EP2300686B1 - Turbine à gaz pourvue d'une aube directrice - Google Patents

Turbine à gaz pourvue d'une aube directrice Download PDF

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Publication number
EP2300686B1
EP2300686B1 EP09765688.8A EP09765688A EP2300686B1 EP 2300686 B1 EP2300686 B1 EP 2300686B1 EP 09765688 A EP09765688 A EP 09765688A EP 2300686 B1 EP2300686 B1 EP 2300686B1
Authority
EP
European Patent Office
Prior art keywords
plenum
gas turbine
blade
outer platform
hot gas
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
EP09765688.8A
Other languages
German (de)
English (en)
Other versions
EP2300686A2 (fr
Inventor
Roland DÜCKERSHOFF
Ulrich Steiger
Ulrich Rathmann
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
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Publication of EP2300686A2 publication Critical patent/EP2300686A2/fr
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Publication of EP2300686B1 publication Critical patent/EP2300686B1/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to the field of gas turbine technology. It relates to a gas turbine with a vane according to the preamble of claim 1.
  • Gas turbines with sequential combustion are known and have proven themselves in industrial operation.
  • Such a gas turbine which has become known in the art as GT24 / 26, for example, from an article of Joos, F. et al., "Field Experience of the Sequential Combustion System for the ABB GT24 / GT26 Gas Turbine Family", IGTI / ASME 98-GT-220, 1998 Sweden ,
  • the local Fig. 1 shows the basic structure of such a gas turbine, where the local Fig. 1 in the present application as Fig. 1 is reproduced. Furthermore, such a gas turbine goes out EP-B1-0 620 362 out.
  • Fig. 1 shows a gas turbine 10 with sequential combustion, in which along an axis 19, a compressor 11, a first combustion chamber 14, a high pressure turbine (HDT) 15, a second combustion chamber 17 and a low pressure turbine (NDT) 18 are arranged.
  • the compressor 11 and the two turbines 15, 18 are part of a rotor which rotates about the axis 19.
  • the compressor 11 sucks in air and compresses it.
  • the compressed air flows into a plenum, and from there into premix burners, where this air mixed with at least one fuel, at least via the fuel supply 12 brought up fuel becomes.
  • premix burners go out in principle EP-A1-0 321 809 or EP-A2-0 704 657 out.
  • the compressed air flows into the premix burners, where the mixing, as stated above, takes place with at least one fuel.
  • This fuel / air mixture then flows into the first combustion chamber 14, into which this mixture passes to form a stable flame front for combustion.
  • the hot gas provided in this way is partially expanded in the subsequent high-pressure turbine 15 under working power and then flows into the second combustion chamber 17, where a further fuel supply 16 takes place. Due to the high temperatures, which still has the hot gas partially released in the high-pressure turbine 15, combustion takes place in the second combustion chamber 17, which combustion is based on autoignition.
  • the hot gas reheated in the second combustion chamber 17 is then expanded in a multistage low-pressure turbine 18.
  • the low-pressure turbine 18 comprises in the flow direction arranged one behind the other a plurality of rows of blades and vanes, which are arranged alternately.
  • the guide vanes of the third row of guide vanes in the flow direction are in Fig. 1 provided with the reference numeral 20 '.
  • a gaseous cooling medium eg compressed air from the compressor of the gas turbine or steam, if the gas turbine is part of a combined cycle power plant
  • a gaseous cooling medium sent through arranged in the blade (often running in serpentine) cooling channels and / or at different points of the blade through corresponding openings (holes , Slits) to the outside, in particular on the outside of the blade to form a cooling film (film cooling).
  • a cooled blade is in the document US-A-5,813,835 described and illustrated.
  • the invention aims to remedy this situation. It is therefore an object of the invention to achieve an effective cooling of the cover plate with much simpler means and to ensure it at gas turbine vane.
  • Essential for the invention is that first means for controlling the cooling medium pressure in the first plenum above the cover plate of the guide vane are provided, and that second means are provided which cause a cooling of the cover plate by specifically escaping from the first plenum cooling medium. As a result, specifically escaping leakage cooling medium can be used to cool the cover plate before it flows out into the hot gas channel.
  • the first means are arranged in the region of the first plenum, wherein the first means comprise a throttle element, which throttles the flow of the cooling medium through the inlet in the cover plate, and the throttle element is formed as a plate which the inlet up on one or more provided in the plate, preferably circular, throttle openings covers.
  • Another embodiment is characterized in that the access to the first plenum is designed as a throttle opening. Through the throttle devices the pressure in the first plenum and the leakage of the cooling medium from the plenum can be adjusted.
