EP3236009A1 - Aube directrice comprenant un tuyau de raccordement - Google Patents

Aube directrice comprenant un tuyau de raccordement Download PDF

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Publication number
EP3236009A1
EP3236009A1 EP16166430.5A EP16166430A EP3236009A1 EP 3236009 A1 EP3236009 A1 EP 3236009A1 EP 16166430 A EP16166430 A EP 16166430A EP 3236009 A1 EP3236009 A1 EP 3236009A1
Authority
EP
European Patent Office
Prior art keywords
guide
connecting tube
outer platform
platform
vane according
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Withdrawn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
EP16166430.5A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Radan RADULOVIC
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 EP16166430.5A priority Critical patent/EP3236009A1/fr
Priority to EP17717143.6A priority patent/EP3420197B1/fr
Priority to PCT/EP2017/058628 priority patent/WO2017182322A1/fr
Priority to CN201780024523.1A priority patent/CN109072700B/zh
Priority to JP2018555205A priority patent/JP6779310B2/ja
Priority to US16/089,645 priority patent/US10876414B2/en
Publication of EP3236009A1 publication Critical patent/EP3236009A1/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Withdrawn legal-status Critical Current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
    • F01D5/12—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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/237—Brazing

Definitions

  • the invention relates to a guide vane for a turbomachine, in particular a gas turbine, with an outer platform in the intended mounted state, an airfoil protruding from the outer platform, which extends in a longitudinal direction and defines a cavity in its interior, an inner platform opposite to the outer platform is disposed and connected to the airfoil, and a connecting tube penetrating the cavity of the airfoil in the longitudinal direction, the first free end is inserted into a passage opening formed in the inner platform and materially connected to the inner platform and the second free end in a cooling fluid inlet opening formed on the outer platform is spaced from its edge and projects outwardly from the outer platform.
  • Turbomachines such as gas turbines are known in the art in various configurations and serve to convert thermal energy and flow energy of a working fluid, in particular a hot gas into rotational energy. They include a housing in which a flow channel extends in an axial direction. In the flow passage, a plurality of turbine stages are arranged one behind the other in the axial direction and spaced from each other.
  • Each turbine stage includes a plurality of vanes which form a vane ring connected to the housing and favorably influence the flow direction of the working fluid.
  • a vane usually comprises a platform which is arranged radially outwards in the intended mounted state of the vane.
  • the vane includes an airfoil, which from the outer Platform protrudes and extends in a longitudinal direction.
  • the vane has an inner platform connected to the airfoil opposite the outer platform.
  • the vane ring is closed inwardly by a retaining ring in which the inner platforms of the vanes are held.
  • each turbine stage includes a plurality of blades that form a blade ring connected to a rotor centrally supported and passing through the housing in the axial direction.
  • a rotor centrally supported and passing through the housing in the axial direction.
  • the retaining rings of the guide vane rings are arranged.
  • the flow channel of the turbomachine is flowed through by a working fluid.
  • the working fluid flowing through the flow channel is deflected by the guide vanes in such a way that it optimally flows against the rotor blades arranged behind it and acts on it with a force.
  • the torque imparted by the vanes causes the rotor to rotate.
  • the rotational energy of the rotor can be converted for example by means of a generator into electrical energy.
  • One way to increase the thermal capacity for example, a guide vane, is to dissipate heat from the vane by means of a cooling fluid. This will be provided in its interior a cavity which is flowed through by the cooling fluid.
  • the retaining rings on the inner sides of the vane rings are strongly heated by hot gas flowing into the circumferential groove.
  • a proven means for cooling a retaining ring is to form the retaining ring with a U-shaped cross-section, whereby in the retaining ring a circumferentialdefluidnut is created.
  • This cooling fluid groove is supplied with cooling fluid which flows from the guide vanes through an outlet opening provided in the inner platform into the cooling fluid groove of the retaining ring.
  • this cooling fluid in the airfoil of the vane has already absorbed heat, which reduces the cooling capacity available to the retaining ring.
