EP2840231A1 - Aube de turbine dotée d'une pale creuse - Google Patents

Aube de turbine dotée d'une pale creuse Download PDF

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Publication number
EP2840231A1
EP2840231A1 EP13181502.9A EP13181502A EP2840231A1 EP 2840231 A1 EP2840231 A1 EP 2840231A1 EP 13181502 A EP13181502 A EP 13181502A EP 2840231 A1 EP2840231 A1 EP 2840231A1
Authority
EP
European Patent Office
Prior art keywords
turbine blade
blade
tube
cavity
turbine
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Withdrawn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
EP13181502.9A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Stephen A. Camillieri
Kerri Santucci
Bradley J. Visser
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 EP13181502.9A priority Critical patent/EP2840231A1/fr
Priority to PCT/EP2014/067091 priority patent/WO2015024800A1/fr
Publication of EP2840231A1 publication Critical patent/EP2840231A1/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Withdrawn legal-status Critical Current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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/231—Preventing heat transfer

Definitions

  • the invention relates to a turbine blade with a hollow airfoil, which extends from a foot-side end to the foot-side end opposite the head end and which has at both ends in each case an access to the cavity, wherein through the cavity a pipe from the one of the two approaches to the other of the two approaches for the passage of a medium separated from extending in the cavity medium extends.
  • a generic turbine blade is, for example, from the EP 1 180 578 A1 known.
  • the pipe disposed inside the turbine blade serves to pass cooling air through another cooling air flow from a foot-side portion of the turbine blade to a head-side portion of the turbine blade to continue to be used there at a comparatively low temperature.
  • the tube is supported by webs on the side walls of the cooling channel, whereby, however, forms a thermal bridge, takes place via the heat energy from the airfoil into the tube and thus in the medium passed through this. This undesired heating through-routed cooling air should be avoided.
  • the object of the invention is therefore to provide a turbine blade mentioned above, in which the arranged in the cavity of the turbine blade for the passage of a medium pipe is permanently reliable and durable.
  • the tube has at least one bracket on at least one of its two tube ends, which bracket is resiliently supported on a wall delimiting the cavity.
  • brackets are provided at one end of the pipe, which are supported on opposite walls. More preferably, it is provided that two brackets are provided at both pipe ends, which are supported in an analogous manner.
  • the invention is based on the finding that, for the reliable attachment of the pipe, this is on the one hand to be arranged in a heat-expansion-tolerant manner.
  • the tube should not rest directly on the cavity bounding the inner sides of the blade walls, otherwise an undesirable heat input may occur in the pipe, whereby the medium flowing through the pipe could heat up.
  • a resilient mounting of the tube required because in-use turbine blade can also be exposed to a vibrational excitation, which can lead to fatigue in the fixture in rigidly mounted pipes.
  • At least one bracket preferably two brackets is or are arranged at each tube end.
  • Each bracket is supported on one of those walls which delimit the cavity or which form the access of the cavity. If two brackets are provided at one end of the pipe, these are supported on opposite walls resiliently.
  • the brackets may have a J-shape with a first portion having an arc of about 180 ° and a second portion extending parallel to the tube. Whose end is supported on the wall in question or fixed there.
  • the division of the temple into two sections is a purely mental subdivision; each strap is a monolithic part of the tube that can either be made with the tube or welded.
  • a comparatively simple embodiment can be provided, which is comparatively inexpensive to produce. Since the two brackets of a pipe end are supported on mutually opposite walls of the cavity, the tube is automatically resiliently clamped in the middle of the cavity at approximately uniformly shaped brackets, which on the one hand ensures a minimum distance to the insides that limit the cavity, and on the other hand, a vibration insensitive mounting.
  • the tube can usually be used in turbine blades produced by casting and thus can be mounted as a retrofitted component during the completion of the turbine blade. This has the consequence that the casting of a body of the turbine blade remains unchanged despite the use of the tube disposed therein, which keeps the expenses during the casting production at a low level.
  • a sliding seat of the bracket can be provided on the walls, whereby the thermally induced strains and relative movements between the cast base of the turbine blade and the tube inserted therein can be compensated.
  • the tube has a length which is slightly greater than or equal to the distance between the two accesses. This ensures that the medium flowing in the tube over the entire span of the airfoil can be guided separately from the guided in the cavity medium.
  • a loss of the tube from the turbine blade can be safely avoided if, according to a further advantageous embodiment, at least one of the brackets is firmly bonded to the relevant wall. Under cohesive welding, soldering or gluing is understood. When using a temperature-resistant, ceramic adhesive thermoinduced cracks are largely avoided when connecting. This increases the life of the turbine blade.
