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EP2384392B2 - Élément structural refroidi pour turbine à gaz - Google Patents
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EP2384392B2 - Élément structural refroidi pour turbine à gaz - Google Patents

Élément structural refroidi pour turbine à gaz Download PDF

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Publication number
EP2384392B2
EP2384392B2 EP10701375.7A EP10701375A EP2384392B2 EP 2384392 B2 EP2384392 B2 EP 2384392B2 EP 10701375 A EP10701375 A EP 10701375A EP 2384392 B2 EP2384392 B2 EP 2384392B2
Authority
EP
European Patent Office
Prior art keywords
pins
wall
impingement cooling
density
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.)
Active
Application number
EP10701375.7A
Other languages
German (de)
English (en)
Other versions
EP2384392B1 (fr
EP2384392A1 (fr
Inventor
Jörg KRÜCKELS
Milan Pathak
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Ansaldo Energia IP UK Ltd
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Filing date
Publication date
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Application filed by Ansaldo Energia IP UK Ltd filed Critical Ansaldo Energia IP UK Ltd
Publication of EP2384392A1 publication Critical patent/EP2384392A1/fr
Publication of EP2384392B1 publication Critical patent/EP2384392B1/fr
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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
    • 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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid

Definitions

  • the present invention relates to the field of gas turbines. It relates to a cooled component for a gas turbine according to the preamble of claim 1. It also relates to a method for operating such a component.
  • Gas turbines are designed for ever higher operating temperatures to increase efficiency.
  • the components and elements in the combustion chamber area and the rotor and guide blades of the downstream turbine, including the other elements that border the hot gas channel, are particularly exposed to thermal stress.
  • thermal stress In order to effectively counteract the thermal stress that occurs, particularly resistant materials such as nickel-based alloys can be used.
  • additional measures must be taken to cool the components, with different cooling methods being used, such as film cooling or impingement cooling.
  • Cooling the guide vanes in the first stages of the turbine is particularly important because this is the area where the highest temperatures in the gas turbine occur.
  • US-B2-7,097,418 It has already been described how the outer platform of a guide vane can be cooled in a particularly simple manner by means of a two-stage impingement cooling system, whereby in a first stage the area at the trailing edge of the vane is cooled and then the cooling air flowing out from there cools the platform at the leading edge in a second stage. In both stages, differently positioned and spaced impingement cooling holes (30, 38 in Fig.3 ) are used. Pins on the back of the platform floor are not used.
  • the invention aims to remedy this situation. It is therefore an object of the invention to create a cooled component of a gas turbine, in particular in the case of a guide vane provided with a platform, the cooling of which is optimally adapted to the locally varying thermal load without causing unnecessary additional consumption of cooling air, i.e. the cooling air used is minimized with the same cooling intensity.
  • the thermally loaded wall to be cooled has a large number of pins protruding from the wall on its rear side in a flat distribution, and that the distribution of the pins within the thermally critical zones of the component has a higher density than in the other areas.
  • the heat transfer between the wall and the cooling air can be changed locally and adapted to the thermal load without necessarily having to use a larger amount of cooling air.
  • An embodiment of the invention is characterized in that the means for generating the jets directed onto the rear side of the wall comprise an impact cooling plate provided with distributed impact cooling holes.
  • the cooling is particularly effective if, according to another embodiment of the invention, the impingement cooling plate is arranged at a distance substantially parallel to the rear side of the wall, and the distribution of the impingement cooling holes is coordinated with the distribution of the pins in such a way that, viewed in a direction perpendicular to the impingement cooling plate, the impingement cooling holes lie between the pins.
  • the variation of the cooling can be intensified by correlating the density of the impingement cooling holes with the density of the pins.
  • the density of the impingement cooling holes and the density of the pins can be locally equal.
  • the component is a guide vane of a gas turbine, which comprises an airfoil extending in a longitudinal direction and a platform adjoining the airfoil and extending transversely to the longitudinal direction, the base of which is the thermally loaded wall cooled by impingement cooling and forms a groove at the transition to the airfoil, wherein the distribution of the pins towards the groove has a higher density than in the remaining areas remote from the groove.
  • Fig.1 is a longitudinal section of the upper part of a gas turbine guide vane with platform and locally varying impingement cooling according to an embodiment of the invention.
  • the guide vane 10 has an overall similar configuration to that shown in the initially mentioned US-B2-7,097,418 It comprises a blade 11 extending in the longitudinal direction of the blade, at the upper end of which a platform 12 is formed, which extends essentially transversely to the longitudinal direction of the blade.
  • the platform 12 has a base or a wall 12a, the underside of which is exposed to the hot gas flowing through the turbine, and which is cooled on the upper side by impingement cooling.
  • a cavity 13 is formed on the top of the platform 12, which is covered by an impact cooling plate 14 arranged parallel to the wall 12a.
  • Impact cooling holes 16 are provided in a predetermined distribution in the impact cooling plate 14, through which compressed cooling air in the form of individual cooling air jets (see the arrows in Fig.1 ) enters the cavity 13 and impacts on the opposite rear side of the wall 12a. During the impact and the subsequent turbulent contact with the rear side of the wall 12a, the cooling air absorbs heat from the wall 12a and is then discharged from the cavity 13 (in Fig.1 not shown).
  • the surface distribution of the impact cooling holes 16 is shown in Fig.2 to see.
  • Fig.4 To improve the heat transfer between wall 12a and the cooling air, vertically projecting, conical or pyramid-shaped pins 15 are arranged on the back of wall 12a (see also Fig.3 , in which the pins 15 are shown in perspective), which increase the contact area between the wall and the cooling air flow and intensify the turbulence.
  • Fig.4 As can be seen, the density of the impingement cooling holes 16 and the density of the pins 15 are locally different, but at the same time correlated with each other, i.e. in the areas where the density of the pins 15 is increased (compression area 18), the density of the impingement cooling holes 16 is also increased, and vice versa. In particular, the densities of the two are locally the same.
  • the impingement cooling holes 16 are preferably arranged "on a gap", i.e. in spaces between the pins 15: Between two parallel rows of pins 15, a row of impingement cooling holes 16 with the same periodicity is placed offset.
  • Fig.1 there is a guide vane in Fig.1 reproduced type on the platform 12 critical zones A c in which precautions against thermal stress are particularly important.
  • One such critical zone is the groove between the wall 12a of the platform 12 and the blade.
  • the density of the pins 15 is significantly increased compared to the rest of the area.
  • the density of the impact cooling holes 16 in this area 18 is also increased, analogous to the density of the pins 15.
  • the transition between the areas of different hole and pin density can be continuous.

