EP3094822B1 - Aube pour une turbine à gaz et procédé de fabrication d'une telle aube - Google Patents

Aube pour une turbine à gaz et procédé de fabrication d'une telle aube Download PDF

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Publication number
EP3094822B1
EP3094822B1 EP15707775.1A EP15707775A EP3094822B1 EP 3094822 B1 EP3094822 B1 EP 3094822B1 EP 15707775 A EP15707775 A EP 15707775A EP 3094822 B1 EP3094822 B1 EP 3094822B1
Authority
EP
European Patent Office
Prior art keywords
inlet
channel
blade
flow rate
outlet
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
EP15707775.1A
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German (de)
English (en)
Other versions
EP3094822A1 (fr
Inventor
Luca Abba
Massimiliano Maritano
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 SpA
Original Assignee
Ansaldo Energia SpA
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Publication of EP3094822A1 publication Critical patent/EP3094822A1/fr
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Publication of EP3094822B1 publication Critical patent/EP3094822B1/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
    • 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
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
    • 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

Definitions

  • the present invention concerns a blade for a gas turbine and a method for manufacturing said blade.
  • the present invention concerns a stator blade of a gas turbine installed in a plant for the production of electrical energy.
  • Stator blades of gas turbines are generally defined by an elongated main body inside which a cooling circuit is provided.
  • a cooling fluid flows through the cooling circuit, generally air drawn from the plant compressor for the production of energy.
  • the air that flows through the cooling circuit has basically two functions: a cooling function and a sealing function.
  • the cooling function is performed by means of a plurality of cooling holes arranged along the main body of the blade supplied by the cooling circuit; the sealing function is performed by means of seal openings formed in the stator ring to which an anchoring portion of the blade is coupled; said seal openings are supplied by the cooling circuit.
  • the seal openings are arranged so as to fill the cavity defined by the stator blade, by the stator ring and by the rotor with air coming from the cooling circuit and prevent the hot evolving gases in the turbine from occupying said cavity. Examples of cooling circuits of this type are disclosed in documents EP 2159376 , US 2009/185893 , EP 1070829 , WO 2010/139766 .
  • One object of the present invention is therefore to produce a blade for a gas turbine which is free from the drawbacks of the known art highlighted here; in particular, one object of the invention is to produce a blade for a gas turbine able to optimise the sealing and cooling functions in a simple inexpensive manner, in both functional and construction terms.
  • the present invention concerns a blade for a gas turbine as claimed in claim 1.
  • the blade comprises a first anchoring portion coupled to the main body and adapted, in use, to be coupled to a stator casing of the gas turbine; and a second anchoring portion coupled to the main body and adapted, in use, to be coupled to a respective stator ring of the gas turbine; the first inlet and the second inlet being formed in the first anchoring portion; the first outlet being formed in the second anchoring portion and the second outlet being formed along the main body.
  • the presence of the anchoring portion for anchoring to the stator casing and the anchoring portion for anchoring to the stator ring identifies a stator blade of a gas turbine.
  • the presence of two distinct channels having respective independent inlets allows independent regulation and optimisation of the seal flow rate and cooling flow rate of the cooling fluid, therefore preventing the cavity defined by the stator blade, the stator ring and the rotor from being filled with the hot evolving gases in the turbine.
  • the first channel and the second channel are in communication.
  • the first connecting conduit is configured in order to have a variable section. In this way the sizing of the connecting conduit is simplified.
  • the blade comprises at least one metering plate arranged in the area of one between the first inlet and the second inlet and configured to reduce the flow section of the first inlet or the second inlet.
  • the metering plate is provided with at least one first hole. In this way it is possible to further regulate the flow into the first or second channel via the sizing of the first hole.
  • the metering plate is formed so that the first hole has a variable section.
  • a further object of the present invention is to provide a manufacturing method for a blade of a gas turbine which guarantees that the hot evolving gases in the turbine do not invade the cavity defined by the stator blade and the rotor.
  • the present invention concerns a manufacturing method for manufacturing a blade for a gas turbine as claimed in claim 11.
  • the reference number 1 indicates a portion of a gas turbine 2 of a plant for the production of electrical energy (not illustrated for the sake of simplicity).
  • the electrical energy production plant is of known type and comprises a compressor (not illustrated), inside which is an air flow, a combustion chamber supplied with fuel and air from the compressor, the gas turbine 2 and a generator (not illustrated), mechanically connected to the shaft of the gas turbine 2 and of the compressor and connected to an electrical distribution network (not illustrated).
  • the gas turbine 2 extends along a longitudinal axis A and comprises a stator 4 and a rotor 5 (both partially illustrated in figure 1 ), which rotates about the axis A.
  • the stator 4 comprises a stator casing 7 (partially illustrated in figure 1 ), which extends around the axis A for the entire length of the gas turbine 2 and is static, a plurality of stator rings 8 centred on the axis A, supported by the stator casing 7 and arranged in sequence along the axis A, and a plurality of stator blades 10.
  • the stator blades 10 are split into arrays and are arranged radially with respect to the axis A. Each stator blade 10 is fixed to the stator casing 7 and to a respective stator ring 8.
  • the rotor 5 comprises a plurality of rotor rings 12, coupled to one another so as to define one single element rotating about the axis A, and a plurality of rotor blades 13 split into arrays and arranged radially with respect to the axis A.
