EP1329593A1 - Aube de turbine - Google Patents

Aube de turbine Download PDF

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Publication number
EP1329593A1
EP1329593A1 EP02001267A EP02001267A EP1329593A1 EP 1329593 A1 EP1329593 A1 EP 1329593A1 EP 02001267 A EP02001267 A EP 02001267A EP 02001267 A EP02001267 A EP 02001267A EP 1329593 A1 EP1329593 A1 EP 1329593A1
Authority
EP
European Patent Office
Prior art keywords
platform
blade
turbine
load
load 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
EP02001267A
Other languages
German (de)
English (en)
Other versions
EP1329593B1 (fr
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 EP02001267A priority Critical patent/EP1329593B1/fr
Priority to AT02001267T priority patent/ATE291677T1/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/fr
Application granted granted Critical
Publication of EP1329593B1 publication Critical patent/EP1329593B1/fr
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 a profiled, extending along a blade axis Airfoil.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • the Energy content of a fuel to generate a rotational movement a turbine shaft used.
  • the fuel will To do this, burned in a combustion chamber, using an air compressor compressed air is supplied. That in the combustion chamber generated by the combustion of the fuel, under high Pressure and high temperature working medium is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
  • the turbine shaft To generate the rotational movement of the turbine shaft are a number of them usually in groups of blades or rows of blades grouped together arranged via a pulse transfer from the flow medium drive the turbine shaft.
  • For guiding the flow medium are also common in the turbine unit between adjacent rows of blades with the turbine housing connected rows of vanes arranged.
  • the turbine blades, in particular, the guide vanes usually have a profiled, suitable guide for the working medium Blade extending along a blade axis on the end of which is used to attach the turbine blade on the respective support body a cross to Blade axis extending in at least one end region as Hook base formed on the platform.
  • Coolant channels are thus an act on the thermally particularly stressed areas of the respective Airfoil with coolant allows.
  • a particularly cheap one Cooling effect and therefore a particularly high level of operational reliability can be reached by using the coolant channels a comparatively large area of space inside each Take the airfoil and add the coolant as close as possible to the respective hot gas Surface is guided.
  • adequate mechanical stability and resilience can ensure the respective turbine blade be flowed through multiple channels, being inside the Blade profile a plurality of coolant-loaded from each other by comparatively thin partitions separate coolant channels are provided.
  • Turbine blade for a comparatively low consumption of coolant may be desirable.
  • the turbine blade with comparatively hot Working medium is with a limited consumption of coolant reliable cooling of the individual components of the turbine blade often only with a comparatively thin wall Execution of the individual components with comparative low material requirement achievable.
  • This can be an actually undesirable use by comparison require thick-walled structural parts, for which then one correspondingly complex cooling with a correspondingly expanded Supply of coolant is to be provided.
  • the invention is therefore based on the object of a turbine blade of the type mentioned above, on the one hand is thermally and mechanically highly resilient and on the other hand ensures a comparatively economical consumption of coolant.
  • the airfoil in one end area is transverse to the airfoil axis extending hot gas platform and above a load platform are molded, a mechanical Connection of the load platform with the hot gas platform only via the airfoil.
  • the invention is based on the consideration that also a thermally highly resilient turbine blade for reliable cooling necessary consumption of coolant can be kept comparatively low by the structural parts are kept largely thin-walled. To do this in With regard to the comparatively strong mechanical stress the turbine blade without any noteworthy danger To allow material damage, the thermal Load pickup on the turbine blade consistently by the mechanical The load suspension must be kept separate. For this are on Blade formed on two platform segments, one of which one, namely the hot gas platform, for recording only the thermal load and another, namely the Load platform, only to accommodate the 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 that sufficiently thick-walled to absorb the mechanical load should be carried out, however, is by means of the hot gas platform of direct thermal exposure shielded by the working medium and thus also in comparison massive design without significant consumption coolant can be kept at a safe operating temperature.
  • a high level of operational reliability with such an arrangement can be achieved by using the comparatively thin-walled Executed hot gas platform consistently free from occurring Thermal stress is maintained.
  • a such a freely expandable design of the hot gas platform can be achieved mechanically as far as possible from the Load platform is kept decoupled.
  • the hot gas platform is essentially kept free of mechanical stress.
  • the load platform especially with regard to their dimensioning advantageously designed such that they are for a full inclusion of the one Airfoil flowing around working medium Forces is suitable.
  • the turbine blade is particularly low in manufacturing and
  • the cost of materials can be provided by being more advantageous Design the load platform in terms of its shape to the one adapted to the given boundary conditions mechanical fixation required structural Components is limited.
  • Such a minimalist design Design is favored by the load platform advantageously on one with respect to a working medium downstream edge of the airfoil is formed. This is seen in the flow direction of the working medium rear edge of the airfoil in the suspension area Load platform expanded, being in the direction of flow of the Working fluid seen front area of the airfoil an extensive waiver of material-intensive, the load platform structural components to be assigned can.
