EP1905950A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1905950A1
EP1905950A1 EP06019819A EP06019819A EP1905950A1 EP 1905950 A1 EP1905950 A1 EP 1905950A1 EP 06019819 A EP06019819 A EP 06019819A EP 06019819 A EP06019819 A EP 06019819A EP 1905950 A1 EP1905950 A1 EP 1905950A1
Authority
EP
European Patent Office
Prior art keywords
blade
platform
rotor
turbine
cooling
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Withdrawn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
EP06019819A
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 EP06019819A priority Critical patent/EP1905950A1/fr
Publication of EP1905950A1 publication Critical patent/EP1905950A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the invention relates to a blade for a turbine of a thermal power plant with a blade root for attaching the blade to a rotor of the turbine and arranged in the region of the blade root platform. Furthermore, the invention relates to a turbine for a thermal power plant with such a blade.
  • Said turbine can be designed as a gas turbine or as a steam turbine.
  • such a turbine includes a flow channel, which is flowed through by a flow medium in the form of hot gas or hot steam. The flow medium drives the turbine via blades attached to the rotor.
  • the aforementioned, arranged in the region of the blade root platform limits the flow channel partially at a radially inner boundary surface of the flow channel.
  • the blade Due to the high temperature of the flow medium flowing through the flow channel, the blade is exposed to a high temperature.
  • the platform is often provided with a thermal barrier coating to counteract overheating of the platform.
  • film cooling holes are holes with very small diameter, which open at the platform adjacent the surface of the flow channel. In turbine operation, cooling air is generally blown out through the film cooling holes, forming a cooling film on the platform surface.
  • the platform has a first element for partially limiting a flow channel of the turbine and a second element formed separately from the first element, wherein the second element in rotor-mounted blade between the rotor and the first Element is arranged, and wherein between the first element and the second element at least one cooling channel for guiding a coolant is arranged.
  • the second element is not a baffle cooling element.
  • the second element of the platform with respect to the rotor is located radially further inboard than the first element of the platform.
  • the second element of the platform is formed separately from the first element, that is, the two elements are not integrally formed.
  • at least one cooling channel for guiding a coolant, such as cooling air, is located between the first element and the second element.
  • the cooling channel can be designed in its position and shape such that thereby improved cooling of the platform is made possible.
  • the at least one cooling channel can be introduced into one or both elements by machining, for example, such that the coolant can flow through the volume of the platform as closely as possible.
  • the at least one cooling channel according to the invention can be made approximately meandering or with a different winding configuration.
  • the shape of the at least one cooling channel is therefore not limited to a rectilinear shape, as is the case with a bore.
  • the recesses forming the cooling channels are formed.
  • the processing may be such that turbulators are formed in the channels for local adaptation of the cooling effect.
  • the cooling effect of the cooling channel can be improved.
  • the cooling channel By constructing the platform with two elements, the cooling channel can namely be arranged completely lying within the platform. Due to the two-element construction of the platform, the provision of an access hole from outside the platform for forming the at least one cooling channel is not necessary. Since the platform according to the present invention can avoid leakage losses of the coolant occurring in such an access hole, the cooling passage can be formed with a relatively large cross section as compared with the conventional cooling holes. Thus, the coolant may be directed at an improved flow rate through the at least one cooling channel, which further contributes to improved cooling of the platform.
  • the separate embodiment of the second element of the platform according to the invention offers advantages in the manufacturing method of the blade.
  • the production is facilitated, thereby increasing the rate of application in the manufacture of the blade.
  • Another advantage of the blade according to the invention lies in facilitating repairability of the platform.
  • the blade is designed to be suitable for a front turbine stage in the turbine.
  • a front turbine stage is meant a turbine stage located near an entrance for the fluid flow into the flow channel of the turbine.
  • the flow medium has a particularly high temperature at this location.
  • a suitable blade for a front turbine stage is thus through the flow medium exposed to particularly high temperatures and thus benefits in particular from the improved cooling property of the embodiment of the blade according to the invention.
  • the at least one cooling channel is designed such that by means of the cooling channel, the coolant can be guided in the axial direction of the rotor when the rotor blade is attached to the rotor.
  • the cooling channel may extend at least in sections parallel to the rotor axis.
  • the coolant can be guided in the flow direction of the flow medium flowing through the flow channel.
  • the coolant may be used at an axial position of the flow passage at which the flow medium has a high temperature with a comparatively low temperature. At further downstream positions of the flow channel, the coolant then has a slightly higher temperature and thus a somewhat reduced cooling capability, which is compensated by the temperature of the flow medium already lowered at these positions.
  • the coolant can develop an improved cooling effect by the design of the cooling channel according to the embodiment of the invention.
  • the platform is not impact cooled in at least the area where the second element overlaps the first element.
  • This area is only convectively cooled by means of the coolant flowing through the channel, possibly also using turbulators formed in the channel. There may still be film cooling in the area.
  • the at least one cooling channel extends along a curved line.
  • the cooling channel can be wound or meander-shaped.
  • the cooling channel with a geometry high complexity. This makes it possible to cool the platform as comprehensively as possible.
  • the first element of the platform is formed integrally with the blade root and / or an element adjoining the blade root.
  • Such an element adjoining the blade root may be an airfoil of the blade.
  • the first element of the platform is formed integrally with a main body of the blade comprising the blade root and the blade. Since the first element of the platform partially limits the flow channel of the turbine, the flow channel can be designed to be correspondingly tight due to the one-piece configuration. Flow losses due to leaks between the platform and blade root can thus be avoided.
  • both the first element and the second element are formed separately from the blade root and / or an adjoining element.
  • each of the first member and the second member is formed separately from a main body of the blade including the blade root and the blade. Necessary repairs to the platform will be further facilitated.
  • the first element of the platform can be replaced independently of the remainder of the blade if necessary.
