EP1329593B1 - Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform - Google Patents

Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform Download PDF

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Publication number
EP1329593B1
EP1329593B1 EP02001267A EP02001267A EP1329593B1 EP 1329593 B1 EP1329593 B1 EP 1329593B1 EP 02001267 A EP02001267 A EP 02001267A EP 02001267 A EP02001267 A EP 02001267A EP 1329593 B1 EP1329593 B1 EP 1329593B1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
vane
turbine
turbine blade
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.)
Expired - Lifetime
Application number
EP02001267A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1329593A1 (de
Inventor
Peter Tiemann
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 AT02001267T priority Critical patent/ATE291677T1/de
Priority to EP02001267A priority patent/EP1329593B1/de
Priority to DE50202538T priority patent/DE50202538D1/de
Priority to JP2003007396A priority patent/JP4249990B2/ja
Priority to CNB031207006A priority patent/CN1313707C/zh
Priority to US10/345,967 priority patent/US6887040B2/en
Publication of EP1329593A1 publication Critical patent/EP1329593A1/de
Application granted granted Critical
Publication of EP1329593B1 publication Critical patent/EP1329593B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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

Definitions

  • the invention relates to a turbine blade with a profiled, along a blade axis extended Airfoil.
  • a vane for a Gas turbine which consists of two components is composed.
  • the first component has that Shovel profile extending through a platform extends through.
  • a second component is for recording of the blade profile in a rectangular, as An impeller cooling plate serving an opening on the, which Profile of the bucket corresponds. It is on the plate one provided circumferential edge, which encompasses the platform and supports.
  • At the side facing away from the platform Plate are mechanical for attachment of the vane provided resilient flanges, which partially from Shovel profile are penetrated.
  • the second component serves to fix the blade profile and to form an impingement cooling element for the H thoroughlygasbeetzyerte Platform.
  • the turbine blades in particular the guide vanes, usually have for the suitable guidance of the working medium a profiled, along a blade axis extended blade on, at the end for attachment of the turbine blade on the respective support body a transverse to Blade axis extending, in at least one end as Hook base trained platform is formed.
  • Such gas turbines for thermodynamic reasons usually for particularly high outlet temperatures of the Combustion off and in the flowing into the turbine unit Working medium from about 1200 ° C to about 1300 ° C. designed.
  • the components are the gas turbine, in particular the turbine blades, comparatively exposed to high thermal loads.
  • a high reliability and a long life of the respective components to ensure the affected components are common cooled formed.
  • the turbine blades are common designed as a so-called hollow profile.
  • the profiled Airfoil features in its interior too referred to as vane core cavities in which a Cooling medium can be performed.
  • Coolant channels By the thus formed Coolant channels is thus an admission of the thermally stressed areas of the respective Blade with coolant allowed.
  • a particularly cheap Cooling effect and thus a particularly high level of operational safety is achievable by the coolant channels a comparatively large area of space inside each of them Occupy the airfoil and adding the coolant as close as possible to the respective, the hot gas exposed Surface is guided.
  • sufficient mechanical stability and resilience can ensure the particular turbine blade flowed through several channels, wherein inside the Blade profiles a plurality of acted upon by coolant, each other by comparatively thin partitions separate coolant channels are provided.
  • Turbine blade for a comparatively low consumption be desirable to coolant.
  • the turbine blade with comparatively hot Working medium is with only limited consumption of coolant a reliable cooling of the individual components of the turbine blade often only over a relatively thin-walled Execution of the individual components with comparatively low material requirement achievable.
  • the gas turbine in individual components of the turbine blade resulting thermal stresses and also occurring considerable mechanical stress lead to material fatigue or even material breakage. This can be a relatively unwanted use comparatively thick-walled structural parts require, for the then one correspondingly complex cooling with correspondingly extended Supply of coolant is to provide.
  • the invention is therefore based on the object, a turbine blade of the type mentioned above, on the one hand thermally and mechanically highly resilient and on the other hand Ensures a comparatively economical consumption of coolant.
  • Airfoil in an end region one transverse to the blade axis extending hot gas platform and overlying a load platform are formed, wherein a mechanical Connection of the load platform with the hot gas platform exclusively takes place over the blade.
  • the invention is based on the consideration that even at a thermally highly resilient turbine blade for a reliable cooling necessary consumption of coolant can be kept comparatively low by the structural parts are kept largely thin-walled. To do this in the In view of the comparatively strong mechanical stress the turbine blade without significant risk of To allow material damage, the thermal should Load absorption at the turbine blade consistently from the mechanical Lifting be kept separate. These are on Airfoil formed two platform segments, of which one, namely the hot gas platform, exclusively for receiving the thermal load and another, namely the Load platform, exclusively for the reception of mechanical Load is designed.
  • the hot gas platform can be kept particularly thin-walled Just because they are designed with almost no mechanical Load is applied.
  • the load platform, the sufficiently thick-walled to absorb the mechanical load should be executed, however, is by means of the hot gas platform from a direct thermal load shielded by the working medium and thus also in comparatively massive version without significant consumption conservees coolant to a safe operating temperature.
  • a high level of operational reliability in such an arrangement is achievable by just the comparatively thin-walled executed hot gas platform consistently free from occurring Heat stress is maintained.
  • the hot gas platform should as far as possible be freely expandable, so that even with changing thermal Exposure due to thermally induced expansion or contraction no tension can occur.
  • a Such freely expandable design of the hot gas platform is achievable by these mechanically as far as possible from the Load platform is kept decoupled.
  • the load platform in particular as regards their sizing advantageously designed in such a way that they are looking for a complete reception by the one Airfoil evolved around working fluid Forces is suitable.