  • the mechanical Fixation of the turbine blade on the load platform Minimum of those required for static certainty Fixation points limited.
  • the load platform points to this advantageously a molded rib for radial hooking and a rib attached to this for axial hooking. With such a configuration, it is sufficient for complete Establishment of the static certainty on the inside of the Turbine blade a single contact point in the axial direction. If necessary, an anti-rotation lock can also be added Radial direction and / or a circumferential fixation on the outside the turbine blade may be provided; these can by suitable means molded onto the respective rib such as grooves or lugs can be realized.
  • the turbine blade is preferably used as a guide blade for a gas turbine, especially for a stationary gas turbine, educated.
  • the advantages achieved with the invention are in particular in that by reducing the mechanical connection the load platform with the hot gas platform on a connection a consistent only via the airfoil Separation of the to absorb the thermal load provided structural part from to accommodate the mechanical Load provided structural part is enabled.
  • the respective Structural parts namely the hot gas platform on the one hand and the load platform, on the other hand, can thus be specific designed for their actual purpose be, in particular the hot gas platform freely expandable and can be designed comparatively thin-walled.
  • the Hot gas platform on the one hand and the load platform on the other can also be completely independent in their design be executed from each other, in particular the Hot gas platform different from the load platform May have width and shape.
  • the load platform can in the form of a minimal solution in its design 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 high thermal load capacity favored by the hot gas platform also a particularly low manufacturing cost achievable with low material consumption.
  • An embodiment of the invention is based on a Drawing explained in more detail.
  • the figure shows in Angled view of a turbine blade.
  • the turbine blade 1 according to the figure has a profiled Blade 2 that extends along a blade axis 4 extends.
  • the airfoil 2 is suitable for influencing one flowing in an associated turbine unit Working medium curved and / or curved.
  • the turbine blade 1 is used as a guide blade for a gas turbine educated. To use the turbine blades 1 even at comparatively high temperatures of the working medium The turbine blade is able to enable temperatures of around 1200 ° C to 1300 ° C 1 designed to be coolable. This is the shovel blade 2 in the manner of an inner profile with a cavity 6 executed via which a coolant, for example cooling steam, is feasible.
  • a coolant for example cooling steam
  • a platform system is located at an end region 8 of the airfoil 2 10 molded onto this.
  • the platform system 10 is there both to absorb the thermal load from the Working medium as well as to absorb the mechanical load trained by the working medium. In order to do so at high thermal load with comparatively low Coolant consumption high mechanical reliability of the To enable the entire system is the platform system 10 for a consequent structural separation of thermally stressed Components formed by mechanically loaded components.
  • the platform system 10 comprises a hot gas platform 12 and on the other hand one of these largely independently held load platform 14.
  • the hot gas platform 12 is provided to absorb the thermal load.
  • the load platform 14 is on the of the flow space for side of the hot gas platform 12 facing away from the working medium and thus arranged above this, so that the hot gas platform 12 in the manner of a heat shield for the load platform 14 acts. This means that there is no thermal stress the load platform 14 by entrained in the working medium Warmth.
  • Both the hot gas platform 12 and the load platform 14 are mechanically connected only to the airfoil 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 on its peripheral edge 16, which for a self-supporting construction is suitably thickened, largely freely expandable without this Limitations due to the load platform 14 could occur. With changing thermal exposure to the hot gas platform 12 and thereby induced lateral expansion or Contractions are thus induced thermal stresses kept particularly low.
  • the load platform 14 is in order to form a radial hook pulled out a rib 22 on which a rib 24 for axial hooking is put on.
  • a fixing pin 26 attached, another Specifies contact point in the axial direction.
  • the rib 24 provided for axial hooking is a groove 28 released to form a circumferential fixation with a structural element molded onto the associated turbine housing can be brought into engagement.
  • To complete the hooking in the radial direction can also in the embodiment only indicated radial ribbing 30 is provided his.
  • the turbine blade 1 thus points mechanically from one another largely decoupled hot gas and load platforms 12 or 14 on. This allows the load platform 14 to be shaped specifically adapted to the given requirements be without thereby disadvantages in the thermal range in Purchase.
  • the thermal load is completely intercepted by the hot gas platform 12 which again completely independent of the shape Load platform 14 can 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 Aube de turbine ayant une plateforme supportant les gaz chaux et une plateforme supportant les charges mécaniques Expired - Lifetime EP1329593B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP02001267A EP1329593B1 (fr) 2002-01-17 2002-01-17 Aube de turbine ayant une plateforme supportant les gaz chaux et une plateforme supportant les charges mécaniques
AT02001267T ATE291677T1 (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 (fr) 2002-01-17 2002-01-17 Aube de turbine ayant une plateforme supportant les gaz chaux et une plateforme supportant les charges mécaniques

