EP2187005B1 - Procédé de fabrication d'une fixation d'aube de turbine pour un dispositif de détermination de la quantité d'écoulement - Google Patents

Procédé de fabrication d'une fixation d'aube de turbine pour un dispositif de détermination de la quantité d'écoulement Download PDF

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Publication number
EP2187005B1
EP2187005B1 EP08019938.3A EP08019938A EP2187005B1 EP 2187005 B1 EP2187005 B1 EP 2187005B1 EP 08019938 A EP08019938 A EP 08019938A EP 2187005 B1 EP2187005 B1 EP 2187005B1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
base body
sealing element
dimensional model
recess
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.)
Not-in-force
Application number
EP08019938.3A
Other languages
German (de)
English (en)
Other versions
EP2187005A1 (fr
Inventor
Roman Dr. Beyer
Uwe Dunkel
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
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP08019938.3A priority Critical patent/EP2187005B1/fr
Priority to US12/616,162 priority patent/US20100124503A1/en
Publication of EP2187005A1 publication Critical patent/EP2187005A1/fr
Application granted granted Critical
Publication of EP2187005B1 publication Critical patent/EP2187005B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • 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
    • F05D2230/68—Assembly methods using auxiliary equipment for lifting or holding
    • 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
    • F05D2260/80—Diagnostics
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Definitions

