EP1008723B1 - Refroidissement de plateformes de turbomachines - Google Patents

Refroidissement de plateformes de turbomachines Download PDF

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Publication number
EP1008723B1
EP1008723B1 EP98811219A EP98811219A EP1008723B1 EP 1008723 B1 EP1008723 B1 EP 1008723B1 EP 98811219 A EP98811219 A EP 98811219A EP 98811219 A EP98811219 A EP 98811219A EP 1008723 B1 EP1008723 B1 EP 1008723B1
Authority
EP
European Patent Office
Prior art keywords
platforms
cooling
fluid
platform
channel
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
EP98811219A
Other languages
German (de)
English (en)
Other versions
EP1008723A1 (fr
Inventor
Hartmut Hähnle
Kenneth Hall
Sriwickrama Prithiviraj Dr. Harasgama
Konrad Dr. Vogeler
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.)
General Electric Switzerland GmbH
Original Assignee
Alstom Schweiz 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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Priority to DE59810806T priority Critical patent/DE59810806D1/de
Priority to EP98811219A priority patent/EP1008723B1/fr
Priority to US09/456,332 priority patent/US6309175B1/en
Publication of EP1008723A1 publication Critical patent/EP1008723A1/fr
Application granted granted Critical
Publication of EP1008723B1 publication Critical patent/EP1008723B1/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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the invention relates to a device for cooling of platforms in Turbomachinery, in particular in gas turbines.
  • the efficiency of turbomachines can be increased by increasing the cycle process parameters of the turbomachine.
  • the relevant cycle process parameters are the pressure and the temperature of the fluid.
  • the fluid temperatures which usually occur during the operation of turbomachines today are already well above the permissible material temperatures of the components, in particular in the turbine inlet region.
  • the components forming the flow channel or projecting into the flow channel are directly exposed to the hot fluid flow.
  • the conditional by the heat conduction of the material heat dissipation of the components is generally not sufficient here to avoid over-temperature of the components. Too high material temperatures initially lead to a decrease in the strength values of the material. This often leads to cracking in components.
  • the flow channel of a turbomachine is often constructed of annularly lined-up platforms.
  • the blades of the turbomachine are often arranged on such platforms. In most cases, one bucket is made in one piece with one platform each. In particular, in stators such platforms are also often arranged in the form of a shroud of the blading at the blade tips of the blades. These platforms are thus exposed directly to the hot fluid flow.
  • a temperature profile of the fluid emerging from the combustion chamber, usually air, in the turbine inlet region has traditionally been desired above the channel height.
  • This temperature profile could be achieved via an admixture of cooling fluid in the edge regions of the hot fluid flow in the outlet region of the combustion chamber.
  • the fluid immediately adjacent to the side walls and thus to the platforms therefore had a significantly reduced temperature compared to the temperature of the core flow.
  • an over-temperature of the platforms could be avoided.
  • the invention is based on the object, platforms efficient and reliable to cool.
  • This object is achieved in that at least in one Section along the running between adjacent platforms Parting line a cooling channel is arranged, which as a slot-shaped depression in both adjacent to the parting line side walls of the platforms is executed, and the one along the parting line changing depth of penetration in the respective platform.
  • the cooling fluid guided in the cooling channel has a lower one Temperature on than the adjacent platforms. This is what happens a convective heat transfer between the to the cooling channel adjacent platforms and the cooling fluid and consequently to one Cooling the platforms. It turned out that in this way realized cooling almost independent of fluctuations of the Operating state of the turbomachine is. Furthermore, compared to the other cooling method described above a much smaller Coolant fluid mass flow required to cool the platforms.
  • the cooling channel extends at least in sections approximately parallel to the platform surface. This ensures that a large area of the platform is cooled evenly. It was found that thus a largely uniform Setting temperature distribution in the refrigerated areas of the platform. So-called 'hot spots' in the form of local overheating of the platforms become thereby avoided.
  • the platforms are one-piece or multi-piece with on the platforms arranged blades executed.
  • the platforms can be on the blade foot or be arranged on the blade head of the blades. Form strung together the platforms one or both side walls of the flow channel.
  • the cooling channel approximately centrally between the blades to arrange.
  • Particularly advantageous is the cooling channel with a Shovel profile course executed approximately similar course. It presented It turns out that an over-temperature is common in the peripheral areas and the free areas of the platforms occurs.
  • the free areas of a platform are the areas that in the top view or the bottom view are not one on the Platform arranged shovel to be covered.
  • the cooling channel course has at least one S-beat in such a way, in that at least a part of the cooling fluid guided in the cooling channel is the one Dividing line overflowed.
  • the Cooling channel as a slot-shaped depression in the at the parting line adjacent side walls of the platform and thus not as closed Cooling channel, but is open towards the parting line, the Cooling fluid accordingly also flow into the parting line.
  • the Cooling fluid supplied to the cooling channel in a simple manner via the parting line become.
