EP1191189A1 - Aube de turbine à gaz - Google Patents

Aube de turbine à gaz Download PDF

Info

Publication number
EP1191189A1
EP1191189A1 EP00120926A EP00120926A EP1191189A1 EP 1191189 A1 EP1191189 A1 EP 1191189A1 EP 00120926 A EP00120926 A EP 00120926A EP 00120926 A EP00120926 A EP 00120926A EP 1191189 A1 EP1191189 A1 EP 1191189A1
Authority
EP
European Patent Office
Prior art keywords
cooling
gas turbine
blade
insert
airfoil
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.)
Withdrawn
Application number
EP00120926A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP00120926A priority Critical patent/EP1191189A1/fr
Priority to JP2002530494A priority patent/JP4669202B2/ja
Priority to DE50113551T priority patent/DE50113551D1/de
Priority to US10/381,485 priority patent/US6874988B2/en
Priority to EP01980405A priority patent/EP1320661B1/fr
Priority to PCT/EP2001/010789 priority patent/WO2002027146A1/fr
Publication of EP1191189A1 publication Critical patent/EP1191189A1/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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

Definitions

  • the invention relates to a gas turbine blade with a Blade edge and a blade edge and with an internal cooling structure comprising a meandering one Cooling channel with directed along the blade axis Sections for guiding a cooling fluid from the leading edge of the airfoil to the trailing edge of the airfoil.
  • the object of the invention is to provide a gas turbine blade, which is particularly efficient a cooling fluid for cooling the Exploits gas turbine blade.
  • this object is achieved by specifying a gas turbine blade directed along a blade axis with an airfoil leading edge and an airfoil trailing edge and with an internal cooling structure comprising one meandering cooling channel with along the blade axis directed sections for guiding a cooling fluid from the airfoil leading edge to the airfoil trailing edge, a first of the sections along the leading edge of the airfoil runs and an entry area for the Has cooling fluid and an outlet area for the cooling fluid, the first section being an impingement cooling insert has that with its leading edge to the airfoil facing the front of the insert parallel to the front edge of the airfoil runs, the impact cooling insert to the outlet area tapered towards.
  • the invention is based on the knowledge that at a conventional internal cooling of a gas turbine blade the front edge of the airfoil through a meandering cooling channel are not always cooled sufficiently efficiently can, because of the particularly high thermal load on the outside the airfoil leading edge has a comparatively small surface on the inside of the front edge of the airfoil. Purely convective cooling using a Cooling fluid flow in the meandering channel section at the front edge of the airfoil may be insufficient to the temperature of the airfoil leading edge increases sufficiently reduce.
  • the invention is based on observation from that cooling alone by means of an impact cooling insert just at the front edge of the airfoil through the higher cooling performance of the impingement cooling a greater heat dissipation allows the cooling of the airfoil as a whole due to the impact cooling insert but comparatively inefficient is because the cooling fluid absorbs less heat overall.
  • a gas turbine blade cooled by cooling air with a Meandering is, for example, that after going through the Meanderka nals from the rear edge of the cooling fluid warmer than that after impingement cooling also from a trailing edge of the blade leaking cooling fluid.
  • the gas turbine guide vane 1 is along a vane axis 3 directed.
  • the gas turbine blade points along the blade axis 3 1 a fastening area in succession 5, a platform area 6, an airfoil area 7 and an inner ring 9.
  • the airfoil area 7 has one Blade edge 8 and a blade edge 10 on.
  • the fastening area 5 has a hooking 11 Interlocking of the gas turbine blade 1 in a not shown Casing of a gas turbine.
  • the inner ring 9 has Paragraphs 13 for engaging in a sealing system for sealing of a hot gas duct, not shown, of a gas turbine compared to a rotor of the gas turbine, also not shown on.
  • the gas turbine blade 1 is hollow.
  • An internal cooling system of the gas turbine blade 1 is as follows explained in more detail:
  • a meandering shape leads through the interior of the gas turbine blade 1 Cooling channel 21.
  • the meandering cooling channel 21 is from sections directed along the blade axis 3 23, 25, 27 removed. These sections 23, 25, 27 are separated from one another by ribs 31.
