EP2137382B1 - Écran thermique de stator - Google Patents

Écran thermique de stator Download PDF

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Publication number
EP2137382B1
EP2137382B1 EP08735874A EP08735874A EP2137382B1 EP 2137382 B1 EP2137382 B1 EP 2137382B1 EP 08735874 A EP08735874 A EP 08735874A EP 08735874 A EP08735874 A EP 08735874A EP 2137382 B1 EP2137382 B1 EP 2137382B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
stator heat
gas turbine
stator
ribs
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
EP08735874A
Other languages
German (de)
English (en)
Other versions
EP2137382A1 (fr
Inventor
Alexander Khanin
Edouard Sloutski
Sergey Vorontsov
Anton Sumin
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
Priority to SI200830743T priority Critical patent/SI2137382T1/sl
Publication of EP2137382A1 publication Critical patent/EP2137382A1/fr
Application granted granted Critical
Publication of EP2137382B1 publication Critical patent/EP2137382B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2240/55—Seals
    • F05D2240/57—Leaf seals
    • 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
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a stator heat shield for a gas turbine according to the preamble of claim 1 and a gas turbine equipped with such a stator heat shield.
  • Statorhitzeschilde are in the installed state of a stator or on a housing of a gas turbine. In this case, they are usually mounted on a guide blade carrier and form a radial boundary for a hot gas path of the gas turbine in the region of rotor blades of the gas turbine. In this case, a plurality of such Statorhitzeschilde is arranged adjacent to each other in the circumferential direction relative to a rotational axis of the rotor with respect to each other, whereby a closed ring of individual Statorhitzeschilden is formed.
  • the individual stator heat shields form ring segments. The stator heat shields protect the housing or the guide blade carrier from being exposed to the hot gas of the gas turbine.
  • the invention deals with the problem of providing an improved embodiment for a stator heat shield or for a gas turbine equipped therewith, which is characterized in particular by an increased service life of the stator heat shields.
  • the present invention is based on the general idea of combining a flapper cooling, a convection cooling and a sealing element cooling with each other in the stator heat shield, thereby providing a plurality of ribs formed on an inner side facing away from a hot gas path of the gas turbine in the installed state of the stator heat shield, which ribs are in the installed state with respect to an axis of rotation a rotor of the gas turbine extend axially and are spaced apart in the circumferential direction, so that can be formed on the inside of several channels. At the same time, these ribs serve to stiffen the respective stator heat shield. On the inside of a baffle plate is also arranged, which rests on the ribs.
  • the respective stator heat shield is provided with a groove, at least on a front side delimiting the stator heat shield in the circumferential direction, into which groove at least one sealing element can be inserted. Two circumferentially adjacent stator heat shields adjoin one another in the region of these end faces, wherein a relatively small gap is formed as a rule.
  • the respective sealing element now engages in the mutually aligned grooves of the two mutually opposite in the gap end faces and thereby closes the gap and thus the connection between the outside facing the hot gas path with a the inside facing cooling gas path.
  • the stator heat shield with a plurality of bores, which open at one end on the inside and the other end on the end face, in such a way that they open out from the groove in the direction of the outside.
  • the holes are arranged spaced apart in the axial direction. Through these holes, cooling gas can pass from the cooling gas path to the hot gas side in the gap between adjacent stator heat shields in the circumferential direction and can there apply cooling gas to the sealing elements.
  • film cooling of the sealing elements as well as the opposite end faces of the adjacent stator heat shields in the gap can be achieved in the region of the gap.
  • a targeted cooling of this area reduces the temperatures at the respective stator heat shield at the front ends, which reduces the heat load of the stator heat shield.
  • FIG. 1 has a gas turbine 1, of which only a small section is shown here, a stator 2 and a rotor 3, which are also shown only partially. From the stator 2 guide vanes 4 are partially visible and a portion of a vane carrier 5. On the guide vane 5 are on the one hand the vanes 4 attached to the other stator stator 5 are also attached to the stator vane 5, one of which is recognizable here. From the rotor 3, only one blade 7 can be seen here, which is arranged between the two guide vanes 4. A dot-dash line indicates a rotation axis 8 about which the rotor 3 rotates during operation of the gas turbine 1 and which defines the axial direction of the gas turbine 1.
  • Axial in the present context thus means parallel to the axis of rotation 8, while a radial direction is perpendicular to the axis of rotation 8 and a circumferential direction along a circular path about the axis of rotation 8 is oriented.
  • the blade 7 is arranged axially between the two guide vanes 4.
  • the stator heat shield 6 is disposed radially of the blade 7 and positioned axially between the two vanes 4.
  • the individual Statorhitzeschilde 6 form segments which are arranged adjacent to each other in the circumferential direction and form a closed circular ring which encloses a blade row, which is formed by circumferentially adjacent blades 7.
