EP2815083B1 - Élément pour une machine thermique, en particulier une turbine à gaz - Google Patents

Élément pour une machine thermique, en particulier une turbine à gaz Download PDF

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Publication number
EP2815083B1
EP2815083B1 EP13704137.2A EP13704137A EP2815083B1 EP 2815083 B1 EP2815083 B1 EP 2815083B1 EP 13704137 A EP13704137 A EP 13704137A EP 2815083 B1 EP2815083 B1 EP 2815083B1
Authority
EP
European Patent Office
Prior art keywords
edge
cooling
corner
component according
component
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
EP13704137.2A
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German (de)
English (en)
Other versions
EP2815083A1 (fr
Inventor
Herbert Brandl
Joerg Krueckels
Felix Reinert
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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Publication of EP2815083A1 publication Critical patent/EP2815083A1/fr
Application granted granted 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
    • 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
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the 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
    • 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
    • F01D5/186—Film 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
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • 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
    • F05D2260/208—Heat transfer, e.g. cooling using heat pipes

Definitions

  • the present invention relates to the field of thermal machines. It relates to a component for a thermal machine, in particular for a gas turbine, according to the preamble of claim 1.
  • thermal machines in particular gas turbines
  • components that on the one hand have design-related corners and edges and on the other hand are exposed at these points during operation of a high thermal load.
  • An example of such a component is a composite of several parts blade of a gas turbine, as shown for example in the pamphlet EP 2 189 626 A1 is disclosed.
  • the Figures 1 and 2 this document are as Fig. 1 reproduced in the present application.
  • a platform member 10 and an airfoil member 20 are assembled into a blade and connected together.
  • the platform element 10 has in the top 11 a passage opening 12 through which the airfoil element 20 can be inserted with the end in a blade tip 18 blade 17.
  • To attach the composite blade serve legs 13, 14 with molded hooks 15, 16 on the underside of the platform element 10 and a blade root 21 on the airfoil element 20, which is connected to the blade 17 via a shaft 19.
  • the inventive component which is provided for a thermal machine, in particular a gas turbine, and has a thermally highly loaded corner or edge, has for cooling the corner or edge in the immediate vicinity of the corner or edge at least one from the surface in the component sinks recessed cooling channel.
  • the corner or edge extends along a predetermined line and the at least one cooling channel extends over a predetermined distance substantially parallel to the corner or edge.
  • the cooling channel has an outlet on the side of the surface to be cooled and an inlet on the opposite side.
  • the at least one cooling channel comprises a cooling tube introduced into a channel.
  • the cooling tube is in each case embedded in a filler filling the channel and thereby thermally coupled to the surrounding material of the component.
  • Another embodiment is characterized in that the channel is closed with the introduced cooling tube to the surface to be cooled.
  • a welded cover layer is provided for closing the channel.
  • a further embodiment of the invention is characterized in that the cooling channel has a distance of its central axis from the surface to be cooled in the range of 1 mm.
  • the cooling channel has an inner diameter in the range of about 1 mm.
  • the component is equipped with a thermal barrier coating. This is especially for highly thermally stressed components, such as those in a gas turbine, in question.
  • the component is designed as a blade of a gas turbine.
  • the blade is composed of separate components, wherein the corner or edge to be cooled is formed at a transition between the separate components.
  • the corner or edge can be bounded on one side by a gap flooded by the hot gas.
  • a technology of the surface near recessed cooling channels for cooling of thermally highly loaded corners or edges of gas turbine components, such as blades, vanes or heat shields used.
  • a configuration according to Fig. 2 There is the problem that the edge 22 is exposed to hot gas from two abutting surfaces ago and thus is particularly highly thermally stressed in the corner region 24.
  • a cooling channel 25 with a small inner diameter running parallel to the edge 22 is provided directly below the surface in order to cool the corner region 24 effectively and with a reduced use of coolant, generally cooling air.
  • the inlet 30 and the outlet 29 of the cooling channel 25 are in Fig. 3 indicated by dashed lines.
  • the cooling channel 25 starts (with the inlet 30) from a plenum filled with cooling air, then runs parallel to the edge 22 to be cooled and then discharges the heated air into the gap 23 via the outlet 29.
  • the outlet 29 can also lead to the surface to discharge the heated air directly into the hot gas stream and to produce on the surface of a cooling air film in the sense of film cooling.
  • Fig. 6 clarifies, where Fig. 6 (A) shows the longitudinal section through an exemplary arrangement, and Fig. 6 (B) the cross-section in the plane BB:
  • a suitable method eg Senkerodieren
  • a suitably shaped tool e.g Senkerodieren
  • a groove 41 in the wall of the component which at one end with a bend 31 a obliquely upwards expires (outlet 29) and at the other end after a bend 31 b has a passage to the bottom (inlet 30).
  • a correspondingly dimensioned and shaped cooling tube 31 is introduced into the channel thus formed and thermally intimately coupled to the surrounding material of the component 26 via a filling material 32 (eg brazing alloy or the like).
  • the arrangement thus formed can then be closed by applying a cover layer 33 by welding. It forms a near-surface cooling channel 27, which is flowed through during operation by the cooling medium 28, for example cooling air.
  • the cooling channel 27 produced in this way has a distance between the central axis surface in the range of 1 mm and an inner diameter in the region of approximately 1 mm. Its length is generally in a range of 10mm to 100mm, preferably 20mm to 40mm. With edge lengths beyond this, a plurality of cooling channels 27 are arranged in succession as shown in FIGS FIGS. 7 and 8 is shown by way of example. Successive cooling channels 27 may differ in length from each other, for example, to take into account different thermal stresses or design constraints. You can be traversed in the interest of optimal cooling effect in the same or in the opposite direction of the cooling medium. The same applies to parallel cooling channels.
  • the at least one cooling channel 37 must be tracked according to the invention of this curved curve.
  • a number of consecutively arranged cooling channels 37 which may also be curved, follows the curve contour.
  • the specific length of the individual channels 37 depends in particular on the thermal load of the platform element 34. It will usually be between 20mm and 40mm.

