EP1505258B1 - Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz - Google Patents

Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz Download PDF

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Publication number
EP1505258B1
EP1505258B1 EP04291990A EP04291990A EP1505258B1 EP 1505258 B1 EP1505258 B1 EP 1505258B1 EP 04291990 A EP04291990 A EP 04291990A EP 04291990 A EP04291990 A EP 04291990A EP 1505258 B1 EP1505258 B1 EP 1505258B1
Authority
EP
European Patent Office
Prior art keywords
wall
face
blade
cavity
rim
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 - Lifetime
Application number
EP04291990A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1505258A1 (fr
Inventor
Jacques Boury
Maurice Judet
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1505258A1 publication Critical patent/EP1505258A1/fr
Application granted granted Critical
Publication of EP1505258B1 publication Critical patent/EP1505258B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/20—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

Definitions

  • the invention relates to a hollow rotor blade for the turbine of a gas turbine engine, in particular for a high pressure type turbine.
  • the present invention relates to the production of a hollow blade of the type which comprises an internal cooling passage, an open cavity located at the free end of the blade and delimited by a bottom wall extending over the entire end of the blade and a flange extending between the leading edge and the trailing edge along the upper surface and the lower surface wall, and cooling channels connecting said passage of internal cooling and the outer face of the intrados wall, said cooling channels being inclined relative to the intrados wall so that they open, at their outlet, on the outer face of the intrados wall; towards the top of said rim.
  • Cooling channels of this type are intended to cool the free end of the blade because they allow to discharge a jet of cooling air from the internal cooling passage, towards the end of the blade at the level of the blade. the upper end of the outer face of the intrados wall.
  • This air jet creates "thermal pumping", that is to say a decrease in the temperature of the metal by absorption of calories in the heart of the metal wall, and a cooling air film that protects the end of the vanes on the intrados side.
  • the blades are hollow to allow their cooling by the air present in an internal cooling passage.
  • These cooling channels located on the side of the intrados wall thus allow the outlet, from the internal cooling passage, of a jet of air colder than that surrounding the intrados wall, this air jet forming a cooling air film located on the outside face of the intrados wall and which is sucked towards the extrados wall.
  • these inclined cooling channels connect the internal cooling passage and the outer face of the cavity flange at the intrados wall by being arranged (see Figure 2 of this document) so as to pass through the bottom wall of the cavity. the cavity and the rim of the cavity at the intrados wall, passing through said cavity.
  • This solution therefore requires a significant material thickness, either for the bottom wall of the cavity or for the rim of the cavity, so as not to call into question the performance of thermomechanical resistance at the end of the blade.
  • this solution greatly limits the flow of cooling air that reaches the top of the rim because most of the flow exits the internal cooling passage through the first section of the cooling channels and enters directly into the cavity without success. on the outside face of the intrados wall.
  • thermomechanical resistance at the end of the blade requires a significant material thickness, either for the bottom wall of the cavity or for the rim of the cavity, so as not to call into question the performance of thermomechanical resistance at the end of the blade.
  • the present invention seeks to solve the aforementioned problems.
  • the present invention aims to provide a hollow rotor blade for the turbine of a gas turbine engine, of the type mentioned above, to cool the end of the blade sufficiently to improve its reliability without reducing the aerodynamic and thermomechanical performance of dawn.
  • the blade is defined by claim 1.
  • the cooling channels can thus emerge closer to the top of the rim without changing the distance between these cooling channels and the bottom wall of the cavity.
  • this material reinforcement generates an extra thickness in the portion of the end of the blade where the rim and the bottom wall meet, on the side of the interior of the cavity.
  • Such a reinforcement is easy to implement without modifying the manufacturing process of the blade because it is sufficient to provide at this location a larger amount of metal from the casting step, especially during the design of the mold corresponding to this part of dawn.
  • This solution also has the additional advantage of not weighing down the structure of the blade significantly.
  • the face of said reinforcement turned towards the cavity forms, with the face of the bottom wall facing the cavity, an angle ( ⁇ ) of between 170 and 100 °, preferably between 135 and 110 °.
  • said angle ( ⁇ ) is substantially equal to 112 °.
