EP1283328A1 - Douille d'étanchéité pour turbines à gaz refroidies - Google Patents

Douille d'étanchéité pour turbines à gaz refroidies Download PDF

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Publication number
EP1283328A1
EP1283328A1 EP01119265A EP01119265A EP1283328A1 EP 1283328 A1 EP1283328 A1 EP 1283328A1 EP 01119265 A EP01119265 A EP 01119265A EP 01119265 A EP01119265 A EP 01119265A EP 1283328 A1 EP1283328 A1 EP 1283328A1
Authority
EP
European Patent Office
Prior art keywords
coolant
channel
gas 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.)
Withdrawn
Application number
EP01119265A
Other languages
German (de)
English (en)
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 EP01119265A priority Critical patent/EP1283328A1/fr
Publication of EP1283328A1 publication Critical patent/EP1283328A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the 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
    • 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
    • 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
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Definitions

  • the invention relates to a gas turbine with a number arranged on a turbine shaft via a blade root Blades, each with an integrated coolant channel exhibit.
  • Gas turbines are used to drive generators in many areas or used by work machines.
  • 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 working medium at high temperature is via a turbine unit downstream of the combustion chamber managed where it relaxes while working.
  • 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 working medium drive the turbine shaft.
  • For guiding the working medium in the turbine unit are usually between neighboring rows of blades with the turbine housing connected rows of vanes arranged.
  • the components and parts exposed to it are high exposed to thermal loads.
  • Ensuring affected components is common cooling of the affected components, in particular of Rotor and / or guide vanes of the turbine unit are provided.
  • the turbine blades are therefore usually designed to be coolable, being particularly effective and reliable Cooling seen in the flow direction of the working medium first rows of blades should be ensured.
  • the respective turbine blade usually has one integrated into the airfoil or the airfoil Coolant channel from which a coolant is targeted especially the thermally stressed zones of the turbine blade is feedable.
  • Cooling air for example, is used as the coolant. This is usually the case for the respective turbine blade in the manner of open cooling via an integrated one Coolant channel supplied. Flowing through from this the cooling air in the branching ducts are provided Areas of the turbine blade. Are on the outlet side these channels left open so that the cooling air after the Flow through the turbine blade and exits with the working medium in the turbine unit mixed.
  • a desirable saving in cooling air requirement for these reasons is achievable by keeping the cooling system closed Cooling system is formed.
  • a closed cooling system is the used coolant, especially cooling air, returned to the combustion process.
  • the cooling air has a comparatively high pressure loss may be subject to, but is usually a local and customized supply of cooling air depending on the intended feed point is comparatively high pressure required. This includes the pressure loss when guiding the cooling air through a closed system to consider.
  • Systems can increase pressure loss significantly contribute to the requirements for the cooling air to be provided.
  • high pressure means that it is comparatively complex Construction of the associated systems, in particular at high pressure requirements to provide the Cooling air compressors required depending on the operating conditions those achievable through closed cooling Efficiency or performance advantages partially or even can fully compensate.
  • the invention is therefore based on the object of a gas turbine of the type mentioned above, in the case of a safe cooling of the blades of the coolant requirement is kept particularly low and a reliable separated Feeding the blades with various coolants, especially with cooling air of different pressures, at particularly low service requirements.
  • a blade associated with the turbine shaft Supply channel for coolant in an outlet side End area is expanded in its cross section, and in the end area with an outer contour on the inner cross section adapted to the end region, in its longitudinal direction slidable feed bushing is arranged.
  • the invention is based on the consideration that for one of the needs for coolant for reliable cooling the blades can be kept particularly low if a coolant leakage is largely excluded, and that on the other hand a higher flexibility of cooling can be achieved is chosen by designing the cooling can have various leads attached close to each other are. Both can be realized if a reliable one Seal between the supply channel for coolant in the Turbine shaft and the coolant channel in the blade can be provided. This in turn is done with simple Funds achieved through targeted use of the company or gas turbine centrifugal force.
  • the socket, the hollow is for the passage of the coolant, then the Center axis of the turbine shaft pressed outward and is therefore on the underside of the blade root. Thereby there is a good sealing effect because the centrifugal force is very high is high. As experiments have shown, it can be in the range of 10,000 g, with g being the acceleration due to gravity is designated.
  • a blade assigned to each blade in the turbine shaft has an integrated drainage channel for coolant in an entry-side initial area in its cross section is expanded, with one in its initial range Outer contour adapted to the inner cross section of the starting area longitudinally displaceable lead bushing is arranged. In this way, both the coolant supply line as well as the coolant drainage Cooling effect reinforcing a highly effective seal of the coolant.
  • the sealing effect can in particular without additional components can be further advantageously increased if an inlet assigned to the supply duct and / or a Discharge channel assigned outlet of the coolant channel in an essentially flat, the end of the Supply channel and / or the initial area of the discharge channel facing contact surface of the respective blade root empties.
  • the feed bushing and if necessary the discharge socket is extremely safe during operation of the gas turbine and with a large contact surface flat against the contact surface of the blade root, which prevents any leakage becomes.
  • Sealing of the coolant channel is also achieved if the feed bushing and, if necessary, the discharge bushing is displaceable on a straight line which is the central axis of the Turbine shaft does not cut. In this case it just does the component running in the direction of the straight line the centrifugal force the seal.