  • two outwardly projecting, preferably hook-shaped, fastening elements for fastening the guide blade on the blade carrier are integrally formed on the upper side of the cover plate, wherein the first plenum is formed between the two fastening elements.
  • the second means comprise a second plenum disposed on the side of the one fastener facing away from the first plenum, the second plenum being supplied from the first plenum with cooling medium escaping therefrom and the second plenum communicating with the hot gas channel via throttling means stands.
  • the gaps between adjacent vanes of a row of vanes are sealed by sealing strips against the hot gas channel, which are inserted into corresponding sealing grooves in the side surfaces of the cover plates of the vanes, wherein the sealing strips are formed in the region of the second plenum as a throttle means and in the region of the second plenum for Achieving a throttle effect shorter and / or much thinner than the associated sealing grooves are formed.
  • a further embodiment of the invention is characterized in that the second plenum is partially bounded by an adjacent in the flow direction of the hot gas flow to the cover plate of the guide blade heat shield segment, and that between the heat shield segment and the cover plate to the hot gas channel through a step gap is arranged, via which the second Plenum communicates with the hot gas channel.
  • a vane can be seen, for example, in the low pressure turbine of a sequential combustion gas turbine Fig. 1 can be used, and is suitable for the realization of the invention.
  • the guide vane 20 comprises a strongly curved airfoil 22 which extends in the longitudinal direction (in the radial direction of the gas turbine) between the vane head 23 and a cover plate 21 and extends in the direction of the hot gas stream 30 from a front edge 27 to a trailing edge 28. Between the two edges 27 and 28, the airfoil 22 is outwardly through a suction side 29 and an (opposite) pressure side (in Fig. 2 not to be seen) limited.
  • the vane 20 is formed by means of the hook-shaped fastening elements 24 and 25 formed on the upper side of the cover plate 21 on the blade carrier (38 in FIG Fig. 5 ), while sealingly engages with the blade head 23 on the rotor.
  • the space between the fasteners 24 and 25 forms in the installed state of the vane ( Fig. 5 ) a first plenum (41) for the cooling air, while a pronounced groove 31 on the other side of the fastening element 25 in the installed state of the guide vane ( Fig. 5 ) is available as a second plenum (42).
  • Sealing grooves are provided in the side surfaces of the cover plate 21, which receive strip seals for sealing the gaps between adjacent vanes of a blade ring.
  • An originating in the cover plate 21 from the casting process core output 32 is flush and thus streamlined closed by a stopper not shown in detail.
  • cooling means (cooling channels, cooling fins, impingement cooling elements, etc.) are provided (not shown in the figures), according to Fig. 4 be supplied via an inlet 36 in the cover plate 21 with cooling medium (cooling air).
  • the cooling medium flowing into the blade originates from the first plenum 41 above the cover plate (FIG. Fig. 6 ), in which it passes through a throttle opening 43 in the blade carrier 38.
  • the comparatively large cross-section of the inlet 36 is closed by a flush inserted, plate-shaped throttle element 34, which (see Fig. 4 , Pos. 35) or several throttle openings of smaller diameter (see Fig. 5 , Pos. 35a).
  • the pressure of the cooling medium 51 in the first plenum is effectively controlled and adjusted.
  • the set pressure causes a targeted (controlled) leakage of the cooling medium 51 c from the first plenum 41 in the adjacent second plenum 42 and the wall of the hot gas channel 44 forming part of the cover plate 21.
  • This allows the cover plate 21 without further constructive measures to simple , safe and easily adjustable way with leakage cooling medium 51 a-51 d are cooled from the cooling of the airfoil (curved arrows in Fig. 6 ).
  • the use of the cooling medium which has flowed into the second plenum 42 for the cooling of the cover plate 21 is preferably influenced by two measures which are more clearly defined in FIG FIGS. 7 and 8
  • a special sealing strip 46 is used which is shorter and / or substantially thinner than the associated sealing groove 26 in order to achieve a throttling effect ( Fig. 8 ).
  • targeted cooling medium from the second plenum 42 through the throttled sealed gap between adjacent cover plates 21 escape into the hot gas channel and cool the cover plates.
  • the weather strip especially thin can be distributed in the base portion 48 of the provided with an additional angle section 47 strip beads 49, 50 are provided to fix the position of the sealing strip 46 in the sealing groove 26 ( Fig. 8 ).
  • step gap 45 is characterized by two gap widths s1 and s2 and a distance x ( Fig. 7 ), where s1 is preferably in the range between 0.1 and 2 mm, s2 is between s1 and 0.1 to 1 mm, and x is in the range between 0.2 mm and 7 mm.