Landscapes

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

Claims (13)

  1. Composant (10, 20; 26; 34) pour une machine thermique, plus particulièrement une turbine à gaz, ce composant (10, 20 ; 26 ; 34) comprenant un angle ou une arête (22 ; 40a,b) fortement sollicitée thermiquement, moyennant quoi, pour le refroidissement de l'angle ou de l'arête (22 ; 40a,b), à proximité immédiate de l'angle ou de l'arête (22 ; 40a,b), se trouve au moins un canal de refroidissement (25, 25a-d ; 27 ; 37 ; 38 ; 39) encastré à partir de la surface dans le composant (10, 20 ; 26 ; 34), le canal de refroidissement (25, 25a-d ; 27 ; 37 ; 38, 39) comprenant une sortie (29) sur le côté de la surface à refroidir et une entrée (30) sur le côté opposé, l'angle ou l'arête (22 ; 40a,b) s'étendant le long d'une ligne prédéterminée, l'au moins un canal de refroidissement (25, 25a-d ; 27 ; 37 ; 38, 39) s'étendant sur un tronçon prédéterminé globalement parallèle à l'angle ou l'arête (22 ; 40a,b), caractérisé en ce que l'au moins un canal de refroidissement (25, 25a-d ; 27 ; 37 ; 38, 39) comprend un tube de refroidissement (31) encastré dans une rainure (41).
  2. Composant selon la revendication 1, caractérisé en ce que, à proximité immédiate de l'angle ou de l'arête (22 ; 40a,b), sont alignés plusieurs canaux de refroidissement (25, 27, 37, 38, 39).
  3. Composant selon la revendication 1 ou 2, caractérisé en ce que, à proximité immédiate de l'angle ou de l'arête (22, 40a,b) sont disposés plusieurs canaux de refroidissement (25a-d) s'étendant parallèlement et encastrés.
  4. Composant selon la revendication 3, caractérisé en ce que les canaux de refroidissement parallèles (25, 27) sont disposés de manière décalée les uns par rapport aux autres.
  5. Composant selon l'une des revendications 1 à 4, caractérisé en ce que le tube de refroidissement (31) est intégré dans un matériau de remplissage (32) remplissant la rainure (41) et est ainsi couplé thermiquement au matériau environnant du composant (10, 20 ; 26 ; 34).
  6. Composant selon l'une des revendications 1 à 5, caractérisé en ce que la rainure (41) avec le tube de refroidissement (31) encastré est scellée en direction de la surface à refroidir.
  7. Composant selon la revendication 6, caractérisé en ce que, pour le scellement de la rainure (41), une couche de recouvrement (33) soudée est prévue.
  8. Composant selon l'une des revendications 1 à 7, caractérisé en ce que le canal de refroidissement (25, 25a-d ; 27 ; 37 ; 38, 39) présente une distance entre son axe central et la surface à refroidir de l'ordre de 1 mm.
  9. Composant selon l'une des revendications 1 à 8, caractérisé en ce que le canal de refroidissement (25, 25a-d ; 27, 37 ; 38, 39) présente un diamètre intérieur de l'ordre d'environ 1 mm.
  10. Composant selon l'une des revendications 1 à 9, caractérisé en ce qu'une couche d'isolation thermique est appliquée sur la surface du composant.
  11. Composant selon l'une des revendications 1 à 10, caractérisé en ce qu'il est conçu comme une aube (10, 20) d'une turbine à gaz.
  12. Composant selon la revendication 11, caractérisé en ce que l'aube est constituée de composants séparés (10, 20) et l'angle ou l'arête (22, 40a,b) à refroidir est réalisé au niveau d'une transition entre les composants séparés (10, 20).
  13. Composant selon la revendication 12, caractérisé en ce que l'angle ou l'arête (22, 40a,b) est limité sur un côté par un interstice (23) alimenté en gaz chaud.
EP13704137.2A 2012-02-17 2013-02-15 Élément pour une machine thermique, en particulier une turbine à gaz Active EP2815083B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH00210/12A CH706107A1 (de) 2012-02-17 2012-02-17 Bauteil für eine thermische Maschine, insbesondere eine Gasturbine.
PCT/EP2013/053116 WO2013121016A1 (fr) 2012-02-17 2013-02-15 Élément pour une machine thermique, en particulier une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2815083A1 EP2815083A1 (fr) 2014-12-24
EP2815083B1 true EP2815083B1 (fr) 2017-06-28