  • the respective stator heat shield 6 separates a hot gas path 9 of the gas turbine 1, indicated by an arrow, from a cooling gas path 10, likewise indicated by an arrow, which runs essentially in the stator 2.
  • the respective stator heat shield 6 has an outer side 11, which faces the hot gas path 9 in the installed state.
  • the stator heat shield 6 has an inner side 12, which faces the cooling gas path 10 and is remote from the hot gas path 9 and from the outer side 11.
  • the stator heat shield 6 has a plurality of ribs 13. These ribs 13 extend axially in the installed state and are preferably designed in a straight line. Furthermore, the ribs 13 are spaced from each other in the circumferential direction.
  • at least one baffle plate 14, which rests on the ribs 13, is arranged on the inner side 12. In the in Fig. 2 As shown, the baffle plate 14 extends only over one half of the inner side 12. A second baffle plate 14 covering the other half is omitted here for better recognition of the ribs 13. Likewise, a single baffle plate 14 may be provided which covers all the ribs 13.
  • the respective stator heat shield 6 also has, in the circumferential direction, two end faces 15, each delimiting the stator heat shield 6 in the circumferential direction. In at least one of these end faces 15, a groove 16 is incorporated. Preferably, in each case such a groove 16 is incorporated in both end faces 15.
  • two stator heat shields 6 which are adjacent to one another in the circumferential direction adjoin one another in the region of these end faces 15, each two such end faces 15 in an in Fig. 3 indicated axial gap 17 are opposite to each other.
  • the grooves 16 are arranged so that they are aligned with each other in the axial gap 17 opposite end faces 15 to each other.
  • the respective groove 16 serves to receive at least one sealing element 18, which is configured, for example, band-shaped or strip-shaped.
  • such a sealing element 18 engages in two mutually aligned grooves 16 at two in the gap 17 opposite end faces 15 at the same time. In this way, the respective sealing element 18 can seal off the axial gap 17, ie separate the hot gas path 9 facing the hot gas path from the cooling gas side facing the cooling gas path 10.
  • the stator heat shield 6 is also equipped with several holes 19.
  • Each of these holes 19 connects the inner side 12 of one of the end faces 15. Accordingly, the respective bore 19 opens at one end to the inner side 12 and the other end to the respective end face 15.
  • the mouth of the respective bore 19 at the respective end face 15 is spaced from the groove 16, in the direction of the outside 11. In this way, through the bores 19, cooling gas can pass from the cooling gas side or from the cooling gas path 10 to the hot gas side of the gap 17, which is open toward the hot gas path 9.
  • the individual holes 19 are according to Fig. 2 spaced apart in the axial direction formed on the respective end face 15 of the stator heat shield 6.
  • the front side 15 provided with the bores 19 is equipped with the recess 20.
  • both end faces 15 are provided with holes 19 and such a recess 20.
  • the recesses 20 also allow the cooling gas to escape sufficiently through the bores 19 if the gap 17 becomes comparatively narrow in the circumferential direction due to relative movements of the adjacent stator heat shields 6.
  • a cooling of the sealing elements 18 can be effected during operation of the gas turbine 1.
  • a cooling gas film can be produced on the hot gas side of the sealing elements 18, which obstructs direct hot gas loading of the sealing elements 18.
  • the circumferential end regions of the respective stator heat shield 6 provided with the end faces 15 can effectively be cooled thereby, on the one hand by the flow of these end regions with cooling gas and on the other hand by the formation of the cooling gas film on the areas of the front side 15 and the outside 11 exposed to the hot gas path 9 ,
  • a recess 21 is formed.
  • the ribs 13 are arranged, in such a way that within the recess 21, a system of mutually communicating channels 22 is formed.
  • the at least one baffle plate 14 covers this system from channels 22 to the cooling gas path 10 from.
  • Within these channels 22 there is a convective heat transfer between the respective stator heat shield 6 and the respective baffle plate 14.
  • a cooling gas flow is conducted through the channel system formed with the channels 22.
  • the respective baffle plate 14 has a plurality of passage openings 23 through which cooling gas can pass from the cooling gas path 10 through the baffle plate 14 into the channels 22.
  • the aforementioned holes 19 now open on the inner side 12 in said recess 21 or in one of the channels 22.
  • brackets 24 are formed here, with the aid of which the respective baffle plate 14 can be fixed to the stator heat shield 6.
  • the respective holders 24 overlap the respective flat plate 14 for this purpose.
  • the ribs 13 each have a certain rib height 25, with which they extend in the radial direction. With this fin height 25, the ribs 13 are here from a bottom of the recess 21 from. Furthermore, the individual ribs 13 in the circumferential direction on a rib spacing 26 from each other. The fin height 25 and fin spacing 26 are matched to one another such that a ratio of fin height 25 to fin spacing 26 is in a range of 0.328 to 0.492.
  • each individual hole 19 has in the axial direction a certain bore spacing 27 to each other. Furthermore, each individual bore has a specific bore diameter 28. The respective bore diameter 28 and the hole spacing 2 are matched to each other to give a bore diameter to hole spacing ratio 27 ranging from 0.0992 to 0.1488.

