EP3420197B1 - Aube directrice comprenant un tuyau de raccordement - Google Patents

Aube directrice comprenant un tuyau de raccordement Download PDF

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Publication number
EP3420197B1
EP3420197B1 EP17717143.6A EP17717143A EP3420197B1 EP 3420197 B1 EP3420197 B1 EP 3420197B1 EP 17717143 A EP17717143 A EP 17717143A EP 3420197 B1 EP3420197 B1 EP 3420197B1
Authority
EP
European Patent Office
Prior art keywords
guide
connecting tube
guide vane
vane according
outer 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.)
Active
Application number
EP17717143.6A
Other languages
German (de)
English (en)
Other versions
EP3420197A1 (fr
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
Publication of EP3420197A1 publication Critical patent/EP3420197A1/fr
Application granted granted Critical
Publication of EP3420197B1 publication Critical patent/EP3420197B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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, having an outer platform in the properly installed state, an airfoil protruding from the outer platform, which extends in a longitudinal direction and defines a cavity in its interior, an inner platform which is opposite The outer platform is arranged and connected to the airfoil, and a connecting tube penetrating the cavity of the airfoil in the longitudinal direction, the first free end of which is inserted into a through opening formed in the inner platform and is integrally connected to the inner platform and the second free end of which is in a cooling fluid inlet opening formed on the outer platform is spaced from the edge thereof and protrudes outward from the outer platform.
  • Turbomachines such as gas turbines, are known in the prior art in various configurations and are used to convert thermal energy and flow energy of a working fluid, in particular a hot gas, into rotational energy. They comprise a housing in which a flow channel extends in an axial direction. In the flow channel, a plurality of turbine stages are arranged one behind the other and spaced apart in the axial direction.
  • Each turbine stage comprises a plurality of guide blades which form a guide blade ring connected to the housing and which have a favorable influence on the flow direction of the working fluid.
  • a guide vane usually comprises a platform which is arranged radially on the outside when the guide vane is installed as intended.
  • the vane further includes an airfoil that protrudes from the outer platform and extends in a longitudinal direction.
  • the guide vane has an inner platform which is connected to the airfoil opposite the outer platform.
  • the guide vane ring is closed off on the inside by a holding ring in which the inner platforms of the guide vanes are held.
  • each turbine stage comprises a plurality of rotor blades, which form a rotor blade ring connected to a rotor which is mounted centrally and passes through the housing in the axial direction.
  • Circumferential grooves are also formed in the rotor, in which the retaining rings of the guide vane rings are arranged.
  • a working fluid flows through the flow channel of the turbomachine.
  • 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 vanes arranged behind it and applies a force.
  • the torque imparted by the guide vanes sets the rotor in rotation.
  • the rotor's rotational energy can be converted into electrical energy, for example, by means of a generator.
  • thermodynamic efficiency of gas turbines is higher, the higher the temperature of the hot gas entering the gas turbine.
  • level of the inlet temperature is limited, inter alia, by the thermal load-bearing capacity of the components arranged in the flow channel. Accordingly, one objective is to create components that have sufficient mechanical resistance for the operation of the gas turbine, even at very high temperatures of the hot gas.
  • One way of increasing the thermal load capacity of a guide vane is to remove heat from the guide vane by means of a cooling fluid.
  • a cavity is provided in its interior, through which the cooling fluid flows.
  • the retaining rings on the inner sides of the guide vane rings are also strongly heated by hot gas flowing into the circumferential groove.
  • a proven means of cooling a retaining ring is to design the retaining ring with a U-shaped cross section, as a result of which a circumferential cooling fluid groove is created in the retaining ring.
  • This cooling fluid groove is supplied with cooling fluid which flows out of the guide vanes through an outlet opening provided in the inner platform into the cooling fluid groove of the retaining ring.
