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EP1914389A1 - Aube de turbine avec joint d'étanchéité séparé - Google Patents

Aube de turbine avec joint d'étanchéité séparé Download PDF

Info

Publication number
EP1914389A1
EP1914389A1 EP06022059A EP06022059A EP1914389A1 EP 1914389 A1 EP1914389 A1 EP 1914389A1 EP 06022059 A EP06022059 A EP 06022059A EP 06022059 A EP06022059 A EP 06022059A EP 1914389 A1 EP1914389 A1 EP 1914389A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
turbine
blade
sealing element
sealing
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Withdrawn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
EP06022059A
Other languages
German (de)
English (en)
Inventor
Katharina Bergander
Georg Dr. Bostanjoglo
Tobias Dr. Buchal
Winfried Dr. Esser
Dirk Dr. Goldschmidt
Torsten Koch
Rudolf Küperkoch
Thorsten Mattheis
Jan Münzer
Ralf Müsgen
Matthias Dr. Oechsner
Ursula Pickert
Volker Dr. Vosberg
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 EP06022059A priority Critical patent/EP1914389A1/fr
Publication of EP1914389A1 publication Critical patent/EP1914389A1/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/502—Thermal properties
    • F05D2300/5021—Expansivity
    • F05D2300/50212—Expansivity dissimilar