  • the first section 23 runs along the front edge 8 of the airfoil meandering cooling channel 21 are on the inside of the Blade area 7 turbulators 29 arranged for Generation of turbulence in one by the meandering Cooling channel 21 provide cooling fluid, which in turn is a improved heat transfer to the cooling fluid.
  • the first partial section 23 faces the fastening area 5 opened and there has an inlet area 33 for cooling fluid on.
  • the end of the first bordering the inner ring 9 Section 23 forms an outlet region 35 for cooling fluid from the first section 23, which then enters the second section 25.
  • an impact cooling insert 37 is arranged in the first section 23.
  • This Impact cooling insert 37 tapers from the entrance area 33 towards the exit area 35, so that three three consecutive cross-sectional areas along the blade axis F1, F2, F3 compared to each other along in this direction become smaller.
  • the impact cooling insert 37 is oriented so that it is parallel with its front face to the leading edge 8 of the airfoil. It extends the entire length of the front edge of the airfoil 8. By tapering the impact cooling insert 37 becomes in one direction from the entry area to the exit area the first partial section 23 released more and more.
  • the impingement cooling insert 37 has impingement cooling bores evenly distributed 43 on.
  • On the inside of the airfoil area 7 are the air guiding ribs surrounding the impingement cooling insert 37 51 arranged. These air guide ribs 51 extend transversely to the blade axis 3. At the same time, they are opposite one inclined plane perpendicular to the blade axis 3.
  • the Air fins 51 each end before they enter the free part of the first section 23 occur.
  • film cooling openings 53 are provided.
  • the impact cooling insert 37 opens in the area of the inner ring 9 an inner ring cooling duct 55.
  • Cooling fluid 61 is then after impingement cooling over the Air guide fins 51 towards the free part of the first Section 23 headed by the taper of the Impingement insert 37 is formed.
  • the cross-sectional area of the Impact cooling insert 37 tapers in proportion to amount of cooling fluid emerging from the impact cooling insert 37.
  • the Cooling fluid 61 is cooling air here.
  • the one at the end of the impact cooling insert 37 impact cooling air remaining in the area of the inner ring 9 is in the area via the inner ring cooling channel 55 of the inner ring 9 and is used to cool the inner ring 9.
  • the in the free part of the first section 23rd Cooling air 61 introduced via the air fins 51 is in the second section 25 and then in the third Section 27 initiated. From there it emerges from the Film cooling holes 53 in the hot gas channel.
  • the airfoil leading edge 8 is particularly effective impact-cooled, but the cooling fluid 61 in the further course passed through the meandering cooling channel 21 and thus in its cooling effect is used as efficiently as possible. Farther can despite the cooling by means of the meandering Cooling channel 21 unheated via the impingement cooling insert 37 Cooling air 61 are fed to the inner ring 9, whereby the Cooling air consumption for cooling the inner ring 9 is kept low becomes.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP00120926A 2000-09-26 2000-09-26 Aube de turbine à gaz Withdrawn EP1191189A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP00120926A EP1191189A1 (fr) 2000-09-26 2000-09-26 Aube de turbine à gaz
JP2002530494A JP4669202B2 (ja) 2000-09-26 2001-09-18 ガスタービン羽根
DE50113551T DE50113551D1 (de) 2000-09-26 2001-09-18 Gasturbinenschaufel
US10/381,485 US6874988B2 (en) 2000-09-26 2001-09-18 Gas turbine blade
EP01980405A EP1320661B1 (fr) 2000-09-26 2001-09-18 Aube de turbine a gaz
PCT/EP2001/010789 WO2002027146A1 (fr) 2000-09-26 2001-09-18 Aube de turbine a gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00120926A EP1191189A1 (fr) 2000-09-26 2000-09-26 Aube de turbine à gaz

Publications (1)

Publication Number Publication Date
EP1191189A1 true EP1191189A1 (fr) 2002-03-27

Family

ID=8169949

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00120926A Withdrawn EP1191189A1 (fr) 2000-09-26 2000-09-26 Aube de turbine à gaz
EP01980405A Expired - Lifetime EP1320661B1 (fr) 2000-09-26 2001-09-18 Aube de turbine a gaz

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP01980405A Expired - Lifetime EP1320661B1 (fr) 2000-09-26 2001-09-18 Aube de turbine a gaz

