EP2706195A1 - Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel - Google Patents

Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel Download PDF

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Publication number
EP2706195A1
EP2706195A1 EP12183096.2A EP12183096A EP2706195A1 EP 2706195 A1 EP2706195 A1 EP 2706195A1 EP 12183096 A EP12183096 A EP 12183096A EP 2706195 A1 EP2706195 A1 EP 2706195A1
Authority
EP
European Patent Office
Prior art keywords
tube
edge
surface section
wall
channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12183096.2A
Other languages
English (en)
French (fr)
Inventor
Richard Bluck
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 EP12183096.2A priority Critical patent/EP2706195A1/de
Priority to CA2883198A priority patent/CA2883198A1/en
Priority to RU2015112104A priority patent/RU2015112104A/ru
Priority to US14/424,249 priority patent/US20150226072A1/en
Priority to PCT/EP2013/067442 priority patent/WO2014037227A1/en
Priority to EP13756361.5A priority patent/EP2893146A1/de
Priority to CN201380045883.1A priority patent/CN104641076A/zh
Publication of EP2706195A1 publication Critical patent/EP2706195A1/de
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the present invention relates to a tube for being installed into a guide vane of a turbine, a guide vane device of a turbine and a method of manufacturing a tube for a guide vane of a turbine.
  • a turbine nozzle guide vane may comprise an internal impingement cooling system into which cooling air is fed through a tube which is mounted in a vane body of the guide vane.
  • the tube comprises holes to direct discrete flows of cooling air against an internal wall of the guide vane.
  • the tube is typically fixed in a close-fit manner within the body of the guide vane in order to restrict radial leakage flows of the cooling air.
  • the tube may be partially flexible in order to provide a good manufacturing variability.
  • the divider may be brazed to the surfaces of the tube. Hence, during assembly of the tube, the higher stiffness of the tube due to the divider may cause a fracture of the brazing connection between the divider and the tube surface.
  • US 4,252,501 discloses a hollow cooled vane for a gas turbine engine which comprises at least two apertured members each mounted spaced from a separate part of a vane interior surface.
  • the first of these members is provided with the supply of cooling air which passes through the apertures in the form of jets to impingement cool the respective first surface.
  • an interconnecting passage is provided to take the cooling air to a second apertured member where an impingement cools the respective second surface.
  • US 5,516,260 A discloses a bonded turbine airfoil with floating wall cooling insert.
  • the airfoil comprises an internal cavity which is split by a forward wall and by an after wall.
  • US 5,259,730 A discloses an impingement cooled airfoil with a bonding foil insert. Inside an inner cavity of the airfoil ribs are inserted in order to provide several cavities inside an inner volume of the guide vane.
  • US 2,873,944 comprises a turbine blade cooling. Inside an inner volume of a blade metal sheets are fixed in order to form passages for the cooling fluid inside the inner volume of the blade.
  • This objective may be solved by a tube for being installed into a guide vane of a turbine, by a guide vane device of a turbine and by a method of manufacturing a tube for a guide vane of a turbine according to the independent claims.
  • a tube for being installed into a guide vane of a turbine comprises a tube wall for forming a fluid channel and a dividing wall which is arranged inside the fluid channel.
  • the dividing wall comprises a first edge and a second edge which is spaced apart from the first edge.
  • the first edge is fixed to a first surface section of the tube wall.
  • the dividing wall is formed in such a way that the second edge resiliently abuts in a detachable manner against a second surface section of the tube wall such that the dividing wall divides the fluid channel into a first channel and a second channel.
  • a guide vane device of a turbine comprises the above-described tube and the guide vane which comprises an inner volume.
  • the tube is arranged inside the inner volume.
  • a method of manufacturing a tube for a guide vane of a turbine is presented.
  • a tube which comprises a tube wall for forming a fluid channel is provided.
  • a first edge of a dividing wall is fixed to a first surface section of the tube wall.
  • a second edge of the dividing wall, which second edge is spaced from the first edge, is resiliently abutted in a detachable manner against the tube wall such that the dividing wall divides the fluid channel into a first channel and a second channel.
  • the guide vane comprises an aerodynamic profile and guides a hot working gas of the turbine in a desired direction.
  • the guide vane is mounted to a turbine housing, and in particular to a guide vane carrier.
  • the guide vane comprises a centre axis (e.g. the symmetry axis) which runs generally along the length of the guide vane and particularly along a radial direction to a rotary axis of a turbine shaft of the turbine.
  • the guide vane comprises an inner volume into which the tube is mountable.
  • the tube comprises the fluid channel, through which cooling fluid (e.g. cooling air) flows.
  • cooling fluid e.g. cooling air
  • the tube wall of the tube is cooled by the cooling air such that also the guide vane is cooled by the cooling air.
  • the tube wall may comprise holes through which the cooling fluid may flow from the fluid channel to an inner surface of the guide vane for cooling purposes.
  • the tube and in particular the fluid channel comprises a centre axis which runs along the length of the tube and generally parallel to the centre axis of the guide vane.
  • the fluid channel comprises a fluid inlet and a fluid outlet, wherein the fluid outlet is located at an opposite end of the tube along the central axis with respect to the fluid inlet.
  • the fluid inlet and the fluid outlet are arranged at opposite ends of the tube in such a way that the cooling fluid flows through the fluid channel along a radial direction with respect to the rotary axis of the turbine shaft.