  • the turbine blade is designed as a guide vane and comprises at least at the foot end of the airfoil extending transversely to the airfoil platform on the side facing away from the airfoil one or more hooks for attachment of the turbine blade is arranged on a blade carrier or are ,
  • the turbine blade may preferably comprise at the head end of the airfoil a further platform extending transversely to the airfoil, on the side facing away from the airfoil one or more hooks for fastening the turbine blade are arranged in an inner ring or are.
  • the invention relates to a turbine blade having a hollow airfoil which extends from a foot-side end to a head-side end opposite the foot-side end and which has access to the cavity at both ends, through the cavity a pipe from the one of the two Access to the other of the two approaches for the passage of a medium separated from the cavity extends.
  • the tube comprise at least one bracket on at least one of its two tube ends, which is resiliently supported on a wall delimiting the cavity.
  • FIG. 1 shows a perspective view of a turbine vane 1.
  • the turbine vane 1 With the help of the foot portion 2, the hook 24, the turbine vane 1 is attached to an inner wall of a turbine blade carrier, not shown.
  • the foot region further comprises a platform 5 for the radially outer hot gas path limitation.
  • an airfoil 18 extends radially in the direction of a central turbine axis 30 of the turbine blade carrier; It therefore comprises a foot-side end 7 and a head-side end 10.
  • the radially inner end of the turbine guide vane 1 forms the head region 3, which has a platform 25 and a radial inner arcuate recess 26 relative to the turbine axis 30.
  • a U-shaped ring 19 is coupled by means of rail-like hook 27.
  • the hooks 27 engage in retaining grooves 28 of the U-shaped ring 19.
  • the arcuate recess 26 of the head portion 3 defines, together with the U-shaped ring 19, a free space 20 whose longitudinal direction 29 extends transversely to the turbine axis 30 and to a blade axis 31.
  • Radially inside the U-shaped ring 19 is a labyrinth seal 21st
  • the blade 18 has a cavity 4 which extends over the span of the blade 18 from a first access 36 arranged on the base side to a second access 35 arranged on the top side.
  • the cavity 4 has a cross-sectional contour 34, which is similar to the outer contour 16 of the blade 18 in the region of the blade 18 and the foot region 2.
  • the cross-sectional contour 34 of the cavity 4 is substantially retained in shape as viewed from the foot region 2 to the head region 3, but may decrease in size. The presence of further cavities is irrelevant to the invention.
  • the cavity 4 can be cast directly during casting of the turbine blade 1 by inserting a casting core. After casting, a tube 13 is inserted into the cavity 4.
  • the tube 13 has a nearly constant elliptical cross section 15, but may also have a different contour.
  • the tube 13 is not a baffle cooling element.
  • an outer channel 9 is formed between the walls of the cavity 4 and the tube 13.
  • the portion of the cooling air 23 flowing in the outer channel 9 serves to cool the blade 18 in a conventional manner and can emerge at the trailing edge of the blade 18 in a known manner.
  • the cooling air 23 is introduced into the inlet opening 37 of the tube 13, which extends up to an upper side 32 of the foot region 2 of the turbine guide vane 1.
  • the cooling air 23 continues to flow to the head portion 3 of the turbine blade 1 and there through the outlet opening 12 into the free space 20.
  • the effluent through the outlet opening 12 in the head portion 3 cooling air 42 initially flows into the free space 20 and cools the U-shaped ring 19, the the space 20 radially limited inside.
  • the attachment of the tube 13 according to the invention is in Fig. 1 Not but is shown by the FIG. 2 explained in detail.
  • FIG. 2 shows a perspective view of the view of the cold gas side 32 of the platform 5 of the turbine blade 1. Due to the selected perspective, the blade 18 is in FIG. 2 not shown, but its curved profile 33 is shown in the illustration.
  • turbine blade 1 in contrast to the embodiment according to FIG. 1 two cavities 4, each with two access points, which is irrelevant to the inventive attachment of the tube 13.
  • the tube 13 In which one of the two cavities 4, the tube 13 is settled, through which a part of that cooling air, which is the top of the turbine blade 1, fed to the other end of the turbine blade 1 without significant heat input.
  • the tube 13 is elliptical in cross section. But it could also be circular, or even have a different shape.
  • brackets 41 are provided, which are in principle J-shaped along their extent and which are supported on the two opposite walls 43, 44 which define the cavity 4.
  • the brackets 41 are monolithic part of the tube 13.
  • the brackets 41 comprise a parallel to the longitudinal direction of the tube 13 extending portion 45 which is chosen so large that a sliding fit is formed on the respective wall 44, whereby a secure fit even with different thermal expansions the relevant pipe end 39 is ensured in the access to the cavity 4.
  • attachment of the pipe end 39 in the access 36 to the cavity 4 may be provided both foot and head side, wherein it has been found to be advantageous that, if at one of the two approaches 35, 36 both bracket 41 with the relevant wall 43, 44th welded, soldered or glued, the other end is not firmly bonded, so that there the sliding seat is established.