  • the first element of the platform may be formed with a material that is different from the material of the airfoil or blade root, and thus perfectly adapted to the mechanical requirements imposed on the blade platform in that area.
  • first element and / or the second element is / are fastened in a form-fitting manner to the blade root and / or the adjoining element.
  • first element and / or the second element is positively connected to one of the blade root and the blade attached to the main body of the blade.
  • the positive fastening can take place, for example, by means of a "conical seat" between the first element or the second element and the corresponding fastening section on the main body of the moving blade.
  • the main body of the blade on the attachment portion and the first element and the second element on matched truncated cone-shaped or conical contact surfaces.
  • the truncated cone or the cone widens in radially pointing away from the turbine rotor direction.
  • the corresponding element of the platform with rotating rotor is pressed by the resulting centrifugal force to the main body of the blade, in particular to the blade root, that is, the interlocking interconnected elements are further wedged together.
  • This ensures that the transition between the individual elements of the platform and the main body of the blade or the blade root during operation of the turbine against the flow medium is effectively sealed. That is, penetration of flow medium in joints between the components is thus prevented.
  • the second element of the platform is positively, materially and / or non-positively attached to the first element of the platform, so that even between the first element and second element no coolant leakage current can occur.
  • the first element and the second element have different materials, in particular the first element comprises an oxidation-resistant material and the second element comprises a material with high strength.
  • the first element of the platform is made of a different material or of a different material composition than the second element of the platform.
  • nickel-based cast alloys and / or oxidation-resistant ODS alloys are suitable.
  • the second element of the platform can be made of Nimonic 90 or heat-resistant steels.
  • the first element is provided with a heat-insulating coating.
  • this coating should be provided on the surface of the first element of the platform which is in contact with the flow medium of the flow channel. Such a coating also helps to prevent overheating of the platform.
  • the second element has a flywheel, which is designed to influence the vibration characteristics of the blade targeted.
  • a targeted mismatching of the blade can be carried out by means of such a flywheel.
  • the natural frequency of the blade can be changed so that during operation of the turbine vibration excitation of the blade is prevented.
  • the blade may be adjusted with a different vibration condition occurring at the particular location.
  • a first embodiment of a blade 10 is shown.
  • the blade 10 extends substantially along a longitudinal axis 12.
  • the blade 10 has a blade root 14 and an airfoil 16.
  • the blade root 14 is designed with a Christmas tree profile and serves to attach the blade 10 to a rotor of a gas turbine or steam turbine.
  • the blade 16 is flown by a flow medium flowing through a flow channel of such a turbine. By the flow of the airfoil 16 by means of the flow medium, the force is transmitted to the blade and thus the rotor of the turbine is set in rotary motion.
  • the platform 18 has a first element 18 a, which is integrally formed with the blade root 14.
  • the first element 18a of the platform 18 serves to partially limit the flow channel of the turbine on its inner circumference. Adjacent blades 10 abut each other on their platforms 18, so that the flow channel is bounded on its inner periphery by means of the individual platforms 18.
  • On the outer circumference of the flow channel is usually limited by means of a turbine housing.
  • On the blade root side, a second element 18b of the platform 10 is arranged on the blade root side.
  • the second element 18b is designed as a separate component and not an impingement cooling element. It thus has no openings distributed over its surface, with which a surface impingement cooling would be possible.
  • first element 18a and the second element 18b extends at least one cooling channel 20 in the axial direction of the rotor for convective cooling of the platform or the platform edge.
  • the cooling channel 20 in successive Windings in the axial direction of the rotor, ie perpendicular to the plane of the drawing shown in FIG. 1 and are returned.
  • trough-shaped recesses adapted to one another can be provided both in the first element 18a and in the second element 18b.
  • recesses for guiding a coolant are provided in only one of the two elements 18a, 18b. The recesses are thus substantially limited by the two elements 18a, 18b and serve as cooling channels 20 for guiding a coolant.
  • FIGS. 2 to 4 show further embodiments of the blade 10 according to the invention. Elements of this blade which correspond to elements of the first embodiment of the blade 10 shown in FIG. 1 are given the same reference numerals.
  • a second embodiment of the blade 10 according to the invention is shown.
  • the rotor blade 10 differs only in that the first element 18a of the platform 18 is likewise designed as a separate component and that the elements 18a and 18b of the platform 18 are connected by means of a "conical seat” or Conical seat are positively connected to the blade root 14.
  • the first element 18a of the platform 18 is formed separately from the blade root 14 and, like the second element 18b, has a truncated cone-shaped abutment surface 26 and 28, respectively.
  • the blade root 14 has in its upper portion corresponding to the contact surfaces 26 and 28 of the platform 18a and 18b adapted truncated cone-shaped contact surfaces 30a and 30b.
  • the elements 18a and 18b of the platform 18 are thus pressed during operation of the turbine by the centrifugal force occurring at a rotating rotor against the blade root 14. Thus, no flow medium from the flow channel penetrates between the platform 18 and the blade root 14.
  • the illustrated in Fig. 3 third embodiment of the blade 10 according to the invention differs with respect to the blade 10 shown in FIG. 2 only in that the first element 18 a of the platform 18 is provided on its surface facing the flow channel with a heat-insulating coating 22.
  • the heat-insulating coating 22 helps to prevent overheating of the platform 18.
  • the illustrated in Fig. 4 fourth embodiment of the blade 10 according to the invention corresponds to the illustrated in Fig. 1 blade 10 with the difference that the second member 18 b is provided with an additional flywheel 24.
  • the flywheel 24 is used to make a targeted Misstuning the blade 10. Thus, resonance excitation of the blade 10 in turbine operation can be prevented.
  • FIG. 5 is a plan view of the blade 10 shown in FIG. 2.
  • the viewing direction in FIG. 5 is directed in the direction of the longitudinal axis from above according to FIG. 2.
  • the blade can be mounted on a turbine rotor extending substantially in the vertical direction as shown in FIG.
  • the platform 18 can be upstream and downstream, i. before and after the blade 16, which are divided by means of a dividing line 32 extending substantially along the rotor into two components 18a which surround the blade 16.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP06019819A 2006-09-21 2006-09-21 Aube de turbine Withdrawn EP1905950A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP06019819A EP1905950A1 (fr) 2006-09-21 2006-09-21 Aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06019819A EP1905950A1 (fr) 2006-09-21 2006-09-21 Aube de turbine