Abstract

La présente invention concerne un écran thermique de stator (6) pour une turbine à gaz (1), comprenant un côté extérieur (11) faisant face, en position montée, à une trajectoire de gaz chaud (9) de la turbine à gaz (1), un côté intérieur (12) opposé au côté extérieur (11), plusieurs nervures (13) réalisées sur le côté intérieur (12) qui, en position montée, s'étendent axialement par rapport à un axe de rotation (8) d'un rotor (3) de la turbine à gaz (1) et qui sont espacées entre elles dans le sens périphérique, au moins une chicane (14) disposée sur le côté intérieur (12), qui repose sur les nervures (13), au moins une rainure (16) réalisée sur un côté frontal (15) délimitant l'écran thermique de stator (6) dans le sens périphérique et dans laquelle au moins un élément d'étanchéité (18) peut être placé et plusieurs trous (19) qui débouchent à une extrémité sur le côté intérieur (12) et à l'autre extrémité sur le côté frontal (15) à une certaine distance de la rainure (16), en direction du côté extérieur (11), et qui sont espacés entre eux dans le sens axial.

Claims (7)

  1. Bouclier thermique de stator de turbine à gaz (1), présentant :
    - un côté extérieur (11) tourné à l'état monté vers le parcours (9) des gaz chauds de la turbine à gaz (1),
    - un côté intérieur (2) non tourné vers le côté extérieur (11),
    - au moins une rainure (16) formée dans un côté frontal (15) qui délimite le bouclier thermique de stator (6) dans la direction périphérique et dans laquelle au moins un élément d'étanchéité (18) peut être inséré,
    - plusieurs alésages (19) dont une extrémité est située sur le côté frontal (15) à distance de la rainure (16) en direction du côté extérieur (11) et qui débouchent à l'autre extrémité sur le côté intérieur (12), les alésages étant disposés à distance mutuelle dans la direction axiale,
    caractérisé en ce que
    - plusieurs nervures (13) formées sur le côté intérieur (12) sont prévues, s'étendent en position montée axialement par rapport à un axe de rotation (8) du rotor (3) de la turbine à gaz (1) et sont disposées à distance mutuelle dans la direction périphérique,
    - en ce qu'au moins une plaque d'incidence (14) est disposée sur le côté intérieur (12) et repose sur les nervures (13),
    - en ce que le rapport entre la hauteur (25) des nervures et la distance (26) entre les nervures est de l'ordre de 0,41 ± 20 % et
    - en ce que le rapport entre le diamètre (28) des alésages et la distance (27) entre les alésages est de l'ordre de 0,124 ± 20 %.
  2. Bouclier thermique de stator selon la revendication 1, caractérisé en ce qu'une découpe (20) formée sur le côté frontal (15) à distance de la rainure (16) en direction du côté extérieur (11) s'étend dans la direction axiale au-dessus des alésages (19) du côté frontal (15) et est ouverte en direction du côté extérieur (11), et en ce que les alésages (19) y débouchent.
  3. Bouclier thermique de stator selon les revendications 1 ou 2, caractérisé en ce qu'un creux (21) dans lequel les nervures (13) sont disposées et forment un système de canaux (22) communiquant les uns avec les autres est formé sur le côté intérieur (12), le système étant recouvert par la ou les plaques d'incidence (14).
  4. Bouclier thermique de stator selon la revendication 3, caractérisé en ce que les alésages (19) débouchent dans le creux (21) ou dans l'un des canaux (22).
  5. Bouclier thermique de stator selon l'une des revendications 1 à 4, caractérisé en ce que la ou les plaques d'incidence (14) présentent plusieurs ouvertures de passage (23).
  6. Bouclier thermique de stator selon l'une des revendications 1 à 5, caractérisé en ce qu'au moins un support (24) qui immobilise sa plaque d'incidence (14) sur le bouclier thermique de stator (6) est formé sur le côté intérieur (12).
  7. Turbine à gaz dotée d'au moins un bouclier thermique (6) de stator selon l'une des revendications 1 à 6.
EP08735874A 2007-04-19 2008-04-07 Écran thermique de stator Active EP2137382B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SI200830743T SI2137382T1 (sl) 2007-04-19 2008-04-07 Statorski toplotni ščit