  • the guide vane comprises a leading edge against which the hot working gas of the turbine streams and a trailing edge, where the hot working gas streams away from the guide vane.
  • the hot working gas heats the section of the guide vane in the vicinity of the leading edge more than the section of the guide vane in the vicinity of the trailing edge.
  • the fluid channel of the tube is divided by the dividing wall into a first channel and a second channel.
  • the first channel and the second channel are divided by the dividing wall in such a way that through the first channel a cooling fluid with different parameters (temperature, mass flow, pressure) in comparison to parameters of a cooling fluid which flows through the second channel is provided.
  • two or a plurality of dividing walls may be arranged inside the fluid channel in order to provide a respective plurality of further channels inside the fluid channel.
  • the dividing wall may be a sheet metal and a metal plate, respectively, which divides the fluid channel into the first channel and the second channel.
  • the dividing wall runs generally along the length of the tube. According to the present invention, the dividing wall is fixed with a first edge to a first surface section of the tube wall and abuts with a second edge against a second surface section of the tube wall.
  • the first edge and the second edge may be for example parallel edges of the dividing wall, wherein the first edge and the second edge are opposite located edges of the dividing wall.
  • the first edge is a free end of the plate.
  • the first edge has a longitudinal extension and is in other words a free end of one side of the dividing wall.
  • the second edge has a similar longitudinal extension and is in other words a free end of another side of the dividing wall, i.e. opposite with respect to the first edge.
  • the dividing wall may have a rectangular shape, wherein the edges and thus the dividing wall run along the length and the centre axis of the tube, respectively.
  • the dividing wall may also comprise a curved shape.
  • the dividing wall may run from a first fluid opening of the fluid channel to a second fluid opening of the fluid channel.
  • each of the first channel and the second channel, which are formed by the dividing wall may have a respective first fluid opening and a respective second fluid inlet. Through each of the respective first and second channels, fluid with different parameters may be injected.
  • the term "resiliently abuts in a detachable manner" means that the second edge is not fixed to the second surface section by any fixation means (such as welding, brazing or gluing means) but only (i.e. sealingly) contacts the second surface section.
  • the contour of the second edge in comparison to the second surface section is formed and adapted in such a way that a sealing between the first channel and the second channel is achievable.
  • the contact of the second edge to the tube wall i.e. the second surface section
  • the dividing wall may be a metal plate and hence elastically deformable and hence comprises resilient properties.
  • the first channel is located more upstream with respect to a flow direction of the hot working gas of the turbine and hence in the vicinity of the leading edge of the guide vane, more cooling fluid or a cooler cooling fluid may be injected such that the cooling efficiency of the cooling fluid in the first channel is higher than a cooling fluid which is injected through the second channel, wherein the second channel is located closer to the vicinity of the trailing edge of the guide vane.
  • the dividing wall is (only) fixed with the first edge to the tube wall of the tube.
  • the opposite second edge only resiliently abuts in a detachable manner against a second surface section of the tube wall.
  • the second edge may slide along the second surface section.
  • the stiffness of the dividing wall is reduced and an easier manufacturing and installation of the tube inside the guide vane is achieved.
  • the tube may expand elastically again, such that the second edge slides along the second surface section into its initial position.
  • the second edge stays in contact and is kept abutted against the second surface such that a sealing between the first channel and the second channel is provided.
  • a compressible and expendable tube for a guide vane is generated without complex manufacturing methods.
  • only one fixing fabricating step for fixing the dividing wall to the tube wall is necessary, namely the fixing of the first edge to the first surface section of the tube wall.
  • the first edge is brazed, welded or glued to the first surface section of the tube wall.
  • the dividing wall is arranged inside the fluid channel in such a way that, if a first fluid pressure in the first channel is higher than a second fluid pressure in the second channel, the second edge is pressed against the tube wall by the fluid pressure and in particular by the differential pressure between the first fluid pressure and the second fluid pressure.
  • the first surface section has a first normal
  • the dividing wall comprises a further first surface section which has a further first normal and which comprise the first edge.
  • An angle between the normal of the first surface section and the further normal of the further first surface section differs to 90°.
  • the dividing wall runs from the first edge not perpendicular with respect to the first normal of first surface section of the tube wall.
  • the further first surface section may define the complete surface of the dividing wall or may only be a part of the overall surface of the dividing wall.
  • the dividing wall may form an L-shaped cross-section or a U-shaped cross-section, wherein the further first surface section defines the section comprising the first edge.
  • the second surface section has a second normal
  • the dividing wall comprises a further second surface section which comprises a second edge
  • the further second surface section has a further second normal.
  • the dividing wall is formed such that a further angle between the second normal of the second surface section and the further second normal of the further second surface section differs from 90°.