  • the invention relates to a method for producing a turbine blade holder for a flow rate determination device and to a turbine blade holder which can be produced by the method.
  • Turbine blades are exposed to high temperatures during operation in a chemically aggressive atmosphere, which can lead to their damage. It is therefore necessary to protect the blades by cooling.
  • cooling air channels are formed in the interior of the turbine blades, which communicate with cooling air holes through the outer wall of the turbine blade. During operation, cooling air is injected through openings in the cooling air channels in the blade root, which flows through the channels to the cooling air holes and out of these. The outflowing cooling air reduces the temperature of the turbine blade.
  • a turbine blade has hitherto been positioned on a metallic base body. Then, a flexible sealing body with the negative geometry of the blade root made of a two-component resin is cast around the base of the blade on the basic body in a positive and non-positive manner. To make this possible, it is necessary to prepare the turbine blade beforehand. Thus, parts of the blade must be milled away or cut away, openings closed, Gieskerne mounted and seals are attached.
  • a measuring apparatus is known with which the flow rate of a cooling medium can be determined by a gas turbine blade with internal cooling channels.
  • the turbine blade is in one of a Fixed metal frame existing turbine blade holding member and sealed with an intermediate wedge-shaped sealing element.
  • the metal frame is attached to a test chamber of a flowmeter.
  • a turbine bucket mounting is described with an inflow channel for the supply of a cooling fluid to internal cooling channels of a turbine blade mounted in the holder.
  • the holder has in the region of the turbine blade base an introduced sealing body made of an elastomeric material with which a lateral escape of the cooling fluid is to be prevented.
  • the object of the invention is therefore to provide a method for producing a turbine blade holder for a flow rate determination device, with the aid of a turbine blade support can be obtained, which meets all sealing, positioning and support requirements.
  • This object is achieved according to the invention by providing a base body of the turbine blade holder with inflow channel formed therein and a three-dimensional model of a turbine blade with a recess having the negative geometry of a seal element to be produced, placing the three-dimensional model on the base body and in one of the contours of the Recess and limited by the body cavity around the inflow around the sealing element applied to the body.
  • the sealing element is poured onto the base body. In this case, the limited by the contour of the recess and the body cavity acts as a mold for the casting material.
  • a basic body of the holder is produced, in which an inflow channel for air or another test fluid is formed.
  • a three-dimensional model of the turbine blade to be tested with the aid of the device is created, which has a recess with the negative geometry of the sealing element to be produced.
  • the model is placed on the base body, wherein the contour of the recess and the base define a cavity around the inflow channel, in which the sealing element is applied to the base body.
  • the basic idea of the invention is to use, instead of the turbine blade itself, a three-dimensional model of this for producing the turbine blade holder. It is particularly advantageous that the negative geometry of the sealing element is already integrated in the model. This makes it possible in a simple manner to apply a sealing element on the base body, which exactly corresponds to the spatial requirements of the turbine blade to be examined. For this reason, the sealing element also meets all sealing, positioning and support requirements. In addition, the costly procurement of turbine blades from mass production is eliminated. Finally, the model can also be easily reproduced as often as desired at low cost.
  • a CAD model in particular an STL model, of the turbine blade to which the recess is added for the creation of the three-dimensional model. Then, based on the modified CAD model, the three-dimensional model is created.
  • the CAD model that is usually already developed during the design of turbine blades can be used to provide, after appropriate modification, i. complement of a recess with which help to create a three-dimensional model.
  • the particular advantage here is that modifications to the three-dimensional model or to the sealing element that can be produced with its aid can be made quickly and easily by adapting the CAD model.
  • the three-dimensional model of the turbine blade can be produced by stereolithography, laser sintering or and / or by Oriol milling. Especially if a modified CAD model of the turbine blade is used, the three-dimensional model can be created so fast, automated and with high precision.
  • a sealing element made of silicone can be applied to the base body.
  • a sealing element made of this material shows a particularly high sealing effect.
  • the recess at least partially form with the negative shape of a sealing lip.
  • a sealing element with a sealing lip can be obtained.
  • the sealing lip protrudes from the sealing element and thus realizes a high specific pressing pressure on the sealing surface when the turbine blade is fixed in the holder.
  • a development of the invention provides for forming the recess in sections with the negative form of support and / or positioning elements. In this way, a turbine bucket mount can be made in which the turbine bucket is secured axially and radially against rotation or tilting.
  • a turbine blade holder of a flow rate determination device is the subject of the invention, which can be produced by the method according to the invention.
  • the single figure of the drawing shows in section a turbine blade holder 1 according to the invention during manufacture.
  • the turbine blade holder 1 comprises a main body 2, in particular made of metal or of a metallic alloy, formed therein inflow 3 and a receiving area 4 for a blade root of a turbine blade to be fixed.
  • a three-dimensional model 5 of the turbine blade to be fixed is placed, that has a recess 6 with the negative geometry of a sealing element to be produced.
  • the recess 6 here has sections of the negative shape of a sealing lip.
  • the contour of the recess 6 and the base body 2 define a cavity 7 around the inflow passage 3 around.
  • a sealing element 8 made of silicone is positively and non-positively poured onto the base body 2.
  • the sealing element 8 fills the cavity 7. This means that the cavity determines the shape of the sealing element 8. Consequently, the sealing element 8 is provided in the transition region to the three-dimensional model 5 with a circumferential sealing lip 9 projecting in the direction of the three-dimensional model 5.
  • the base body 2 is first produced by means of methods known in the art, for example using a CNC machine. Then, the three-dimensional model 5 is created. In particular, a (virtual) CAD model of the turbine blade that already exists from the design process can serve as a starting point. The recess 6 is added to this CAD model. Subsequently, based on the thus modified CAD model, the three-dimensional model 5 is produced in a manner known per se, for example by stereolithography. The three-dimensional model 5 is placed on the base body 2. Subsequently, silicone is introduced into the cavity 7 until it is completely filled. The silicone then forms the sealing element 8 in the cavity 7.
  • a (virtual) CAD model of the turbine blade that already exists from the design process can serve as a starting point.
  • the recess 6 is added to this CAD model.
  • the three-dimensional model 5 is produced in a manner known per se, for example by stereolithography.
  • the three-dimensional model 5 is placed on the base body 2. Subsequent
  • the turbine blade to be fixed with its foot area can be used.
  • the turbine blade rests on the sealing element 8.
  • the region of the sealing lip 9 results in a particularly high pressing pressure, whereby a high sealing effect is ensured. If the turbine blade holder 1 according to the invention is used in a flow rate determination, no air escapes between the turbine blade and the turbine blade holder 1.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Laser Beam Processing (AREA)

Claims (7)