Landscapes

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

Claims (4)

  1. Elément (10) refroidi pour une turbine à gaz, lequel, pour le refroidissement d'une paroi (12a) exposée à des contraintes thermiques sur un côté avant, présentes sur le côté arrière de la paroi (12a), selon une répartition plane (17), une multiplicité de pointes (15) dépassant de la paroi, ainsi que des moyens (14, 16) pour la production de jets d'un agent de refroidissement dirigés dans la zone des pointes (15) vers le côté arrière de la paroi (12a) et servant au refroidissement par impact, les moyens pour la production des jets dirigés vers le côté arrière de la paroi comprenant une tôle de refroidissement par impact (14) avec des trous de refroidissement par impact (16) disposés de façon répartie, et la densité des trous de refroidissement par impact (16) étant corrélée avec la densité des pointes (15), la répartition des pointes (15) à l'intérieur des zones critiques (Ac) de l' élément (10) présentant une densité plus élevée que dans les autres zones de l'élément, caractérisé en ce que, dans les zones où la densité des pointes est accrue, la densité des trous de refroidissement par impact (16) est également accrue, et inversement;
    caractérisé en ce que l'élément est une aube directrice (10) de la turbine à gaz qui comprend une ailette (11) s'étendant dans une direction longitudinale et une plateforme (12), se raccordant à l'ailette (11) et s'étendant transversalement à la direction longitudinale, dont le fond est la paroi (12a) exposée à des contraintes thermiques et refroidie par refroidissement par impact, et forme une cannelure (Ac) au niveau de la transition vers l'ailette (11), et en ce que la répartition des pointes (15) présente une densité plus élevée en direction de la cannelure (Ac) que dans les zones restantes éloignées de la cannelure (Ac).
  2. Elément refroidi selon la revendication 1, caractérisé en ce que la tôle de refroidissement par impact (14) est disposée de façon espacée, essentiellement parallèle au côté arrière de la paroi (12a), et en ce que la répartition des trous de refroidissement par impact (16) est harmonisée avec la répartition des pointes (15) de telle sorte que, vu dans une direction perpendiculaire à la tôle de refroidissement par impact (14), les trous de refroidissement par impact (16) sont situés respectivement entre les pointes (15).
  3. Elément refroidi selon la revendication 1, caractérisé en ce que la densité des trous de refroidissement par impact (16) et la densité des pointes (15) sont localement identiques.
  4. Procédé de fonctionnement d'un élément refroidi pour une turbine à gaz selon l'une des revendications 1 - 3, caractérisé en ce que, pour améliorer le transfert thermique entre la paroi (12a) et l'air de refroidissement mis en oeuvre sous la forme de jets d'air de refroidissement individuels s'écoulant à travers des trous de refroidissement par impact (16), ces jets d'air de refroidissement s'écoulent sur le côté arrière de cette paroi équipée de pointes (15) de forme conique ou pyramidale dépassant perpendiculairement, en ce que les jets d'air de refroidissement réalisent un impact entre les espaces intermédiaires formés par les pointes de telle sorte que, lors de cet impact, il apparaît un écoulement turbulent agissant sur la paroi, qui provoque un refroidissement supplémentaire.
EP10701375.7A 2009-01-30 2010-01-28 Élément structural refroidi pour turbine à gaz Active EP2384392B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00140/09A CH700319A1 (de) 2009-01-30 2009-01-30 Gekühltes bauelement für eine gasturbine.
PCT/EP2010/051018 WO2010086381A1 (fr) 2009-01-30 2010-01-28 Élément structural refroidi pour turbine à gaz

Publications (3)

Publication Number Publication Date
EP2384392A1 EP2384392A1 (fr) 2011-11-09
EP2384392B1 EP2384392B1 (fr) 2017-05-31
EP2384392B2 true EP2384392B2 (fr) 2024-09-04

Family

ID=40600054

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10701375.7A Active EP2384392B2 (fr) 2009-01-30 2010-01-28 Élément structural refroidi pour turbine à gaz

Country Status (5)

Country Link
US (1) US8444376B2 (fr)
EP (1) EP2384392B2 (fr)
CH (1) CH700319A1 (fr)
RU (1) RU2539950C2 (fr)
WO (1) WO2010086381A1 (fr)

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Also Published As

Publication number Publication date
EP2384392B1 (fr) 2017-05-31
RU2011135942A (ru) 2013-03-10
CH700319A1 (de) 2010-07-30
US8444376B2 (en) 2013-05-21
WO2010086381A1 (fr) 2010-08-05
RU2539950C2 (ru) 2015-01-27
US20120020768A1 (en) 2012-01-26
EP2384392A1 (fr) 2011-11-09

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