Country Status (5)

Country Link
US (1) US6874988B2 (fr)
EP (2) EP1191189A1 (fr)
JP (1) JP4669202B2 (fr)
DE (1) DE50113551D1 (fr)
WO (1) WO2002027146A1 (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1413714A2 (fr) * 2002-10-22 2004-04-28 Siemens Aktiengesellschaft Aube de guidage pour turbine
EP1469164A2 (fr) 2003-04-15 2004-10-20 General Electric Company Refroidissement des aubes de guidage de turbine
FR2858829A1 (fr) * 2003-08-12 2005-02-18 Snecma Moteurs Aube refroidie de moteur a turbine a gaz
US7150601B2 (en) * 2004-12-23 2006-12-19 United Technologies Corporation Turbine airfoil cooling passageway
EP1452690A3 (fr) * 2003-02-27 2007-02-28 General Electric Company Refroidissement par convection forcée d'une tuyère de guidage pour turbines à gaz
GB2443638A (en) * 2006-11-09 2008-05-14 Rolls Royce Plc An air-cooled component
EP2105580A1 (fr) * 2008-03-25 2009-09-30 General Electric Company Tuyère de turbine refroidie à refroidissement hybride
CN101122243B (zh) * 2006-03-29 2011-04-20 斯奈克玛 一种涡轮机组喷嘴导向叶片的冷却衬套
RU2486039C1 (ru) * 2012-04-19 2013-06-27 Общество с ограниченной ответственностью "ТУРБОКОН" (ООО "ТУРБОКОН") Способ пайки сопловых лопаток с охлаждающими отверстиями турбины гтд и защитная паста для использования в этом способе
EP3023587A1 (fr) * 2014-10-15 2016-05-25 Honeywell International Inc. Moteurs à turbine à gaz présentant un meilleur refroidissement de profil de bord d'attaque
CN106255806A (zh) * 2014-05-08 2016-12-21 西门子股份公司 涡轮组件和相应的操作方法
EP2653659A3 (fr) * 2012-04-19 2017-08-16 General Electric Company Ensemble de refroidissement pour système de turbine à gaz
WO2023147117A1 (fr) * 2022-01-28 2023-08-03 Raytheon Technologies Corporation Aube refroidie à rail avant pour moteur à turbine à gaz

