EP3187685A1 - Procede de fabrication d'un corps de base d'un aube de turbine - Google Patents

Procede de fabrication d'un corps de base d'un aube de turbine Download PDF

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Publication number
EP3187685A1
EP3187685A1 EP15202827.0A EP15202827A EP3187685A1 EP 3187685 A1 EP3187685 A1 EP 3187685A1 EP 15202827 A EP15202827 A EP 15202827A EP 3187685 A1 EP3187685 A1 EP 3187685A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
base body
turbine blade
main body
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Withdrawn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
EP15202827.0A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
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 EP15202827.0A priority Critical patent/EP3187685A1/fr
Priority to PCT/EP2016/080179 priority patent/WO2017114644A1/fr
Priority to EP16812708.2A priority patent/EP3362648B1/fr
Priority to JP2018538742A priority patent/JP6586242B2/ja
Priority to US16/063,752 priority patent/US10669857B2/en
Priority to CN201680077021.0A priority patent/CN108474254B/zh
Publication of EP3187685A1 publication Critical patent/EP3187685A1/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Withdrawn legal-status Critical Current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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/027—Arrangements for balancing
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/61—Assembly methods using limited numbers of standard modules which can be adapted by machining
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the invention relates to a method for producing a base body of a turbine blade, comprising at least the successive steps, providing the base body, which successively comprises a blade root, a blade platform and an airfoil along a virtual longitudinal axis, detecting a value of a parameter of the base body representing a vibration characteristic Comparing the detected value with a predetermined target interval and if the detected value is outside the target interval, reducing the mass of the main body. Furthermore, the invention relates to a blade ring for a rotor of an axial flow turbine.
  • a protective layer As a protective layer, a MCrAlY type anticorrosion layer is often applied to the turbine blade produced by a casting process. The application of the protective layer takes place in the region of that surface which is exposed during operation to the hot gas of the gas turbine. This area includes both the airfoil and the platform of the turbine blade on which the airfoil forms.
  • a heat-insulating layer can also be applied in the abovementioned area in order to minimize the heat input from the hot gas into the base material of the turbine blade. The application of the layers thereby alters the vibration behavior of the turbine blade.
  • the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine.
  • care is also taken to ensure that the finished turbine blade as a whole satisfies the requirements for natural resonance, also with regard to the expected rotor speeds.
  • the object of the invention is to provide a method for producing basic bodies of turbine blades, the natural frequencies of which correspond to the requirements for use within a stationary gas turbine. Another object is to provide a blade ring, the blades are particularly robust against induced by the hot gas vibrational excitation.
  • the invention is based on the recognition that the introduction of the recesses for setting the natural frequency need not be made solely on the blade.
  • the measure for influencing the vibration properties of the turbine blades or of their cast base body can also take place on the blade root or on the so-called platform underside.
  • the platform underside is that side of the platform of a turbine blade or the base body, which faces the hot gas side of the platform and thus faces the blade root.
  • the introduction of recesses or the reduction of a dimension below the target value can be provided. Of course, both measures could be combined.
  • the invention proposes that the blade root on the blade root and / or on the underside of the platform has an area whose shape and / or dimensions are chosen so that they have no structural mechanical functions. Due to this property and the dimensions originally provided, the base body comprises at least one region which is regarded as a sacrificial region in order to modify the vibration properties of the base body by reducing the mass there without the functional properties changing as well. To reduce the mass, for example, a recess can be made in a planar side of the blade root. Another example is the reduction in the width of a ridge provided on the platform underside of the turbine bucket.
  • the areas are located where the measures described above can be performed without significantly deteriorating the structural integrity of the body. This leaves the predetermined service life of the turbine blade unaffected.
  • the method can also be applied after the coating of turbine blades with an erosion and / or thermal barrier coating.
  • the method according to the invention is applied in a rather late phase of the manufacturing process of the turbine blades.
  • the base body usually produced in the casting process has already been brought to the specified size before the value of the parameter representing a vibration characteristic is detected.
  • the vibration measurement is carried out on the almost finished turbine blade and thus further manufacturing steps that can also change the vibration characteristics of the body or the turbine blade, at least largely avoided.
  • the method can also be carried out before coating the base body, if it can be predicted by what (average) value the detected value of the parameter changes due to the then subsequently applied coating. Then already in an earlier stage of the manufacturing process, the aforementioned measures can be carried out to select those basic body whose vibration characteristics and values could not be transferred into the associated target intervals despite the implementation of the inventive measures. Hereby expenses for waste can be avoided at an early stage.
