EP3362648A1 - Procédé de fabrication d'un corps de base d'une aube de turbine - Google Patents

Procédé de fabrication d'un corps de base d'une aube de turbine

Info

Publication number
EP3362648A1
EP3362648A1 EP16812708.2A EP16812708A EP3362648A1 EP 3362648 A1 EP3362648 A1 EP 3362648A1 EP 16812708 A EP16812708 A EP 16812708A EP 3362648 A1 EP3362648 A1 EP 3362648A1
Authority
EP
European Patent Office
Prior art keywords
blade
turbine
turbine blade
base body
platform
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
EP16812708.2A
Other languages
German (de)
English (en)
Other versions
EP3362648B1 (fr
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
Publication of EP3362648A1 publication Critical patent/EP3362648A1/fr
Application granted granted Critical
Publication of EP3362648B1 publication Critical patent/EP3362648B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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 basic body, which along a virtual longitudinal axis successively comprises a blade root, a blade platform and an airfoil, detecting a value of a parameter representing a vibration characteristic of
  • the invention relates to a blade ring for a rotor of an axially flowed through turbine.
  • a corrosion protective layer of the MCrAlY type is frequently ⁇ fig ⁇ be applied to the produced in a casting process turbine blade.
  • the application of the protective layer takes place in the area of that surface which during operation is exposed to the hot gas of the gas turbine.
  • This range includes both the airfoil and the platform of the turbine ⁇ shovel to which the airfoil anformt.
  • a heat insulating layer within the aforementioned range may be applied to keep the heat input from the hot gas into the base material of the turbine ⁇ shovel as low as possible. The application of the layers thereby alters the vibration behavior of the turbine blade.
  • Hot gas-based vibration excitation with the respective excitation frequencies does not lead to an unduly high vibration of the blade. Accordingly, in the prior art, the turbine blades are designed such that their natural frequency deviates from the excitation frequencies of the stationary gas turbine. In the development of the turbine blade is also taken to ensure that the finished turbine blade total meets the requirements be ⁇ lug the natural resonance, even in terms of to be expected rotor speeds.
  • Vibration response of the turbine blade and in particular ih ⁇ res airfoil detected Provided that the vibratory response of the turbine blade does not satisfy the predetermined frequency values at natural frequency, this is to be discarded or to manipulate ⁇ means of suitable measures so that it is meets the requirements of the natural frequency and therefore suitable for the operation.
  • a recess, a ⁇ accommodated in the tip of the blade whereby the Mass of the turbine blade at its rem free, swingable end can be reduced.
  • the vibration characteristic is positively influenced.
  • Their Eigenfre ⁇ frequency can be moved by removing the mass to higher values.
  • 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 the provision of a blade ring, ⁇ sen running blades particularly robust against one of
  • the invention is based on the realization that the Einbrin ⁇ gen of the recesses must be made to adjust the natural frequency, not only on the airfoil.
  • 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 be provided below the setpoint.
  • both measures could be combined with each other.
  • the advantages of both measures is that they do not change the constructive ⁇ turmechanische integrity of the blade worsen the aerodynamics. This makes it possible to achieve the predetermined life span and power values of the blade body or the turbine blade ultimately resulting therefrom.
  • 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 of the width of a web which is provided on the platform underside of the turbine blade.
  • the areas are located there, where the measures described above can be carried out without changing the time required for the occurring during the operation of relevant mechanical stress devischa ⁇ African integrity of the base body significantly 29lech ⁇ tert. Consequently, those moments of inertia and that rigidity of the turbine blade to be changed, which border the life of the turbine blade in any case not be ⁇ .
  • the range in question is or are the ⁇ be taken of those areas outside surfaces of the body which are überströmbar of a hot gas.
  • 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.
  • This ensures that the vibration measurement is carried out on the almost finished turbine blade and thus further Fer ⁇ tion steps that can change the vibration characteristics of the body or the turbine blade, at least largely avoided.
  • the method can also prior to the coat of the base body are performed when ahead determinable by which the (average) value of the detected value of Para ⁇ meters due to the then subsequently applied coating changes.
  • the aforementioned measures can be carried out in order 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. In this way, the expense of waste can be avoided at an early stage.
  • FIG. 1 shows a flowchart with the different production steps of a method according to the invention for producing a main body of a turbine blade
  • FIG. 2 shows a flowchart with further manufacturing steps
  • FIG. 3 shows a perspective view of an underside of a base body of a turbine blade.
  • the method 10 according to the invention is shown in FIG.
  • the method 10 for producing a main body 30 (FIG.
  • a turbine blade comprises in a first step 12, the provision of the main body 30 of the turbine blade ⁇ blade.
  • the main body 30 comprises along a virtual Longitudinal axis 31 successively a blade root 32, a platform 34 and an airfoil 36th
  • 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 egg ⁇ gene 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, according to the invention vibration-altering measures are carried out 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 County ⁇ ge L of the blade root can be shortened by a few hundredths of a millimeter to a level 32 which is below the otherwise provided target value 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. This changes the weight and possibly the contact surface of the turbine run ⁇ fel under centrifugal force, which has a favorable effect on the vibration property of the turbine blade. If in doubt, the second, third and fourth and fourth
  • Steps 14, 16, 18 repeatedly executed as a series to check the suitability of the base body 30. Only when the un ⁇ ters visited turbine blades meets the requirements in terms of vibration property, this whe- the reindeer manufacturing process is passed.
  • 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 type
  • Protective layer may be provided, which comprises as a bondcoat a layer of the type MCrAlY on which a ceramic thermal barrier coating (TBC) has been applied further out.
  • TBC ceramic thermal barrier coating
  • 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 is a frequency shift of the natural frequency.
  • the shape of the recesses 50 is arbitrary.
  • FIG. 2 shows a second flowchart for a further embodiment of a manufacturing method.
  • the manufacturing method includes the previously mentioned steps 12, 14, 16, 18, supplemented by partial DA between intended preparation steps 13 and 19, the preparation step 13 in which the base body 30 was He ⁇ supplemented on the one hand made at least largely to size becomes.
  • 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 allows the off ⁇ scrap rates in the production of turbine blades re- cuted be.