  • a higher cooling capacity of the cooling fluid in the retaining ring can be achieved by a special jumper tube, which penetrates the cavity of the blade of the guide blade in the longitudinal direction and through which the cooling fluid flows in a direct way and largely unheated in theisserfluidnut the retaining ring.
  • a first free end of the connecting tube is inserted into a passage opening formed in the inner platform and connected to the inner platform in a material-locking manner.
  • the second free end of the connecting tube is spaced apart from the edge thereof in a cooling fluid inlet opening formed on the outer platform and projects outwardly from the outer platform.
  • connecting tubes can have positioning means in their second free end region, which extend in opposite directions starting from the connecting tube and are supported on the pressure-side and suction-side edges of the cooling fluid inlet opening.
  • positioning means can be insufficient to with regard to strong operational vibrations the turbomachine and thermal changes in length of the connecting pipe to ensure a sufficiently reliable positioning of the connecting pipe in the cooling fluid inlet opening.
  • a guide vane of the type mentioned in which at least one guide means is attached to the outer platform for guiding the connecting tube, that is designed and arranged such that it leads the connecting tube in the event of a thermal change in length in the longitudinal direction.
  • the invention is based on the consideration to provide on the outer platform guide means for guiding the connecting tube, which allow movement of the connecting tube due to thermal change in length, without endangering its positioning in the cooling fluid inlet opening.
  • the guide means provided on the outer platform can restrict the degrees of freedom of movement of the connection pipe to the longitudinal direction of the guide blade.
  • the at least one guide means extends from the outer platform in the direction of the connecting tube and surrounds a portion of the connecting tube at least partially, in particular completely, leaving a game.
  • a guide means holds the connecting tube with respect to the outer platform, in particular with respect to the distance from the edge of the cooling fluid inlet opening in a predetermined position.
  • the at least one guide means has a guide opening. This guide opening is penetrated by the connecting pipe or a portion of the connecting pipe, whereby the connecting pipe is held securely transversely to the longitudinal direction.
  • At least one guide projection extending in the longitudinal direction is formed on the second free end of the connecting tube corresponding to the guide opening of the at least one guide means, which engages through the guide opening of the at least one guide means.
  • the guide opening may have a smaller cross-sectional area than the connecting tube, which can also reduce the dimensions of the guide means. The smaller the dimensions of the guide means, the less the cooling fluid is prevented from entering the cooling fluid inlet opening.
  • the at least one guide projection is formed like a pin.
  • the cross section of the guide projection perpendicular to the longitudinal direction may be, for example, round, square or rectangular.
  • two guide means are provided, which extend from opposite regions of the outer platform in the direction of the connecting tube and in particular face each other.
  • the two guide means are formed as sheets, which cohesively with the outer platform in particular by welding or soldering.
  • Welded or soldered plates represent particularly inexpensive and easy to produce guide means.
  • two guide projections can be arranged opposite one another and spaced from one another on the connecting tube and can be encompassed by a respective guide means.
  • the distance between the two guide projections in the range of 5 and 10 and is preferably 7. Such distances correspond to the diameters of conventional connecting pipes.
  • the two guide means may be provided on the pressure side and on the suction side of the connection pipe. This arrangement allows particularly short guide means, which is associated with an improved vibration behavior of the guide means.
  • the blade can have a peripheral wall.
  • the connecting tube is arranged in the cavity spaced from the circumferential wall. In this way, a thermal bridge between the connecting pipe and the hot peripheral wall of the airfoil is avoided and the cooling fluid flowing around the connecting pipe additionally provides for heat insulation.
  • the cohesive connection between the connecting tube and the inner platform can be produced by welding or soldering.
