EP1113144B1 - Dispositif refroidi de détournement d'un fluide pour une turbomachine travaillant à des températures élevées - Google Patents

Dispositif refroidi de détournement d'un fluide pour une turbomachine travaillant à des températures élevées Download PDF

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Publication number
EP1113144B1
EP1113144B1 EP00127254A EP00127254A EP1113144B1 EP 1113144 B1 EP1113144 B1 EP 1113144B1 EP 00127254 A EP00127254 A EP 00127254A EP 00127254 A EP00127254 A EP 00127254A EP 1113144 B1 EP1113144 B1 EP 1113144B1
Authority
EP
European Patent Office
Prior art keywords
deflection apparatus
flow deflection
blade
separating walls
cooling
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.)
Expired - Lifetime
Application number
EP00127254A
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German (de)
English (en)
Other versions
EP1113144A3 (fr
EP1113144A2 (fr
Inventor
Jörgen Ferber
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1113144A2 publication Critical patent/EP1113144A2/fr
Publication of EP1113144A3 publication Critical patent/EP1113144A3/fr
Application granted granted Critical
Publication of EP1113144B1 publication Critical patent/EP1113144B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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

Definitions

  • the present invention relates to the field of thermal machines. It relates to a cooled Strömungsumschvortechnisch for working at high temperatures turbomachine according to the preamble of claim 1.
  • Such a flow diverter is well known, for example, in the form of a cooled guide or blade for a gas turbine engine of the prior art.
  • FIG. 1 and 2 is reproduced in cross-section or longitudinal section of an exemplary blade of a gas turbine, as it is currently used.
  • the blade 10 consists essentially of an airfoil 11 and a blade root 12, with which it is attached to the rotor of the gas turbine.
  • In the interior of the (hollow) airfoil 11 extend in the longitudinal direction of the blade 10 a plurality of cooling channels 17, through which a through the blade root 12 entering cooling fluid, usually cooling air, flows.
  • the cooling fluid passes coolingly along the inner sides of the hot gas walls 14 in the cooling channels 17 and then exits (for film cooling) through corresponding film cooling holes located at the leading edge 18, the trailing edge 19 and at the blade tip (the effluent cooling fluid is at Fig. 2 represented by the arrows).
  • the individual cooling channels 17 are separated from one another by partitions 13, which at the same time ensure by deflections 16 that the cooling fluid flows through adjacent cooling channels one after the other in alternating directions.
  • a turbine blade vane is known in which thin, straight dividers are inserted in the hollow interior to form counter-rotating radial cooling channels.
  • the US-A-4,252,501 discloses a comparable arrangement of inserts in a cooled blade.
  • a gas turbine vane in which a deflection aid in the form of a bent sheet metal insert is arranged in the connecting region of two counter-rotating, radial cooling channels which are separated by solid, cast walls.
  • the EP-A-0 534 586 shows a gas turbine blade in which a preferably cast, separate baffle is firmly inserted between two separate front and rear parts of the blade.
  • the object is solved by the entirety of the features of claim 1.
  • the essence of the invention is to no longer produce the delimiting the cooling channels serving partitions together with the device, in particular to pour, but form as a separate bays, which are later inserted into the device and fixed there. It is particularly simple and inexpensive, characterized in that the cooling fluid flows in opposite directions in two adjacent cooling channels, the cooling fluid is deflected from the output of a cooling channel in the input of the other cooling channel by means of a deflection, and the deflection is generated by a U-shaped curved partition ,
  • the invention thus differs significantly from solutions such as those in the US-A-5,145,315 or the US-A-5,516,260 are described in which special inserts are used in cast cooling ducts for special steering of the cooling fluid.
  • a first preferred embodiment of the Strömungsumschvor Vietnamese container is characterized in that the Strömungsumschvor Vietnamese container is formed as a hollow cast part, and in that the rail of the flow deflection are formed in the form of receptacles, in which the partitions are inserted.
  • the partitions are preferably formed as flat strips of a metallic or heat-resistant non-metallic (ceramic or composite) material.
  • a secure fit of the inserts is achieved when according to a second preferred embodiment of the invention, the inserted partitions for attachment cohesively, preferably by soldering or welding, are connected to the Strömungsumschvorraum.
  • the partitions can be straight.
  • a particularly preferred embodiment of the Strömungsumschvor Vietnamese according to the invention is characterized in that the Strömungsumschvoriques is a blade of a gas turbine. This results in considerable simplifications due to the comparatively complicated geometry of the blade by the invention.
  • cooling channels or partitions extend substantially in the radial direction with respect to the axis of rotation of the gas turbine, that the inserted partitions for fastening cohesively, preferably by Soldering or welding, are connected to the blade, and that the material connection is arranged at the near-axis end of the partition walls.
  • FIGS. 3 and 4 is an embodiment of a cooled Strömungsumschvoriques according to the invention in the form of a blade for a gas turbine reproduced in cross-section or longitudinal section.
  • the blade 20 is similar in geometry to the prior art blade 10 of FIGS Figures 1 and 2 ,
  • the blade 20 in turn consists essentially of an airfoil 21 and a blade root 22, with which it is attached to the rotor of the gas turbine.
  • a plurality of cooling passages 27 extend in the longitudinal direction of the blade 20 through which a cooling fluid entering through the blade root 22 flows.
  • the cooling fluid sweeps in the cooling channels 27 cooling along the inner sides of the hot gas walls 24 along and also exits through corresponding film cooling openings to the outside, which are arranged at the leading edge 28, the trailing edge 29, and at the blade tip.
  • the individual cooling channels 27 are separated from one another by partitions 23, which at the same time ensure, by means of deflections 26, that the cooling fluid flows through adjacent cooling channels one after the other in alternating directions.
  • the partitions 23 are not cast, ie, produced together with the blade 20 in one cast, but the partitions 23 are formed as separate, strip-shaped inserts, which are introduced after the casting of the blade 20 through the blade root 22 or the opposite blade tip ,
  • the partition walls 23 introduce selectively and secure after insertion, rail-shaped receptacles 30 are integrally formed on the inner sides of the hot gas walls, in which the partitions 23 are guided during insertion with the longitudinal edges.
  • the partitions (slots) 23 may have any shape. You can e.g. just be. If a plurality of cooling channels are connected to each other by deflections 26, it is advantageous if the partitions 23 are bent in a U-shape.
  • the dividing walls 23 may be fixed on one or more sides, e.g. by soldering or welding. They can be fixed in the blade tip area or in the blade root area. The latter has the advantage that the insert or the partition is loaded in the occurring centrifugal forces to train, and so bulging is avoided.
  • the retractable partitions are provided immediately in the manufacture of the blades.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (8)

