EP2998507A1 - Eine gekühlte Turbinenschaufel, welche interne Verbindungsrippen zwischen den Kühlräumen beinhaltet, welche Sollbruchstellen zur Verringerung von Thermischen Spannungen aufweisen - Google Patents

Eine gekühlte Turbinenschaufel, welche interne Verbindungsrippen zwischen den Kühlräumen beinhaltet, welche Sollbruchstellen zur Verringerung von Thermischen Spannungen aufweisen Download PDF

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Publication number
EP2998507A1
EP2998507A1 EP14184930.7A EP14184930A EP2998507A1 EP 2998507 A1 EP2998507 A1 EP 2998507A1 EP 14184930 A EP14184930 A EP 14184930A EP 2998507 A1 EP2998507 A1 EP 2998507A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
rib
turbine
crack
rib element
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Withdrawn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
EP14184930.7A
Other languages
German (de)
English (en)
French (fr)
Inventor
Fathi Ahmad
Björn Buchholz
Stephen A. Camillieri
Nihal Kurt
Radan RADULOVIC
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 EP14184930.7A priority Critical patent/EP2998507A1/de
Priority to US15/509,625 priority patent/US10287892B2/en
Priority to PCT/EP2015/069618 priority patent/WO2016041761A1/de
Priority to JP2017520962A priority patent/JP6346993B2/ja
Priority to CN201580049802.4A priority patent/CN106715833B/zh
Priority to EP15756632.4A priority patent/EP3161264A1/de
Publication of EP2998507A1 publication Critical patent/EP2998507A1/de
Withdrawn legal-status Critical Current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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • 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