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)

Abstract

L'invention concerne un procédé de fabrication d'aubes mobiles de turbine ou de leurs corps de base (30), dont la caractéristique de fréquence peut être adaptée de manière particulièrement simple aux conditions marginales requises. Selon l'invention, des évidements (50) sont ménagés dans l'emplanture d'aube (32) et/ou une dimension est réduite de façon à être inférieure à la valeur de consigne correspondante, lorsque le corps de base (30) présente des caractéristiques vibratoires insuffisantes. On obtient ainsi une méthode permettant d'ajuster de manière particulièrement simple et variable la caractéristique vibratoire de l'aube mobile de turbine. Cela permet de réduire le taux de rebut lors de la fabrication d'aubes mobiles de turbine.
EP16812708.2A 2015-12-28 2016-12-08 Procede de fabrication d'un corps de base d'un aube de turbine Active EP3362648B1 (fr)

Applications Claiming Priority (2)

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

Publications (2)

Publication Number Publication Date
EP3362648A1 true EP3362648A1 (fr) 2018-08-22
EP3362648B1 EP3362648B1 (fr) 2019-10-23

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 Before (1)

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

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)

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5215442A (en) * 1991-10-04 1993-06-01 General Electric Company Turbine blade platform damper
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
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
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
US20170028703A1 (en) * 2014-04-10 2017-02-02 United Technologies Corporation Real-time resonant inspection for additive manufacturing
EP2957792B1 (fr) * 2014-06-20 2020-07-29 United Technologies Corporation Rotor à réponse vibratoire réduite pour une turbine à gaz

Also Published As

Publication number Publication date
CN108474254B (zh) 2020-04-24
JP2019500545A (ja) 2019-01-10
CN108474254A (zh) 2018-08-31
US10669857B2 (en) 2020-06-02
EP3362648B1 (fr) 2019-10-23
US20190338645A1 (en) 2019-11-07
EP3187685A1 (fr) 2017-07-05
WO2017114644A1 (fr) 2017-07-06
JP6586242B2 (ja) 2019-10-02

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