  • this cooling fluid has already absorbed heat in the airfoil of the guide vane, which reduces the cooling capacity available for the retaining ring.
  • a first free end of the connecting tube is inserted into a through opening formed in the inner platform and is integrally connected to the inner platform.
  • the second free end of the connecting tube is arranged in a cooling fluid inlet opening formed on the outer platform at a distance from the edge thereof and projects outward from the outer platform.
  • connecting pipes can have positioning means in their second free end region, which extend from the connecting pipe in opposite directions and are supported on the pressure-side and the suction-side edge of the cooling fluid inlet opening. It has been shown, however, that these positioning means can be insufficient to provide sufficiently reliable positioning in view of strong operational vibrations of the turbomachine and thermal changes in length of the connecting pipe to ensure the connecting pipe in the cooling fluid inlet opening.
  • FIG. 1 An alternative attachment of such a connecting tube shows the US 2004/0062637 A1 , according to which the connecting pipe is welded to the interior of the turbine blade via several spacers.
  • the GB 2 058 944 A. a turbine blade with an impact cooling insert.
  • a guide vane according to claim 1 in which at least one guide means is fastened to the outer platform for guiding the connecting tube, which is designed and arranged such that it forms the sliding tube in the event of a thermal change in length, with the formation of a sliding seat Longitudinal leads.
  • the invention is based on the idea of providing guide means for guiding the connecting tube on the outer platform, 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 limit the degrees of freedom of movement of the connecting tube to the longitudinal direction of the guide vane.
  • the at least one guide means extends from the outer platform in the direction of the connecting tube and encompasses a section of the Connection tube at least partially, in particular completely leaving a game.
  • a guide means holds the connecting tube in a predetermined position with respect to the outer platform, in particular with regard to the distance from the edge of the cooling fluid inlet opening.
  • the at least one guide means has a guide opening. This guide opening is penetrated by the connecting tube or a section of the connecting tube, whereby the connecting tube 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 and extends through the guide opening of the at least one guide means.
  • the guide opening can have a smaller cross-sectional area than the connecting tube, as a result of which the dimensions of the guide means can also be reduced. 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 preferably designed in the manner of a pin.
  • the cross section of the guide protrusion can be formed, for example, round, square or rectangular perpendicular to the longitudinal direction.
  • Two guide means are particularly preferably provided, which extend from opposite regions of the outer platform in the direction of the connecting tube and in particular point towards one another. A rotation movement of the connecting tube about its longitudinal axis can be counteracted by two guide means arranged in this way, which further improves the positioning effect of the guide means.
  • the two guide means are designed as sheets which are integrally connected to the outer platform, in particular by welding or soldering are. Welded or soldered sheets are particularly cost-effective and easy to manufacture guide means.
  • two guide projections can be arranged opposite one another and spaced apart from one another on the connecting tube and can be encompassed by a respective guide means.
  • the distance between the two guide projections is preferably in the range from 5 to 10 and is preferably 7. Such distances correspond to the diameters of conventional connecting pipes.
  • the two guide means can be provided on the pressure side and on the suction side of the connecting pipe. This arrangement enables particularly short guide means, which is associated with an improved vibration behavior of the guide means.
  • the airfoil can have a peripheral wall.
  • the connecting tube is arranged in the cavity at a distance from the peripheral 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 thermal insulation.
  • the integral 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 guide vane ring.
  • the Figures 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 guide vane 1 has an outer platform 2, which is arranged radially on the outside when the guide vane 1 is mounted as intended.
