EP3236010A1 - Aube directrice comprenant un tuyau de raccordement - Google Patents

Aube directrice comprenant un tuyau de raccordement Download PDF

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Publication number
EP3236010A1
EP3236010A1 EP16166435.4A EP16166435A EP3236010A1 EP 3236010 A1 EP3236010 A1 EP 3236010A1 EP 16166435 A EP16166435 A EP 16166435A EP 3236010 A1 EP3236010 A1 EP 3236010A1
Authority
EP
European Patent Office
Prior art keywords
flange
guide vane
connecting tube
platform
longitudinal direction
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Withdrawn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
EP16166435.4A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Nihal Kurt
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP16166435.4A priority Critical patent/EP3236010A1/fr
Priority to PCT/EP2017/059100 priority patent/WO2017182423A1/fr
Publication of EP3236010A1 publication Critical patent/EP3236010A1/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Withdrawn legal-status Critical Current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
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

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 of the vane, an outer platform protruding airfoil extending in a longitudinal direction and in the interior of which a cavity is provided, an inner platform, which is connected to the airfoil opposite to the outer platform, and a connecting pipe penetrating the cavity of the airfoil in the longitudinal direction, provided with a flange extending transversely to the longitudinal direction at its outwardly facing free end region and inserted into a through hole of the outer platform is, wherein the passage opening in the region of an outwardly facing projection is formed with a curved outer surface on which rests the flange and with which the flange is integrally connected.
  • 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 passes through 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.
  • the connecting tube is inserted into a passage opening of the outer platform.
  • the passage opening is usually formed in the region of an outwardly facing projection with a curved outer surface.
  • the connecting tube is provided in its outwardly facing free end region with a transversely extending to the longitudinal direction of the flange, which rests against the outer surface of the projection and is integrally connected thereto.
  • FIG. 8 shows by way of example a welded joint between a connecting pipe and an outer platform according to the usual practice, for which a strong weld had to be produced.
  • a guide vane of the type mentioned in which the flange has at least one incision extending inwardly from an outer edge of the flange.
  • the invention is based on the consideration of improving the deformability of the flange in order to be able to adapt its shape to differently curved outer surfaces.
  • at least one incision is provided in the flange, which extends inwardly from an outer edge of the flange. This at least one incision reduces the stiffness of the flange, which makes it easier to deform and adapt to the outer surface of the projection.
  • the at least one incision extends substantially in the direction of the connecting tube. Such cuts facilitate handling of the individual parts of the flange in conforming to the outer surface of the projection.
  • the flange is annular and has a width transverse to the longitudinal direction in the range of 2 mm to 20 mm and preferably between 5 mm and 15 mm.
  • This latitude area corresponds to common guide vanes available for the investment of the flange area of the projection of the outer platform.
  • the flange has a quadrangular, in particular rectangular or trapezoidal outer contour whose corners are in particular rounded, wherein the at least one incision is advantageously provided in one of the corners.
  • Flanges of this shape match the protrusions of many common vanes.
  • an incision may be provided at each corner to facilitate adaptation of the flange to the outer surface of the outer platform protrusion. In this case, diagonally extending cuts result in a particularly uniform adaptability of the flange.
  • the flange may have a thickness in the range of 1 mm to 1.5 mm and preferably 1.2 mm in the longitudinal direction. With this choice of the thickness of the flange, a simple deformability of the flange is ensured.
  • the at least one incision has a width which corresponds at least to the thickness of the flange. Such narrow cuts leave the contact surface of the flange almost unchanged.
  • the at least one incision terminates spaced from the connecting tube, wherein the distance between the inner end of the incision and the connecting tube is at least equal to the thickness of the flange.
  • the at least one incision does not completely sever the flange, so that the annular shape of the flange adjacent to the connecting tube is not impaired.
  • a plurality of spaced incisions are provided in the flange. Multiple cuts further improve the deformability of the flange, thereby its stiffness decreases and thus increases the adaptability.
  • the connecting tube can be welded or soldered to the outer platform. Welding and brazing are joining processes that have proven successful in connection with guide vanes.
  • the connecting tube comprises a metal or a metal alloy, in particular a nickel-based alloy such as IN625 or Nimonic90 or consists thereof.
  • the inner end of the connecting tube is inserted into a further passage opening, which is provided in the inner platform, and held displaceable therein.
  • a further passage opening which is provided in the inner platform, and held displaceable therein.
  • the connecting tube has a quadrangular, rectangular or trapezoidal cross-section, the corners of which are in particular rounded.
  • Such cross sections are particularly suitable for the arrangement of the connecting tube within the blade of a guide vane.
  • the airfoil comprises a peripheral wall defining a leading leading edge and trailing leading edge extending in the longitudinal direction, respectively, and having a concave pressure side portion and a convex suction side portion.
  • the connecting tube may be arranged in the cavity spaced from the peripheral wall. Due to the distance there is no thermal bridge between the peripheral wall and the connecting tube, so that the connecting pipe heats up as little as possible during operation of the turbomachine.
  • At least one web is provided in the cavity, which extends from a platform in the longitudinal direction into the cavity and connects the pressure-side portion of the peripheral wall with the suction-side portion of the peripheral wall. Such webs serve to divide the cavity in the airfoil in the longitudinal direction to form one or more cooling fluid passage sections.
  • a plurality of webs are formed and arranged in the cavity such that each web extends from a platform towards the opposite platform and ends at a distance therefrom, adjacent webs extending from different platforms to provide a meandering cooling fluid channel in the cavity define.
  • the airfoil flows through the airfoil along several loops. It is advantageous to provide the first loop, in which the cooling fluid provides the highest cooling power, in the region of the leading edge of the guide vane, since this is exposed to a particularly high thermal load by the hot gas.