  • connection between the connecting tube and the inner platform is preferably fluid-tight. This prevents heated cooling fluid from escaping from the cavity into the retaining ring of the vane ring.
  • FIGS. 1 to 3 show a guide vane 1 for a turbomachine, not shown, in particular a gas turbine according to an embodiment of the present invention.
  • the vane 1 has an outer flat 2, which is arranged in the intended mounted state of the vane 1 radially outward. Further, the vane 1 includes an airfoil 3 extending in a longitudinal direction L and projecting from the outer platform 2. In the interior of the airfoil 3, a cavity 4 is defined.
  • the guide blade 1 has an inner platform 5, which is arranged opposite to the outer platform 2 and connected to the blade 3.
  • the guide vane 1 comprises a connecting tube 6, which passes through the cavity 4 of the airfoil 3 in the longitudinal direction L.
  • a first free end of the connecting tube 6 is connected to the inner platform 5 by welding material fit and fluid-tight.
  • the second free end of the connecting tube 6 is arranged in a cooling fluid inlet opening 7 formed on the outer platform 2 at a distance from its edge 8 and protrudes outwards from the outer platform 2.
  • the guide means 9 are fastened to the outer platform 2, which extend from opposite regions of the outer platform 2 in the direction of the connecting tube 6 and face each other.
  • the guide means 9 are formed as sheets, which are arranged on the pressure side and the suction side of the airfoil 3 and are connected to the outer platform 2 cohesively by welding.
  • Each guide means 9 has a slot-shaped guide opening 10 to completely surround a portion 11 of the connecting tube 6 while leaving a game.
  • a partial encompassing can alternatively also suffice.
  • the two sections 11 are presently provided as in the longitudinal direction L extending guide projections 11 which are formed on the second free end of the connecting tube 6 corresponding to the guide openings 10 and the guide openings 10 of the two guide means 9 pass through.
  • the guide projections 11 are formed like a pin with rectangular cross-section and arranged opposite each other and spaced from each other on the connecting pipe 6. The distance between the two guide projections 11 is about 7.
  • the airfoil 3 has a peripheral wall 12, to which the connecting pipe 6 is arranged in the cavity 4 at a distance.
  • FIGS. 4 and 5 schematically show a portion of a turbomachine with guide vanes according to the invention 1.
  • the Turbomachine comprises a housing 13 in which in a axial direction A, a flow channel 14 extends. Furthermore, the turbomachine comprises a plurality of turbine stages 15, each comprising a vane ring 16 and a blade ring 17, wherein the turbine stages 15 are arranged in the flow channel 14 in the axial direction A one behind the other and spaced from each other.
  • the vane rings 15 are each formed from a plurality of guide vanes 1 according to the invention and each comprise a U-shaped retaining ring 18 with a circumferentialdefluidnut 19, in which the inner platforms 5 of the vanes 1 are held.
  • the flow channel 14 is flowed through by an expanding hot gas.
  • the guide vanes 1 of the vane rings 15 are simultaneously flowed through by a cooling fluid and cooled.
  • a portion of the cooling fluid flows to cool the airfoil 3 through the cooling fluid inlet opening 7 in the cavity 4, while another part of the cooling fluid for cooling the retaining rim 18 through the connecting pipe 6 directly and without heating contact with the peripheral wall 12 of the airfoil 3 in the retaining ring 18th flows.
  • An advantage of the guide vane 1 according to the invention is that the connecting tube 6 can move in the longitudinal direction L in the guide openings 10 of the guide means 9 in the case of a thermally induced change in length, without leaving its position in the cooling fluid inlet opening 7 with respect to its edge 8. Beyond that freedom of movement of the connecting tube 6 relative to the outer platform 2 are avoided by the attached to the outer platform 2 guide means 9.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16166430.5A 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement Withdrawn EP3236009A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP16166430.5A EP3236009A1 (fr) 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement
EP17717143.6A EP3420197B1 (fr) 2016-04-21 2017-04-11 Aube directrice comprenant un tuyau de raccordement
PCT/EP2017/058628 WO2017182322A1 (fr) 2016-04-21 2017-04-11 Aube directrice comportant un tube de jonction
CN201780024523.1A CN109072700B (zh) 2016-04-21 2017-04-11 具有连接管的导向静叶
JP2018555205A JP6779310B2 (ja) 2016-04-21 2017-04-11 接続管を有するガイドベーン
US16/089,645 US10876414B2 (en) 2016-04-21 2017-04-11 Guide vane having a connecting tube