  • Each rotor blade 13 is provided with one free end 14 and one end 15 coupled to a respective rotor 12.
  • the stator rings 8 extend around the rotor rings 12 and are spaced from one another so that radial arrays of the rotor blades 13 and radial arrays of stator blades 10 alternate along the axis A.
  • the plurality of rotor rings 12, the stator rings 8 and the stator casing 7 define an expansion channel 16 inside which the hot gases coming from the combustion chamber flow.
  • Each stator blade 10 comprises an elongated main body 18, which extends along a respective axis with radial extension B with respect to the axis A, a first anchoring portion 19 coupled to one end 20 of the main body 18 and coupled, in use, to the stator casing 7, a second anchoring portion 21 coupled to one end 22 of the main body 18 opposite the end 20 and coupled, in use, to the respective stator ring 8.
  • the second anchoring portions 21 of the adjacent stator blades 10 and the respective stator ring 8 define, when coupled, an annular seal chamber 23.
  • the stator ring 8 is provided with a plurality of seal openings 24, which establish communication between the seal chamber 23 and an open annular cavity 25.
  • the annular cavity 25 is defined by the stator ring 8, by the anchoring portion 21 of the stator blades coupled to the stator ring 8 and by the rotor rings 12 adjacent to the stator ring 8.
  • each stator blade 10 further comprises a cooling circuit 28 supplied with a cooling fluid.
  • the cooling circuit 28 comprises at least one first cooling channel 29, preferably bent in a U shape, and a second cooling channel 30.
  • the first cooling channel 29 is therefore defined by two branches 31, which extend mainly into the main body 18 substantially parallel to the axis B.
  • the second cooling channel 29 extends mainly into the main body 18 substantially along the axis B.
  • the first cooling channel 29 is provided with a first inlet 32 formed in the first anchoring portion 19 and a first outlet 33 formed in the second anchoring portion 21.
  • the second cooling channel 30 is provided with a second inlet 35 formed in the first anchoring portion 19 and a plurality of outlet holes 36 formed along the main body 18.
  • the first inlet 32 and the second inlet 35 are substantially arranged side by side.
  • the first cooling channel 29 and the second cooling channel 30 are preferably connected.
  • first cooling channel 29 and the second cooling channel 30 are connected by means of two connecting conduits 37, which are preferably parallel and extend orthogonally to the axis B.
  • first cooling channel 29 and the second cooling channel 30 are connected by means of one single appropriately sized connecting conduit.
  • the flow section of one or more connecting conduits between the first cooling channel 29 and the second cooling channel 30 is adjustable, for example by means of the use of a metering plate coupled to the connecting conduit having a variable section opening, or any other means able to shutter the section of the connecting conduit to which it is coupled.
  • the second inlet 35 of the second cooling channel 30 formed in the first anchoring portion 19 is preferably coupled to a metering plate 40 configured so as to reduce the flow section of the second inlet 35.
  • the metering plate 40 is provided with two holes 41 and has a substantially identical shape to the section of the second inlet 35.
  • the coupling of the metering plate 40 to the second inlet 35 determines a reduction in the flow section of the second inlet 35.
  • the holes 41 are appropriately sized so as to obtain the desired reduction in flow section.
  • the metering plate 40 is welded to the first anchoring portion 19.
  • the metering plate is provided with one single flow hole.
  • the metering plate is shaped so as to define one or more holes having an adjustable flow section.
  • the metering plate could be provided with a mobile member configured to partially or completely close one or more holes of the metering plate.
  • the metering plate could be defined by a first portion and a second portion couplable to each other and shaped so as to define, together, a variable section opening.
  • the first portion and the second portion could be coupled geometrically in a plurality of positions to define the variable section opening.
  • the plate is without holes and completely closes the inlet to which it is coupled so as to reduce 100% the inlet flow rate.
  • the cooling fluid that circulates in the cooling circuit 28 is preferably air coming from a draw-off circuit 41 (schematically illustrated), configured to draw air from the compressor of the electrical energy production plant and to feed it to a plurality of stator chambers 43 formed in the stator casing 7.
  • Each stator chamber 43 communicates with the cooling circuit 28 of all the stator blades 10 of the same array through the first inlets 32 and the second inlets 35.
  • the cooling circuit 28 of each stator blade 10 receives, through the first inlet 32 and the second inlet 35, an overall air flow rate QTOT from the respective stator chamber 43 and supplies a cooling air flow rate QR to the expansion channel 26 through the plurality of outlet holes 36 formed along the main body 18 and a seal air flow rate QS to the seal chamber 23 through the first outlet 33.
  • the first inlet 32 and the second inlet 35, the first outlet 33, the outlet holes 36 and the connecting conduits 37 are sized so as to have a seal flow rate QS and a cooling flow rate QR equal to respective reference values.
  • the blade is usually produced by casting and the presence of manufacturing defects does not guarantee that the reference values of the seal flow rate QS and the cooling flow rate QR are actually observed.
  • a manufacturing method which involves the performance of tests on the blades just produced, during which the seal flow rate QS coming out of the first outlet 33 and the cooling flow rate QR which crosses the outlet holes 36 are detected.
  • the manufacturing method provides for reduction of the flow section of one between the first inlet 32 and the second inlet 35 or both the inlets 32 and 35.
  • the method provides for reduction of the flow section of the second inlet 35 by coupling of the appropriately sized metering plate 40.
  • the sizing of the metering plate 40 contributes to further regulating the air supply to the second cooling channel 30 and therefore to regulating the flow rate of cooling air QR.