  • the dividing wall runs from the second edge not perpendicular with respect to the second normal of second surface section of the tube wall.
  • the tube has the above-described centre axis which runs between a first tube end and a second tube end.
  • the tube is divided along a dividing direction into a first tube part, i.e. a first tube half, and a second tube part, i.e. a second tube half.
  • the dividing direction comprises at least a component which is parallel to the centre axis.
  • a dividing line between the first tube part and the second tube part runs along the length of the tube and parallel to the centre axis of the tube, respectively.
  • first tube part and the second tube part may be fabricated independently from each other, wherein after fixing the first tube part with the second tube part, the tube and respectively the fluid channel are formed.
  • first tube part and the second tube part are welded, brazed, glued together or joined together by adding material.
  • the first edge of the dividing wall is fixed to the first tube part and wherein the dividing wall is formed in such a way that the second edge resiliently abuts in a detachable manner against the second tube part such that the dividing wall divides the fluid channel into the first channel and the second channel.
  • the first edge is fixed to the first tube part in particular before the first tube part and the second tube part are fixed together.
  • the first edge of the dividing wall is fixed to the first tube part, wherein the first tube part is fixed to the second tube part after the first edge has been fixed to the first tube part.
  • the second edge abuts against the second tube part.
  • the dividing wall is fixed with its first edge to the first tube part.
  • the fixation of the first edge to the first tube part is easy because the first surface section is easily accessible.
  • a dividing wall is arranged inside the fluid channel of the tube, wherein only one first edge is (non-detachably) fixed, e.g. by welding, to a first surface section of the tube wall. Due to the abutting of the second edge of the dividing wall at the second surface section a fluid channel is dividable into the first channel and the second channel although only the first edge is (rigidly) fixed to the first section of the tube wall.
  • the dividing wall and in particular a further surface section comprising the first edge and/or a further surface section comprising the second edge, is angled relatively to the respective first and second surface section of the tube wall and are thus non-perpendicular.
  • the dividing wall is only welded to one surface of the tube inside the fluid channel, in particular along the tubes length (i.e. along the centre axis) prior to the welding of the second tube part to the first tube part.
  • the size of the dividing wall is set and predetermined in such a way, that a width of the dividing wall between the first surface section and the second surface section of the tube is large enough such that the second edge resiliently abuts permanently against the second surface section during operation of the turbine, so that a reliable separation of the first channel to the second channel by the dividing wall is achieved.
  • the second edge of the turbine is located more upstream i.e. closer to the leading edge of the guide vane in comparison to the first edge.
  • the manufacturing method enables the dividing wall to be attached using a stronger welded joint (as compared to brazing).
  • angling the dividing wall with respect to the respective first and second normals of the respective first and second surface sections of the tube wall and by allowing the second edge to remain free from any permanently fixing means this will achieve flexibility of the tube to enable reduced installation forces during installation of the tube into the guide vane.
  • the dividing wall will ensure a seal between the first channel and the second channel.
  • a pressure difference between fluid in the first channel and the second channel will assist to close and to press the dividing wall against the tube wall.
  • Fig. 1 shows a guide vane device (i.e. a dual chamber impingement guide vane device) for a turbine, wherein the guide vane device comprises a guide vane 120 and a tube 100.
  • the tube 100 is arranged inside the inner volume 121 of the guide vane 120.
  • the guide vane device may be particularly of a turbine section of a gas turbine, which will be in contact with a hot working fluid from the outside and particularly also in contact with a cooling fluid guided to the interior of the guide vane device.
  • the tube 100 may be installed into the inner volume 121 of the guide vane 120 by a press-fit connection for example. Therefore, the (elastically compressible) tube 100 may be compressed during installation into the inner volume 121 and released after placing the tube 100 into the inner volume 121, such that the tube 100 extends again into its initial position and such that the press-fit connection between the tube 100 and the guide vane 120 is achieved. Therefore, the tube 100 has to provide a low stiffness on the one side but has also to be robust enough on the other side.
  • the tube 100 comprises a dividing wall 110 which is arranged inside the fluid channel which is housed and surrounded by a tube wall 101 of the tube 100.
  • the dividing wall 110 comprises a first edge 111 and a second edge 112 which is spaced apart from the first edge 111.
  • the first edge 111 is fixed to the first surface section of the tube wall 101, e.g. by welding.
  • the dividing wall 110 is formed in such a way that the second edge 112 abuts resiliently abuts against a second surface section of the tube wall 101 such that the dividing wall 110 divides the fluid channel into a first channel I and a second channel II.
  • the dividing wall 110 comprises a length between the first edge 111 and the second edge 112, wherein the length is adapted such that the second edge 112 is in contact with the second surface section (and hence abuts against the second surface section) when the first edge is fixed with the first surface section. Furthermore, the dividing wall 110 is angled relative to the respective first surface section of the tube wall 101 and/or to the second surface section of the tube wall 101, respectively. In other words, the dividing wall 110 runs between the first edge 111 and the second edge 112 non-parallel with respect to a first normal n1 of the first surface section and/or with respect to a second normal n2 of the second surface section, respectively. Hence, the dividing wall 110 runs angled relative to the respective surface sections of the inner surface of the tube wall 101.