  • said face of the reinforcement turned towards the cavity is substantially parallel to the direction of the cooling channels.
  • This preferred embodiment makes it possible to obtain the best mechanical reinforcement with the minimum of material at the level of the reinforcement.
  • the distance (A) between the output of the cooling channels and said top of the flange is less than the distance (B) between the output of the cooling channels and said face of the reinforcement turned in the direction of the cavity.
  • This arrangement makes it possible to arrange the outlet of the cooling channels as close as possible to the top of the rim, which is cooled very effectively.
  • the distance (B) between the exit of the cooling channels and said face of the reinforcement facing towards said cavity is at least equal, and in particular exactly equal, to the distance (C) separating the intersection (C1) between the inner face of the rim at the upper surface of the wall and the face of the bottom wall facing toward said cavity of the intersection (C2) between the outer face of the wall of extrados and the face of the bottom wall facing away from said cavity.
  • FIG 1 is visible, in perspective, an example of a conventional hollow rotor blade 10 for a gas turbine. Cooling air (not shown) flows inside the blade from the bottom of the blade root 12 in the radial (vertical) direction towards the free end 14 of the blade (in top in Figure 1), then this cooling air escapes through an outlet to join the main gas flow.
  • Cooling air (not shown) flows inside the blade from the bottom of the blade root 12 in the radial (vertical) direction towards the free end 14 of the blade (in top in Figure 1), then this cooling air escapes through an outlet to join the main gas flow.
  • this cooling air circulates in an internal cooling passage situated inside the blade and which ends at the free end 14 of the blade at the level of through-holes 15.
  • the body of the blade is profiled so that it defines a lower surface wall 16 (on the left in all the figures) and an extrados wall 18 (on the right in all the figures).
  • the intrados wall 16 has a generally concave shape and is the first face to the flow of hot gases, that is to say the gas pressure side, while the extrados wall 18 is convex and is presented by following the flow of hot gases, that is to say the suction side of the gas.
  • intrados and extrados walls 18 are joined at the location of the leading edge 20 and at the location of the trailing edge 22 which extend radially between the free end 14 of the blade and the top of the foot 12 of dawn.
  • the internal cooling passage 24 is delimited by the inner face 26a of a bottom wall 26 which extends over the entire free end 14 of the blade, between the intrados wall 16 and the extrados wall 18, hence from the leading edge 20 to the trailing edge 22.
  • the intrados and extrados walls 16, 18 form the rim 28 of an open cavity 30 in the direction opposite to the internal cooling passage 24, either radially towards the inner side. outside (upwards in all the figures).
  • this open cavity 30 is therefore delimited laterally by the internal face of this flange 28 and in the lower part by the outer face 26b of the bottom wall 26.
  • the flange 28 thus forms a thin wall along the profile of the blade which protects the free end 14 of the blade 10 from contact with the corresponding annular surface of the turbine casing.
  • inclined cooling channels 32 pass through the intrados wall 16 to connect the internal cooling passage 24 to the outside face of the intrados wall 16. .
  • These cooling channels 32 are inclined so that they open towards the top 28a of the rim so as to cool as much as possible this vertex 28a, along the intrados wall 16.
  • a reinforcement 34 of material is provided between the face of the flange 28 facing the cavity 30, along the intrados wall 16, and the face 26b of the bottom wall 26 facing the cavity 30.
  • This material reinforcement 34 is advantageously made so as to form a face 34a turned towards the cavity 30 which is substantially flat, so that the transition between the outer face 26b of the bottom wall 26 facing the cavity 30 and the inner face of the flange 28 is carried out in stages.
  • This reinforcement 34 is placed along at least a portion of the intrados wall.
  • This reinforcement 34 may consist of a continuous band or a series of protuberances, provided that this reinforcement 34 of material is present in each transverse plane passing through a cooling channel 32.
  • the face of said reinforcement turned towards the cavity is substantially flat and forms, with the face of the bottom wall facing the cavity, an angle ⁇ equal to 112 °.
  • the flange 28 which advantageously forms a thin wall, therefore has a small thickness, namely less than 1.5 mm, of preferably less than 1 mm and preferably a thickness of between 0.3 and 0.8 mm.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04291990A 2003-08-06 2004-08-04 Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz Expired - Lifetime EP1505258B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0309688A FR2858650B1 (fr) 2003-08-06 2003-08-06 Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz
FR0309688 2003-08-06