Landscapes

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

Claims (12)

  1. Aube pour turbine à gaz (2) comprenant :
    un corps principal (18) ;
    une première partie d'ancrage (19) couplée au corps principal (18) et configurée pour être, lors de l'utilisation, couplée à un carter de stator (7) de la turbine à gaz (2) ;
    une seconde partie d'ancrage (21) couplée au corps principal (18) et configurée pour être, lors de l'utilisation, couplée à une couronne de stator (8) respective de la turbine à gaz (2) ;
    un circuit de refroidissement (28) alimenté en fluide de refroidissement et comprenant un premier canal (29) et au moins un deuxième canal (30) agencé, au moins en partie, à l'intérieur du corps principal (18) ; le premier canal (29) étant pourvu d'une première entrée (32) et d'une première sortie (33) ; le deuxième canal (30) étant pourvu d'une deuxième entrée (35), distincte de la première entrée (32), et d'une pluralité de deuxièmes sorties (36) formées le long du corps principal (18) et distinctes de la première sortie (33) ; la première entrée (32) et la deuxième entrée (35) étant formées dans la première partie d'ancrage (19) ; la première sortie (33) étant formée dans la seconde partie d'ancrage (21) ;
    l'aube étant caractérisée en ce que le premier canal (29) et le deuxième canal (30) sont en communication fluidique au moyen d'au moins un premier conduit de raccord (37) pour permettre le passage d'une certaine quantité de fluide de refroidissement.
  2. Aube selon la revendication 1, dans laquelle le premier canal (29) et le deuxième canal (30) sont connectés au moyen d'au moins un deuxième conduit de raccord (37).
  3. Aube selon l'une quelconque des revendications 1 et 2, dans laquelle la section d'écoulement du premier conduit de raccord (37) est réglable.
  4. Aube selon la revendication 2, dans laquelle le premier conduit de raccord et le deuxième conduit de raccord (37) sont sensiblement identiques.
  5. Aube selon l'une quelconque des revendications précédentes, comprenant au moins une plaque de mesure (40) couplée à la première entrée (32) et/ou à la deuxième entrée (35) et conçue pour réduire respectivement la section d'écoulement de la première entrée (32) et/ou de la deuxième entrée (35).
  6. Aube selon la revendication 5, dans laquelle la plaque de mesure (40) est pourvue d'au moins un premier trou (41).
  7. Aube selon la revendication 6, dans laquelle la plaque de mesure (40) est conçue de sorte que le premier trou (41) présente une section variable.
  8. Aube selon la revendication 7, dans laquelle la plaque de mesure (40) comprend au moins un élément mobile conçu pour fermer, au moins partiellement, au moins le premier trou (41).
  9. Aube selon la revendication 7, dans laquelle la plaque de mesure (40) comprend une première partie et une deuxième partie pouvant être couplées l'une à l'autre et formées de façon à définir, ensemble, au moins le premier trou (41) présentant une section variable.
  10. Aube selon la revendication 9, dans laquelle la première partie et la deuxième partie peuvent être couplées géométriquement dans une pluralité de positions pour définir le premier trou (41) présentant une section variable.
  11. Procédé de fabrication d'une aube (10) pour une turbine à gaz (2) comprenant les étapes de :
    • fabrication d'une aube (10) pourvue d'un circuit de refroidissement (28) comprenant un premier canal (29) et au moins un deuxième canal (30) ; le premier canal (29) étant pourvu d'une première entrée (32) et d'une première sortie (33) ; le deuxième canal (30) étant pourvu d'une deuxième entrée (35), distincte de la première entrée (32), et d'une pluralité de deuxièmes sorties (36) formées le long du corps principal (18) et distinctes de la première sortie (33) ; le premier canal (29) et le deuxième canal (30) sont en communication fluidique au moyen d'au moins un premier conduit de raccord (37) pour permettre le passage d'une certaine quantité de fluide de refroidissement ;
    • la fourniture d'un débit (QTOT) défini d'un fluide de refroidissement à la fois à la première entrée (32) et à la deuxième entrée (35) ;
    • la détection d'un premier débit (QS) de fluide de refroidissement s'écoulant à travers la première sortie (33) ;
    • la détection d'un second débit (QR) de fluide de refroidissement s'écoulant à travers la deuxième sortie (36) ;
    • la comparaison du premier débit (QS) et du second débit (QR) de fluide de refroidissement à des valeurs de référence respectives ;
    • la réduction de la section d'écoulement d'au moins une entre la première entrée (32) et la deuxième entrée (35) si le premier débit (QS) et/ou le second débit (QR) ne reflètent pas les valeurs de référence.
  12. Procédé selon la revendication 11 dans lequel l'étape de réduction de la section d'écoulement d'au moins une entre la première entrée (32) et la deuxième entrée (35) comprend l'étape de couplage d'une plaque de mesure (40) à au moins une entre la première entrée (32) et la deuxième entrée (35).
EP15707775.1A 2014-01-13 2015-01-13 Aube pour une turbine à gaz et procédé de fabrication d'une telle aube Active EP3094822B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ITMI20140033 2014-01-13
PCT/IB2015/050247 WO2015104695A1 (fr) 2014-01-13 2015-01-13 Aube pour turbine à gaz et son procédé de fabrication