  • a particularly good sealing effect is achieved when the feed bushing is advantageous and / or the lead bushing related to the central axis the turbine shaft are / is radially displaceable. Consequently the feed bushing and / or the discharge bushing is exact oriented towards the centrifugal force, which is their optimal Use for sealing possible.
  • each Socket with the associated channel piece formed annulus intended.
  • the respective bushing on their facing away from the blade root Tapered end and with a circumferential sealing ring Mistake.
  • Air is preferably provided as the coolant in the gas turbine, that is particularly easy to provide in this case and is manageable.
  • Coolant supply bushing in the end area of a arranged in the turbine shaft supply duct and fitted into it, one in the operation of the gas turbine with the centrifugal force increasing seal from the supply channel and a coolant channel in a blade is, whereby different supply lines are placed close to each other can be prevented and loss of coolant becomes.
  • a recess for example a bore, to provide the end region of the supply duct as well as the socket as such with extremely small manufacturing tolerances producible, since this is preferably Round body. Due to the small tolerances is a high sealing effect also along the longitudinal direction of the bush achievable.
  • the respective blade is also special can be assembled or disassembled with little effort.
  • the gas turbine 1 or FIG. 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive the compressor 2 and a generator, not shown or a work machine. To do this are the turbine 6 and the compressor 2 on a common, also as a turbine rotor designated turbine shaft 8 arranged with the the generator or the working machine is also connected and which is rotatably mounted about its central axis 9.
  • the combustion chamber 4 is provided with a number of burners 10 Combustion of a liquid or gaseous fuel. It is still not closer to its inner wall provided heat shield elements.
  • the turbine 6 has a number of with the turbine shaft 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of fixed guide vanes 14, which is also ring-shaped with the formation of Guide vane rows attached to an inner wall 16 of the turbine 6 are.
  • the blades 12 serve to drive the Turbine shaft 8 by momentum transfer from the turbine 6 flowing through Working medium M.
  • the guide vanes 14, however, serve to flow the working medium M between each two seen in the flow direction of the working medium M. successive rows of blades or blade rings.
  • a successive pair from a wreath of Guide vanes 14 or a row of guide vanes and from one Wreath of blades 12 or a row of blades is also referred to as the turbine stage.
  • Each guide vane 14 has one which is also referred to as a blade root Platform 18, which is used to fix the respective guide vane 14 on the inner wall 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparison heavily loaded component that the outer boundary a hot gas duct for the one flowing through the turbine 6 Working medium M forms.
  • Each blade 12 is analog Way over a platform 20 also referred to as a blade root attached to the turbine shaft 8.
  • each guide ring 21 is also hot, flowing through the turbine 6 Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite to it 12 spaced by a gap.
  • the between Guide rings 21 arranged adjacent rows of guide vanes serve in particular as cover elements that cover the inner wall 16 or other housing installation parts before a thermal Overuse by the flowing through the turbine 6 protects hot working medium M.
  • the gas turbine 1 for a comparatively high outlet temperature of the working medium emerging from the combustion chamber 4 M designed from about 1200 ° C to 1300 ° C.
  • the blades 12 and Guide vanes 14 designed to be coolable as cooling medium by cooling air.
  • FIG 2 is by means of a blade root 20 on the Turbine shaft 8 arranged blade 12 of the gas turbine shown enlarged.
  • the blade 12 has an in they integrated coolant channel 24, the course of which here is reproduced only in a highly simplified manner, and therefore is drawn in dashed lines.
  • Air as coolant K to reduce the thermal load the blade 12 guided, a feeding of the Coolant channel 24 through an integrated in the turbine shaft 8, here only simplified supply channel 26 takes place.
  • the flow direction of the coolant K becomes indicated by arrows 28.
  • the supply channel 26 is expanded, and in this End region 30 is a displaceable in its longitudinal direction L1 Feed bushing 32 arranged.
  • the outer contour of the Feed bushing 32 is on the inside cross section of the end portion 30 of the feed channel 26 adapted so that the socket 32 sealing on the inner wall of the feed channel 26 is applied.
  • the blade 12 has a closed cooling, what means that the coolant K is derived from the blade 12 and is returned. This derivation and return takes place by means of an integrated in the turbine shaft 8 Discharge channel 34.
  • the transition from the coolant channel 24 to Discharge channel 34 is analogous to the transition from the feed channel 26 to the coolant duct 24: the discharge duct 34 is in an entry-side initial area 36 with a expanded cross-section, being in the initial area 36 a lead bushing displaceable in its longitudinal direction L2 38, the outer contour of the inner cross section of the Starting area 36 is sealingly adapted, is arranged.
  • Both the feed bushing 32 and the drain bushing 38 are related to the central axis 9 of the turbine shaft 8 radially displaceable.
  • FIG. 3 An exploded view of a connection area of a Turbine shaft 8 with a further blade 12 one The gas turbine is shown in FIG. 3.
  • a coolant channel 24 having blade root 20 in a disk groove 46 on the Turbine shaft 8 arranged.
  • the turbine shaft 8 with a feed channel 26 and a drain channel 34 for Provide coolant, the supply channel 26 in one End area 30 and the discharge channel 34 in an initial area 36 is provided with a cross-sectional expansion.
  • a feed bush 32 In the end portion 30 is a feed bush 32 and in the Starting area 36 a lead bushing 38 slidably mounted.
  • the centrifugal force Bushes 32, 38 pressed against the flat contact surface 52 which creates tight transitions between channels 24, 26, 34 result.
  • the discharge channel 34 shown in FIG. 3 could also be a be another supply channel through which another coolant than the blade root 20 through the feed channel 26 is feedable.
  • the sockets 32, 38 in the extended areas 30, 36 of the channels 26, 34 and the Blade foot 20 would not result in any changes.
  • sealing is a crosstalk between the Channels 26, 34 excluded.
  • the Guide bush 32 and / or the department bush 38 on her respective end 60 facing away from the blade root 18 or 20 be beveled.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP01119265A 2001-08-09 2001-08-09 Douille d'étanchéité pour turbines à gaz refroidies Withdrawn EP1283328A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01119265A EP1283328A1 (fr) 2001-08-09 2001-08-09 Douille d'étanchéité pour turbines à gaz refroidies