Publications (2)

Publication Number Publication Date
EP1505258A1 EP1505258A1 (fr) 2005-02-09
EP1505258B1 true EP1505258B1 (fr) 2008-01-02

Family

ID=33548310

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04291990A Expired - Lifetime EP1505258B1 (fr) 2003-08-06 2004-08-04 Aube creuse de rotor pour la turbine d'un moteur à turbine à gaz

Country Status (9)

Country Link
US (2) US7192250B2 (es)
EP (1) EP1505258B1 (es)
JP (1) JP4184323B2 (es)
CA (1) CA2478746C (es)
DE (1) DE602004010965T2 (es)
ES (1) ES2297354T3 (es)
FR (1) FR2858650B1 (es)
RU (1) RU2345226C2 (es)
UA (1) UA82059C2 (es)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2858650B1 (fr) * 2003-08-06 2007-05-18 Snecma Moteurs Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz
US7704047B2 (en) * 2006-11-21 2010-04-27 Siemens Energy, Inc. Cooling of turbine blade suction tip rail
US7857588B2 (en) * 2007-07-06 2010-12-28 United Technologies Corporation Reinforced airfoils
US7922451B1 (en) 2007-09-07 2011-04-12 Florida Turbine Technologies, Inc. Turbine blade with blade tip cooling passages
FR2923524B1 (fr) * 2007-11-12 2013-12-06 Snecma Aube metallique fabriquee par moulage et procede de fabrication de l'aube
US8206108B2 (en) * 2007-12-10 2012-06-26 Honeywell International Inc. Turbine blades and methods of manufacturing
GB2461502B (en) * 2008-06-30 2010-05-19 Rolls Royce Plc An aerofoil
US8262357B2 (en) * 2009-05-15 2012-09-11 Siemens Energy, Inc. Extended length holes for tip film and tip floor cooling
JP2011163123A (ja) * 2010-02-04 2011-08-25 Ihi Corp タービン動翼
US8777567B2 (en) 2010-09-22 2014-07-15 Honeywell International Inc. Turbine blades, turbine assemblies, and methods of manufacturing turbine blades
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
JP6092661B2 (ja) * 2013-03-05 2017-03-08 三菱日立パワーシステムズ株式会社 ガスタービン翼
RU2529273C1 (ru) * 2013-09-11 2014-09-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Рабочая лопатка турбины газотурбинного двигателя
US9856739B2 (en) 2013-09-18 2018-01-02 Honeywell International Inc. Turbine blades with tip portions having converging cooling holes
US9816389B2 (en) 2013-10-16 2017-11-14 Honeywell International Inc. Turbine rotor blades with tip portion parapet wall cavities
US9879544B2 (en) 2013-10-16 2018-01-30 Honeywell International Inc. Turbine rotor blades with improved tip portion cooling holes
WO2016118135A1 (en) * 2015-01-22 2016-07-28 Siemens Energy, Inc. Turbine airfoil cooling system with chordwise extending squealer tip cooling channel
US9885243B2 (en) 2015-10-27 2018-02-06 General Electric Company Turbine bucket having outlet path in shroud
US10156145B2 (en) * 2015-10-27 2018-12-18 General Electric Company Turbine bucket having cooling passageway
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud
US20180161853A1 (en) * 2016-12-13 2018-06-14 General Electric Company Integrated casting core-shell structure with floating tip plenum
US11015453B2 (en) 2017-11-22 2021-05-25 General Electric Company Engine component with non-diffusing section
CN110044668B (zh) * 2018-01-17 2022-05-24 中国航发商用航空发动机有限责任公司 表征薄壁叶片铸件叶身性能的试样制造方法
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
KR102466386B1 (ko) 2020-09-25 2022-11-10 두산에너빌리티 주식회사 터빈 블레이드 및 이를 포함하는 터빈
CN112576316B (zh) * 2020-11-16 2023-02-21 哈尔滨工业大学 涡轮叶片
US11608746B2 (en) 2021-01-13 2023-03-21 General Electric Company Airfoils for gas turbine engines
CN114018542B (zh) * 2021-11-02 2023-07-21 中国航发沈阳发动机研究所 一种发动机流道内应用磁流体流动力学技术的试验装置

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4589823A (en) * 1984-04-27 1986-05-20 General Electric Company Rotor blade tip
US5660523A (en) * 1992-02-03 1997-08-26 General Electric Company Turbine blade squealer tip peripheral end wall with cooling passage arrangement
US5348446A (en) * 1993-04-28 1994-09-20 General Electric Company Bimetallic turbine airfoil
JP3137527B2 (ja) * 1994-04-21 2001-02-26 三菱重工業株式会社 ガスタービン動翼チップ冷却装置
US6231307B1 (en) * 1999-06-01 2001-05-15 General Electric Company Impingement cooled airfoil tip
US6224337B1 (en) * 1999-09-17 2001-05-01 General Electric Company Thermal barrier coated squealer tip cavity
US6602052B2 (en) * 2001-06-20 2003-08-05 Alstom (Switzerland) Ltd Airfoil tip squealer cooling construction
US6790005B2 (en) * 2002-12-30 2004-09-14 General Electric Company Compound tip notched blade
FR2858650B1 (fr) * 2003-08-06 2007-05-18 Snecma Moteurs Aube creuse de rotor pour la turbine d'un moteur a turbine a gaz
US6916150B2 (en) * 2003-11-26 2005-07-12 Siemens Westinghouse Power Corporation Cooling system for a tip of a turbine blade

Also Published As

Publication number Publication date
FR2858650B1 (fr) 2007-05-18
RU2345226C2 (ru) 2009-01-27
RU2004123964A (ru) 2006-01-27
UA82059C2 (uk) 2008-03-11
ES2297354T3 (es) 2008-05-01
EP1505258A1 (fr) 2005-02-09
CA2478746C (fr) 2012-10-09
JP2005054799A (ja) 2005-03-03
CA2478746A1 (fr) 2005-02-06
US7927072B2 (en) 2011-04-19
JP4184323B2 (ja) 2008-11-19
US7192250B2 (en) 2007-03-20
US20050063824A1 (en) 2005-03-24
DE602004010965T2 (de) 2009-01-02
US20100254823A1 (en) 2010-10-07
DE602004010965D1 (de) 2008-02-14
FR2858650A1 (fr) 2005-02-11

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