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16166430.5A EP3236009A1 (fr) 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement

Publications (1)

Publication Number Publication Date
EP3236009A1 true EP3236009A1 (fr) 2017-10-25

Family

ID=55802307

Family Applications (2)

Application Number Title Priority Date Filing Date
EP16166430.5A Withdrawn EP3236009A1 (fr) 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement
EP17717143.6A Active EP3420197B1 (fr) 2016-04-21 2017-04-11 Aube directrice comprenant un tuyau de raccordement

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP17717143.6A Active EP3420197B1 (fr) 2016-04-21 2017-04-11 Aube directrice comprenant un tuyau de raccordement

Country Status (5)

Country Link
US (1) US10876414B2 (fr)
EP (2) EP3236009A1 (fr)
JP (1) JP6779310B2 (fr)
CN (1) CN109072700B (fr)
WO (1) WO2017182322A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2058944A (en) * 1979-09-14 1981-04-15 United Technologies Corp Vane cooling structure
US20040062637A1 (en) * 2002-09-27 2004-04-01 Bryan Dube Integral swirl knife edge injection assembly
DE69917524T2 (de) * 1998-04-09 2005-06-16 Snecma Moteurs Verfahren zur Verminderung des Spiels zwischen Fluidzuleitung und Leitschaufelkammer eines Turboreaktors
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3301527A (en) 1965-05-03 1967-01-31 Gen Electric Turbine diaphragm structure
JP2004028036A (ja) 2002-06-28 2004-01-29 Hitachi Ltd ガスタービン静翼及びガスタービン
FR2851286B1 (fr) 2003-02-18 2006-07-28 Snecma Moteurs Aubes de turbine refroidie a fuite d'air de refroidissement reduite
JP2012246785A (ja) 2011-05-25 2012-12-13 Mitsubishi Heavy Ind Ltd ガスタービン静翼
US9617870B2 (en) * 2013-02-05 2017-04-11 United Technologies Corporation Bracket for mounting a stator guide vane arrangement to a strut in a turbine engine
CA2903730A1 (fr) * 2013-03-08 2014-09-12 Rolls-Royce North American Technologies, Inc. Procede de formation d'un ensemble aile portante composite de moteur a turbine a gaz et ensemble aile portante correspondante
US9581028B1 (en) * 2014-02-24 2017-02-28 Florida Turbine Technologies, Inc. Small turbine stator vane with impingement cooling insert
US9920869B2 (en) * 2014-05-22 2018-03-20 United Technologies Corporation Cooling systems for gas turbine engine components

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2058944A (en) * 1979-09-14 1981-04-15 United Technologies Corp Vane cooling structure
DE69917524T2 (de) * 1998-04-09 2005-06-16 Snecma Moteurs Verfahren zur Verminderung des Spiels zwischen Fluidzuleitung und Leitschaufelkammer eines Turboreaktors
US20040062637A1 (en) * 2002-09-27 2004-04-01 Bryan Dube Integral swirl knife edge injection assembly
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse

Also Published As

Publication number Publication date
CN109072700B (zh) 2021-01-29
CN109072700A (zh) 2018-12-21
US10876414B2 (en) 2020-12-29
WO2017182322A1 (fr) 2017-10-26
US20190120068A1 (en) 2019-04-25
EP3420197B1 (fr) 2020-02-05
EP3420197A1 (fr) 2019-01-02
JP6779310B2 (ja) 2020-11-04
JP2019516039A (ja) 2019-06-13

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