  1. Dispositif refroidi de détournement de fluide (20) pour une turbomachine travaillant à des températures élevées, lequel dispositif de détournement de fluide (20) présente, à l'intérieur, une pluralité de canaux de refroidissement (27) s'étendant parallèlement et séparés les uns des autres par des parois de séparation (23), pour guider un fluide de refroidissement, le fluide de refroidissement s'écoulant dans deux canaux de refroidissement adjacents (27) à chaque fois dans des sens opposés, et le fluide de refroidissement étant détourné depuis la sortie d'un canal de refroidissement dans l'entrée de l'autre canal de refroidissement au moyen d'un détournement (26), et les parois de séparation (23) étant réalisées sous forme d'inserts séparés pouvant être insérés ultérieurement dans le dispositif de détournement de fluide (20), caractérisé en ce que le détournement (26) est produit par une paroi de séparation (23) courbée en forme de U.
  2. Dispositif de détournement de fluide selon la revendication 1, caractérisé en ce que le dispositif de détournement de fluide (20) est réalisé sous forme de pièce coulée creuse, et en ce que des logements (30) en forme de rail, dans lesquels les parois de séparation (23) sont insérées, sont formés à l'intérieur du dispositif de détournement de fluide (20).
  3. Dispositif de détournement de fluide selon l'une quelconque des revendications 1 et 2, caractérisé en ce que les parois de séparation (23) sont réalisées sous forme de bandes plates.
  4. Dispositif de détournement de fluide selon l'une quelconque des revendications 1 à 3, caractérisé en ce que les parois de séparation insérées (23) sont connectées pour la fixation par engagement par coopération de matière au dispositif de détournement de fluide (20).
  5. Dispositif de détournement de fluide selon la revendication 4, caractérisé en ce que les parois de séparation insérées (23) sont connectées pour la fixation par brasage ou soudage au dispositif de détournement de fluide (20).
  6. Dispositif de détournement de fluide selon l'une quelconque des revendications 1 à 5, caractérisé en ce que le dispositif de détournement de fluide est une aube (20) d'une turbine à gaz.
  7. Dispositif de détournement de fluide selon la revendication 6, caractérisé en ce que l'aube (20) est une aube mobile, en ce que les canaux de refroidissement (27) ou les parois de séparation (23) s'étendent essentiellement dans la direction radiale par rapport à l'axe de rotation de la turbine à gaz et en ce que les parois de séparation insérées (23) sont connectées pour la fixation par engagement par coopération de matière à l'aube (20).
  8. Dispositif de détournement de fluide selon la revendication 7, caractérisé en ce que les parois de séparation insérées (23) sont connectées pour la fixation par brasage ou soudage à l'aube (20).
EP00127254A 1999-12-29 2000-12-18 Dispositif refroidi de détournement d'un fluide pour une turbomachine travaillant à des températures élevées Expired - Lifetime EP1113144B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19963716A DE19963716A1 (de) 1999-12-29 1999-12-29 Gekühlte Strömungsumlenkvorrichtung für eine bei hohen Temperaturen arbeitende Strömungsmaschine
DE19963716 1999-12-29