  • the cooling fluid channel has three substantially straight and extending in the longitudinal direction of the channel sections, which are arranged starting from the leading edge one behind the other and spaced from each other, and two turns adjacent to the adjacent channel sections of the meandering cooling fluid channel connect to the inner platform or adjacent to the outer platform.
  • the connecting tube is arranged in the central channel portion of the cooling fluid channel. In this arrangement, the flow directions of the cooling fluid in the central channel portion and in the connecting tube are opposite.
  • the FIG. 1 shows a guide blade 1 for a turbomachine, not shown, in particular a gas turbine, according to a first embodiment of the present invention.
  • the guide vane 1 has an outer platform 2, which is arranged in the intended mounted state of the guide vane 1 radially outward.
  • the outer platform 2 comprises an outwardly facing projection 3 with a curved outer surface 4. In the region of the projection 3, a through hole 5 is formed.
  • the guide vane 1 comprises an airfoil 6 projecting from the outer platform 2, which extends in a longitudinal direction L and has a peripheral wall 7 which defines a front leading edge 8 and a trailing trailing edge 9 and has a pressure-side section 10 and a suction-side section 11 , In the interior of the airfoil 6, a cavity 12 is provided.
  • the guide blade 1 comprises a connecting tube 13 with a trapezoidal cross-section, the corners 14 are rounded.
  • the connecting tube 13 is inserted into the passage opening 5, passes through the cavity 12 of the airfoil 6 and is arranged in the cavity 12 at a distance from the circumferential wall 7. It is made of a nickel base alloy such as IN625 or Nimonic90, but may alternatively comprise or consist of a metal or metal alloy in general.
  • the connecting tube 13 is provided at its outer free end portion with a flange 15 which is integrally formed by welding to the connecting tube 13.
  • the flange 15 bears against the outside on the curved outer surface 4 and is connected to it by material bonding by welding.
  • the flange 15 is annular and has transversely to the longitudinal direction L a varying width in the range between 5mm and 15mm.
  • the outer contour of the flange 15 is trapezoidal, wherein the corners 14 of the flange 15 are rounded. Based on the longitudinal direction L, the flange 15 has a thickness of about 1.2mm.
  • four cuts 17 are arranged, which extend from an outer edge of the flange 15 diagonally inwardly in the direction of the connecting tube 13 and divide the flange 15 into four flange portions 16.
  • the incisions 17 have a width which corresponds at least to the thickness of the flange 15.
  • the incisions 17 end at a distance from the connecting tube 13. The distance between the inner end 18 of an incision 17 and the connecting tube 13 corresponds to the thickness of the flange 15.
  • the vane 1 comprises an inner platform 19, which is arranged opposite to the outer platform 2 and connected to the blade 6.
  • a further passage opening 20 is provided, in which the connecting pipe 13 is inserted so that it is slidably held therein.
  • the flange 15 is first welded to the connecting tube 13. Then, the flange portions 16 lying between the cuts 17 are individually adapted by bending to the outer surface 4 of the projection 3 of the outer platform 2 such that the flange 15 abuts the curved outer surface 4 as well as possible. In a further step, the connecting tube 13 is inserted from the outside into the passage opening 5, so that its inner end is held displaceably in the passage opening 20 of the inner platform 19. Finally, the flange 15 is welded fluid-tight with the outer surface 4 of the projection 3.
  • FIGS. 2 to 5 show a guide vane 1 for a turbomachine, in particular gas turbine, according to a second embodiment of the present invention. It has the same basic structure as the guide vane previously described according to the first embodiment.
  • two webs 21 are provided in the cavity 12, each connecting the pressure-side portion of the peripheral wall with the suction-side portion of the peripheral wall.
  • the two webs 21 are formed and arranged such that each web 21, starting from a platform 2, 19 in the longitudinal direction L in the direction of the respective opposite platform 19, 2 extends into the cavity 12.
  • the two webs 21 extend from different platforms 2, 19, whereby a meandering cooling fluid channel 22 is defined in the cavity 12.
  • the cooling fluid channel 22 includes three substantially straight and extending in the longitudinal direction L channel sections 23, which are arranged starting from the leading edge 8 in a row and spaced from each other, and two turns 24, the adjacent channel sections 23 adjacent to the inner platform 19 or adjacent to the connect outer platform 2 together.
  • the connecting tube 13 is arranged in the middle of the three channel sections 23.
  • FIGS. 6 and 7 schematically show a portion of a turbomachine with guide vanes according to the invention 1.
  • the turbomachine comprises a housing 25 in which in a axial direction A, a flow channel 26 extends. Furthermore, the turbomachine comprises a plurality of turbine stages 27, each comprising a vane ring 28 and a blade ring 29, wherein the turbine stages 27 are arranged in the flow channel 26 in the axial direction A one behind the other and spaced from each other.
  • the vane rings 29 are each formed from a plurality of guide vanes 1 according to the invention and each comprise a U-shaped retaining ring 30 with a circumferentialdefluidnut 31, in which the inner platforms 19 of the vanes 1 are held.
  • the flow channel 26 is flowed through by an expanding hot gas.
  • the vane rings 29 are simultaneously cooled by a cooling fluid.
  • each vane 1 is flowed through by the cooling fluid.
  • a part of the cooling fluid flows through the cooling fluid channel 22 for cooling the blade 6, while another part of the cooling fluid for cooling the retaining rim 30 flows directly and without heating contact with the peripheral wall 7 of the blade 6 through the connecting tube 13 into the retaining ring 30.
  • An advantage of the guide blade 1 according to the invention is that the cut annular flange 15 can be adapted well to the curved outer surface 4 of the projection 3 of the outer platform 2 by bending the sections 26 of the flange 15 defined between the cuts 17 independently of each other, that they are individually adapted to the outer surface 4 of the projection 3. In this way, a fluid-tight connection between the connecting tube 13 and the outer platform 2 can be created easily and stress-free.
  • This also opens up the possibility of using separate cooling fluid circuits for the cooling fluid channel 22 and the connecting tube 13, which differ with regard to the temperature and the pressure of the cooling fluid flowing therein, without an undesired exchange occurring between the two cooling fluid circuits.
  • the arrangement of the connecting tube 13 in the central channel portion 23 causes a particularly good separation of the two cooling channel circuits, since neither the outer platform 2 nor the inner platform 19 in the region of the central channel portion 23 have a cooling fluid passage.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP16166435.4A 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement Withdrawn EP3236010A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP16166435.4A EP3236010A1 (fr) 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement
PCT/EP2017/059100 WO2017182423A1 (fr) 2016-04-21 2017-04-18 Aube directrice comportant un tube de jonction et procédé de fabrication d'une aube directrice