Definitions

  • the invention relates to a turbine blade with an internally cooled turbine blade in which a cavity is divided by rib elements in at least one coolant-carrying cooling channel.
  • the invention further relates to a turbine, in particular a gas turbine, with at least one turbine stage comprising a plurality of turbine blades.
  • a turbine blade of this type is equipped with an internally cooled turbine blade in order to withstand even high temperatures prevailing in the turbine, especially in a hot gas turbine, thermally and mechanically.
  • the turbine blades are often thermally and mechanically loaded higher, in which case it hardly plays a role, whether it is the turbine blade to a vane or a blade of the turbine.
  • an internally cooled turbine blade has a cavity through which a cooling medium can be passed.
  • a fin element or a plurality of rib elements is usually additionally arranged in order to form at least one cooling channel with an often meandering cooling channel profile in the cavity.
  • both a front side wall thereof and a corresponding rear wall of the turbine airfoil may be in the region of the turbine airfoil stiffening rib element thermo-mechanically high stress.
  • partially critical states of stress can be set on the turbine blade, whereby the turbine blade is exposed to particularly disadvantageous loading conditions in some areas, which there can lead to faster material fatigue over time.
  • the transition regions between the rib element and the front or the rear side wall of the turbine blade leaf are to be mentioned in particular.
  • the present object is achieved by a turbine blade with an internally cooled turbine blade in which a cavity is divided by rib elements in at least one coolant cooling channel, wherein in at least one of the rib members means for generating a longitudinally extending ribs of the element at least partially extending division crack are arranged.
  • the dividing crack in the rib element can be produced particularly simply if corresponding means for generating the dividing crack are introduced for this purpose in the relevant rib element. In this way, the course of the dividing crack within the rib element in the longitudinal direction and transverse direction can already be well predefined.
  • thermo-mechanical stresses in critical areas of the turbine airfoil can significantly reduce thermo-mechanical stresses in critical areas of the turbine airfoil.
  • the present purpose-formed split crack is configured such that it enables an improved stress distribution within the rib element, in transition areas between the actual rib element and the front wall of the turbine blade and / or the rear wall of the turbine blade, but also in the actual outer walls of the turbine blade.
  • a reduction in stress of at least 10% or preferably more than 20% or 25% can be achieved, in particular in critical areas around the fin element end, but also within the rib element itself.
  • the term “material fatigue” particularly includes fatigue cracking, which is caused especially by thermo-mechanical fatigue of the airfoil material.
  • LCF fatigue low cycle fatigue
  • ie short-term or low-load cycle fatigue should be mentioned in terms of a low load cycle number.
  • the number of load changes that can be achieved can be considerably increased, and thus, in particular, the danger of premature LCF fatigue can be significantly reduced if, according to the invention, a suitably suitable division crack is provided on the rib element. It has been found that a relevant LCF life expectancy of a turbine blade can be significantly increased by the dividing crack according to the invention within the rib element.
  • the relevant rib element is designed by the division crack such that thermo-mechanical stresses occurring within the turbine blade leaf and thus also a related material fatigue can be reduced.
  • the dividing crack does not interfere with this, or at least only to a negligible extent, the actual separating function, which the rib elements arranged in the cavity exert with respect to a multiply wound cooling channel.
  • such a separation crack can be provided only on a rib element that configures a cooling channel or on a plurality of rib elements delimiting the cooling channel.
  • the means for generating the division crack can be configured in many ways.
  • the means for generating can be provided if the means for generating the dividing crack comprise a material weakening, in particular a notch.
  • Such material weakening can be of various kinds. Preferably, it is present as a notch formed in the rib member.
  • the means for generating and especially by means of the material weakening structurally simple, a well-functioning crack start point or line-like crack initiation area are formulated on the rib element.
  • the material weakening or the notch may be formed on the head side on the rib element as a crack starting point or along the longitudinal extension of the rib element as a crack start line.
  • the means for generating the dividing crack thus formulate starting aids, from which the dividing crack propagates in the longitudinal direction and / or in the transverse direction through the rib element.
  • the means for generating can also be provided by a pin arranged on a casting core, by means of which a notch is produced at the end of the rib element during casting. After casting the turbine blade, remove the pin with the casting core. The notch then serves as a crack starting point for a division crack, which can only arise in operation with sufficiently large mechanical load and then grows along the rib on.
  • the means for generating the dividing crack on the rib element can be implemented if cumulatively or alternatively means for generating the dividing crack are driven in the head side into the at least one rib element.
  • appropriately designed means for generating the dividing crack can be particularly easily introduced or driven into the rib element if the means for generating the dividing fracture comprise a wedge element or a mandrel element.
  • the present object of the invention according to another aspect of the invention is also achieved by a turbine blade with an internally cooled turbine blade in which a cavity is divided by rib elements in at least one coolant-carrying cooling channel, wherein at least one of the rib elements means for generating a predetermined breaking point in the at least a rib member to produce a in the longitudinal direction of the at least one rib member at least partially extending dividing crack.
  • the relevant rib element comprises such means for generating a predetermined breaking point in the rib element
  • the profile of the dividing crack in the longitudinal direction of the rib element can be generated in a particularly precise predetermined manner.
  • the dividing crack extends even more precisely through the rib element both in a predefined longitudinal direction and in a predefined transverse direction.
  • means for generating the predetermined breaking point comprise a material weakening or a plurality of material weakenings within the at least one rib element.