Definitions

  • the invention relates to a turbine blade for a turbine, comprising an airfoil and a fastening member for fastening the turbine blade to a holding element of the turbine. Furthermore, the invention relates to a turbine for a thermal power plant with such a turbine blade.
  • Previously known turbine blades are typically each designed as a monolithic cast component with integral blade platforms.
  • the blade platforms when mounted in the turbine state, define a turbine flow channel through which a flow medium, such as hot gas or superheated steam, drives the turbine.
  • a flow medium such as hot gas or superheated steam
  • the flow channel is not always optimally tight.
  • a not inconsiderable amount of flow medium often emerges from the flow channel.
  • This object is achieved according to the invention with a generic turbine blade, which has a arranged at a transition region between the airfoil and the attachment member and designed as a separate component sealing member for sealing the turbine blade against an adjacent element of the turbine. Furthermore, the object is achieved according to the invention with a turbine, which is provided with such a turbine blade. Moreover, the object is achieved according to the invention with a sealing element for a turbine blade, which turbine blade has an airfoil and a fastening member for fastening the turbine blade to a holding element of the turbine, wherein the sealing element for arranging at a transition region of Turbine blade between the blade and the attachment member for sealing the turbine blade against an adjacent element of the turbine is designed and designed as a separate component.
  • the turbine blade may be designed in particular for use in a gas turbine or a steam turbine.
  • the turbine blade is designed as a rotor blade.
  • the fastening member is advantageously designed as a blade root, which can be fastened to the holding element in the form of a turbine rotor.
  • the turbine blade may also be designed as a guide blade.
  • the adjacent element is a stationary element of the turbine.
  • an attachment for the turbine blade is provided, with which the turbine blade can be sealed in the transition region between the airfoil and the attachment member with respect to an adjacent element of the turbine blade, in particular an adjacent turbine blade of the turbine.
  • the sealing element is designed to seal with respect to an adjacent element of the turbine blade which is fixedly arranged in the turbine.
  • the seal is made with respect to a platform of a neighboring arranged vane.
  • the sealing element is advantageously formed on the upper or with respect to the rotor axis of the turbine radially outer platform for sealing against a platform of an adjacent guide blade.
  • the sealing is generally carried out with respect to a moving blade platform in turbine operation.
  • the manufacturing method for the sealing member may be selected independently of the manufacturing method for another part of the turbine blade.
  • the sealing member need not be made by the casting process typically used for the turbine blade.
  • the manufacturing method of the turbine blade is facilitated by the inventive provision of the sealing element.
  • an airfoil and the turbine blade attachment member can be optimized for their mechanical properties without regard to the sealing properties of the material. The manufacturability of the turbine blade is facilitated in particular when using SX and DS alloys by means of the inventive solution.
  • the sealing element as a separate component facilitates repairs of the turbine blade. For example, when the sealing of the flow channel worsens, only the sealing element can be exchanged. An exchange of the entire turbine blade can thus be avoided.
  • the turbine blade has a transverse extent and is arranged in the state fastened to the holding element of the turbine with its transverse extent substantially along a rotor of the turbine.
  • the transition region has transverse faces aligned transversely to the transverse extent of the turbine blade and the sealing element is arranged at least on one of the end faces.
  • the sealing element is thus arranged on an end face of the transition region of the turbine blade and in particular on a blade platform which points in the direction of the axial extent of the turbine.
  • the flow channel is thus effectively sealed at the junctions between the various blade stages. Effective sealing at these junctions is particularly important because the flow fluid in the flow channel is substantially transverse to the flow passage sealed transitions flows and thus the risk of fluid leakage at these points is particularly large.
  • the turbine blade it is expedient for the turbine blade to have a longitudinal extent with respect to which it can be fastened radially to a rotor axis of the turbine on the holding element of the turbine, and the sealing element projects transversely to the longitudinal extent of the turbine blade from the transition area between the airfoil and the fastening element.
  • a platform of the turbine blade also protrudes transversely to the longitudinal extent of the turbine blade.
  • the orientation of the sealing element is substantially parallel to such a platform. This alignment of the sealing element makes it possible to produce a particularly effective seal with respect to the adjacent element of the turbine blade.
  • the transition region comprises a blade platform and the sealing element is arranged on the blade platform and / or on a section of the transitional region adjoining the blade platform on the side of the fastening member.
  • the sealing element can be arranged offset parallel to the longitudinal extent of the turbine blade in the direction of the fastening member.
  • the sealing element can advantageously be arranged slightly below the platform.
  • the sealing element is arranged on the blade platform, it can form a part, in particular a substantial part of the blade platform.
  • the sealing member partially limits the flow channel of the turbine. This avoids cavities outside the flow channel into which the flow medium could penetrate. However, such penetration of the flow medium into cavities could lead to flow turbulences, which can be avoided according to the embodiment of the invention.
  • the sealing element and at least one other element of the turbine blade on different materials.
  • the sealing member is made of a different material or a different material composition than the at least one other element of the turbine blade.
  • a main part of the turbine blade comprising an airfoil and the attachment member can be made of single crystal or directionally solidified alloy.
  • the sealing element can then be made of conventionally solidified material.
  • a positive fastening can be produced in particular by means of a groove / web connection between the sealing element and the transition region.
  • a web-shaped element can be inserted into a groove adapted in its shape to the web-shaped element along a connecting surface between the sealing element and the transition region.
  • the web-shaped element can be designed dovetailed in cross-section.
  • a cohesive connection can in particular by means of a soldered or welded connection or by application coating, such. B. cold spraying are made.
  • the cohesive connection can take place along a curved connection surface.
  • the connection surface may be curved in such a way that the section line resulting between the connection surface and a sectional plane parallel to the longitudinal extension of the turbine blade has a curved course.
  • this cutting plane is advantageously also arranged parallel to the transverse extent of the turbine blade.
  • the connecting surface between the sealing element and the transition region can be configured step-shaped.