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH6452007 2007-04-19
PCT/EP2008/054140 WO2008128876A1 (fr) 2007-04-19 2008-04-07 Écran thermique de stator

Publications (2)

Publication Number Publication Date
EP2137382A1 EP2137382A1 (fr) 2009-12-30
EP2137382B1 true EP2137382B1 (fr) 2012-05-30

Family

ID=38349602

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08735874A Active EP2137382B1 (fr) 2007-04-19 2008-04-07 Écran thermique de stator

Country Status (6)

Country Link
US (1) US7997856B2 (fr)
EP (1) EP2137382B1 (fr)
CA (1) CA2684371C (fr)
MX (1) MX2009011266A (fr)
SI (1) SI2137382T1 (fr)
WO (1) WO2008128876A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014150182A1 (fr) * 2013-03-15 2014-09-25 United Technologies Corporation Ensemble rotor à enclenchement avec bouclier thermique

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WO2008128876A1 (fr) 2007-04-19 2008-10-30 Alstom Technology Ltd Écran thermique de stator
IT1395732B1 (it) * 2009-08-03 2012-10-19 Ansaldo Energia Spa Apparecchiatura per l'investigazione sperimentale di sistemi di tenuta assiale di turbine a gas
FR2968350B1 (fr) * 2010-12-06 2016-01-29 Snecma Anneau sectorise de turbine pour turbomachine, et turbomachine equipee d'un tel anneau
US8876458B2 (en) 2011-01-25 2014-11-04 United Technologies Corporation Blade outer air seal assembly and support
EP2508713A1 (fr) * 2011-04-04 2012-10-10 Siemens Aktiengesellschaft Turbine à gaz comprenant un écran thermique et procédé d'opération
US8814507B1 (en) 2013-05-28 2014-08-26 Siemens Energy, Inc. Cooling system for three hook ring segment
EP2826962B1 (fr) * 2013-07-15 2016-06-22 MTU Aero Engines GmbH Turbomachine avec segments d'étanchéité et segments d'aube directrice
EP2835500A1 (fr) * 2013-08-09 2015-02-11 Siemens Aktiengesellschaft Elément d'insertion et turbine à gaz
WO2015084550A1 (fr) * 2013-12-03 2015-06-11 United Technologies Corporation Écrans thermiques pour joints d'étanchéité à l'air
EP2949873A1 (fr) * 2014-05-27 2015-12-02 Siemens Aktiengesellschaft Turbomachine avec blindage à l'ingestion et utilisation de la turbomachine
WO2016028310A1 (fr) 2014-08-22 2016-02-25 Siemens Aktiengesellschaft Système de refroidissement de carénage pour des carénages adjacents à des surfaces portantes dans des moteurs à turbine à gaz
EP3118420A1 (fr) * 2015-07-15 2017-01-18 Siemens Aktiengesellschaft Élément de paroi pouvant être refroidi avec plaque de refroidissement par impact
ES2723400T3 (es) 2015-12-07 2019-08-27 MTU Aero Engines AG Estructura de carcasa de una turbomáquina con pantalla de protección térmica
US10513943B2 (en) 2016-03-16 2019-12-24 United Technologies Corporation Boas enhanced heat transfer surface
GB2559804A (en) * 2017-02-21 2018-08-22 Siemens Ag Heatshield for a gas turbine
US10428689B2 (en) * 2017-05-17 2019-10-01 Rolls-Royce Deutschland Ltd & Co Kg Heat shield for a gas turbine engine
US20180347399A1 (en) * 2017-06-01 2018-12-06 Pratt & Whitney Canada Corp. Turbine shroud with integrated heat shield
US11168702B2 (en) 2017-08-10 2021-11-09 Raytheon Technologies Corporation Rotating airfoil with tip pocket

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Cited By (2)

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Publication number Priority date Publication date Assignee Title
WO2014150182A1 (fr) * 2013-03-15 2014-09-25 United Technologies Corporation Ensemble rotor à enclenchement avec bouclier thermique
US10309251B2 (en) 2013-03-15 2019-06-04 United Technologies Corporation Interlocking rotor assembly with thermal shield

Also Published As

Publication number Publication date
US20100047062A1 (en) 2010-02-25
US7997856B2 (en) 2011-08-16
SI2137382T1 (sl) 2012-10-30
CA2684371A1 (fr) 2008-10-30
EP2137382A1 (fr) 2009-12-30
WO2008128876A1 (fr) 2008-10-30
MX2009011266A (es) 2009-11-02
CA2684371C (fr) 2014-10-21

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