  • the turbine blade is with particularly low manufacturing and Material expenditure available by in advantageous Design the load platform in terms of their design on the one adapted to the given boundary conditions mechanical fixation required structural Components is limited.
  • Such a minimalist running Design is favored by the load platform advantageously at one with respect to a working medium formed downstream edge of the airfoil. It is seen in the flow direction of the working medium rear edge of the airfoil in the suspension area to Extended loading platform, wherein in the flow direction of the Working fluid seen front area of the airfoil a major waiver of material-consuming, the load platform attributable structural components take place can.
  • the load platform advantageously a molded rib for Radialverhakung and on this patch rib for Axialverhakung on.
  • the static determination on the inside of the Turbine blade a single point of contact in the axial direction.
  • a rotation in Radial direction and / or a peripheral fixation on the outside be provided the turbine blade; these can by suitable means formed on the respective rib such as grooves or noses, be realized.
  • the turbine blade is preferably as a guide vane for a gas turbine, in particular for a stationary gas turbine, educated.
  • the advantages achieved by the invention are in particular in that by the reduction of the mechanical connection the load platform with the hot gas platform on a connection exclusively on the blade a consistent Separation of to absorb the thermal load provided structural part of the for receiving the mechanical Load provided structural part is enabled.
  • the respective ones Structural parts, namely the hot gas platform on the one hand and the load platform, on the other hand, can thus be specific designed to their actual purpose be, in particular, the hot gas platform freely expandable and can be made comparatively thin-walled.
  • the Hot gas platform on the one hand and the load platform on the other are completely independent in their design be executed from each other, in particular the Hot gas platform one different from the load platform Can have width and shape.
  • the load platform can do this in the manner of a minimal solution in its shape completely geared to the needs of power transmission be, in this sense superfluous structural areas can be saved. This is in addition to one too favored by the hot gas platform high thermal capacity also a particularly low production cost achievable with only low material consumption.
  • the turbine blade 1 according to the figure has a profiled Airfoil 2, which extends along a blade axis. 4 extends.
  • the blade 2 is suitable for influencing a flowing in an associated turbine unit Working medium arched and / or curved.
  • the turbine blade 1 is used as a guide vane for a gas turbine educated. To use the turbine blades 1 even at relatively high temperatures of the working medium from about 1200 ° C to 1300 ° C, is the turbine blade 1 formed coolable. This is the blade 2 in the manner of an internal profiling with a cavity. 6 executed, via which a coolant, such as cooling steam, is feasible.
  • a coolant such as cooling steam
  • a platform system 10 molded to this.
  • the platform system 10 is included both to absorb the thermal load through the Working medium as well as to absorb the mechanical stress formed by the working medium.
  • high thermal reliability of the To enable complete system is the platform system 10 for a consistent structural separation thermally contaminated Components of mechanically loaded components formed.
  • the platform system 10 on the one hand comprises a hot gas platform 12 and on the other hand one of this largely independently held load platform 14.
  • the hot gas platform 12 is provided for receiving the thermal load.
  • the load platform 14 is on the from the flow space for the working medium side facing away from the hot gas platform 12th and thus arranged over this lying, so that the hot gas platform 12 in the manner of a heat shield for the load platform 14 acts. This is no thermal impact the load platform 14 carried by in the working medium Warmth.
  • Both the hot gas platform 12 and the load platform 14 are mechanically connected exclusively to the blade 2; a direct mechanical connection of the load platform 14 with the hot gas platform 12, for example via cross struts or support plates is not provided.
  • the hot gas platform 12 is thus at its peripheral edge 16, for a Self-supporting construction is designed to be suitably thickened largely executed freely expandable, without regard to this Restrictions could occur through the load platform 14. With changing thermal loading of the hot gas platform 12 and thereby induced lateral expansions or Contractions are thus induced thermal stresses thus kept very low.
  • the load platform 14 due to the thermal shielding by the hot gas platform 12 thermally only comparatively is slightly loaded and thus comparatively easy is coolable to a reliable operating temperature is to completely absorbed by the working medium on the Shuufelblatt 2 acting forces and comparatively thick-walled.
  • the load platform 14 In its shape is the load platform 14, however, in the manner of a minimized Execution on a comparatively small number of mechanical Fixed points, largely renouncing beyond designed structural components. This is the Load platform 14 only at the respect to the flow direction the working medium in the associated turbine unit seen downstream edge 18 of the airfoil. 2 molded; seen at the flow direction of the working medium front edge 20 of the airfoil 2, however, is on its upper end 8 no continuous continuation of education a structural element belonging to the load platform 14 intended.
  • the turbine blade 1 thus has mechanically from each other largely decoupled hot gas and load platforms 12 or 14 on.
  • This allows the load platform 14 in its shape specifically adapted to the given requirements be without causing disadvantages in the thermal range in Buy are to take.
  • the thermal impact is, however, completely intercepted by the hot gas platform 12, the again in their shape completely independent of the Load platform 14 may be executed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
EP02001267A 2001-09-12 2002-01-17 Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform Expired - Lifetime EP1329593B1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
AT02001267T ATE291677T1 (de) 2002-01-17 2002-01-17 Turbinenschaufel mit einer heissgasplattform und einer lastplattform
EP02001267A EP1329593B1 (de) 2002-01-17 2002-01-17 Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform
DE50202538T DE50202538D1 (de) 2002-01-17 2002-01-17 Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform
JP2003007396A JP4249990B2 (ja) 2002-01-17 2003-01-15 タービン翼
CNB031207006A CN1313707C (zh) 2002-01-17 2003-01-17 透平机叶片
US10/345,967 US6887040B2 (en) 2001-09-12 2003-01-17 Turbine blade/vane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02001267A EP1329593B1 (de) 2002-01-17 2002-01-17 Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform