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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)

Claims (8)

  1. Turbine à gaz (10) comprenant une aube directrice (20), laquelle aube directrice (20) est fixée sur un support d'aube (38) et comprend une pale d'aube (22) s'étendant dans la direction radiale depuis une plaque de recouvrement (21) vers l'intérieur dans un canal de gaz chaud (44), un fluide de refroidissement (51) s'écoulant à travers l'intérieur de l'aube directrice (20), lequel fluide de refroidissement s'écoule à travers un accès (43) dans le support d'aube (38) dans une première chambre (41) disposée au-dessus de la plaque de recouvrement (21) et de là par le biais d'une entrée (36) prévue dans la plaque de recouvrement (21) à l'intérieur de l'aube directrice (20), des premiers moyens (34, 35 ; 35a, 43) étant prévus pour la commande de la pression de fluide de refroidissement dans la première chambre (41), et des deuxièmes moyens (42, 45, 46) étant prévus, lesquels provoquent un refroidissement de la plaque de recouvrement (21) par le fluide de refroidissement s'échappant de manière ciblée hors de la première chambre (41), caractérisée en ce que les premiers moyens (34, 35 ; 35a, 43) sont disposés dans la région de la première chambre (41), et en ce que les premiers moyens comprennent un élément d'étranglement (34) qui étrangle le courant du fluide de refroidissement à travers l'entrée (36) dans la plaque de recouvrement (21).
  2. Turbine à gaz selon la revendication 1, caractérisée en ce que l'élément d'étranglement (34) est réalisé sous forme de plaque, qui recouvre l'entrée (36) à l'exception d'au moins une ouverture d'étranglement (35, 35a) prévue dans la plaque, de préférence de forme ronde circulaire.
  3. Turbine à gaz selon l'une quelconque des revendications 1 à 2, caractérisée en ce que l'accès à la première chambre (41) est réalisé sous forme d'au moins une ouverture d'étranglement (43).
  4. Turbine à gaz selon l'une quelconque des revendications 1 à 3, caractérisée en ce que des éléments de fixation (24, 25) pour la fixation de l'aube directrice (20) sur le support d'aube (38), faisant saillie vers l'extérieur à distance les uns des autres et de préférence en forme de crochets, sont façonnés sur le côté supérieur de la plaque de recouvrement (21), et en ce que la première chambre (41) est réalisée entre les deux éléments de fixation (24, 25).
  5. Turbine à gaz selon la revendication 4, caractérisée en ce que les deuxièmes moyens comprennent une deuxième chambre (42) qui est disposée du côté d'un élément de fixation (25) opposé à la première chambre (41), en ce que la deuxième chambre (42) est alimentée à partir de la première chambre (41) avec du fluide de refroidissement s'échappant de celle-ci, et en ce que la deuxième chambre (42) est en liaison avec le canal de gaz chaud (44) par le biais de moyens d'étranglement (45, 46).
  6. Turbine à gaz selon la revendication 5, caractérisée en ce que les interstices existant entre des aubes directrices adjacentes (20) d'une rangée d'aubes directrices sont étanchéifiés par des bandes d'étanchéité (46) vis-à-vis du canal de gaz chaud (44), lesquelles bandes d'étanchéité sont insérées dans des rainures d'étanchéité correspondantes (26) dans les surfaces latérales des plaques de recouvrement (21) des aubes directrices (20) et en ce que les bandes d'étanchéité (46) dans la région de la deuxième chambre (42) sont réalisées sous forme de moyen d'étranglement.
  7. Turbine à gaz selon la revendication 6, caractérisée en ce que les bandes d'étanchéité (46) dans la région de la deuxième chambre (42) sont réalisées plus courtes et/ou essentiellement plus minces que les rainures d'étanchéité associées (26) pour obtenir un effet d'étranglement.
  8. Turbine à gaz selon la revendication 6 ou 7, caractérisée en ce que la deuxième chambre (42) est limitée en partie par un segment accumulateur de chaleur (39) adjacent à la plaque de recouvrement (21) de l'aube directrice (20) dans la direction d'écoulement du flux de gaz chaud (30), et en ce qu'un interstice étagé (45) est disposé entre le segment accumulateur de chaleur (39) et la plaque de recouvrement (21) vers le canal de gaz chaud (44), par le biais duquel la deuxième chambre (42) est en liaison avec le canal de gaz chaud (44).
EP09765688.8A 2008-05-26 2009-05-13 Turbine à gaz pourvue d'une aube directrice Active EP2300686B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH7902008 2008-05-26
PCT/EP2009/055768 WO2009153108A2 (fr) 2008-05-26 2009-05-13 Turbine à gaz pourvue d'une aube directrice