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GB2395232B (en) * 2002-11-12 2006-01-25 Rolls Royce Plc Turbine components
US6969230B2 (en) * 2002-12-17 2005-11-29 General Electric Company Venturi outlet turbine airfoil
US7090461B2 (en) * 2003-10-30 2006-08-15 Siemens Westinghouse Power Corporation Gas turbine vane with integral cooling flow control system
US7131816B2 (en) * 2005-02-04 2006-11-07 Pratt & Whitney Canada Corp. Airfoil locator rib and method of positioning an insert in an airfoil
FR2893080B1 (fr) * 2005-11-07 2012-12-28 Snecma Agencement de refroidissement d'une aube d'une turbine, aube de turbine le comportant, turbine et moteur d'aeronef en etant equipes
EP1921269A1 (fr) * 2006-11-09 2008-05-14 Siemens Aktiengesellschaft Aube de turbine
US7775769B1 (en) 2007-05-24 2010-08-17 Florida Turbine Technologies, Inc. Turbine airfoil fillet region cooling
FR2919897B1 (fr) * 2007-08-08 2014-08-22 Snecma Secteur de distributeur de turbine
US8197210B1 (en) * 2007-09-07 2012-06-12 Florida Turbine Technologies, Inc. Turbine vane with leading edge insert
FR2921937B1 (fr) * 2007-10-03 2009-12-04 Snecma Procede d'aluminisation en phase vapeur d'une piece metallique de turbomachine
US8043057B1 (en) * 2007-12-21 2011-10-25 Florida Turbine Technologies, Inc. Air cooled turbine airfoil
US7946801B2 (en) * 2007-12-27 2011-05-24 General Electric Company Multi-source gas turbine cooling
US20090220331A1 (en) * 2008-02-29 2009-09-03 General Electric Company Turbine nozzle with integral impingement blanket
BRPI0911722B1 (pt) * 2008-07-31 2022-09-13 Pharmaessentia Corp Conjugado de peptídeo-polímero
US20100054915A1 (en) * 2008-08-28 2010-03-04 United Technologies Corporation Airfoil insert
EP2256297B8 (fr) * 2009-05-19 2012-10-03 Alstom Technology Ltd Aube de turbine à gaz dotée d'un refroidissement amélioré
US8142153B1 (en) * 2009-06-22 2012-03-27 Florida Turbine Technologies, Inc Turbine vane with dirt separator
EP2333240B1 (fr) * 2009-12-03 2013-02-13 Alstom Technology Ltd Aube de turbine en deux parties avec des caractéristiques de refroidissement et de vibrations améliorées
US8628294B1 (en) * 2011-05-19 2014-01-14 Florida Turbine Technologies, Inc. Turbine stator vane with purge air channel
EP2540969A1 (fr) * 2011-06-27 2013-01-02 Siemens Aktiengesellschaft Refroidissement par projection d'aubes ou pales de turbine
US9145780B2 (en) 2011-12-15 2015-09-29 United Technologies Corporation Gas turbine engine airfoil cooling circuit
JP5948436B2 (ja) * 2011-12-29 2016-07-06 ゼネラル・エレクトリック・カンパニイ 翼冷却回路
US9845691B2 (en) 2012-04-27 2017-12-19 General Electric Company Turbine nozzle outer band and airfoil cooling apparatus
US9995150B2 (en) * 2012-10-23 2018-06-12 Siemens Aktiengesellschaft Cooling configuration for a gas turbine engine airfoil
US10240470B2 (en) * 2013-08-30 2019-03-26 United Technologies Corporation Baffle for gas turbine engine vane
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane
FR3037829B1 (fr) * 2015-06-29 2017-07-21 Snecma Noyau pour le moulage d'une aube ayant des cavites superposees et comprenant un trou de depoussierage traversant une cavite de part en part
US10337334B2 (en) 2015-12-07 2019-07-02 United Technologies Corporation Gas turbine engine component with a baffle insert
US10577947B2 (en) * 2015-12-07 2020-03-03 United Technologies Corporation Baffle insert for a gas turbine engine component
US10280841B2 (en) 2015-12-07 2019-05-07 United Technologies Corporation Baffle insert for a gas turbine engine component and method of cooling
US10422233B2 (en) 2015-12-07 2019-09-24 United Technologies Corporation Baffle insert for a gas turbine engine component and component with baffle insert
US10443407B2 (en) * 2016-02-15 2019-10-15 General Electric Company Accelerator insert for a gas turbine engine airfoil
EP3236010A1 (fr) * 2016-04-21 2017-10-25 Siemens Aktiengesellschaft Aube directrice comprenant un tuyau de raccordement
DE102016216858A1 (de) * 2016-09-06 2018-03-08 Rolls-Royce Deutschland Ltd & Co Kg Laufschaufel für eine Turbomaschine und Verfahren für den Zusammenbau einer Laufschaufel für eine Turbomaschine
US10669861B2 (en) * 2017-02-15 2020-06-02 Raytheon Technologies Corporation Airfoil cooling structure
US10577943B2 (en) * 2017-05-11 2020-03-03 General Electric Company Turbine engine airfoil insert
US10815806B2 (en) * 2017-06-05 2020-10-27 General Electric Company Engine component with insert
US10570751B2 (en) 2017-11-22 2020-02-25 General Electric Company Turbine engine airfoil assembly
KR102048863B1 (ko) * 2018-04-17 2019-11-26 두산중공업 주식회사 인서트 지지부를 구비한 터빈 베인
US10787913B2 (en) 2018-11-01 2020-09-29 United Technologies Corporation Airfoil cooling circuit
CN109441557B (zh) * 2018-12-27 2024-06-11 哈尔滨广瀚动力技术发展有限公司 一种带有冷却结构的船用燃气轮机的高压涡轮导叶
CN110925027A (zh) * 2019-11-29 2020-03-27 大连理工大学 一种涡轮叶片尾缘渐缩型倾斜排气劈缝结构
US11525397B2 (en) 2020-09-01 2022-12-13 General Electric Company Gas turbine component with ejection circuit for removing debris from cooling air supply
CN114320483A (zh) * 2021-12-27 2022-04-12 北京航空航天大学 一种低压驱动冲击冷却结构
CN117489418B (zh) * 2023-12-28 2024-03-15 成都中科翼能科技有限公司 一种涡轮导向叶片及其前冷气腔的冷气导流件