  • a turbine blade is understood to mean that which is finished and provided for being able to be attached to a rotor of a turbine without further processing.
  • the basic body of a turbine blade is understood to mean a turbine blade blank which is still in the middle of the manufacturing process, at the end of which the finished turbine blade is located.
  • the invention relates only to some of the manufacturing steps required overall for manufacturing a ready-to-use turbine blade, wherein the method steps mentioned here can also represent the very last production steps for producing the ready-to-use turbine blade.
  • the inventive method 10 is in FIG. 1 shown.
  • the method 10 for producing a basic body 30 (FIG. Fig. 3 ) of a turbine blade comprises in a first step 12 the provision of the main body 30 of the turbine blade.
  • the base body 30 comprises along a virtual longitudinal axis 31 successively a blade root 32, a platform 34 and an airfoil 36.
  • the contour of the blade root 32 is fir-tree-shaped when viewed perpendicularly on its planar end face 38 and merges via a so-called blade neck 40 into an underside 42 of the platform 34.
  • the platform Opposite the underside 42, the platform has a hot gas side 44, at which the airfoil 36 connects monolithically. This is drop-shaped and aerodynamically curved to form a pressure side 46 and a suction side 48.
  • the blade root 32 extends over a length L between the two axially opposite planar end faces 38.
  • a size of at least one parameter of the base body 30 is detected, wherein at least one of the parameters represents a vibration property of the base body.
  • the natural frequencies and the vibration modes are detected by the usual methods.
  • a third production step 16 the detected value (s) is compared with an (associated) target interval. If the detected values lie outside the associated target interval, vibration-changing measures are carried out according to the invention on the blade root 32 and / or on the underside 42 of the platform as the fourth production step.
  • These can be the introduction of one or more recesses 50 and / or the reduction of the previous dimensions such as length, width or height of certain features arranged there.
  • the length L of the blade root 32 can be shortened by a few hundredths of a millimeter to a level which is below the otherwise prescribed setpoint for the length L.
  • the reduction of the mass of the main body 30 takes place in the region 49, which were provided in particular for it.
  • the weight and possibly the contact surface of the turbine blade changes under centrifugal force, which has a favorable effect on the vibration characteristic of the turbine blade.
  • the second, third and fourth steps 14, 16, 18 are repeatedly executed as a series in order to check the suitability of the main body 30. Only when the investigated turbine blades meet the requirements with regard to the vibration characteristic is it passed on to the further production process.
  • the base body 30 or the turbine blade may also be one which is or should be provided with a protective layer.
  • the protective layer is preferably a corrosion protection layer of the MCrAlY type.
  • a two-layer or multi-layer protective layer comprising, as a bondcoat, a layer of the MCrAlY type on which a ceramic thermal barrier coating (TBC) has been applied further out.
  • TBC ceramic thermal barrier coating
  • the natural frequency can not be strongly influenced enough that it meets the requirements. In this case, the body is not suitable for commercial use.
  • the coating of the main body 30 can be carried out before the first execution of the second production step 14 or after the last time the fourth production step 18 is carried out.
  • recess 50 By means of the end face arranged in the blade root 32 recess 50 is a frequency shift of the natural frequency.
  • the shape of the recesses 50 is arbitrary.
  • Fig. 2 shows a second flowchart for another embodiment of a manufacturing process.
  • the production method comprises the previously mentioned steps 12, 14, 16, 18, supplemented by production steps 13 and 19 to be carried out partially between them.
  • the production step 13 was completed, in which the base body 30 is at least largely made to measure.
  • the dimensions of the main body 30 that are subject to the greasing tolerances are brought to the planned nominal values, which in turn can also be subject to tolerances.
  • a hitherto uncoated base body 30 can be provided with an erosion and / or thermal barrier coating.
  • the invention thus proposes a method for producing turbine blades or their basic bodies 30, whose frequency characteristic can be adapted particularly easily to the required boundary conditions.
  • a method is specified with which the vibration characteristic of the turbine blade can be set particularly easily and variably. This can reduce the reject rate in the manufacture of turbine blades.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15202827.0A 2015-12-28 2015-12-28 Procede de fabrication d'un corps de base d'un aube de turbine Withdrawn EP3187685A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP15202827.0A EP3187685A1 (fr) 2015-12-28 2015-12-28 Procede de fabrication d'un corps de base d'un aube de turbine
PCT/EP2016/080179 WO2017114644A1 (fr) 2015-12-28 2016-12-08 Procédé de fabrication d'un corps de base d'une aube de turbine
EP16812708.2A EP3362648B1 (fr) 2015-12-28 2016-12-08 Procede de fabrication d'un corps de base d'un aube de turbine
JP2018538742A JP6586242B2 (ja) 2015-12-28 2016-12-08 タービンブレードのベース本体を製造するための方法
US16/063,752 US10669857B2 (en) 2015-12-28 2016-12-08 Method for producing a base body of a turbine blade
CN201680077021.0A CN108474254B (zh) 2015-12-28 2016-12-08 用于制造涡轮动叶的基体的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15202827.0A EP3187685A1 (fr) 2015-12-28 2015-12-28 Procede de fabrication d'un corps de base d'un aube de turbine