  1. Procédé de fabrication d'une fixation ( 1 ) d'aube de turbine pour un dispositif de détermination des quantités d'écoulement, dans lequel la fixation ( 1 ) d'aube de turbine comprend une pièce ( 2 ) de base ayant un canal ( 3 ) d'entrée qui y est formé et un élément ( 8 ) d'étanchéité, le procédé ayant au moins les stades suivants :
    - production de la pièce ( 2 ) de base ;
    - production d'un modèle ( 5 ) en trois dimensions d'une aube de turbine ayant un évidement ( 6 ), qui a la géométrie négative de l'élément ( 8 ) d'étanchéité ;
    - mise du modèle ( 5 ) en trois dimensions sur la pièce ( 2 ) de base ;
    - coulée de l'élément ( 8 ) d'étanchéité dans une cavité ( 7 ), délimitée par le contour de l' évidement ( 6 ) et par la pièce ( 2 ) de base, autour du canal ( 3 ) d'entrée, sur la pièce ( 2 ) de base et
    - retrait du modèle ( 5 ) en trois dimensions de la pièce ( 2 ) de base.
  2. Procédé suivant la revendication 1,
    caractérisé en ce que
    on utilise, pour la production du modèle ( 5 ) en trois dimensions, un modèle CAD,
    notamment un modèle STL, de l'aube de turbine,
    l'évidement ( 6 ) étant ajouté au modèle CAD et ensuite le modèle ( 5 ) en trois dimensions étant produit sur la base du modèle CAD ainsi modifié.
  3. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que
    on produit le modèle ( 5 ) en trois dimensions de l'aube de turbine par stéréolithographie, par frittage laser et/ou par fraisage Oriol.
  4. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que
    l'élément ( 5 ) d'étanchéité est en silicone.
  5. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que
    l'évidement ( 6 ) est constitué au moins par endroits en ayant la forme négative d'une lèvre ( 9 ) d'étanchéité.
  6. Procédé suivant l'une des revendications précédentes,
    caractérisé en ce que
    l'évidement ( 6 ) est constitué au moins par endroits en ayant la forme négative d'éléments d'appui et/ou de mise en position.
  7. Fixation ( 1 ) d'aube de turbine d'un dispositif de détermination de quantité d'écoulement,
    la fixation ( 1 ) d'aube de turbine comprenant une pièce ( 2 ) de base ayant un canal ( 3 ) d'entrée qui y est formé et un élément ( 8 ) d'étanchéité produit par un procédé suivant l'une des revendications précédentes.
EP08019938.3A 2008-11-14 2008-11-14 Procédé de fabrication d'une fixation d'aube de turbine pour un dispositif de détermination de la quantité d'écoulement Not-in-force EP2187005B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP08019938.3A EP2187005B1 (fr) 2008-11-14 2008-11-14 Procédé de fabrication d'une fixation d'aube de turbine pour un dispositif de détermination de la quantité d'écoulement
US12/616,162 US20100124503A1 (en) 2008-11-14 2009-11-11 Method for producing a turbine blade holder for an internal flow rate determination device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08019938.3A EP2187005B1 (fr) 2008-11-14 2008-11-14 Procédé de fabrication d'une fixation d'aube de turbine pour un dispositif de détermination de la quantité d'écoulement

Publications (2)

Publication Number Publication Date
EP2187005A1 EP2187005A1 (fr) 2010-05-19
EP2187005B1 true EP2187005B1 (fr) 2015-04-01

Family

ID=40551970

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08019938.3A Not-in-force EP2187005B1 (fr) 2008-11-14 2008-11-14 Procédé de fabrication d'une fixation d'aube de turbine pour un dispositif de détermination de la quantité d'écoulement

Country Status (2)

Country Link
US (1) US20100124503A1 (fr)
EP (1) EP2187005B1 (fr)

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3566669A (en) * 1968-09-04 1971-03-02 Harry Parker Method and apparatus for thermally examining fluid passages in a body
US6820468B2 (en) 2001-03-26 2004-11-23 General Electric Company Fixture for holding a gas turbine engine blade
US20030128736A1 (en) * 2001-11-01 2003-07-10 Dalio Brian A. Turbine component inspection system
US6857325B2 (en) 2003-05-09 2005-02-22 Mitsubishi Heavy Industries, Ltd. Moving blade support jig, moving blade support apparatus, and flow rate measuring apparatus
US20050006047A1 (en) * 2003-07-10 2005-01-13 General Electric Company Investment casting method and cores and dies used therein
US6935187B1 (en) * 2004-03-03 2005-08-30 General Electric Company Test method for assessing thermal mechanical fatigue performance of a test material
CA2517940A1 (fr) * 2004-09-24 2006-03-24 Ems-Chemie Ag Methode de moulage par injection de pieces en plastique
US7388204B2 (en) * 2005-12-07 2008-06-17 Meyer Tool, Inc. Apparatus and method for analyzing relative outward flow characterizations of fabricated features
US7671338B2 (en) * 2006-06-14 2010-03-02 Meyer Tool, Inc. Apparatus and method for analyzing relative outward flow characterizations of fabricated features
DE502007002038D1 (de) * 2007-04-12 2009-12-31 Siemens Ag Anlagen- und Vorrichtungskonzept für eine Shotpeeninganlage zum Verfestigen von Gasturbinen Laufschaufelfüssen

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Publication number Publication date
EP2187005A1 (fr) 2010-05-19
US20100124503A1 (en) 2010-05-20

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