Publications (2)

Publication Number Publication Date
EP1329593A1 EP1329593A1 (de) 2003-07-23
EP1329593B1 true EP1329593B1 (de) 2005-03-23

Family

ID=8185296

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02001267A Expired - Lifetime EP1329593B1 (de) 2001-09-12 2002-01-17 Turbinenschaufel mit einer Heissgasplattform und einer Lastplattform

Country Status (6)

Country Link
US (1) US6887040B2 (ja)
EP (1) EP1329593B1 (ja)
JP (1) JP4249990B2 (ja)
CN (1) CN1313707C (ja)
AT (1) ATE291677T1 (ja)
DE (1) DE50202538D1 (ja)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7604456B2 (en) * 2006-04-11 2009-10-20 Siemens Energy, Inc. Vane shroud through-flow platform cover
FR2953252B1 (fr) * 2009-11-30 2012-11-02 Snecma Secteur de distributeur pour une turbomachine
US20110200430A1 (en) * 2010-02-16 2011-08-18 General Electric Company Steam turbine nozzle segment having arcuate interface
US8356975B2 (en) * 2010-03-23 2013-01-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured vane platform
US9976433B2 (en) 2010-04-02 2018-05-22 United Technologies Corporation Gas turbine engine with non-axisymmetric surface contoured rotor blade platform
US8920117B2 (en) 2011-10-07 2014-12-30 Pratt & Whitney Canada Corp. Fabricated gas turbine duct
US9546557B2 (en) * 2012-06-29 2017-01-17 General Electric Company Nozzle, a nozzle hanger, and a ceramic to metal attachment system
US20140023517A1 (en) * 2012-07-23 2014-01-23 General Electric Company Nozzle for turbine system
US9289826B2 (en) * 2012-09-17 2016-03-22 Honeywell International Inc. Turbine stator airfoil assemblies and methods for their manufacture
US9506362B2 (en) * 2013-11-20 2016-11-29 General Electric Company Steam turbine nozzle segment having transitional interface, and nozzle assembly and steam turbine including such nozzle segment
US11346234B2 (en) 2020-01-02 2022-05-31 Rolls-Royce Plc Turbine vane assembly incorporating ceramic matrix composite materials
US11732596B2 (en) 2021-12-22 2023-08-22 Rolls-Royce Plc Ceramic matrix composite turbine vane assembly having minimalistic support spars

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Also Published As

Publication number Publication date
US20030133802A1 (en) 2003-07-17
CN1436920A (zh) 2003-08-20
ATE291677T1 (de) 2005-04-15
CN1313707C (zh) 2007-05-02
JP4249990B2 (ja) 2009-04-08
DE50202538D1 (de) 2005-04-28
JP2003214109A (ja) 2003-07-30
EP1329593A1 (de) 2003-07-23
US6887040B2 (en) 2005-05-03

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