Publications (2)

Publication Number Publication Date
EP2300686A2 EP2300686A2 (fr) 2011-03-30
EP2300686B1 true EP2300686B1 (fr) 2013-08-07

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP09765688.8A Active EP2300686B1 (fr) 2008-05-26 2009-05-13 Turbine à gaz pourvue d'une aube directrice

Country Status (4)

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US (1) US8210797B2 (fr)
EP (1) EP2300686B1 (fr)
ES (1) ES2432622T3 (fr)
WO (1) WO2009153108A2 (fr)

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JP4841678B2 (ja) * 2010-04-15 2011-12-21 川崎重工業株式会社 ガスタービンのタービン静翼
RU2547542C2 (ru) * 2010-11-29 2015-04-10 Альстом Текнолоджи Лтд Осевая газовая турбина
EP2518278A1 (fr) * 2011-04-28 2012-10-31 Siemens Aktiengesellschaft Canal de refroidissement de carter de turbine comprenant un fluide de refroidissement s'écoulant vers l'amont
EP2644833A1 (fr) * 2012-03-26 2013-10-02 Alstom Technology Ltd Anneau de support
US8961108B2 (en) * 2012-04-04 2015-02-24 United Technologies Corporation Cooling system for a turbine vane
ES2664322T3 (es) * 2013-06-06 2018-04-19 MTU Aero Engines AG Segmento de álabes directores de una turbomáquina y una turbina
EP3199759A1 (fr) 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Aube de turbine pour une turbomachine thermique
EP3199760A1 (fr) 2016-01-29 2017-08-02 Siemens Aktiengesellschaft Aube de turbine dotée d'un élément d'étranglement
US10641174B2 (en) 2017-01-18 2020-05-05 General Electric Company Rotor shaft cooling
FR3070716B1 (fr) * 2017-09-06 2020-10-02 Safran Aircraft Engines Languette d'etancheite de segments de stator
FR3070718B1 (fr) * 2017-09-06 2019-08-23 Safran Aircraft Engines Ensemble de turbine a secteurs d'anneau
US10655489B2 (en) * 2018-01-04 2020-05-19 General Electric Company Systems and methods for assembling flow path components
US11035251B2 (en) * 2019-09-26 2021-06-15 General Electric Company Stator temperature control system for a gas turbine engine

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Also Published As

Publication number Publication date
EP2300686A2 (fr) 2011-03-30
WO2009153108A2 (fr) 2009-12-23
ES2432622T3 (es) 2013-12-04
US8210797B2 (en) 2012-07-03
WO2009153108A3 (fr) 2010-07-15
US20110085894A1 (en) 2011-04-14

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