UA86568C2 - Лопатка газової турбіни з контурами охолодження - Google Patents
Лопатка газової турбіни з контурами охолодженняInfo
- Publication number
- UA86568C2 UA86568C2 UA20040706345A UA20040706345A UA86568C2 UA 86568 C2 UA86568 C2 UA 86568C2 UA 20040706345 A UA20040706345 A UA 20040706345A UA 20040706345 A UA20040706345 A UA 20040706345A UA 86568 C2 UA86568 C2 UA 86568C2
- Authority
- UA
- Ukraine
- Prior art keywords
- cavity
- side cavity
- radially
- pressure side
- suction side
- Prior art date
Links
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
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
-
- 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
-
- 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
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Лопатка (10) турбіни газотурбінного двигуна містить у своїй центральній частині перший центральний контур (А) охолодження, який має у своєму складі принаймні одну зовнішню порожнину (30), принаймні одну внутрішню порожнину (32), принаймні одну центральну порожнину (34), розташовану між зовнішньою порожниною (30) і внутрішньою порожниною (32), перший вхідний отвір, розташований на радіально нижньому краї зовнішньої порожнини, другий вхідний отвір, розташований на радіально нижньому краї внутрішньої порожнини, принаймні один перший канал, що з'єднує радіально верхній край зовнішньої порожнини (30) з радіально верхнім краєм центральної порожнини (34), принаймні один другий канал, що з'єднує радіально верхній край внутрішньої порожнини (32) з радіально верхнім краєм центральної порожнини (34), і вихідні отвори (44), які відкриваються в центральну порожнину (34) і на корито (22) лопатки.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0309535A FR2858352B1 (fr) | 2003-08-01 | 2003-08-01 | Circuit de refroidissement pour aube de turbine |
Publications (1)
Publication Number | Publication Date |
---|---|
UA86568C2 true UA86568C2 (uk) | 2009-05-12 |
Family
ID=33523050
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
UA20040706345A UA86568C2 (uk) | 2003-08-01 | 2004-07-30 | Лопатка газової турбіни з контурами охолодження |
Country Status (7)
Country | Link |
---|---|
US (1) | US7033136B2 (uk) |
EP (1) | EP1503038A1 (uk) |
JP (1) | JP4287795B2 (uk) |
CA (1) | CA2475083C (uk) |
FR (1) | FR2858352B1 (uk) |
RU (1) | RU2296225C2 (uk) |
UA (1) | UA86568C2 (uk) |
Families Citing this family (62)
Publication number | Priority date | Publication date | Assignee | Title |
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ES2312890T3 (es) * | 2004-07-26 | 2009-03-01 | Siemens Aktiengesellschaft | Elemento enfriado de una turbomaquina y procedimiento de moldeo de este elemento enfriado. |
FR2875425B1 (fr) | 2004-09-21 | 2007-03-30 | Snecma Moteurs Sa | Procede de fabrication d'une aube de turbomachine, assemblage de noyaux pour la mise en oeuvre du procede. |
US7246999B2 (en) * | 2004-10-06 | 2007-07-24 | General Electric Company | Stepped outlet turbine airfoil |
US7438527B2 (en) * | 2005-04-22 | 2008-10-21 | United Technologies Corporation | Airfoil trailing edge cooling |
FR2890103A1 (fr) * | 2005-08-25 | 2007-03-02 | Snecma | Deflecteur d'air pour circuit de refroidissement pour aube de turbine a gaz |
US7695246B2 (en) * | 2006-01-31 | 2010-04-13 | United Technologies Corporation | Microcircuits for small engines |