Publications (2)

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

Family

ID=8185296

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02001267A Expired - Lifetime EP1329593B1 (fr) 2001-09-12 2002-01-17 Aube de turbine ayant une plateforme supportant les gaz chaux et une plateforme supportant les charges mécaniques

Country Status (6)

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

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

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3610769A (en) * 1970-06-08 1971-10-05 Gen Motors Corp Porous facing attachment
GB1516757A (en) * 1975-10-14 1978-07-05 United Technologies Corp Turbomachinery vane or blade with cooled platforms
GB1605219A (en) * 1975-10-02 1984-08-30 Rolls Royce Stator vane for a gas turbine engine
US5249418A (en) * 1991-09-16 1993-10-05 General Electric Company Gas turbine engine polygonal structural frame with axially curved panels
WO1999054597A1 (fr) * 1998-04-21 1999-10-28 Siemens Aktiengesellschaft Pale de turbine
US20010018020A1 (en) * 1998-08-31 2001-08-30 Peter Tiemann Turbine guide blade

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2500745A (en) 1944-09-21 1950-03-14 Gen Electric Bucket structure for high-temperature turbomachines
BE794195A (fr) 1972-01-18 1973-07-18 Bbc Sulzer Turbomaschinen Aube directrice refroidie pour des turbines a gaz
GB1605309A (en) 1975-03-14 1989-02-01 Rolls Royce Stator blade for a gas turbine engine
IT1079131B (it) 1975-06-30 1985-05-08 Gen Electric Perfezionato raffreddamento applicabile particolarmente a elementi di turbomotori a gas
US4283822A (en) 1979-12-26 1981-08-18 General Electric Company Method of fabricating composite nozzles for water cooled gas turbines
DE3244255A1 (de) * 1982-11-30 1984-06-14 Messerschmitt-Bölkow-Blohm GmbH, 8012 Ottobrunn Bahnvermessungs- und ueberwachungssystem
US4987736A (en) 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US5076049A (en) 1990-04-02 1991-12-31 General Electric Company Pretensioned frame
EP0550126A1 (fr) 1992-01-02 1993-07-07 General Electric Company Bouclier thermique pour post-combusteur
FR2707698B1 (fr) 1993-07-15 1995-08-25 Snecma Turbomachine munie d'un moyen de soufflage d'air sur un élément de rotor.
US5396763A (en) 1994-04-25 1995-03-14 General Electric Company Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield
JPH08135402A (ja) 1994-11-11 1996-05-28 Mitsubishi Heavy Ind Ltd ガスタービン静翼構造
US5797725A (en) * 1997-05-23 1998-08-25 Allison Advanced Development Company Gas turbine engine vane and method of manufacture
US6375415B1 (en) * 2000-04-25 2002-04-23 General Electric Company Hook support for a closed circuit fluid cooled gas turbine nozzle stage segment

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3610769A (en) * 1970-06-08 1971-10-05 Gen Motors Corp Porous facing attachment
GB1605219A (en) * 1975-10-02 1984-08-30 Rolls Royce Stator vane for a gas turbine engine
GB1516757A (en) * 1975-10-14 1978-07-05 United Technologies Corp Turbomachinery vane or blade with cooled platforms
US5249418A (en) * 1991-09-16 1993-10-05 General Electric Company Gas turbine engine polygonal structural frame with axially curved panels
WO1999054597A1 (fr) * 1998-04-21 1999-10-28 Siemens Aktiengesellschaft Pale de turbine
US20010018020A1 (en) * 1998-08-31 2001-08-30 Peter Tiemann Turbine guide blade

Also Published As

Publication number Publication date
JP4249990B2 (ja) 2009-04-08
CN1313707C (zh) 2007-05-02
EP1329593B1 (fr) 2005-03-23
US20030133802A1 (en) 2003-07-17
ATE291677T1 (de) 2005-04-15
JP2003214109A (ja) 2003-07-30
CN1436920A (zh) 2003-08-20
DE50202538D1 (de) 2005-04-28
US6887040B2 (en) 2005-05-03

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