Publications (1)

Publication Number Publication Date
EP3187685A1 true EP3187685A1 (fr) 2017-07-05

Family

ID=55027506

Family Applications (2)

Application Number Title Priority Date Filing Date
EP15202827.0A Withdrawn EP3187685A1 (fr) 2015-12-28 2015-12-28 Procede de fabrication d'un corps de base d'un aube de turbine
EP16812708.2A Active EP3362648B1 (fr) 2015-12-28 2016-12-08 Procede de fabrication d'un corps de base d'un aube de turbine

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP16812708.2A Active EP3362648B1 (fr) 2015-12-28 2016-12-08 Procede de fabrication d'un corps de base d'un aube de turbine

Country Status (5)

Country Link
US (1) US10669857B2 (fr)
EP (2) EP3187685A1 (fr)
JP (1) JP6586242B2 (fr)
CN (1) CN108474254B (fr)
WO (1) WO2017114644A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0537922A1 (fr) * 1991-10-04 1993-04-21 General Electric Company Amortisseur de vibrations des plates-formes d'aubes de turbines
EP1905950A1 (fr) * 2006-09-21 2008-04-02 Siemens Aktiengesellschaft Aube de turbine
EP1985803A1 (fr) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Procédé pour la fabrication des aubes de turbine avec revêtement
WO2015157381A1 (fr) * 2014-04-10 2015-10-15 United Technologies Corporation Inspection par résonance en temps réel pour fabrication additive

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6390775B1 (en) * 2000-12-27 2002-05-21 General Electric Company Gas turbine blade with platform undercut
US6786696B2 (en) 2002-05-06 2004-09-07 General Electric Company Root notched turbine blade
US6814543B2 (en) * 2002-12-30 2004-11-09 General Electric Company Method and apparatus for bucket natural frequency tuning
FR2851285B1 (fr) * 2003-02-13 2007-03-16 Snecma Moteurs Realisation de turbines pour turbomachines ayant des aubes a frequences de resonance ajustees differentes et procede d'ajustement de la frequence de resonance d'une aube de turbine
DE102005006414A1 (de) * 2005-02-12 2006-08-24 Mtu Aero Engines Gmbh Verfahren zum Bearbeiten eines integral beschaufelten Rotors
US9410436B2 (en) * 2010-12-08 2016-08-09 Pratt & Whitney Canada Corp. Blade disk arrangement for blade frequency tuning
EP2762678A1 (fr) * 2013-02-05 2014-08-06 Siemens Aktiengesellschaft Procédé de désaccordage d'une matrice d'aube directrice
EP2957792B1 (fr) * 2014-06-20 2020-07-29 United Technologies Corporation Rotor à réponse vibratoire réduite pour une turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0537922A1 (fr) * 1991-10-04 1993-04-21 General Electric Company Amortisseur de vibrations des plates-formes d'aubes de turbines
EP1905950A1 (fr) * 2006-09-21 2008-04-02 Siemens Aktiengesellschaft Aube de turbine
EP1985803A1 (fr) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Procédé pour la fabrication des aubes de turbine avec revêtement
WO2015157381A1 (fr) * 2014-04-10 2015-10-15 United Technologies Corporation Inspection par résonance en temps réel pour fabrication additive

Also Published As

Publication number Publication date
CN108474254B (zh) 2020-04-24
JP2019500545A (ja) 2019-01-10
CN108474254A (zh) 2018-08-31
EP3362648A1 (fr) 2018-08-22
US10669857B2 (en) 2020-06-02
EP3362648B1 (fr) 2019-10-23
US20190338645A1 (en) 2019-11-07
WO2017114644A1 (fr) 2017-07-06
JP6586242B2 (ja) 2019-10-02

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