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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)
EP13181502.9A 2013-08-23 2013-08-23 Aube de turbine dotée d'une pale creuse Withdrawn EP2840231A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13181502.9A EP2840231A1 (fr) 2013-08-23 2013-08-23 Aube de turbine dotée d'une pale creuse
PCT/EP2014/067091 WO2015024800A1 (fr) 2013-08-23 2014-08-08 Aube de turbine présentant une pale creuse

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13181502.9A EP2840231A1 (fr) 2013-08-23 2013-08-23 Aube de turbine dotée d'une pale creuse

Publications (1)

Publication Number Publication Date
EP2840231A1 true EP2840231A1 (fr) 2015-02-25

Family

ID=49033898

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13181502.9A Withdrawn EP2840231A1 (fr) 2013-08-23 2013-08-23 Aube de turbine dotée d'une pale creuse

Country Status (2)

Country Link
EP (1) EP2840231A1 (fr)
WO (1) WO2015024800A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3050229A1 (fr) * 2016-04-18 2017-10-20 Snecma Carter d'echappement de turbomachine
EP3236009A1 (fr) * 2016-04-21 2017-10-25 Siemens Aktiengesellschaft Aube directrice comprenant un tuyau de raccordement
EP3228817A3 (fr) * 2016-04-06 2018-02-28 General Electric Company Système de dérivation d'air destiné à refroidir un arbre de rotor
WO2023246804A1 (fr) * 2022-06-21 2023-12-28 中国航发商用航空发动机有限责任公司 Structure d'aube directrice de turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3064302B1 (fr) * 2017-03-23 2019-06-07 Safran Aircraft Engines Appuis centraux de tubes servitude a retour elastique
US10557572B2 (en) * 2017-09-29 2020-02-11 United Technologies Corporation Conduit with damping fingers

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1210254B (de) * 1962-03-26 1966-02-03 Rolls Royce Gasturbinentriebwerk mit gekuehlten Turbinen-laufschaufeln
EP0919700A1 (fr) * 1997-06-19 1999-06-02 Mitsubishi Heavy Industries, Ltd. Dispositif d'etancheite pour aubes de stator de turbine a gaz
EP1180578A1 (fr) * 2000-08-16 2002-02-20 Siemens Aktiengesellschaft Aubes statoriques pour une turbomachine
US20040022633A1 (en) * 2002-07-31 2004-02-05 Kraft Robert J. Insulated cooling passageway for cooling a shroud of a turbine blade
US20040062637A1 (en) * 2002-09-27 2004-04-01 Bryan Dube Integral swirl knife edge injection assembly

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1210254B (de) * 1962-03-26 1966-02-03 Rolls Royce Gasturbinentriebwerk mit gekuehlten Turbinen-laufschaufeln
EP0919700A1 (fr) * 1997-06-19 1999-06-02 Mitsubishi Heavy Industries, Ltd. Dispositif d'etancheite pour aubes de stator de turbine a gaz
EP1180578A1 (fr) * 2000-08-16 2002-02-20 Siemens Aktiengesellschaft Aubes statoriques pour une turbomachine
US20040022633A1 (en) * 2002-07-31 2004-02-05 Kraft Robert J. Insulated cooling passageway for cooling a shroud of a turbine blade
US20040062637A1 (en) * 2002-09-27 2004-04-01 Bryan Dube Integral swirl knife edge injection assembly

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3228817A3 (fr) * 2016-04-06 2018-02-28 General Electric Company Système de dérivation d'air destiné à refroidir un arbre de rotor
US10519873B2 (en) 2016-04-06 2019-12-31 General Electric Company Air bypass system for rotor shaft cooling
FR3050229A1 (fr) * 2016-04-18 2017-10-20 Snecma Carter d'echappement de turbomachine
EP3236009A1 (fr) * 2016-04-21 2017-10-25 Siemens Aktiengesellschaft Aube directrice comprenant un tuyau de raccordement
WO2017182322A1 (fr) * 2016-04-21 2017-10-26 Siemens Aktiengesellschaft Aube directrice comportant un tube de jonction
CN109072700A (zh) * 2016-04-21 2018-12-21 西门子股份公司 具有连接管的导向静叶
US20190120068A1 (en) * 2016-04-21 2019-04-25 Siemens Aktiengesellschaft Guide vane having a connecting tube
US10876414B2 (en) * 2016-04-21 2020-12-29 Siemens Aktiengesellschaft Guide vane having a connecting tube
CN109072700B (zh) * 2016-04-21 2021-01-29 西门子股份公司 具有连接管的导向静叶
WO2023246804A1 (fr) * 2022-06-21 2023-12-28 中国航发商用航空发动机有限责任公司 Structure d'aube directrice de turbine

Also Published As

Publication number Publication date
WO2015024800A1 (fr) 2015-02-26

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