US20070297916A1 (en) * | 2006-06-22 | 2007-12-27 | United Technologies Corporation | Leading edge cooling using wrapped staggered-chevron trip strips |
US8690538B2 (en) * | 2006-06-22 | 2014-04-08 | United Technologies Corporation | Leading edge cooling using chevron trip strips |
US7513744B2 (en) * | 2006-07-18 | 2009-04-07 | United Technologies Corporation | Microcircuit cooling and tip blowing |
US7534089B2 (en) * | 2006-07-18 | 2009-05-19 | Siemens Energy, Inc. | Turbine airfoil with near wall multi-serpentine cooling channels |
US7780413B2 (en) * | 2006-08-01 | 2010-08-24 | Siemens Energy, Inc. | Turbine airfoil with near wall inflow chambers |
US7527475B1 (en) | 2006-08-11 | 2009-05-05 | Florida Turbine Technologies, Inc. | Turbine blade with a near-wall cooling circuit |
US20080085193A1 (en) * | 2006-10-05 | 2008-04-10 | Siemens Power Generation, Inc. | Turbine airfoil cooling system with enhanced tip corner cooling channel |
US8197184B2 (en) * | 2006-10-18 | 2012-06-12 | United Technologies Corporation | Vane with enhanced heat transfer |
US7568887B1 (en) * | 2006-11-16 | 2009-08-04 | Florida Turbine Technologies, Inc. | Turbine blade with near wall spiral flow serpentine cooling circuit |
US7717676B2 (en) | 2006-12-11 | 2010-05-18 | United Technologies Corporation | High aspect ratio blade main core modifications for peripheral serpentine microcircuits |
US7704048B2 (en) * | 2006-12-15 | 2010-04-27 | Siemens Energy, Inc. | Turbine airfoil with controlled area cooling arrangement |
US8047790B1 (en) * | 2007-01-17 | 2011-11-01 | Florida Turbine Technologies, Inc. | Near wall compartment cooled turbine blade |
US7901182B2 (en) * | 2007-05-18 | 2011-03-08 | Siemens Energy, Inc. | Near wall cooling for a highly tapered turbine blade |
US7740445B1 (en) | 2007-06-21 | 2010-06-22 | Florida Turbine Technologies, Inc. | Turbine blade with near wall cooling |
US7963745B1 (en) * | 2007-07-10 | 2011-06-21 | Florida Turbine Technologies, Inc. | Composite turbine blade |
US8376706B2 (en) * | 2007-09-28 | 2013-02-19 | General Electric Company | Turbine airfoil concave cooling passage using dual-swirl flow mechanism and method |
US20120000072A9 (en) * | 2008-09-26 | 2012-01-05 | Morrison Jay A | Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components |
US8167558B2 (en) * | 2009-01-19 | 2012-05-01 | Siemens Energy, Inc. | Modular serpentine cooling systems for turbine engine components |
US8079821B2 (en) * | 2009-05-05 | 2011-12-20 | Siemens Energy, Inc. | Turbine airfoil with dual wall formed from inner and outer layers separated by a compliant structure |
US8147196B2 (en) * | 2009-05-05 | 2012-04-03 | Siemens Energy, Inc. | Turbine airfoil with a compliant outer wall |
US8535004B2 (en) * | 2010-03-26 | 2013-09-17 | Siemens Energy, Inc. | Four-wall turbine airfoil with thermal strain control for reduced cycle fatigue |
US9011077B2 (en) | 2011-04-20 | 2015-04-21 | Siemens Energy, Inc. | Cooled airfoil in a turbine engine |
US20120315139A1 (en) * | 2011-06-10 | 2012-12-13 | General Electric Company | Cooling flow control members for turbomachine buckets and method |
FR2982903B1 (fr) * | 2011-11-17 | 2014-02-21 | Snecma | Aube de turbine a gaz a decalage vers l'intrados des sections de tete et a canaux de refroidissement |
US9200523B2 (en) * | 2012-03-14 | 2015-12-01 | Honeywell International Inc. | Turbine blade tip cooling |
US9297262B2 (en) * | 2012-05-24 | 2016-03-29 | General Electric Company | Cooling structures in the tips of turbine rotor blades |