  • the material weakening and thus also the predetermined breaking point are configured linearly in the longitudinal direction of the rib element, so that the dividing crack along the rib element can form correspondingly defined.
  • the means for generating the predetermined breaking point formulate alternative starting aids, from which the Dividing crack propagates in the transverse direction through the rib element.
  • This line-like weakening of the material or the predetermined breaking point can be structurally particularly simply designed as a notch on a rib element longitudinal side.
  • the predetermined breaking point can also be formulated by a multiplicity of point-like material weakenings, which are arranged linearly along the longitudinal extent of the rib element one after the other approximately on a rib element longitudinal side.
  • the means for generating the predetermined breaking point are arranged on both sides of the at least one rib element within the at least one rib element, the profile of the dividing crack can be produced even more precisely within the rib element.
  • the dividing crack extends over more than half or over more than two-thirds of the length of the at least one rib element, preferably over the entire length of the at least one rib element. Alone with a partial rip formed only partially along the rib element, sufficient decoupling of the front side wall and the rear side wall in the region of the rib element can be achieved.
  • the dividing crack extends from a first rib element side surface to a second rib element side surface opposite the first rib element side surface.
  • the dividing crack hereby tensions a dividing tear plane, which is arranged substantially perpendicular to at least one of the rib element side faces.
  • this division tear plane is oriented approximately the same as the turbine blade outer walls.
  • the object of the invention is also achieved by a turbine, in particular a gas turbine, having at least one turbine stage comprising a plurality of turbine blades, wherein the at least one turbine stage comprises turbine blades and / or turbine vanes according to a turbine blade according to one of the features described herein.
  • the rib element is designed in such a way that the division crack is generated during startup of the turbine, namely by the rib element having as a whole such a thin rib element cross-section which sooner or later tears during operation of the turbine by a division crack in the sense of the invention.
  • the separation crack is initiated during a startup on the basis of the present means for generating the division crack and / or the means for generating the predetermined breaking point.
  • the split crack can be advantageously generated within the fin member when the turbine is in operation.
  • turbine blade 1 is a guide blade 2 of a hot gas turbine, not shown here.
  • the turbine blade 1 has an internally cooled turbine blade 3, wherein, as shown in FIG. 1 at least partially the inside 4 of the front side wall 5 of the turbine airfoil 3 is shown.
  • On the right hand side there is a leading edge region 6 of the turbine blade 3.
  • On the left hand side there is a trailing edge region 7 of the turbine blade 3, on which a multiplicity of cooling air outlet bores 8 (numbered only by way of example) are present.
  • the turbine blade 3 has a cavity 10, wherein according to the illustration of the FIG. 1 this cavity 10 is only partially illustrated by the inside 4.
  • FIG. 1 further recognizes two rib elements 11 and 12 located in the cavity 10, by means of which a multiply wound cooling channel 13 with a meandering cooling channel course within the cavity 10 is configured.
  • cooling air can be passed as coolant through the turbine blade 3 in order to cool it from the inside.
  • the cooling air coming from a foot region 14 of the turbine blade root 15 flows through the turbine blade 3, with part of the cooling air continuing in the direction 16 into a region 17 of the turbine blade tip 18.
  • the meandering cooling channel course of the coiled cooling channel 13 is configured, at least in the region of the partial view shown, by the two rib elements 11 and 12, the first rib element 11 spatially separating two cooling channel sections.
  • the first rib element 11 ends freely in the cooling channel 13 with its rib element end 24 defined by its head side 23.
  • thermo-mechanical stresses within the turbine blade 3 can be significantly reduced by this dividing crack 30, which pulls through the rib element 11, which also reduces the risk of premature material fatigue at the surrounding regions 28.
  • corresponding means 33 for producing the dividing crack 30 at least partially extending in the longitudinal direction 29 of the rib element 11 in the form of a wedge element 34 are arranged on the head side 23.
  • the wedge element 34 was in this case inserted through a present in the turbine blade 1, but not shown here functional opening and thereby hammered into the head side 23 of the rib member 11.
  • means 35 for producing a predetermined breaking point 36 in the form of notches 39 running linearly on both rib side faces 37 and 38 are additionally realized on the rib element 11.
  • these notches 39 make a crack starting point (not separately numbered) on the rib member 11.
  • the predetermined breaking point 36 or the crack starting line may extend over the entire length of the rib element 11, or as shown in this embodiment, only over a partial distance along the rib member 11. It is crucial that at least in sections a material weakening is provided on the corresponding rib member 11 to to create a precisely extending dividing crack 30.
  • the means 33 for generating the dividing crack 30 can be completely dispensed with.
  • the means 33 for generating the division crack 30 may also be provided in the casting core of a casting mold in order to produce only a notch as a crack starting point on the rib element 11.
  • the means 33 for producing the dividing crack 30 are subsequently removed again with the casting mold, leaving only the notch on the ribbed element 11.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP14184930.7A 2014-09-16 2014-09-16 Eine gekühlte Turbinenschaufel, welche interne Verbindungsrippen zwischen den Kühlräumen beinhaltet, welche Sollbruchstellen zur Verringerung von Thermischen Spannungen aufweisen Withdrawn EP2998507A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP14184930.7A EP2998507A1 (de) 2014-09-16 2014-09-16 Eine gekühlte Turbinenschaufel, welche interne Verbindungsrippen zwischen den Kühlräumen beinhaltet, welche Sollbruchstellen zur Verringerung von Thermischen Spannungen aufweisen
US15/509,625 US10287892B2 (en) 2014-09-16 2015-08-27 Turbine blade and turbine
PCT/EP2015/069618 WO2016041761A1 (de) 2014-09-16 2015-08-27 Eine gekühlte turbinenschaufel, welche interne verbindungsrippen zwischen den kühlräumen beinhaltet, welche sollbruchstellen zur verringerung von thermischen spannungen aufweisen
JP2017520962A JP6346993B2 (ja) 2014-09-16 2015-08-27 タービンブレード及びタービン
CN201580049802.4A CN106715833B (zh) 2014-09-16 2015-08-27 涡轮叶片和涡轮
EP15756632.4A EP3161264A1 (de) 2014-09-16 2015-08-27 Eine gekühlte turbinenschaufel, welche interne verbindungsrippen zwischen den kühlräumen beinhaltet, welche sollbruchstellen zur verringerung von thermischen spannungen aufweisen