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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1413714A3 (fr) * 2002-10-22 2004-12-22 Siemens Aktiengesellschaft Aube de guidage pour turbine
EP1413714A2 (fr) * 2002-10-22 2004-04-28 Siemens Aktiengesellschaft Aube de guidage pour turbine
EP1452690A3 (fr) * 2003-02-27 2007-02-28 General Electric Company Refroidissement par convection forcée d'une tuyère de guidage pour turbines à gaz
EP1469164A2 (fr) 2003-04-15 2004-10-20 General Electric Company Refroidissement des aubes de guidage de turbine
EP1469164A3 (fr) * 2003-04-15 2008-04-23 General Electric Company Refroidissement des aubes de guidage de turbine
FR2858829A1 (fr) * 2003-08-12 2005-02-18 Snecma Moteurs Aube refroidie de moteur a turbine a gaz
EP1508670A3 (fr) * 2003-08-12 2005-03-09 Snecma Moteurs Aube refroidie de moteur à turbine à gaz
US7204675B2 (en) 2003-08-12 2007-04-17 Snecma Moteurs Cooled gas turbine engine vane
EP1508670A2 (fr) * 2003-08-12 2005-02-23 Snecma Moteurs Aube refroidie de moteur à turbine à gaz
US7150601B2 (en) * 2004-12-23 2006-12-19 United Technologies Corporation Turbine airfoil cooling passageway
CN101122243B (zh) * 2006-03-29 2011-04-20 斯奈克玛 一种涡轮机组喷嘴导向叶片的冷却衬套
GB2443638A (en) * 2006-11-09 2008-05-14 Rolls Royce Plc An air-cooled component
GB2443638B (en) * 2006-11-09 2008-11-26 Rolls Royce Plc An air-cooled aerofoil
US7976277B2 (en) 2006-11-09 2011-07-12 Rolls-Royce, Plc Air-cooled component
EP2105580A1 (fr) * 2008-03-25 2009-09-30 General Electric Company Tuyère de turbine refroidie à refroidissement hybride
RU2486039C1 (ru) * 2012-04-19 2013-06-27 Общество с ограниченной ответственностью "ТУРБОКОН" (ООО "ТУРБОКОН") Способ пайки сопловых лопаток с охлаждающими отверстиями турбины гтд и защитная паста для использования в этом способе
EP2653659A3 (fr) * 2012-04-19 2017-08-16 General Electric Company Ensemble de refroidissement pour système de turbine à gaz
CN106255806A (zh) * 2014-05-08 2016-12-21 西门子股份公司 涡轮组件和相应的操作方法
CN106255806B (zh) * 2014-05-08 2019-05-31 西门子股份公司 涡轮组件和相应的操作方法
US10450881B2 (en) 2014-05-08 2019-10-22 Siemens Aktiengesellschaft Turbine assembly and corresponding method of operation
EP3023587A1 (fr) * 2014-10-15 2016-05-25 Honeywell International Inc. Moteurs à turbine à gaz présentant un meilleur refroidissement de profil de bord d'attaque
US10119404B2 (en) 2014-10-15 2018-11-06 Honeywell International Inc. Gas turbine engines with improved leading edge airfoil cooling
US10934856B2 (en) 2014-10-15 2021-03-02 Honeywell International Inc. Gas turbine engines with improved leading edge airfoil cooling
WO2023147117A1 (fr) * 2022-01-28 2023-08-03 Raytheon Technologies Corporation Aube refroidie à rail avant pour moteur à turbine à gaz

Also Published As

Publication number Publication date
EP1320661B1 (fr) 2008-01-30
US6874988B2 (en) 2005-04-05
EP1320661A1 (fr) 2003-06-25
US20040022630A1 (en) 2004-02-05
WO2002027146A1 (fr) 2002-04-04
DE50113551D1 (de) 2008-03-20
JP4669202B2 (ja) 2011-04-13
JP2004510091A (ja) 2004-04-02

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