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16166435.4A EP3236010A1 (fr) 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement

Publications (1)

Publication Number Publication Date
EP3236010A1 true EP3236010A1 (fr) 2017-10-25

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EP16166435.4A Withdrawn EP3236010A1 (fr) 2016-04-21 2016-04-21 Aube directrice comprenant un tuyau de raccordement

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EP (1) EP3236010A1 (fr)
WO (1) WO2017182423A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3495623A1 (fr) * 2017-12-11 2019-06-12 United Technologies Corporation Aube statorique, moteur à turbine à gaz et turbine associés

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1543707A (en) * 1975-02-03 1979-04-04 Rolls Royce Vane for fluid flow machine
US20040022630A1 (en) * 2000-09-26 2004-02-05 Peter Tiemann Gas turbine blade
US8011881B1 (en) * 2008-01-21 2011-09-06 Florida Turbine Technologies, Inc. Turbine vane with serpentine cooling
EP2604800A2 (fr) * 2011-12-15 2013-06-19 General Electric Company Aube statorique pour un moteur à turbine à gaz

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1543707A (en) * 1975-02-03 1979-04-04 Rolls Royce Vane for fluid flow machine
US20040022630A1 (en) * 2000-09-26 2004-02-05 Peter Tiemann Gas turbine blade
US8011881B1 (en) * 2008-01-21 2011-09-06 Florida Turbine Technologies, Inc. Turbine vane with serpentine cooling
EP2604800A2 (fr) * 2011-12-15 2013-06-19 General Electric Company Aube statorique pour un moteur à turbine à gaz

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3495623A1 (fr) * 2017-12-11 2019-06-12 United Technologies Corporation Aube statorique, moteur à turbine à gaz et turbine associés
US10619492B2 (en) 2017-12-11 2020-04-14 United Technologies Corporation Vane air inlet with fillet

Also Published As

Publication number Publication date
WO2017182423A1 (fr) 2017-10-26

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