  • the abovementioned cutting line between the connecting surface and a cutting plane parallel to the longitudinal extent of the turbine blade has a step-shaped course.
  • the sealing element is fastened to the transition region by means of an intermediate piece arranged between the sealing element and the transition region.
  • an intermediate piece arranged between the sealing element and the transition region.
  • the turbine blade is in the attached to the holding member state for adjustment slightly parallel to a rotor axis of the turbine displaceable and designed the sealing member such that in this displacement of the turbine blade caused by the sealing member relative to the adjacent element seal is maintained.
  • the sealing element has a contact member which protrudes from a main portion of the sealing element.
  • the contact member is aligned parallel to the longitudinal extent of the turbine blade and advantageously points to the flow channel. The contact member is for abutment with a sealing surface of the adjacent element of the turbine.
  • the contact member may be formed as at least one tapered contact member made of wear-resistant material.
  • a tapered contact member is also referred to as a sealing tip and is advantageously triangular in cross-section, ie cone-shaped. The tip of the contact member is located in the assembled state to a sealing element of the adjacent element.
  • the sealing element is designed to exert a contact pressure on the adjacent element.
  • the direction of the contact pressure causing normal force is aligned substantially parallel to a longitudinal extension of the turbine blade.
  • the normal force causing a frictional force between the sealing element and the adjacent element of the turbine blade is directed substantially perpendicular to the extension of the sealing element.
  • the normal force acts essentially radially to the rotor of the turbine with mounted turbine blade.
  • the sealing element which is preferably arranged on a moving blade, is arranged to be movable relative to the adjacent element, preferably a guide blade.
  • the sealing element has at least two parts which have different materials and are connected to one another along a connecting surface extending essentially transversely to a longitudinal extent of the turbine blade.
  • the sealing element is constructed in a layered manner, in particular by means of the at least two parts, wherein the layers run essentially transversely to the longitudinal extension of the turbine blade or parallel to the blade platform.
  • the sealing element is advantageously designed as a bimetal, ie, the two parts of the sealing element are designed with materials with different coefficients of linear expansion. The two parts are materially or positively connected with each other. When the temperature changes so that the sealing element bends in one direction.
  • the bimetal is configured such that the sealing element bends at a higher temperature in a direction in which the sealing with the adjacent element of the turbine blade improves becomes.
  • the bending force generated by the temperature increase causes the sealing member presses with its contact area against a sealing surface of the adjacent element of the turbine blade.
  • the flow channel facing part of the sealing element oxidation-resistant material such. B. ODS or oxide ceramic has.
  • the susceptibility to wear of the sealing element can be reduced.
  • FIG. 1 shows a first embodiment of a turbine blade 10 according to the invention in plan view. The viewing direction of this view is executed radially on the rotor mounted on a rotor of an associated turbine turbine blade 10.
  • FIG. 2 shows a side view of the turbine blade 10 according to FIG. 1.
  • the turbine blade 10 is designed as a rotor blade and has an airfoil 12, a blade platform 14 and a fastening member 16 in the form of a blade root.
  • the turbine blade 10 has a transverse extent, which is characterized in FIG. 1 with a so-called transverse axis 18.
  • the transverse axis 18 When mounted on the turbine rotor state, the transverse axis 18 is arranged substantially along the axial extent of the turbine rotor.
  • the turbine blade 10 has a longitudinal extent, which is characterized in Fig. 2 with a so-called longitudinal axis 20.
  • the longitudinal axis 20 is aligned radially with respect to the turbine rotor upon attachment of the turbine blade 10 on the turbine rotor.
  • a sealing element 22 designed as a separate component is fastened in a transition area between the airfoil 12 and the attachment member 16, in this case on the platform 14, a sealing element 22 designed as a separate component is fastened. But the sealing member 22 may also be below the platform 14, that is secured in an upper region of the fastening member 16.
  • a detail D of the turbine blade 10 according to FIG. 2, which comprises the region of the sealing element 22, is shown enlarged in FIG. 2a.
  • the sealing element 22 has an engagement element 30 in the form of a dovetail for the form-fitting fastening of the sealing element 22 to the blade platform 14. When fastened, the sealing element 22 projects transversely to the longitudinal axis 20 of the turbine blade 10 from the blade platform 14. It leads it is also the transverse to the longitudinal axis 20 of the turbine blade 10 arranged blade platform 14 substantially.
  • the sealing element 22 has a contact element 26 in the form of a web which extends along a platform edge extending into the plane of the drawing.
  • the contact member 26 abuts a sealing surface 28 of an adjacent element 24 of the turbine blade 10 in the form of the platform of an adjacent turbine vane.
  • FIG. 3 shows a detail of a second exemplary embodiment of the turbine blade 10 according to the invention. As in FIG. 2 a, this detail view shows the region of the sealing element 22.
  • the sealing element 22 is fastened to the blade platform 14 by means of a soldered or welded connection. This cohesive connection takes place along a curved connection surface 32.
  • FIG. 4 shows the connection of the sealing element 22 with the blade platform 14 of a third exemplary embodiment of the turbine blade 10 according to the invention.
  • the connecting surface 32 between the sealing element 22 and the blade platform 14 has a step shape.
  • 5 shows the connection region between the sealing element 22 and the blade platform 14 for a fourth exemplary embodiment of the turbine blade 10 according to the invention.
  • an intermediate piece 34 is arranged between the sealing element 22 and the blade platform 14.
  • the sealing element 22 is designed as a bimetal.
  • the sealing element 22 has a first part 36 and second part 38 of materials of different coefficients of linear expansion on.
  • the two parts 36 and 38 of the sealing element 22 extend along a connecting surface 40 arranged transversely to the longitudinal axis 20.
  • the sealing element 22 bends such that the engagement element 30 is moved upwards or downwards, as indicated by the reference numeral 42 Double arrow illustrated.
  • FIG. 7 shows a section of a sixth exemplary embodiment of the turbine blade 10 according to the invention in the region of the sealing element 22.
  • the sealing element 22 differs from the sealing element shown in FIG. 2a in that it has a multiplicity of contact elements 26, which are triangular in cross-section or designed as so-called sealing tips 44.
  • the sealing tips 44 are made of wear-resistant material. This can be produced by application coating (eg cold spraying) and fixed to a main body of the sealing element 22 by means of a material connection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06022059A 2006-10-20 2006-10-20 Aube de turbine avec joint d'étanchéité séparé Withdrawn EP1914389A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06022059A EP1914389A1 (fr) 2006-10-20 2006-10-20 Aube de turbine avec joint d'étanchéité séparé