Publications (3)

Publication Number Publication Date
EP1113144A2 EP1113144A2 (fr) 2001-07-04
EP1113144A3 EP1113144A3 (fr) 2004-05-19
EP1113144B1 true EP1113144B1 (fr) 2008-09-03

Family

ID=7934954

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00127254A Expired - Lifetime EP1113144B1 (fr) 1999-12-29 2000-12-18 Dispositif refroidi de détournement d'un fluide pour une turbomachine travaillant à des températures élevées

Country Status (3)

Country Link
US (1) US6419449B2 (fr)
EP (1) EP1113144B1 (fr)
DE (2) DE19963716A1 (fr)

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DE10215375A1 (de) * 2002-04-08 2003-10-16 Siemens Ag Turbinenlaufschaufel
DE10313875B3 (de) * 2003-03-21 2004-10-28 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Vorrichtung und Verfahren zum Analysieren eines Informationssignals
US7104757B2 (en) 2003-07-29 2006-09-12 Siemens Aktiengesellschaft Cooled turbine blade
US7625178B2 (en) * 2006-08-30 2009-12-01 Honeywell International Inc. High effectiveness cooled turbine blade
US7762784B2 (en) * 2007-01-11 2010-07-27 United Technologies Corporation Insertable impingement rib
US7955053B1 (en) 2007-09-21 2011-06-07 Florida Turbine Technologies, Inc. Turbine blade with serpentine cooling circuit
US10156143B2 (en) * 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
CH701031A1 (de) 2009-05-15 2010-11-15 Alstom Technology Ltd Verfahren zum Aufarbeiten einer Turbinenschaufel.
US8545180B1 (en) * 2011-02-23 2013-10-01 Florida Turbine Technologies, Inc. Turbine blade with showerhead film cooling holes
US20150004120A1 (en) * 2013-06-28 2015-01-01 L'oreal Compositions and methods for treating hair
EP3117169B1 (fr) 2014-03-13 2018-05-09 BAE Systems PLC Échangeur de chaleur
US10472976B2 (en) 2015-06-05 2019-11-12 Rolls-Royce Corporation Machinable CMC insert
US10458653B2 (en) 2015-06-05 2019-10-29 Rolls-Royce Corporation Machinable CMC insert
US10401028B2 (en) 2015-06-05 2019-09-03 Rolls-Royce American Technologies, Inc. Machinable CMC insert
US10465534B2 (en) 2015-06-05 2019-11-05 Rolls-Royce North American Technologies, Inc. Machinable CMC insert
US10544682B2 (en) 2017-08-14 2020-01-28 United Technologies Corporation Expansion seals for airfoils

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Also Published As

Publication number Publication date
DE50015339D1 (de) 2008-10-16
US6419449B2 (en) 2002-07-16
EP1113144A3 (fr) 2004-05-19
US20020018711A1 (en) 2002-02-14
EP1113144A2 (fr) 2001-07-04
DE19963716A1 (de) 2001-07-05

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