EP1512489A1 - Aube pour turbine - Google Patents

Aube pour turbine Download PDF

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Publication number
EP1512489A1
EP1512489A1 EP03020211A EP03020211A EP1512489A1 EP 1512489 A1 EP1512489 A1 EP 1512489A1 EP 03020211 A EP03020211 A EP 03020211A EP 03020211 A EP03020211 A EP 03020211A EP 1512489 A1 EP1512489 A1 EP 1512489A1
Authority
EP
European Patent Office
Prior art keywords
blade
slot
trailing edge
length
turbine
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.)
Granted
Application number
EP03020211A
Other languages
German (de)
English (en)
Other versions
EP1512489B1 (fr
Inventor
Fathi Ahmad
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 EP03020211A priority Critical patent/EP1512489B1/fr
Priority to DE50306044T priority patent/DE50306044D1/de
Priority to US10/931,089 priority patent/US7160084B2/en
Publication of EP1512489A1 publication Critical patent/EP1512489A1/fr
Application granted granted Critical
Publication of EP1512489B1 publication Critical patent/EP1512489B1/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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades

Definitions

  • the invention relates to a blade along a blade axis directed and formed from a body blade of a Turbine comprising a foot area, a head area and an airfoil with one from the foot area to the head area reaching leaf height.
  • the invention also relates to a Method for preventing the propagation of cracks in the Airfoil of the blade of a turbine.
  • Turbines become flow media in a flow channel transported to gain energy from this. These are in the Flow channel arranged turbine blades. For example are in the flow channel of an axial gas turbine in Flow direction alternately alternately Vanes formed vane rings and off Blades formed blade rings arranged.
  • the Guide vanes steer the flow medium in a suitable manner on the blades, which are connected to a rotor and be set in rotation so that kinetic energy of the Flow medium is converted into rotational energy.
  • Such blades in turbomachinery are common exposed to considerable mechanical stress. Especially at at the same time high temperature and high speeds, as in a gas turbine, it comes to a high Material stress of the blade material. This allows Cracks form in the blade material, which build up in the course of the Spread time with continued use. After all There may be a failure of the blade, the Shovel breaks or fragments are removed. For In the direction of flow subsequent blades this can cause considerable damage. A cracking and Crack propagation is thus to be monitored. Depending on Speed of the processes can thereby become one significant reduction in the availability of the turbine come, because regular service intervals to the downtime of the Lead turbine.
  • JP 2000018001 is a gas turbine blade shown at the relief slots in the direction of Bucket axis are introduced to the edge of the head area. These relief slots serve to reduce thermal Tensions in this area. By reducing thermal Tensions should be reduced cracking.
  • the Relief slots are limited to the head area.
  • JP 10299408 shows a gas turbine blade in which Areas of high thermal stresses elliptical holes are introduced, which are to reduce a crack propagation.
  • the holes are in the transition region of the blade and Platform arranged in the airfoil area the Ellipse main axis is directed perpendicular to the blade axis. A corresponding orientation of the holes can be found the trailing edge.
  • the object of the invention is the specification of a turbine blade, exposed to the very low thermal stresses is.
  • this object is achieved by a along directed to a blade axis and from a base body formed turbine blade, comprising a foot area, a Head section and an airfoil with one from the foot area to the head area reaching leaf height and with one of a Blade leading edge to a blade trailing edge reaching sheet width, being in a transitional area between the blade trailing edge and the foot area one Rounding is formed, passing across the Blade trailing edge formed through a discharge slot is.
  • the invention is based on the recognition that the Vane trailing edge of a turbine blade in one area above the rounded transition area between the Vane trailing edge and the foot area and in this rounded transition area itself particularly high is exposed to mechanical stresses. Furthermore, the lies Invention based on the knowledge that the Bucket trailing edge through slots extending transversely to it with appropriate dimensioning not inadmissible is mechanically destabilized. By introducing a Relief slot transverse to the blade trailing edge through the Bucket trailing edge is now a significant Relief from thermal stresses thereby achieved that can be compensated by the slot thermal expansion is.
  • the relief slot is in the vicinity of Rounding. Especially in an area near the Rounding is subject to the blade trailing edge particularly high thermal stresses. Through the relief slot can these tensions in this particularly affected area effectively degraded. More preferably, the Relief slot while less than 20% of the blade height removed from the rounding. Particularly preferred is a Distance of the relief slot from the rounding of less than 10% of the blade height.