  • the dividing wall 110 comprises a further first surface section which comprises the first edge 111, wherein an angle ⁇ between the first normal n1 of the first surface section and the further first normal fn1 of the further first surface section differs to 90°.
  • the dividing wall 110 may comprise a further second surface section which comprises the second edge 112, wherein the dividing wall 110 is formed such that a further angle ⁇ between the second normal n2 of the second surface section and a further second normal fn2 of the further second surface section differs from 90°.
  • the second edge 112 slides in particular along the second surface section in an upstream direction with respect to the flow direction 124 of the working gas of the turbine.
  • the dividing wall 110 as shown in Fig. 1 is arranged inside the fluid channel in such a way, that if a first fluid pressure p1 in the first channel I is higher than a second fluid pressure p2 in the second channel II, the second edge 112 is pressed against the tube wall 101 by the first fluid pressure p1, i.e. by the pressure difference between the first fluid pressure p1 and the second fluid pressure p2.
  • the second edge 112 of the dividing wall 110 is located closer to a leading edge 122 of the guide vane 120 and hence more upstream with respect to the flow direction 124 of the working gas of the turbine than the first edge 111 of the dividing wall 110.
  • the first channel I which is located closer to the leading edge 122 of the guide vane 120, a higher cooling efficiency is desired and hence a higher fluid pressure p1 is generated in comparison to the second channel II, which is located more downstream with respect to the flow direction 124 of the working gas and closer to the trailing edge 123, respectively.
  • the first fluid pressure p1 is higher than the second fluid pressure p2 and because the second edge 112, which abuts against the second surface section, is located more upstream with respect to the first edge 111, which is fixed to the first surface section, the pressure surplus in the first channel I with respect to the second pressure p2 forces and presses the second edge 112 against the second surface section of the tube wall 101.
  • the fluid channel and in particular the first channel I and the second channel II comprise a respective fluid inlet and a respective fluid outlet, such that separated cooling fluids with separated cooling fluid parameters may be injected in each of the channels I, II.
  • the respective fluid inlets and outlets are located at opposite ends of the tube 100 with respect to a centre axis 102 of the tube 100.
  • the centre axis 102 runs generally along a radial direction with respect to a turbine shaft of the turbine.
  • the tube 100 may comprise a first turbine section 103 (i.e. a first turbine half) and a second tube part 104 (second tube half).
  • the first tube part 103 and the second tube part 104 are divided along a dividing line 105, wherein the dividing line runs approximately parallel to the centre axis 102 and along the length of the tube, respectively.
  • the dividing line 105 may only have one component which is parallel to the centre axis 102.
  • the dividing line 105, 105' runs from one free end to an oppositely located free end with respect to the centre axis 102.
  • Fig. 2 shows the exemplary embodiment shown in Fig. 1 and hence comprises similar features as already explained above for Fig. 1 .
  • the first tube end 201 and the second tube end 202 is shown. Furthermore, it is shown that the tube wall 101 comprises a plurality of holes 203.
  • the cooling fluid may stream from the first channel I and the second channel II into the inner volume 121. Specifically, the cooling fluid streams through the holes 203 and impinges against the inner surface of the inner wall of the guide vane 120. Hence, an impingement cooling is provided.
  • a dividing direction 204 is shown, along which the tube 100 is divided into the first tube part 103 and the second tube part 104.
  • Fig. 3 shows the tube 100, wherein the tube 100 comprises the first tube part 103 and the second tube part 104.
  • Fig. 3 shows the tube before the first tube part 103 and the second tube part 104 are fixed together.
  • the dividing wall 110 may already be fixed (e.g. by welding) with its first edge 111 to the first surface section of the tube wall 101 and respectively of the first tube part 103.
  • the dividing wall 110 is formed in such a way (with respect to its size and extension) that after the first tube part 103 is fixed (e.g. by welding) to the second tube part 104, the second edge 112 of the dividing wall 110 resiliently abuts against the second surface section of the second tube part 104.
  • the dividing wall 110 can already be fixed with its first edge 111 and after the first tube part 103 is fixed to the second tube part 104 no further fixing steps are necessary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12183096.2A 2012-09-05 2012-09-05 Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel Withdrawn EP2706195A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP12183096.2A EP2706195A1 (de) 2012-09-05 2012-09-05 Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel
CA2883198A CA2883198A1 (en) 2012-09-05 2013-08-22 Impingement tube for gas turbine vane with a partition wall
RU2015112104A RU2015112104A (ru) 2012-09-05 2013-08-22 Трубка принудительного охлаждения для лопатки газовой турбины, имеющая разделительную стенку
US14/424,249 US20150226072A1 (en) 2012-09-05 2013-08-22 Welded dual chamber impingement tube
PCT/EP2013/067442 WO2014037227A1 (en) 2012-09-05 2013-08-22 Impingement tube for gas turbine vane with a partition wall
EP13756361.5A EP2893146A1 (de) 2012-09-05 2013-08-22 Prallröhre für gasturbinenschaufel mit einer trennwand
CN201380045883.1A CN104641076A (zh) 2012-09-05 2013-08-22 用于燃气轮机叶片的具有隔壁的冲击管