Publications (1)

Publication Number Publication Date
EP1905950A1 true EP1905950A1 (fr) 2008-04-02

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ID=37776832

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06019819A Withdrawn EP1905950A1 (fr) 2006-09-21 2006-09-21 Aube de turbine

Country Status (1)

Country Link
EP (1) EP1905950A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1992787A1 (fr) 2007-05-15 2008-11-19 General Electric Company Assemblage de pales de rotor de turbine comprenant une plateforme détachable
EP2540971A1 (fr) * 2011-06-27 2013-01-02 General Electric Company Procédé de fabrication d'un passage de refroidissement de plate-forme dans une aube de rotor de turbine, et passage de refroidissement de plate-forme associé
WO2013121016A1 (fr) * 2012-02-17 2013-08-22 Alstom Technology Ltd Élément pour une machine thermique, en particulier une turbine à gaz
EP2644834A1 (fr) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Aube de turbine ainsi que son procédé de fabrication correspondant
DE102012213017A1 (de) * 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Herstellung einer Turbinenschaufel
CN106468179A (zh) * 2015-08-22 2017-03-01 熵零股份有限公司 叶片冷却方法及其系统
EP3187685A1 (fr) * 2015-12-28 2017-07-05 Siemens Aktiengesellschaft Procede de fabrication d'un corps de base d'un aube de turbine
DE102011053874B4 (de) 2010-09-30 2022-07-21 General Electric Company Vorrichtung und Verfahren zum Kühlen von Plattformbereichen von Turbinenrotorschaufeln