  • the slot has a length of at least 2% of the sheet width. In this expansion becomes a special high effect in the relief achieved by the slot.
  • the slot has at most a length of 5% of Blade width.
  • a larger extension of the slot length than this 5% of the sheet width only leads to a comparatively little further relief from thermal Tension, while on the other hand by too big Slot length the mechanical stability of the blade trailing edge would suffer.
  • At least two, more preferably at least provided three relief slots may be a larger portion of the blade trailing edge be relieved of thermal stresses. moreover can be counteracted overall higher thermal stresses become.
  • all relief slots are in an area smaller than 25% of the blade height from the fillet away.
  • three relief slots are provided, wherein a first, the rounding nearest slot a first Length, a second, along the blade axis the first Slot following second slot a second length and a third, following the second slot along the blade axis third slot has a third length, wherein the third length greater than the second length and the second length is greater than the first length.
  • the turbine blade is a gas turbine blade.
  • Gas turbine blades are particularly high temperatures exposed. Accordingly, it comes right here to build particularly high thermal stresses.
  • a circular Extension will be the radii of curvature of the slot at End limiting surfaces reduced and thus the especially at such curvatures occurring stresses reduced.
  • the circular extension is a Circular hole from which the slot through the Vane trailing edge extends therethrough.
  • the slot is preferably cut by means of a laser beam or he is milled.
  • FIG. 1 shows a gas turbine 1.
  • the gas turbine 1 is along directed a turbine axis 10 and points along the Turbine axis 10 consecutively a compressor 3, a Combustion chamber 5 and a turbine part 7.
  • the compressor 3 and the turbine part 7 are on a common Turbine shaft 9 is arranged.
  • a Hot gas channel 12 formed in the vanes 11 and Blades 13, which are arranged on the turbine shaft 9 are, stick in.
  • the compressor air 15 is fuel in the combustion chamber 5 burned to hot gas 17, which through the hot gas channel 12 flows. It puts over the effect on the Blades 13, the turbine shaft 9 in motion.
  • the Rotational energy of the turbine shaft 9 may be e.g. to the generation electrical energy can be used.
  • FIG. 2 shows a gas turbine guide vane 31.
  • the gas turbine guide vane 31 has a foot region 33 with a platform 34.
  • an airfoil 35 connects.
  • the airfoil 35 ends in a head region 37, which in particular also has a platform, which is not shown here.
  • the platform 34 and also the illustrated platform of the head region 37 serve to delimit the hot gas channel 12.
  • the airfoil 35 has a blade height h .
  • the airfoil 35 has a blade width b .
  • the blade airfoil 35 extends from a blade leading edge 39 to a blade trailing edge 41.
  • a blade outer wall 63 encloses the cavity.
  • Stabilizing side ribs 65 are arranged in the cavity between the suction side 47 and the pressure side 45.
  • Figure 3 shows a section of a longitudinal section through the Gas turbine guide vane 31 in the area of the rounding 73 between blade trailing edge 41 and platform 34.
  • the Relief slots 51 extend transversely to the Blade trailing edge 41 through the blade trailing edge 41st therethrough.
  • the blade trailing edge 41 may be e.g. alone be formed by the suction side 47, while the pressure side 45 step-like ends and cooling air openings in this stage are provided, which cool the blade trailing edge 41. This would be an open blade trailing edge 41. It may as well a closed blade trailing edge 41 are present in the rounded the pressure side 45 in the suction side 47 and while the blade trailing edge 41 forms.
  • the Relief slots 51 end with their the Blade trailing edge 41 opposite ends in circular extensions 53, in which comparatively little tension due to a relatively low curvature be caused.
  • the closest to the rounding Relief slot 51 has a smaller amount than that in Blade axis direction next following second Relief slot on.
  • the second relief slot is again shorter than that in the direction of the blade axis on him the third and the furthest 73 the third Relief slot 51.
  • cooling air 67 is the Cooling initiated. This cooling air 67 emerges from the slot 51 from the hollow interior of the gas turbine blade 34 from.
  • the slot 51 is shaped so that the cooling air 67th a cooling film on the surface of the airfoil 35th forms.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03020211A 2003-09-05 2003-09-05 Aube pour turbine Expired - Lifetime EP1512489B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03020211A EP1512489B1 (fr) 2003-09-05 2003-09-05 Aube pour turbine
DE50306044T DE50306044D1 (de) 2003-09-05 2003-09-05 Schaufel einer Turbine
US10/931,089 US7160084B2 (en) 2003-09-05 2004-08-31 Blade of a turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03020211A EP1512489B1 (fr) 2003-09-05 2003-09-05 Aube pour turbine

Publications (2)