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12183096.2A EP2706195A1 (de) 2012-09-05 2012-09-05 Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel

Publications (1)

Publication Number Publication Date
EP2706195A1 true EP2706195A1 (de) 2014-03-12

Family

ID=46762971

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12183096.2A Withdrawn EP2706195A1 (de) 2012-09-05 2012-09-05 Kühleinsatz mit einer Trennwand zur Prallkühlung einer Leitschaufel
EP13756361.5A Withdrawn EP2893146A1 (de) 2012-09-05 2013-08-22 Prallröhre für gasturbinenschaufel mit einer trennwand

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13756361.5A Withdrawn EP2893146A1 (de) 2012-09-05 2013-08-22 Prallröhre für gasturbinenschaufel mit einer trennwand

Country Status (6)

Country Link
US (1) US20150226072A1 (de)
EP (2) EP2706195A1 (de)
CN (1) CN104641076A (de)
CA (1) CA2883198A1 (de)
RU (1) RU2015112104A (de)
WO (1) WO2014037227A1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3514330A1 (de) * 2018-01-18 2019-07-24 United Technologies Corporation Geteiltes leitblech für komponenten von gasturbinentriebwerken

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US20150226072A1 (en) 2015-08-13
WO2014037227A1 (en) 2014-03-13
CN104641076A (zh) 2015-05-20
RU2015112104A (ru) 2016-10-27
EP2893146A1 (de) 2015-07-15
CA2883198A1 (en) 2014-03-13

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