(58)の半径方向外面(56)は、前記外側シュラウドベース(20)の前記下流セクション(54)の半径方向外面(60)よりもさらに半径方向内方に配置されており、
前記下流漏れ流調整装置(58)の前記半径方向外面(56)と前記外側シュラウドベース(20)の前記下流セクション(54)の前記半径方向外面(60)との間の交差部(68)は、前記全体として細長い翼(32)が配置されるように構成されているタービンエンジンの長手方向軸線(62)に対して非平行かつ非直交であり、
前記下流漏れ流調整装置(58)の前記半径方向外面(56)と前記外側シュラウドベース(20)の前記下流セクション(54)の前記半径方向外面(60)との間の前記交差部(68)は、半径方向外方へ延びる壁面(30)から形成されており、
前記下流漏れ流調整装置(58)の前記半径方向外面(56)は、遠位エッジ(76)が、前記下流漏れ流調整装置(58)と前記外側シュラウドベース(20)の前記下流セクション(54)の前記半径方向外面(60)との間の、半径方向外方へ延びる壁面(30)における近位エッジ(78)よりも、半径方向でさらに外方に配置されるように、傾斜している
ことを特徴とする、タービン翼(10)。 - 前記下流漏れ流調整装置(58)は、前記外側シュラウドボディ(50)から前記外側シュラウドベース(20)の下流エッジ(84)まで延びていることを特徴とする、請求項1記載のタービン翼(10)。
- 前記下流漏れ流調整装置(58)の半径方向外面(56)と前記外側シュラウドベース(20)の前記下流セクション(54)の前記半径方向外面(60)との間の前記交差部(68)は、前記全体として細長い翼(32)と前記少なくとも1つの外側シュラウド(22)との交差部(70)において前記全体として細長い翼(32)の前記正圧面(38)とほぼ整列していることを特徴とする、請求項1または2記載のタービン翼(10)。
- 前記半径方向外方へ延びる壁面(30)は、前記外側シュラウドベース(20)の前記下流セクション(54)の前記半径方向外面(60)との交差部に斜面(72)を有し、前記下流漏れ流調整装置(58)の前記半径方向外面(56)との交差部(68)に斜面(74)を有することを特徴とする、請求項1から3までのいずれか1項記載のタービン翼(10)。
- 前記下流漏れ流調整装置(58)の前記半径方向外面(56)から半径方向外方へ延びる少なくとも1つの補強レール(80)をさらに備えることを特徴とする、請求項1から4までのいずれか1項記載のタービン翼(10)。
- 前記少なくとも1つの補強レール(80)の半径方向外側の遠位端部(82)は、前記外側シュラウドベース(20)の前記下流セクション(54)の前記半径方向外面(60)よりもさらに半径方向内方に配置されていることを特徴とする、請求項5記載のタービン翼(10)。
- 前記少なくとも1つの補強レール(80)の前記半径方向外側の遠位端部(82)は、線形の面であることを特徴とする、請求項6記載のタービン翼(10)。
- 前記少なくとも1つの補強レール(80)は、前記外側シュラウドボディ(50)から前記外側シュラウドベース(20)の下流エッジ(84)まで延びていることを特徴とする、請求項6記載のタービン翼(10)。
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2015/020907 WO2016148694A1 (en) | 2015-03-17 | 2015-03-17 | Shrouded turbine airfoil with leakage flow conditioner |
Publications (2)
Publication Number | Publication Date |
---|---|
JP2018513297A JP2018513297A (ja) | 2018-05-24 |
JP6567072B2 true JP6567072B2 (ja) | 2019-08-28 |
Family
ID=52808154
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP2017548873A Active JP6567072B2 (ja) | 2015-03-17 | 2015-03-17 | 漏れ流調整装置を備えるシュラウド付きタービン翼 |
Country Status (5)
Country | Link |
---|---|
US (1) | US10053993B2 (ja) |
EP (1) | EP3271555B1 (ja) |
JP (1) | JP6567072B2 (ja) |
CN (1) | CN107407153B (ja) |
WO (1) | WO2016148694A1 (ja) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102018215728A1 (de) * | 2018-09-17 | 2020-03-19 | MTU Aero Engines AG | Gasturbinen-Laufschaufel |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
JP2001055902A (ja) * | 1999-08-18 | 2001-02-27 | Toshiba Corp | タービン動翼 |
US6354795B1 (en) | 2000-07-27 | 2002-03-12 | General Electric Company | Shroud cooling segment and assembly |
US6379528B1 (en) | 2000-12-12 | 2002-04-30 | General Electric Company | Electrochemical machining process for forming surface roughness elements on a gas turbine shroud |
US6491498B1 (en) * | 2001-10-04 | 2002-12-10 | Power Systems Mfg, Llc. | Turbine blade pocket shroud |
US6679681B2 (en) * | 2002-04-10 | 2004-01-20 | General Electric Company | Flush tenon cover for steam turbine blades with advanced sealing |
US7396205B2 (en) * | 2004-01-31 | 2008-07-08 | United Technologies Corporation | Rotor blade for a rotary machine |
US7097428B2 (en) * | 2004-06-23 | 2006-08-29 | General Electric Company | Integral cover bucket design |
US7387488B2 (en) | 2005-08-05 | 2008-06-17 | General Electric Company | Cooled turbine shroud |
US7452183B2 (en) | 2005-08-06 | 2008-11-18 | General Electric Company | Thermally compliant turbine shroud assembly |
US7438520B2 (en) | 2005-08-06 | 2008-10-21 | General Electric Company | Thermally compliant turbine shroud mounting assembly |
US7448846B2 (en) | 2005-08-06 | 2008-11-11 | General Electric Company | Thermally compliant turbine shroud mounting |
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 |
US7604453B2 (en) | 2006-11-30 | 2009-10-20 | General Electric Company | Methods and system for recuperated circumferential cooling of integral turbine nozzle and shroud assemblies |
US7690885B2 (en) | 2006-11-30 | 2010-04-06 | General Electric Company | Methods and system for shielding cooling air to facilitate cooling 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 |
US20100034647A1 (en) | 2006-12-07 | 2010-02-11 | General Electric Company | Processes for the formation of positive features on shroud components, and related articles |