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06022059A EP1914389A1 (fr) 2006-10-20 2006-10-20 Aube de turbine avec joint d'étanchéité séparé

Publications (1)

Publication Number Publication Date
EP1914389A1 true EP1914389A1 (fr) 2008-04-23

Family

ID=37832119

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06022059A Withdrawn EP1914389A1 (fr) 2006-10-20 2006-10-20 Aube de turbine avec joint d'étanchéité séparé

Country Status (1)

Country Link
EP (1) EP1914389A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100040463A1 (en) * 2008-08-18 2010-02-18 Rolls-Royce Plc Sealing means
DE102013220276A1 (de) * 2013-10-08 2015-04-09 MTU Aero Engines AG Strömungsmaschine
JP2015197082A (ja) * 2014-04-02 2015-11-09 三菱日立パワーシステムズ株式会社 動翼及び回転機械
CN112487583A (zh) * 2020-12-17 2021-03-12 清华大学 贯流可逆式机组桨叶全三维加权设计方法和装置
EP4269752A1 (fr) * 2022-04-28 2023-11-01 Hamilton Sundstrand Corporation Joints d'extrémité de rotor multimétalliques adaptatifs fabriqués de manière additive

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR559351A (fr) * 1921-12-03 1923-09-14 Vickers Electrical Co Ltd Perfectionnements se rapportant aux garnitures employées avec les aubes des turbines à vapeur
JPS5912102A (ja) * 1982-07-12 1984-01-21 Toshiba Corp ラビリンスパツキン
EP0995881A2 (fr) * 1998-10-19 2000-04-26 Asea Brown Boveri AG Joint d'étanchéitée
EP1167695A1 (fr) * 2000-06-21 2002-01-02 Siemens Aktiengesellschaft Turbine à gaz et aube statorique pour une turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR559351A (fr) * 1921-12-03 1923-09-14 Vickers Electrical Co Ltd Perfectionnements se rapportant aux garnitures employées avec les aubes des turbines à vapeur
JPS5912102A (ja) * 1982-07-12 1984-01-21 Toshiba Corp ラビリンスパツキン
EP0995881A2 (fr) * 1998-10-19 2000-04-26 Asea Brown Boveri AG Joint d'étanchéitée
EP1167695A1 (fr) * 2000-06-21 2002-01-02 Siemens Aktiengesellschaft Turbine à gaz et aube statorique pour une turbine à gaz

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100040463A1 (en) * 2008-08-18 2010-02-18 Rolls-Royce Plc Sealing means
US8221060B2 (en) * 2008-08-18 2012-07-17 Rolls-Royce Plc Sealing means
DE102013220276A1 (de) * 2013-10-08 2015-04-09 MTU Aero Engines AG Strömungsmaschine
US9835040B2 (en) 2013-10-08 2017-12-05 MTU Aero Engines AG Turbomachine
JP2015197082A (ja) * 2014-04-02 2015-11-09 三菱日立パワーシステムズ株式会社 動翼及び回転機械
CN112487583A (zh) * 2020-12-17 2021-03-12 清华大学 贯流可逆式机组桨叶全三维加权设计方法和装置
EP4269752A1 (fr) * 2022-04-28 2023-11-01 Hamilton Sundstrand Corporation Joints d'extrémité de rotor multimétalliques adaptatifs fabriqués de manière additive

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