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0314606A2 (fr) * 1987-10-27 1989-05-03 United Technologies Corporation Dispositif d'équilibrage avec passage d'air intégré pour turbines
EP0937863A2 (fr) * 1998-02-23 1999-08-25 Mitsubishi Heavy Industries, Ltd. Plateforme pour une aube mobile d'une turbine à gaz
EP0940561A1 (fr) * 1998-03-03 1999-09-08 Mitsubishi Heavy Industries, Ltd. Plateau d'un ailette mobile d'une turbine à gaz
EP0955449A1 (fr) * 1998-03-12 1999-11-10 Mitsubishi Heavy Industries, Ltd. Aube pour turbine à gaz
US6092991A (en) * 1998-03-05 2000-07-25 Mitsubishi Heavy Industries, Ltd. Gas turbine blade
US6120249A (en) * 1994-10-31 2000-09-19 Siemens Westinghouse Power Corporation Gas turbine blade platform cooling concept

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0314606A2 (fr) * 1987-10-27 1989-05-03 United Technologies Corporation Dispositif d'équilibrage avec passage d'air intégré pour turbines
US6120249A (en) * 1994-10-31 2000-09-19 Siemens Westinghouse Power Corporation Gas turbine blade platform cooling concept
EP0937863A2 (fr) * 1998-02-23 1999-08-25 Mitsubishi Heavy Industries, Ltd. Plateforme pour une aube mobile d'une turbine à gaz
EP0940561A1 (fr) * 1998-03-03 1999-09-08 Mitsubishi Heavy Industries, Ltd. Plateau d'un ailette mobile d'une turbine à gaz
US6092991A (en) * 1998-03-05 2000-07-25 Mitsubishi Heavy Industries, Ltd. Gas turbine blade
EP0955449A1 (fr) * 1998-03-12 1999-11-10 Mitsubishi Heavy Industries, Ltd. Aube pour turbine à gaz

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7976281B2 (en) 2007-05-15 2011-07-12 General Electric Company Turbine rotor blade and method of assembling the same
EP1992787A1 (fr) 2007-05-15 2008-11-19 General Electric Company Assemblage de pales de rotor de turbine comprenant une plateforme détachable
DE102011053874B4 (de) 2010-09-30 2022-07-21 General Electric Company Vorrichtung und Verfahren zum Kühlen von Plattformbereichen von Turbinenrotorschaufeln
US8734111B2 (en) 2011-06-27 2014-05-27 General Electric Company Platform cooling passages and methods for creating platform cooling passages in turbine rotor blades
EP2540971A1 (fr) * 2011-06-27 2013-01-02 General Electric Company Procédé de fabrication d'un passage de refroidissement de plate-forme dans une aube de rotor de turbine, et passage de refroidissement de plate-forme associé
CH706107A1 (de) * 2012-02-17 2013-08-30 Alstom Technology Ltd Bauteil für eine thermische Maschine, insbesondere eine Gasturbine.
CN104114818A (zh) * 2012-02-17 2014-10-22 阿尔斯通技术有限公司 用于热机尤其燃气轮机的构件
US9777577B2 (en) 2012-02-17 2017-10-03 Ansaldo Energia Ip Uk Limited Component for a thermal machine, in particular a gas turbine
WO2013121016A1 (fr) * 2012-02-17 2013-08-22 Alstom Technology Ltd Élément pour une machine thermique, en particulier une turbine à gaz
WO2013144245A1 (fr) 2012-03-29 2013-10-03 Siemens Aktiengesellschaft Aube de turbine ainsi que procédé de fabrication d'aube de turbine correspondant
EP2644834A1 (fr) * 2012-03-29 2013-10-02 Siemens Aktiengesellschaft Aube de turbine ainsi que son procédé de fabrication correspondant
CN104204417A (zh) * 2012-03-29 2014-12-10 西门子公司 涡轮叶片以及相关的用于制造涡轮叶片的方法
DE102012213017A1 (de) * 2012-07-25 2014-01-30 Siemens Aktiengesellschaft Verfahren zur Herstellung einer Turbinenschaufel
CN106468179A (zh) * 2015-08-22 2017-03-01 熵零股份有限公司 叶片冷却方法及其系统
EP3187685A1 (fr) * 2015-12-28 2017-07-05 Siemens Aktiengesellschaft Procede de fabrication d'un corps de base d'un aube de turbine
US10669857B2 (en) 2015-12-28 2020-06-02 Siemens Aktiengesellschaft Method for producing a base body of a turbine blade

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