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP01119265A EP1283328A1 (fr) 2001-08-09 2001-08-09 Douille d'étanchéité pour turbines à gaz refroidies

Publications (1)

Publication Number Publication Date
EP1283328A1 true EP1283328A1 (fr) 2003-02-12

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EP01119265A Withdrawn EP1283328A1 (fr) 2001-08-09 2001-08-09 Douille d'étanchéité pour turbines à gaz refroidies

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EP (1) EP1283328A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2312124A3 (fr) * 2009-10-14 2011-11-16 Kawasaki Jukogyo Kabushiki Kaisha Agencement d'étanchéité dans un moteur à turbine à gaz

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931623A (en) * 1957-05-02 1960-04-05 Orenda Engines Ltd Gas turbine rotor assembly
DE19644543A1 (de) * 1996-10-26 1998-04-30 Asea Brown Boveri Vorrichtung zur Dichtung des Strömungsüberganges eines Kühlmediums zwischen Rotor und Laufschaufel
EP0860587A2 (fr) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Tubulure de connexion pour le transfert d'un fluide de réfroidissement d'un disque de rotor à une aube d'une turbomachine
EP0860586A2 (fr) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Tubulure de connexion pour le transfert d'un fluide de réfroidissement d'un disque de rotor à une aube d'une turbomachine
EP0890710A2 (fr) * 1997-07-07 1999-01-13 Mitsubishi Heavy Industries, Ltd. Refroidissement des aubes de turbine à vapeur

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931623A (en) * 1957-05-02 1960-04-05 Orenda Engines Ltd Gas turbine rotor assembly
DE19644543A1 (de) * 1996-10-26 1998-04-30 Asea Brown Boveri Vorrichtung zur Dichtung des Strömungsüberganges eines Kühlmediums zwischen Rotor und Laufschaufel
EP0860587A2 (fr) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Tubulure de connexion pour le transfert d'un fluide de réfroidissement d'un disque de rotor à une aube d'une turbomachine
EP0860586A2 (fr) * 1997-02-21 1998-08-26 Mitsubishi Heavy Industries, Ltd. Tubulure de connexion pour le transfert d'un fluide de réfroidissement d'un disque de rotor à une aube d'une turbomachine
EP0890710A2 (fr) * 1997-07-07 1999-01-13 Mitsubishi Heavy Industries, Ltd. Refroidissement des aubes de turbine à vapeur

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2312124A3 (fr) * 2009-10-14 2011-11-16 Kawasaki Jukogyo Kabushiki Kaisha Agencement d'étanchéité dans un moteur à turbine à gaz
US8562294B2 (en) 2009-10-14 2013-10-22 Kawasaki Jukogyo Kabushiki Kaisha Sealing arrangement for use with gas turbine engine

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