WO2015024800A1 - Aube de turbine présentant une pale creuse - Google Patents

Aube de turbine présentant une pale creuse Download PDF

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Publication number
WO2015024800A1
WO2015024800A1 PCT/EP2014/067091 EP2014067091W WO2015024800A1 WO 2015024800 A1 WO2015024800 A1 WO 2015024800A1 EP 2014067091 W EP2014067091 W EP 2014067091W WO 2015024800 A1 WO2015024800 A1 WO 2015024800A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
turbine blade
cavity
tube
turbine
Prior art date
Application number
PCT/EP2014/067091
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Stephen A. CAMILLIERI
Kerri Santucci
Bradley J. Visser
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2015024800A1 publication Critical patent/WO2015024800A1/fr

Links

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 blade, which extends from a foot-side end to ei ⁇ nem 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 Pipe from one of the two entrances to the other of the two
  • a generic turbine blade is, for example, from the
  • EP 1 180 578 AI known.
  • the tube arranged in the interior of the turbine blade serves for the passage of cooling air through another cooling air flow from a foot-side region of the turbine blade to a head-side region of the turbine blade in order 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 passage pipe need not be attached to the turbine blade itself.
  • it can also be fastened to the guide vane support on which the relevant turbine blade is likewise supported so that coolant conducted through the vane support can flow directly into the passage pipe.
  • the turbomache is attached via a coil spring or a bellows on the guide vane.
  • the object of the invention is therefore to provide a turbine blade mentioned in the introduction, in which the tube arranged in the cavity of the turbine blade for the passage of a medium is fastened in a permanently reliable and long-lasting manner.
  • the pipe at least one in ⁇ at least at its pipe ends a bracket spring supported on ei ⁇ ner bounding the cavity wall.
  • a bracket spring supported on ei ⁇ ner bounding the cavity wall.
  • two 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 recognition that in order to reli ⁇ permeable mounting of the tube on the one hand this is to arrange thermal expan- sion tolerant.
  • the tube should not rest directly on the cavity bounding the inner sides of the blade walls, otherwise an undesirable heat input into the tube may occur, whereby the medium flowing through the tube could heat up.
  • a resilient mounting of the tube he ⁇ required, since in-use turbine blade can also be exposed to a vibrational excitation, which can lead to fatigue in mounting in rigidly mounted pipes.
  • each tube end at least one bracket, preferably two brackets being arranged ⁇ is or are.
  • Each bracket is supported by one of nigen walls that limit the cavity or form the access of the cavity. If two Bü ⁇ gel are provided at a pipe end, these are based on opposite walls resiliently.
  • the brackets may have a J-5 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 Bü ⁇ gels into two sections is a purely mental Untertei ⁇ le) lung; each strap is monolithic part of the tube that
  • the or each bracket is preferably as L-, J- or U-shaped element or correspondingly shaped tab out ⁇ forms.
  • a sliding fit of the bracket can be provided on the walls, whereby the thermally induced expansions and relative movements between the molded senen body 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 in bonding thermoplastic induced cracks are far ⁇ avoided. 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 to
  • Attachment of the turbine blade is arranged on a blade carrier or are.
  • the turbine blade preferably to include transverse to the blade extending further platform at the head end of the Schaufelblat ⁇ tes, on the side opposite the blade side, one or a plurality of hooks for securing the turbine blade is arranged in an inner ring or are.
  • the invention relates to a turbine blade with a hollow blade which extends from a foot-side end to a head-side end opposite the base end and which has access to the cavity at both ends, through which a tube of one of the two accesses to the other of the two approaches for the passage of a medium separated from the cavity extends.
  • the tube comprises at least one bracket to at least one of its two tube ends, the resiliently supported on a bounding the cavity wall.
  • Figure 1 shows a turbine vane in a perspective
  • Figure 2 is a perspective view of the back ei ⁇ ner platform of the turbine blade with a extending into the blade tube.
  • FIG. 1 shows a perspective view of a Turbi ⁇ nenleitschaufel 1.
  • the hook 24 having the turbine guide vane 1 is secured to a non ⁇ represent provided inner wall of a turbine blade carrier.
  • 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 includes with ⁇ towards a foot-side end 7 and a head-side end 10th
  • the blade 18 has in this embodiment ei ⁇ nen cavity 4, which extends over the span of the Schau ⁇ selflatts 18 from a foot side arranged first access 36 to a head side arranged second access 35. On the foot side, the turbine blade 1 as a medium
  • the cavity 4 has a cross-section ⁇ contour 34 that is similar in the region of the blade 18 and the foot ⁇ portion 2 of the outer contour 16 of the airfoil 18th
  • the cross-sectional contour 34 of the cavity 4 is essentially retained in its shape when viewed from the foot region 2 up 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 up to the head region 3 of the turbine blade 1 and there through the outlet opening 12 into the free space 20.
  • the cooling air portion 42 flowing out through the outlet opening 12 in the head region 3 first flows into the free space 20 and cools the U-shaped ring 19 that limits the free space 20 radially inward.
  • the attachment of the tube 13 according to the invention is not shown in Fig. 1, but will erläu ⁇ tert on the basis of Figure 2 in detail.
  • Figure 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 show ⁇ blade 18 is not shown in Figure 2, but its curved profile 33 is shown in the illustration.
  • the turbine blade 1 shown in Figure 2 in contrast to the embodiment of Figure 1 has two cavities 4, each with two approaches, which is irrelevant for the erfindungsge ⁇ proper attachment of 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 Turbinenschau ⁇ fel 1 supplied to the other end of the turbine blade 1 without substantial heat input can be performed.
  • 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 egg ⁇ nen parallel to the longitudinal direction of the tube 13 extending Ab- section 45, which is chosen so large that a sliding fit is formed on the respective wall 44, whereby a secure fit of the respective pipe end 39 is ensured in access to the cavity 4, even with different thermal expansions.
  • the attachment of the pipe end 39 shown in Figure 2 in the access 36 to the cavity 4 may be provided both foot and head side, wherein it has turned out ⁇ advantage that, if at one of the two approaches 35, 36 both bracket 41 with is the respective wall 43, 44 is welded, soldered or glued, the other end is not integrally fixed ⁇ positively, so that there etab the sliding seat ⁇ lines.