Publication Number Publication Date
EP1512489A1 true EP1512489A1 (fr) 2005-03-09
EP1512489B1 EP1512489B1 (fr) 2006-12-20

Family

ID=34130157

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03020211A Expired - Lifetime EP1512489B1 (fr) 2003-09-05 2003-09-05 Aube pour turbine

Country Status (3)

Country Link
US (1) US7160084B2 (fr)
EP (1) EP1512489B1 (fr)
DE (1) DE50306044D1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1712782A2 (fr) * 2005-04-07 2006-10-18 General Electric Canada Rainures de décharge de contraintes pour les aubes d'une turbine Francis
EP1757773A1 (fr) * 2005-08-26 2007-02-28 Siemens Aktiengesellschaft Aube creuse de turbine
DE102015207760A1 (de) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Heißgasführendes Gehäuse
JP2016539273A (ja) * 2013-10-21 2016-12-15 シーメンス アクティエンゲゼルシャフト タービンブレード
CN106795770A (zh) * 2014-08-27 2017-05-31 西门子股份公司 涡轮叶片和涡轮机
WO2018215519A1 (fr) * 2017-05-23 2018-11-29 Siemens Aktiengesellschaft Procédé de fabrication d'une aube de turbine et aube de turbine
DE102019103640A1 (de) * 2019-02-13 2020-08-13 Mitsubishi Hitachi Power Systems Europe Gmbh Brennstoffdüse mit Dehnungsschlitzen für einen Kohlenstaubbrenner
CN114227180A (zh) * 2021-12-29 2022-03-25 哈尔滨汽轮机厂有限责任公司 一种提升汽轮机叶片加工精度的方法

Families Citing this family (17)

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Publication number Priority date Publication date Assignee Title
KR101070904B1 (ko) * 2004-08-20 2011-10-06 삼성테크윈 주식회사 레이디얼 터빈 휠
US9840931B2 (en) * 2008-11-25 2017-12-12 Ansaldo Energia Ip Uk Limited Axial retention of a platform seal
EP2299056A1 (fr) * 2009-09-02 2011-03-23 Siemens Aktiengesellschaft Refroidissement d'un composant de turbine à gaz sous la forme d'un disque de rotor ou d'une aube
US8556584B2 (en) * 2011-02-03 2013-10-15 General Electric Company Rotating component of a turbine engine
CH705838A1 (de) * 2011-12-05 2013-06-14 Alstom Technology Ltd Abgasgehäuse für eine Gasturbine sowie Gasturbine mit einem Abgasgehäuse.
US20130177430A1 (en) * 2012-01-05 2013-07-11 General Electric Company System and method for reducing stress in a rotor
US9228448B2 (en) * 2013-09-20 2016-01-05 United Technologies Corporation Background radiation measurement system
US9506365B2 (en) 2014-04-21 2016-11-29 Honeywell International Inc. Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof
US10458389B2 (en) * 2014-07-14 2019-10-29 Lm Wp Patent Holding A/S Profile wedge for attachment of an aeroshell extender piece
US20160047251A1 (en) * 2014-08-13 2016-02-18 United Technologies Corporation Cooling hole having unique meter portion
US11280214B2 (en) 2014-10-20 2022-03-22 Raytheon Technologies Corporation Gas turbine engine component
US11077527B2 (en) * 2015-12-21 2021-08-03 General Electric Company Modified components and methods for modifying components
US10415408B2 (en) * 2016-02-12 2019-09-17 General Electric Company Thermal stress relief of a component
FR3048998B1 (fr) * 2016-03-16 2019-12-13 Safran Aircraft Engines Rotor de turbine comprenant une entretoise de ventilation
FR3056630B1 (fr) * 2016-09-26 2018-12-07 Safran Aircraft Engines Disque aubage monobloc de soufflante pour turbomachine d'aeronef
KR102048874B1 (ko) * 2018-04-09 2019-11-26 두산중공업 주식회사 유연성이 향상된 터빈 베인
US20210115796A1 (en) * 2019-10-18 2021-04-22 United Technologies Corporation Airfoil component with trailing end margin and cutback

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Publication number Priority date Publication date Assignee Title
JPS5596303A (en) * 1979-01-16 1980-07-22 Mitsubishi Heavy Ind Ltd Manufacturing method of moving blade in rotary unit
JPS63248902A (ja) * 1987-04-03 1988-10-17 Hitachi Ltd ガスタ−ビン静翼
JP2000018001A (ja) * 1998-06-30 2000-01-18 Mitsubishi Heavy Ind Ltd 動翼熱応力軽減装置
US20010016163A1 (en) * 2000-02-23 2001-08-23 Yasuoki Tomita Gas turbine moving blade
US20030138322A1 (en) * 2002-01-23 2003-07-24 Snecma Moteurs Moving blade for a high pressure turbine, the blade having a trailing edge of improved thermal behavior