Family

ID=47714135

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13704137.2A Active EP2815083B1 (fr) 2012-02-17 2013-02-15 Élément pour une machine thermique, en particulier une turbine à gaz

Country Status (6)

Country Link
US (1) US9777577B2 (fr)
EP (1) EP2815083B1 (fr)
JP (1) JP2015508141A (fr)
CN (1) CN104114818B (fr)
CH (1) CH706107A1 (fr)
WO (1) WO2013121016A1 (fr)

Families Citing this family (13)

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Publication number Priority date Publication date Assignee Title
EP3034799B1 (fr) 2014-12-19 2018-02-07 Ansaldo Energia IP UK Limited Élément d'aubage pour une machine d'écoulement de fluide
JP6677969B2 (ja) * 2015-01-27 2020-04-08 三菱重工業株式会社 タービン翼及びタービン並びにタービン翼の製造方法
US10443395B2 (en) * 2016-03-18 2019-10-15 General Electric Company Component for a turbine engine with a film hole
US20180161859A1 (en) * 2016-12-13 2018-06-14 General Electric Company Integrated casting core-shell structure for making cast component with non-linear holes
US11391161B2 (en) 2018-07-19 2022-07-19 General Electric Company Component for a turbine engine with a cooling hole
US11499433B2 (en) 2018-12-18 2022-11-15 General Electric Company Turbine engine component and method of cooling
US10767492B2 (en) 2018-12-18 2020-09-08 General Electric Company Turbine engine airfoil
US11174736B2 (en) 2018-12-18 2021-11-16 General Electric Company Method of forming an additively manufactured component
US11566527B2 (en) 2018-12-18 2023-01-31 General Electric Company Turbine engine airfoil and method of cooling
US11352889B2 (en) 2018-12-18 2022-06-07 General Electric Company Airfoil tip rail and method of cooling
US10844728B2 (en) 2019-04-17 2020-11-24 General Electric Company Turbine engine airfoil with a trailing edge
US11359494B2 (en) * 2019-08-06 2022-06-14 General Electric Company Engine component with cooling hole
US11952918B2 (en) * 2022-07-20 2024-04-09 Ge Infrastructure Technology Llc Cooling circuit for a stator vane braze joint

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EP1905950A1 (fr) * 2006-09-21 2008-04-02 Siemens Aktiengesellschaft Aube de turbine
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Also Published As

Publication number Publication date
US9777577B2 (en) 2017-10-03
CN104114818A (zh) 2014-10-22
WO2013121016A1 (fr) 2013-08-22
JP2015508141A (ja) 2015-03-16
CN104114818B (zh) 2017-06-23
US20140334914A1 (en) 2014-11-13
CH706107A1 (de) 2013-08-30
EP2815083A1 (fr) 2014-12-24

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