  • the guide blade 1 comprises an airfoil 3 which extends in a longitudinal direction L and protrudes from the outer platform 2.
  • a cavity 4 is defined in the interior of the airfoil 3.
  • the guide vane 1 has an inner platform 5 which is arranged opposite the outer platform 2 and is connected to the airfoil 3.
  • the guide vane 1 comprises a connecting tube 6 which penetrates 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 in a cohesive and fluid-tight manner.
  • the second free end of the The connecting tube 6 is arranged in a cooling fluid inlet opening 7 formed on the outer platform 2 at a distance from the edge 8 thereof and projects outward from the outer platform 2.
  • two guide means 9 are attached to the outer platform 2, which extend from opposite areas of the outer platform 2 in the direction of the connecting tube 6 and face each other.
  • the guide means 9 are designed as sheets which are arranged on the pressure side and the suction side of the airfoil 3 and are integrally connected to the outer platform 2 by welding.
  • Each guide means 9 has a slot-shaped guide opening 10 in order to completely encompass a section 11 of the connecting tube 6 while leaving play.
  • a partial change of grip can alternatively also suffice.
  • the two sections 11 are provided as guide projections 11 which extend in the longitudinal direction L and are formed on the second free end of the connecting tube 6 corresponding to the guide openings 10 and pass through the guide openings 10 of the two guide means 9.
  • the guide projections 11 are pin-shaped with a rectangular cross section and are arranged opposite one another and spaced apart on the connecting tube 6. The distance between the two guide projections 11 is approximately 7 mm.
  • the airfoil 3 has a peripheral wall 12, to which the connecting tube 6 is arranged at a distance in the cavity 4.
  • FIGS. 4 and 5 schematically show a section of a turbomachine with guide vanes 1 according to the invention
  • Turbomachine comprises a housing 13, in which a flow channel 14 extends in an axial direction A.
  • the turbomachine comprises a plurality of turbine stages 15, each comprising a guide vane ring 16 and a moving vane ring 17, the turbine stages 15 being arranged one behind the other and spaced apart from one another in the flow channel 14 in the axial direction A.
  • the guide vane rings 15 are each formed from a plurality of guide vanes 1 according to the invention and each comprise a U-shaped holding ring 18 with a circumferential cooling fluid groove 19 in which the inner platforms 5 of the guide vanes 1 are held.
  • an expanding hot gas flows through the flow channel 14.
  • a cooling fluid flows through and cools the guide vanes 1 of the guide vane rings 15 simultaneously.
  • a part of the cooling fluid flows through the cooling fluid inlet opening 7 in the cavity 4 for cooling the airfoil 3, while another part of the cooling fluid flows through the connecting tube 6 for cooling the holding ring 18 directly and without heating contact with the peripheral wall 12 of the airfoil 3 in the holding ring 18 flows.
  • One 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 case of a thermally induced length change in the guide openings 10 of the guide means 9 without leaving its position in the cooling fluid inlet opening 7 with respect to the edge 8 thereof. Beyond this, freedom of movement of the connecting tube 6 relative to the outer platform 2 is avoided by the guide means 9 attached to the outer platform 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Aube (1) directrice d'une turbomachine, notamment d'une turbine à gaz, comprenant une plateforme (2) extérieure à l'état monté conformément aux prescription, un corps (3) d'aube, qui est en saillie de la plateforme (2) extérieure, qui s'étend dans une direction (L) longitudinale et qui définit, à l'intérieur, une cavité (4), une plateforme (5) intérieure, qui est disposée en opposition à la plateforme (2) extérieure et qui est reliée au corps (3) de l'aube, et un tuyau (6) de liaison passant dans la direction (L) longitudinale dans la cavité (4) du corps (3) de l'aube, dont la première extrémité est insérée dans une ouverture de passage constituée dans la plateforme (5) intérieure et est reliée à coopération de matière à la plateforme (5) intérieure et dont la deuxième extrémité libre passe dans une ouverture (7) d'entrée de fluide de refroidissement constituée sur la plateforme (2) extérieure et à distance du bord (8) de l'ouverture et dépasse vers l'extérieur de la plateforme (2) extérieure,
    dans laquelle, à la plateforme (2) extérieure, est fixé, pour guider le tuyau (6) de liaison, au moins un moyen (9) de guidage constitué et disposé de manière à guider, avec formation d'un siège coulissant, le tuyau (6) de liaison dans le cas d'une variation thermique de longueur dans la direction (L) longitudinale,