EP2703601B8 (en) * | 2012-08-30 | 2016-09-14 | General Electric Technology GmbH | Modular Blade or Vane for a Gas Turbine and Gas Turbine with Such a Blade or Vane |
US9314838B2 (en) | 2012-09-28 | 2016-04-19 | Solar Turbines Incorporated | Method of manufacturing a cooled turbine blade with dense cooling fin array |
US9206695B2 (en) | 2012-09-28 | 2015-12-08 | Solar Turbines Incorporated | Cooled turbine blade with trailing edge flow metering |
US9228439B2 (en) | 2012-09-28 | 2016-01-05 | Solar Turbines Incorporated | Cooled turbine blade with leading edge flow redirection and diffusion |
US9482101B2 (en) | 2012-11-28 | 2016-11-01 | United Technologies Corporation | Trailing edge and tip cooling |
US8920124B2 (en) * | 2013-02-14 | 2014-12-30 | Siemens Energy, Inc. | Turbine blade with contoured chamfered squealer tip |
US10378381B2 (en) | 2013-10-24 | 2019-08-13 | United Technologies Corporation | Airfoil with skin core cooling |
FR3020402B1 (fr) * | 2014-04-24 | 2019-06-14 | Safran Aircraft Engines | Aube pour turbine de turbomachine comprenant un circuit de refroidissement a homogeneite amelioree |
FR3021697B1 (fr) * | 2014-05-28 | 2021-09-17 | Snecma | Aube de turbine a refroidissement optimise |
US9957815B2 (en) * | 2015-03-05 | 2018-05-01 | United Technologies Corporation | Gas powered turbine component including serpentine cooling |
JP6025941B1 (ja) | 2015-08-25 | 2016-11-16 | 三菱日立パワーシステムズ株式会社 | タービン動翼、及び、ガスタービン |
US10030526B2 (en) * | 2015-12-21 | 2018-07-24 | General Electric Company | Platform core feed for a multi-wall blade |
US10060269B2 (en) | 2015-12-21 | 2018-08-28 | General Electric Company | Cooling circuits for a multi-wall blade |
US10563518B2 (en) * | 2016-02-15 | 2020-02-18 | General Electric Company | Gas turbine engine trailing edge ejection holes |
FR3048718B1 (fr) * | 2016-03-10 | 2020-01-24 | Safran | Aube de turbomachine a refroidissement optimise |
US10119406B2 (en) * | 2016-05-12 | 2018-11-06 | General Electric Company | Blade with stress-reducing bulbous projection at turn opening of coolant passages |
US10267162B2 (en) * | 2016-08-18 | 2019-04-23 | General Electric Company | Platform core feed for a multi-wall blade |
CN106761951A (zh) * | 2017-01-23 | 2017-05-31 | 中国航发沈阳发动机研究所 | 一种涡轮转子叶片的前缘冷却结构及具有其的发动机 |
FR3062675B1 (fr) * | 2017-02-07 | 2021-01-15 | Safran Helicopter Engines | Aube haute pression ventilee de turbine d'helicoptere comprenant un conduit amont et une cavite centrale de refroidissement |
RU177804U1 (ru) * | 2017-10-20 | 2018-03-13 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Охлаждаемая полая лопатка турбины |
FR3079262B1 (fr) | 2018-03-23 | 2022-07-22 | Safran Helicopter Engines | Aube fixe de turbine a refroidissement par impacts de jets d'air |
KR102153064B1 (ko) * | 2018-10-22 | 2020-09-07 | 두산중공업 주식회사 | 터빈 블레이드 및 이를 포함하는 가스 터빈 |
US11377964B2 (en) | 2018-11-09 | 2022-07-05 | Raytheon Technologies Corporation | Airfoil with cooling passage network having arced leading edge |
US11788416B2 (en) * | 2019-01-30 | 2023-10-17 | Rtx Corporation | Gas turbine engine components having interlaced trip strip arrays |
JP7206129B2 (ja) * | 2019-02-26 | 2023-01-17 | 三菱重工業株式会社 | 翼及びこれを備えた機械 |
FR3099522B1 (fr) * | 2019-07-30 | 2021-08-20 | Safran Aircraft Engines | Aube mobile de turbomachine à circuit de refroidissement ayant une double rangée de fentes d’évacuation |