  • cooling channel is open towards the parting line, it is expedient to use the Cooling channel arranged by means of at least one in the cooling channel Sealing element, preferably a sealing strip inserted in the cooling channel, opposite to a fluid applied to the top of the platforms, in the Usually the hot fluid, seal. As a result, an outflow of the Cooling fluid prevented from the cooling channel.
  • Sealing element preferably a sealing strip inserted in the cooling channel, opposite to a fluid applied to the top of the platforms, in the Usually the hot fluid, seal.
  • an open to the parting line cooling channel is advantageous at least in a section along the parting line in a sealing chamber and a Cooling chamber divided. This subdivision of the cooling channel preferably takes place via a gradation of the channel height.
  • the sealing chamber is to arrange a Sealing element expediently designed with a larger channel height.
  • the Cooling chamber advantageously has a smaller channel height at the same time greater penetration depth.
  • FIG. 1 shows a platform 110 for use in a turbomachine typical embodiment shown in a side view.
  • the hatching was not used here, as usual, for marking cut surfaces, but merely serves to illustrate the presentation.
  • the Platform 110 in one piece with one on the platform arranged blade 120 executed.
  • the platform 110 is in one Arrangement shown with a rotor disc 121 of the turbomachine. This Arrangement corresponds to the typical structure of a bladed Turbine rotor of a turbomachine. Shown is only one of the am Scope of the rotor disc lined up, each with platforms running Blades. Form the platforms strung together on the circumference of the runner in this case, the hub-side side wall of the flow channel of the turbomachine.
  • the hot fluid flow 125 as the main flow of Turbomachine flows in the representation from right to left along the Top of the platform 110. This results in an immediate Heat transfer between the hot fluid 125 and the platform 110.
  • the Temperature of the hot fluid 125 is in this case at least in the full load range of Turbomachine above the maximum permissible material temperature of the platform.
  • a cooling channel 130 arranged.
  • the cooling channel 130 is approximately parallel to that of the hot Fluid flow facing top of the platform 110. According to the Representation is the cooling channel 130 as a slot-shaped depression in the Side wall of the platform 110 executed.
  • Cooling channel 130 is fed here from two reservoirs with cooling fluid.
  • Cooling fluid 126 flows from between the platform and the rotor disk arranged cooling fluid reservoir 155 via an opening 150 in the cooling channel 130.
  • Another way of supplying cooling fluid to the cooling channel 130 results here via the lateral opening 151 of the cooling channel.
  • the feed the cooling channel 130 with cooling fluid 126 is thus here in relation to the Main flow 125 upstream.
  • the outflow is related to the Main flow at the downstream end of the cooling channel instead.
  • the in Figure 1 illustrated cooling channel 130 ends without specially shaped outlet in the Platform 110. The cooling fluid 126 escapes via the parting line.
  • FIG. 2 shows two juxtaposed platforms 210, 210 'in plan view.
  • a blade 220, 220 ' is arranged in each case.
  • a cooling channel 230 is arranged in the side walls of the platforms 210, 210' adjoining the parting line 211 along the parting line 211.
  • the cooling channel 230 consists of slot-shaped recesses in the side walls of both platforms 210, 210 '.
  • the arrangement of the cooling channel 230 was chosen in the illustrated embodiment so that the cooling channel 230 approximately centrally between the blades 220, 220 'extends and in this case has a profile similar to the blade profile.
  • This profile of the cooling channel 230 which is similar to the blade profile, is achieved in that the course of the cooling channel 230 along the parting line 211 has two S-strikes.
  • the sealing chamber 235 here consists of slit-shaped depressions which are arranged in both adjacent to the parting line 211 side walls with approximately the same and along the parting line 211 constant penetration depth. Furthermore, the sealing chamber 235 has a greater channel height compared to the cooling chamber 236. This feature is not apparent due to the representation perspective of Figure 2.
  • the sealing element which is expediently to be arranged in the sealing chamber is not shown. This sealing element seals the cooling channel against the hot fluid flow on the top of the platforms.
  • the cooling chamber 236 is designed in the same way as the sealing chamber 235 as a slot-shaped depression but with a smaller channel height. In contrast to the sealing chamber, the cooling chamber 236, however, as shown in Figure 2, a greater penetration depth in the platforms 210, 210 'a.
  • the feeding of the cooling channel 230 with cooling fluid 226 takes place in relation to the hot fluid flow 225 at the upstream end of the cooling passage 230 via a longitudinal slot 250 from a lower side reservoir.
  • Cooling channel 230 flows from the cooling fluid 226 the cooling channel 230 via a Outlet opening 252 in a downstream, not shown in Figure 2 Component gap.
  • a seal of the cooling channel 330 is shown in FIG. 3 as a section through two Side-by-side platforms 310, 310 'shown.
  • the cooling channel 330 is here from slot-shaped depressions in both to the parting line formed adjacent side walls of the platforms 310, 310 '.
  • the first Platform 310 is again in one piece with one located on the platform Shovel 320 executed.
  • the cooling channel 330 is over a gradation of Channel height in a sealing chamber 335 and a cooling chamber 336 divided.
  • a sealing strip 340 inserted so that he in the Cooling passage 330 flowing cooling fluid to one on the tops of the Platforms adjacent fluid seals.
  • the sealing strip 340 has at its at the rear end, a flange 341 on. This flange 341 serves here Guide the sealing fluid in the overflow of the parting line 311st