    caractérisée en ce que
    le au moins un moyen (9) de guidage s'étend, à partir de la plateforme (2) extérieure, en direction du tuyau (6) de liaison et entoure le tuyau (6) de liaison, au moins en partie, notamment complètement, en laissant un jeu.
  2. Aube directrice suivant l'une des revendications précédentes,
    caractérisée en ce que
    le au moins un moyen (9) de guidage a une ouverture (10) de guidage.
  3. Aube directrice suivant la revendication 2,
    caractérisée en ce que,
    à la deuxième extrémité libre du tuyau (6) de liaison correspondant à l'ouverture (10) de guidage du au moins un moyen (9) de guidage, est constituée au moins une saillie (11) de guidage, qui s'étend dans la direction (L) longitudinale et qui passe dans l'ouverture (10) de guidage du au moins un moyen (9) de guidage.
  4. Aube directrice suivant la revendication 3,
    caractérisée en ce que
    la au moins une saillie (11) de guidage est constituée en étant de type à broche.
  5. Aube directrice suivant l'une des revendications précédentes,
    caractérisée en ce qu'
    il est prévu deux moyens (9) de guidage, qui s'étendent à partir de parties opposées de la plateforme (2) extérieure en direction du tuyau (6) de liaison et sont notamment tournés l'un vers l'autre.
  6. Aube directrice suivant la revendication 5,
    caractérisée en ce que
    les deux moyens (9) de guidage sont constitués sous la forme de tôles, qui sont reliées à la plateforme (2) extérieure par coopération de matière, notamment par soudage ou par brasage.
  7. Aube directrice suivant l'une des revendications 5 ou 6,
    caractérisée en ce qu'
    au tuyau (6) de liaison sont disposées deux saillies (11) de guidage opposées l'une à l'autre et à distance l'une de l'autre et entourées, respectivement, d'un moyen (9) de guidage.
  8. Aube directrice suivant la revendication 7,
    caractérisée en ce que
    la distance entre les deux saillies (11) de guidage est dans la plage de 5 à 10, en étant de préférence de 7.
  9. Aube directrice suivant l'une des revendications 7 ou 8,
    caractérisée en ce que
    les deux moyens (9) de guidage sont prévus sur l'intrados et l'extrados du tuyau (6) de liaison.
  10. Aube directrice suivant l'une des revendications précédentes,
    caractérisée en ce que corps (3) de l'aube a une paroi (12) de pourtour.
  11. Aube directrice suivant la revendication 10,
    caractérisée en ce que
    le tuyau (6) de liaison est disposé dans la cavité (4) en étant à distance de la paroi (12) de pourtour.
  12. Aube directrice suivant l'une des revendications précédentes,
    caractérisée en ce que
    la liaison à coopération de matière, entre le tuyau (6) de liaison et la plateforme (5) intérieure, est obtenue par soudage ou brasage.
  13. Aube directrice suivant l'une des revendications précédentes,
    caractérisé en ce que
    la liaison entre le tuyau (6) de liaison et la plateforme (5) intérieure est étanche au fluide.
EP17717143.6A 2016-04-21 2017-04-11 Aube directrice comprenant un tuyau de raccordement Active EP3420197B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP16166430.5A EP3236009A1 (fr) 2016-04-21 2016-04-21 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

Publications (2)

Publication Number Publication Date
EP3420197A1 EP3420197A1 (fr) 2019-01-02
EP3420197B1 true EP3420197B1 (fr) 2020-02-05

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 Before (1)

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

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)

Family Cites Families (12)

* 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
US4288201A (en) * 1979-09-14 1981-09-08 United Technologies Corporation Vane cooling structure
FR2777318B1 (fr) * 1998-04-09 2000-05-12 Snecma Procede de reduction du jeu existant entre une chemise et un distributeur de turbine d'un turboreacteur
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
US6884023B2 (en) * 2002-09-27 2005-04-26 United Technologies Corporation Integral swirl knife edge injection assembly
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
EP2840231A1 (fr) * 2013-08-23 2015-02-25 Siemens Aktiengesellschaft Aube de turbine dotée d'une pale creuse
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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
EP3420197A1 (fr) 2019-01-02
US10876414B2 (en) 2020-12-29
CN109072700A (zh) 2018-12-21
JP2019516039A (ja) 2019-06-13
EP3236009A1 (fr) 2017-10-25
US20190120068A1 (en) 2019-04-25
WO2017182322A1 (fr) 2017-10-26
JP6779310B2 (ja) 2020-11-04
CN109072700B (zh) 2021-01-29

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