Publications (2)

Publication Number Publication Date
EP3094822A1 EP3094822A1 (fr) 2016-11-23
EP3094822B1 true EP3094822B1 (fr) 2021-10-06

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EP15707775.1A Active EP3094822B1 (fr) 2014-01-13 2015-01-13 Aube pour une turbine à gaz et procédé de fabrication d'une telle aube

Country Status (4)

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EP (1) EP3094822B1 (fr)
KR (1) KR20160125952A (fr)
CN (1) CN106471214B (fr)
WO (1) WO2015104695A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FI125111B (en) 2013-11-19 2015-06-15 Kemira Oyj A method for analyzing a sample comprising a first and a second crust inhibitor
JP6791777B2 (ja) * 2017-02-10 2020-11-25 三菱パワー株式会社 地熱タービン
EP3663522B1 (fr) * 2018-12-07 2021-11-24 ANSALDO ENERGIA S.p.A. Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator
CN110043328B (zh) * 2018-12-17 2021-10-22 中国航发沈阳发动机研究所 一种冷却式变几何低压涡轮导向叶片
EP3816402B1 (fr) * 2019-11-04 2023-01-04 ANSALDO ENERGIA S.p.A. Ensemble de stator pour turbine à gaz et turbine à gaz comportant ledit ensemble de stator
EP4019742B1 (fr) * 2020-12-23 2024-10-23 ANSALDO ENERGIA S.p.A. Ensemble d'étanchéité pour un jeu d'aubes d'un moteur à turbine à gaz et moteur à turbine à gaz comprenant un tel ensemble d'étanchéité

Family Cites Families (4)

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Publication number Priority date Publication date Assignee Title
US6186741B1 (en) * 1999-07-22 2001-02-13 General Electric Company Airfoil component having internal cooling and method of cooling
US8016547B2 (en) * 2008-01-22 2011-09-13 United Technologies Corporation Radial inner diameter metering plate
US20100054915A1 (en) * 2008-08-28 2010-03-04 United Technologies Corporation Airfoil insert
IT1394713B1 (it) * 2009-06-04 2012-07-13 Ansaldo Energia Spa Pala di turbina

Non-Patent Citations (1)

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Also Published As

Publication number Publication date
WO2015104695A1 (fr) 2015-07-16
CN106471214B (zh) 2019-04-02
KR20160125952A (ko) 2016-11-01
EP3094822A1 (fr) 2016-11-23
CN106471214A (zh) 2017-03-01

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