Landscapes

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

Claims (5)

  1. Plateformes d'une turbomachine, en particulier d'une turbine à gaz, dans laquelle au moins deux plateformes (_10 ; _10') sont disposées l'une à côté de l'autre, un joint de séparation (_11) s'étend entre les plateformes (_10 ; _10') et un canal de refroidissement (_30) est disposé au moins dans une portion le long du joint de séparation (_11) aux fins de refroidir les plateformes (_10 ; _10') au moyen d'un réfrigérant (226), ce canal de refroidissement étant réalisé sous forme de renfoncement en forme de fente dans deux parois latérales des plateformes (_10 ; _10') adjacentes au joint de séparation (_11), caractérisées en ce que le canal de refroidissement (_30) présente une profondeur de pénétration dans la plateforme respective (_10 ; _10') qui varie le long du joint de séparation (_11).
  2. Plateformes d'une turbomachine selon la revendication 1, caractérisées en ce que des aubes (_20 ; _20') sont disposées sur les plateformes (_10 ; _10') et le canal de refroidissement (_30) est disposé approximativement au centre entre les aubes (_20 ; _20') avec une étendue similaire au profil des aubes.
  3. Plateformes d'une turbomachine selon la revendication 1, caractérisées en ce que le canal de refroidissement (_30) présente dans son étendue au moins une forme en S de sorte qu'au moins une partie du réfrigérant (226) guidé dans le canal de refroidissement (_30) s'écoule au-dessus du joint de séparation (_11).
  4. Plateformes d'une turbomachine selon la revendication 1, caractérisées en ce que le canal de refroidissement (_30) est rendu étanche par rapport à un fluide s'appliquant à la partie supérieure des plateformes (_10 ; _10') au moyen d'au moins une bande d'étanchéité (340) disposée dans le canal de refroidissement (_30).
  5. Plateformes d'une turbomachine selon la revendication 4, caractérisées en ce que le canal de refroidissement (_30) est divisé en une chambre d'étanchéité (_35) et une chambre de refroidissement (_36) au moins dans une portion le long du joint de séparation (_11) par le biais d'un échelonnement de la hauteur du canal.
EP98811219A 1998-12-10 1998-12-10 Refroidissement de plateformes de turbomachines Expired - Lifetime EP1008723B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
DE59810806T DE59810806D1 (de) 1998-12-10 1998-12-10 Plattformkühlung in Turbomaschinen
EP98811219A EP1008723B1 (fr) 1998-12-10 1998-12-10 Refroidissement de plateformes de turbomachines
US09/456,332 US6309175B1 (en) 1998-12-10 1999-12-08 Platform cooling in turbomachines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP98811219A EP1008723B1 (fr) 1998-12-10 1998-12-10 Refroidissement de plateformes de turbomachines