FR2923524B1 (fr) * | 2007-11-12 | 2013-12-06 | Snecma | Aube metallique fabriquee par moulage et procede de fabrication de l'aube |
US8104292B2 (en) | 2007-12-17 | 2012-01-31 | General Electric Company | Duplex turbine shroud |
US8147192B2 (en) | 2008-09-19 | 2012-04-03 | General Electric Company | Dual stage turbine shroud |
US20120051930A1 (en) | 2010-08-31 | 2012-03-01 | General Electric Company | Shrouded turbine blade with contoured platform and axial dovetail |
FR2970999B1 (fr) * | 2011-02-02 | 2015-03-06 | Snecma | Aubes de turbomachine en cmc, roue mobile de turbomachine et turbomachine les comportant et procede pour leur fabrication |
US8721291B2 (en) | 2011-07-12 | 2014-05-13 | Siemens Energy, Inc. | Flow directing member for gas turbine engine |
US8864452B2 (en) | 2011-07-12 | 2014-10-21 | Siemens Energy, Inc. | Flow directing member for gas turbine engine |
US9109455B2 (en) * | 2012-01-20 | 2015-08-18 | General Electric Company | Turbomachine blade tip shroud |
US9683446B2 (en) * | 2013-03-07 | 2017-06-20 | Rolls-Royce Energy Systems, Inc. | Gas turbine engine shrouded blade |
-
2015
- 2015-03-17 WO PCT/US2015/020907 patent/WO2016148694A1/en active Application Filing
- 2015-03-17 CN CN201580077841.5A patent/CN107407153B/zh active Active
- 2015-03-17 JP JP2017548873A patent/JP6567072B2/ja active Active
- 2015-03-17 US US15/552,982 patent/US10053993B2/en active Active
- 2015-03-17 EP EP15714096.3A patent/EP3271555B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20180030838A1 (en) | 2018-02-01 |
JP2018513297A (ja) | 2018-05-24 |
CN107407153A (zh) | 2017-11-28 |
EP3271555A1 (en) | 2018-01-24 |
EP3271555B1 (en) | 2019-10-09 |
CN107407153B (zh) | 2019-09-27 |
US10053993B2 (en) | 2018-08-21 |
WO2016148694A1 (en) | 2016-09-22 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10577955B2 (en) | Airfoil assembly with a scalloped flow surface | |
JP6461382B2 (ja) | シュラウド付きタービンブレード | |
EP3015650A1 (en) | Gas turbine engine component with converging/diverging cooling passage | |
EP3093436A1 (en) | Blade/disk dovetail backcut for blade/disk stress reduction for a second stage of a turbomachine | |
EP3216999A1 (en) | Gas turbine engine with an offtake | |
KR102403377B1 (ko) | 배기 디퓨저 | |
US9494043B1 (en) | Turbine blade having contoured tip shroud | |
US11274563B2 (en) | Turbine rear frame for a turbine engine | |
US10844739B2 (en) | Platforms with leading edge features | |
CN111828098B (zh) | 具有后缘的涡轮发动机翼型件及其冷却方法 | |
JP6567072B2 (ja) | 漏れ流調整装置を備えるシュラウド付きタービン翼 | |
US10876411B2 (en) | Non-axisymmetric end wall contouring with forward mid-passage peak | |
US10473118B2 (en) | Controlled convergence compressor flowpath for a gas turbine engine | |
US11959393B2 (en) | Turbine engine with reduced cross flow airfoils | |
US8784050B2 (en) | Aggregate vane assembly | |
US10344604B2 (en) | Turbomachine diffuser including flow mixing lobes and method | |
US20240018874A1 (en) | Rotor blade and rotor blade assembly for a turbomachine | |
EP3611346A1 (en) | Diffuser having platform vanes | |
EP2299057A1 (en) | Gas Turbine | |
WO2016148691A1 (en) | Shrouded turbine airfoil with knife edge seal |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20171114 |
|
A621 | Written request for application examination |
Free format text: JAPANESE INTERMEDIATE CODE: A621 Effective date: 20171114 |
|
A977 | Report on retrieval |
Free format text: JAPANESE INTERMEDIATE CODE: A971007 Effective date: 20180914 |
|
A131 | Notification of reasons for refusal |
Free format text: JAPANESE INTERMEDIATE CODE: A131 Effective date: 20181001 |
|
A601 | Written request for extension of time |
Free format text: JAPANESE INTERMEDIATE CODE: A601 Effective date: 20181226 |
|
A521 | Request for written amendment filed |
Free format text: JAPANESE INTERMEDIATE CODE: A523 Effective date: 20190301 |
|
TRDD | Decision of grant or rejection written | ||
A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 20190701 |
|
A61 | First payment of annual fees (during grant procedure) |
Free format text: JAPANESE INTERMEDIATE CODE: A61 Effective date: 20190730 |
|
R150 | Certificate of patent or registration of utility model |
Ref document number: 6567072 Country of ref document: JP 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 |