Landscapes

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

Abstract

L'invention concerne une aube de turbine (1) présentant une pale creuse (18), qui s'étend d'une extrémité (7) côté pied, à une extrémité (10) côté tête, opposée à l'extrémité (7) côté pied, et qui présente aux deux extrémités (7, 10), respectivement, un accès (35, 36) à un espace creux (4), un tube (13) s'étendant à travers l'espace creux (4), de l'un des deux accès (35), à l'autre des deux accès (36), pour la traversée d'un milieu à travers l'espace creux (4). Dans le but d'obtenir une aube de turbine (1) fiable et durable, et résistant aux vibrations s'exerçant sur l'aube de turbine (1), l'invention est caractérisée en ce que le tube (13) comprend, à chacune de ses deux extrémités (39), au moins un étrier (41), qui prend appui élastiquement sur une paroi (43, 44) délimitant l'espace creux (4).
PCT/EP2014/067091 2013-08-23 2014-08-08 Aube de turbine présentant une pale creuse WO2015024800A1 (fr)

Applications Claiming Priority (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
EP13181502.9 2013-08-23

Publications (1)

Publication Number Publication Date
WO2015024800A1 true WO2015024800A1 (fr) 2015-02-26

Family

ID=49033898

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/067091 WO2015024800A1 (fr) 2013-08-23 2014-08-08 Aube de turbine présentant une pale creuse

Country Status (2)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2017187040A (ja) * 2016-04-06 2017-10-12 ゼネラル・エレクトリック・カンパニイ ロータシャフト冷却用の空気バイパスシステム
US20190101231A1 (en) * 2017-09-29 2019-04-04 United Technologies Corporation Conduit with damping fingers
US11136894B2 (en) * 2017-03-23 2021-10-05 Safran Aircraft Engines Central support for auxiliary tubes with elastic return

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3050229B1 (fr) * 2016-04-18 2018-04-27 Safran Aircraft Engines Carter d'echappement de turbomachine
EP3236009A1 (fr) * 2016-04-21 2017-10-25 Siemens Aktiengesellschaft Aube directrice comprenant un tuyau de raccordement
CN117307258A (zh) * 2022-06-21 2023-12-29 中国航发商用航空发动机有限责任公司 一种涡轮导叶结构

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 (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2017187040A (ja) * 2016-04-06 2017-10-12 ゼネラル・エレクトリック・カンパニイ ロータシャフト冷却用の空気バイパスシステム
US10519873B2 (en) 2016-04-06 2019-12-31 General Electric Company Air bypass system for rotor shaft cooling
JP7118595B2 (ja) 2016-04-06 2022-08-16 ゼネラル・エレクトリック・カンパニイ ロータシャフト冷却用の空気バイパスシステム
US11136894B2 (en) * 2017-03-23 2021-10-05 Safran Aircraft Engines Central support for auxiliary tubes with elastic return
US20190101231A1 (en) * 2017-09-29 2019-04-04 United Technologies Corporation Conduit with damping fingers
US10557572B2 (en) * 2017-09-29 2020-02-11 United Technologies Corporation Conduit with damping fingers

Also Published As

Publication number Publication date
EP2840231A1 (fr) 2015-02-25

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