Publications (2)

Publication Number Publication Date
EP1008723A1 EP1008723A1 (fr) 2000-06-14
EP1008723B1 true EP1008723B1 (fr) 2004-02-18

Family

ID=8236479

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98811219A Expired - Lifetime EP1008723B1 (fr) 1998-12-10 1998-12-10 Refroidissement de plateformes de turbomachines

Country Status (3)

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US (1) US6309175B1 (fr)
EP (1) EP1008723B1 (fr)
DE (1) DE59810806D1 (fr)

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JP4508482B2 (ja) * 2001-07-11 2010-07-21 三菱重工業株式会社 ガスタービン静翼
US6945749B2 (en) * 2003-09-12 2005-09-20 Siemens Westinghouse Power Corporation Turbine blade platform cooling system
GB0328952D0 (en) * 2003-12-12 2004-01-14 Rolls Royce Plc Nozzle guide vanes
US7097417B2 (en) * 2004-02-09 2006-08-29 Siemens Westinghouse Power Corporation Cooling system for an airfoil vane
US7309212B2 (en) * 2005-11-21 2007-12-18 General Electric Company Gas turbine bucket with cooled platform leading edge and method of cooling platform leading edge
US7416391B2 (en) * 2006-02-24 2008-08-26 General Electric Company Bucket platform cooling circuit and method
US7604456B2 (en) * 2006-04-11 2009-10-20 Siemens Energy, Inc. Vane shroud through-flow platform cover
EP1892383A1 (fr) * 2006-08-24 2008-02-27 Siemens Aktiengesellschaft Ailette de turbine à gaz à plate-forme refroidie
US8152436B2 (en) 2008-01-08 2012-04-10 Pratt & Whitney Canada Corp. Blade under platform pocket cooling
US8727726B2 (en) * 2009-08-11 2014-05-20 General Electric Company Turbine endwall cooling arrangement
US8647064B2 (en) 2010-08-09 2014-02-11 General Electric Company Bucket assembly cooling apparatus and method for forming the bucket assembly
US9416666B2 (en) * 2010-09-09 2016-08-16 General Electric Company Turbine blade platform cooling systems
US9366142B2 (en) 2011-10-28 2016-06-14 General Electric Company Thermal plug for turbine bucket shank cavity and related method
US8858160B2 (en) 2011-11-04 2014-10-14 General Electric Company Bucket assembly for turbine system
US8870525B2 (en) 2011-11-04 2014-10-28 General Electric Company Bucket assembly for turbine system
US8845289B2 (en) 2011-11-04 2014-09-30 General Electric Company Bucket assembly for turbine system
US8840370B2 (en) 2011-11-04 2014-09-23 General Electric Company Bucket assembly for turbine system
US9022735B2 (en) 2011-11-08 2015-05-05 General Electric Company Turbomachine component and method of connecting cooling circuits of a turbomachine component
EP2762679A1 (fr) * 2013-02-01 2014-08-06 Siemens Aktiengesellschaft Aube de rotor de turbine à gaz et turbine à gaz
WO2015026430A1 (fr) * 2013-08-20 2015-02-26 United Technologies Corporation Plaque de revêtement de plateforme de canalisation
US20170022839A1 (en) * 2013-12-09 2017-01-26 United Technologies Corporation Gas turbine engine component mateface surfaces
US20190085706A1 (en) * 2017-09-18 2019-03-21 General Electric Company Turbine engine airfoil assembly

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US4902198A (en) * 1988-08-31 1990-02-20 Westinghouse Electric Corp. Apparatus for film cooling of turbine van shrouds
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5382135A (en) * 1992-11-24 1995-01-17 United Technologies Corporation Rotor blade with cooled integral platform
US5634766A (en) * 1994-08-23 1997-06-03 General Electric Co. Turbine stator vane segments having combined air and steam cooling circuits
JP3457831B2 (ja) * 1997-03-17 2003-10-20 三菱重工業株式会社 ガスタービン動翼の冷却プラットフォーム

Also Published As

Publication number Publication date
EP1008723A1 (fr) 2000-06-14
DE59810806D1 (de) 2004-03-25
US6309175B1 (en) 2001-10-30

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