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14184930.7A EP2998507A1 (de) 2014-09-16 2014-09-16 Eine gekühlte Turbinenschaufel, welche interne Verbindungsrippen zwischen den Kühlräumen beinhaltet, welche Sollbruchstellen zur Verringerung von Thermischen Spannungen aufweisen

Publications (1)

Publication Number Publication Date
EP2998507A1 true EP2998507A1 (de) 2016-03-23

Family

ID=51570285

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14184930.7A Withdrawn EP2998507A1 (de) 2014-09-16 2014-09-16 Eine gekühlte Turbinenschaufel, welche interne Verbindungsrippen zwischen den Kühlräumen beinhaltet, welche Sollbruchstellen zur Verringerung von Thermischen Spannungen aufweisen
EP15756632.4A Pending EP3161264A1 (de) 2014-09-16 2015-08-27 Eine gekühlte turbinenschaufel, welche interne verbindungsrippen zwischen den kühlräumen beinhaltet, welche sollbruchstellen zur verringerung von thermischen spannungen aufweisen

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15756632.4A Pending EP3161264A1 (de) 2014-09-16 2015-08-27 Eine gekühlte turbinenschaufel, welche interne verbindungsrippen zwischen den kühlräumen beinhaltet, welche sollbruchstellen zur verringerung von thermischen spannungen aufweisen

Country Status (5)

Country Link
US (1) US10287892B2 (ja)
EP (2) EP2998507A1 (ja)
JP (1) JP6346993B2 (ja)
CN (1) CN106715833B (ja)
WO (1) WO2016041761A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10844726B2 (en) 2017-10-23 2020-11-24 MTU Aero Engines AG Blade and rotor for a turbomachine and turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110185498B (zh) * 2019-05-27 2021-11-12 中国航发湖南动力机械研究所 防轮盘爆裂叶片及其薄弱结构的设计方法
US11459894B1 (en) 2021-03-10 2022-10-04 Raytheon Technologies Corporation Gas turbine engine airfoil fairing with rib having radial notch

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Publication number Priority date Publication date Assignee Title
US3973874A (en) * 1974-09-25 1976-08-10 General Electric Company Impingement baffle collars
WO2007012592A1 (de) * 2005-07-27 2007-02-01 Siemens Aktiengesellschaft Gekühlte turbinenschaufel für eine gasturbine und verwendung einer solchen turbinenschaufel
EP1757773A1 (de) * 2005-08-26 2007-02-28 Siemens Aktiengesellschaft Hohle Turbinenschaufel
EP1895102A1 (de) * 2006-08-23 2008-03-05 Siemens Aktiengesellschaft Beschichtete Turbinenschaufel

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Publication number Priority date Publication date Assignee Title
US5337805A (en) 1992-11-24 1994-08-16 United Technologies Corporation Airfoil core trailing edge region
JP3040660B2 (ja) 1994-06-06 2000-05-15 三菱重工業株式会社 ガスタービン動翼プラットフォームの冷却機構
JP3642537B2 (ja) * 1995-03-23 2005-04-27 株式会社東芝 ガスタービン冷却翼
JP2000018001A (ja) * 1998-06-30 2000-01-18 Mitsubishi Heavy Ind Ltd 動翼熱応力軽減装置
US6428273B1 (en) * 2001-01-05 2002-08-06 General Electric Company Truncated rib turbine nozzle
JP2003322003A (ja) * 2002-05-02 2003-11-14 General Electric Co <Ge> 後方に流れる単一の３経路蛇行冷却回路を有するタービン翼形部
US20050265839A1 (en) * 2004-05-27 2005-12-01 United Technologies Corporation Cooled rotor blade
JP2010190198A (ja) * 2009-02-20 2010-09-02 Mitsubishi Heavy Ind Ltd タービン用翼

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3973874A (en) * 1974-09-25 1976-08-10 General Electric Company Impingement baffle collars
WO2007012592A1 (de) * 2005-07-27 2007-02-01 Siemens Aktiengesellschaft Gekühlte turbinenschaufel für eine gasturbine und verwendung einer solchen turbinenschaufel
EP1757773A1 (de) * 2005-08-26 2007-02-28 Siemens Aktiengesellschaft Hohle Turbinenschaufel
EP1895102A1 (de) * 2006-08-23 2008-03-05 Siemens Aktiengesellschaft Beschichtete Turbinenschaufel

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10844726B2 (en) 2017-10-23 2020-11-24 MTU Aero Engines AG Blade and rotor for a turbomachine and turbomachine

Also Published As

Publication number Publication date
WO2016041761A1 (de) 2016-03-24
US10287892B2 (en) 2019-05-14
JP2017532493A (ja) 2017-11-02
CN106715833A (zh) 2017-05-24
JP6346993B2 (ja) 2018-06-20
CN106715833B (zh) 2019-12-06
EP3161264A1 (de) 2017-05-03
US20170260863A1 (en) 2017-09-14

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