US11192626B2 (en) * | 2019-10-28 | 2021-12-07 | The Boeing Company | Leading edge cooling systems and methods |
KR102466386B1 (ko) | 2020-09-25 | 2022-11-10 | 두산에너빌리티 주식회사 | 터빈 블레이드 및 이를 포함하는 터빈 |
CN114215609B (zh) * | 2021-12-30 | 2023-07-04 | 华中科技大学 | 一种可强化冷却的叶片内冷通道及其应用 |
CN115341959B (zh) * | 2022-07-26 | 2023-07-21 | 南京航空航天大学 | 一种组合式叶片 |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE487558A (uk) * | 1948-03-03 | |||
GB742477A (en) * | 1952-10-31 | 1955-12-30 | Rolls Royce | Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors |
JP3006174B2 (ja) * | 1991-07-04 | 2000-02-07 | 株式会社日立製作所 | 内部に冷却通路を有する部材 |
FR2689176B1 (fr) * | 1992-03-25 | 1995-07-13 | Snecma | Aube refrigeree de turbo-machine. |
WO1998045577A1 (de) * | 1997-04-07 | 1998-10-15 | Siemens Aktiengesellschaft | Verfahren zur kühlung einer turbinenschaufel |
FR2765265B1 (fr) * | 1997-06-26 | 1999-08-20 | Snecma | Aubage refroidi par rampe helicoidale, par impact en cascade et par systeme a pontets dans une double peau |
DE59905944D1 (de) * | 1998-08-31 | 2003-07-17 | Siemens Ag | Turbinenschaufel |
US6126396A (en) * | 1998-12-09 | 2000-10-03 | General Electric Company | AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers |
GB9901218D0 (en) * | 1999-01-21 | 1999-03-10 | Rolls Royce Plc | Cooled aerofoil for a gas turbine engine |
US6174133B1 (en) * | 1999-01-25 | 2001-01-16 | General Electric Company | Coolable airfoil |
US6769866B1 (en) * | 1999-03-09 | 2004-08-03 | Siemens Aktiengesellschaft | Turbine blade and method for producing a turbine blade |
US6164913A (en) * | 1999-07-26 | 2000-12-26 | General Electric Company | Dust resistant airfoil cooling |
US6257831B1 (en) * | 1999-10-22 | 2001-07-10 | Pratt & Whitney Canada Corp. | Cast airfoil structure with openings which do not require plugging |
DE10064269A1 (de) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Komponente einer Strömungsmaschine mit Inspektionsöffnung |
US6478535B1 (en) * | 2001-05-04 | 2002-11-12 | Honeywell International, Inc. | Thin wall cooling system |
GB0114503D0 (en) * | 2001-06-14 | 2001-08-08 | Rolls Royce Plc | Air cooled aerofoil |
US6595748B2 (en) * | 2001-08-02 | 2003-07-22 | General Electric Company | Trichannel airfoil leading edge cooling |
FR2829174B1 (fr) * | 2001-08-28 | 2006-01-20 | Snecma Moteurs | Perfectionnement apportes aux circuits de refroidissement pour aube de turbine a gaz |
-
2003
- 2003-08-01 FR FR0309535A patent/FR2858352B1/fr not_active Expired - Lifetime
-
2004
- 2004-07-16 EP EP04291819A patent/EP1503038A1/fr not_active Withdrawn
- 2004-07-21 JP JP2004212949A patent/JP4287795B2/ja not_active Expired - Fee Related
- 2004-07-21 CA CA2475083A patent/CA2475083C/fr not_active Expired - Fee Related
- 2004-07-22 US US10/895,855 patent/US7033136B2/en active Active
- 2004-07-26 RU RU2004122669/06A patent/RU2296225C2/ru not_active IP Right Cessation
- 2004-07-30 UA UA20040706345A patent/UA86568C2/uk unknown
Also Published As
Publication number | Publication date |
---|---|
RU2004122669A (ru) | 2006-01-20 |
EP1503038A1 (fr) | 2005-02-02 |
CA2475083A1 (fr) | 2005-02-01 |
JP2005054776A (ja) | 2005-03-03 |
US7033136B2 (en) | 2006-04-25 |
US20050025623A1 (en) | 2005-02-03 |
FR2858352B1 (fr) | 2006-01-20 |
CA2475083C (fr) | 2011-09-13 |
RU2296225C2 (ru) | 2007-03-27 |
FR2858352A1 (fr) | 2005-02-04 |
JP4287795B2 (ja) | 2009-07-01 |
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