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US2193686A (en) * 1938-10-24 1940-03-12 Frederick L Craddock Mixing apparatus
KR900007253B1 (ko) * 1986-05-19 1990-10-06 우수이 고꾸사이 산교 가부시기가이샤 고속축류팬용 블레이드
JPH10299408A (ja) 1997-04-22 1998-11-10 Hitachi Ltd ガスタービン静翼
US6174135B1 (en) * 1999-06-30 2001-01-16 General Electric Company Turbine blade trailing edge cooling openings and slots
US6490791B1 (en) 2001-06-22 2002-12-10 United Technologies Corporation Method for repairing cracks in a turbine blade root trailing edge
US6929451B2 (en) * 2003-12-19 2005-08-16 United Technologies Corporation Cooled rotor blade with vibration damping device

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5596303A (en) * 1979-01-16 1980-07-22 Mitsubishi Heavy Ind Ltd Manufacturing method of moving blade in rotary unit
JPS63248902A (ja) * 1987-04-03 1988-10-17 Hitachi Ltd ガスタ−ビン静翼
JP2000018001A (ja) * 1998-06-30 2000-01-18 Mitsubishi Heavy Ind Ltd 動翼熱応力軽減装置
US20010016163A1 (en) * 2000-02-23 2001-08-23 Yasuoki Tomita Gas turbine moving blade
US20030138322A1 (en) * 2002-01-23 2003-07-24 Snecma Moteurs Moving blade for a high pressure turbine, the blade having a trailing edge of improved thermal behavior

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* Cited by examiner, † Cited by third party
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PATENT ABSTRACTS OF JAPAN vol. 004, no. 143 (M - 035) 8 October 1980 (1980-10-08) *
PATENT ABSTRACTS OF JAPAN vol. 013, no. 041 (M - 791) 30 January 1989 (1989-01-30) *
PATENT ABSTRACTS OF JAPAN vol. 2000, no. 04 31 August 2000 (2000-08-31) *

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1712782A3 (fr) * 2005-04-07 2011-04-27 General Electric Canada Rainures de décharge de contraintes pour les aubes d'une turbine Francis
EP1712782A2 (fr) * 2005-04-07 2006-10-18 General Electric Canada Rainures de décharge de contraintes pour les aubes d'une turbine Francis
EP1757773A1 (fr) * 2005-08-26 2007-02-28 Siemens Aktiengesellschaft Aube creuse de turbine
JP2007064219A (ja) * 2005-08-26 2007-03-15 Siemens Ag 中空タービン翼
US7845905B2 (en) 2005-08-26 2010-12-07 Siemens Aktiengesellschaft Hollow turbine blade
JP4689558B2 (ja) * 2005-08-26 2011-05-25 シーメンス アクチエンゲゼルシヤフト 中空タービン翼
JP2016539273A (ja) * 2013-10-21 2016-12-15 シーメンス アクティエンゲゼルシャフト タービンブレード
CN106795770B (zh) * 2014-08-27 2018-12-11 西门子股份公司 涡轮叶片和涡轮机
CN106795770A (zh) * 2014-08-27 2017-05-31 西门子股份公司 涡轮叶片和涡轮机
DE102015207760A1 (de) * 2015-04-28 2016-11-03 Siemens Aktiengesellschaft Heißgasführendes Gehäuse
WO2018215519A1 (fr) * 2017-05-23 2018-11-29 Siemens Aktiengesellschaft Procédé de fabrication d'une aube de turbine et aube de turbine
DE102019103640A1 (de) * 2019-02-13 2020-08-13 Mitsubishi Hitachi Power Systems Europe Gmbh Brennstoffdüse mit Dehnungsschlitzen für einen Kohlenstaubbrenner
WO2020165357A1 (fr) 2019-02-13 2020-08-20 Mitsubishi Hitachi Power Systems Europe Gmbh Injecteur de combustible à fentes de dilatation pour un brûleur à charbon pulvérisé
CN114227180A (zh) * 2021-12-29 2022-03-25 哈尔滨汽轮机厂有限责任公司 一种提升汽轮机叶片加工精度的方法

Also Published As

Publication number Publication date
US20050106028A1 (en) 2005-05-19
US7160084B2 (en) 2007-01-09
EP1512489B1 (fr) 2006-12-20
DE50306044D1 (de) 2007-02-01

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