EP3183497B1 - Élément formant bouclier thermique et procédé de fabrication de celui-ci - Google Patents

Élément formant bouclier thermique et procédé de fabrication de celui-ci Download PDF

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Publication number
EP3183497B1
EP3183497B1 EP15778966.0A EP15778966A EP3183497B1 EP 3183497 B1 EP3183497 B1 EP 3183497B1 EP 15778966 A EP15778966 A EP 15778966A EP 3183497 B1 EP3183497 B1 EP 3183497B1
Authority
EP
European Patent Office
Prior art keywords
heat shield
shield element
cooling air
wall
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
EP15778966.0A
Other languages
German (de)
English (en)
Other versions
EP3183497A1 (fr
Inventor
Thomas Hauser
Andreas Kreutzer
Patrick Lapp
Sebastian Piegert
Simon Purschke
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP3183497A1 publication Critical patent/EP3183497A1/fr
Application granted granted Critical
Publication of EP3183497B1 publication Critical patent/EP3183497B1/fr
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/005—Combined with pressure or heat exchangers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05004—Special materials for walls or lining
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • the invention relates to a heat shield element, in particular for lining a combustion chamber wall with integrated cooling air ducts according to the preamble of claim 1.
  • the object of the invention is to provide a heat shield element of the type mentioned, which allows the lowest possible consumption of cooling air at an advantageous cooling and the same time as simple and inexpensive to manufacture and assemble.
  • the generic heat shield element is intended for use in a combustion chamber, which is in particular the combustion chamber in a gas turbine.
  • the heat shield element initially comprises a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side.
  • Surrounding the wall is an edge which extends from the hot side to beyond the plane of the cold side.
  • the edge has an inner side adjacent to the cold side and an opposite side to the hot side adjoining outside.
  • a fastening device Arranged substantially in the middle of the wall is a fastening device which extends from the wall away from the hot side and out past the cold side.
  • the fastening device has a passage opening, so that a fastening means can be attached to the fastening device when passed through the passage opening.
  • a plurality of cooling channels are introduced into the heat shield element according to the invention, which pass through the wall of the heat shield element from the fastening device to the edge. It is provided that in the fastening device cooling air inlets are arranged in the cooling air ducts, wherein cooling air outlets are arranged from the cooling air ducts in the region of the edge.
  • first cooling air outlets are arranged on the outside of the edge, so that an outlet of the cooling air takes place in the gap between adjacent heat shield elements.
  • the coolant flows through all parts of the heat shield element in the order fastener, wall, edge and thus cools in all areas before the cooling air is discharged into the gap between two heat shield elements in the combustion chamber at the edge and locks the gap against indentation of Hot gas from the combustion chamber.
  • third cooling air outlets are arranged on the hot side of the wall in the region of the edge, so that an exit of the cooling air takes place immediately adjacent to the gap into the combustion chamber. This allows for additional film cooling of the heat shield element.
  • the hot side of the heat shield element can thus be kept homogeneous at a constant temperature, since a protective Forming boundary layer between the hot combustion chamber gases and the heat shield element.
  • the return of the cooling air flow leads to the underside of the heat shield elements that now the heated air flow is dissipate, which in turn causes a consequential problem towards the cooling air.
  • the arrangement according to the invention of the first and / or third cooling air outlets at the edge of the heat shield element with an outflow of the heated cooling air into the gap and / or into the combustion chamber removes the heat from the heat shield element, without the heat transferring the interior, i. the cold side, reaches the heat shield element. With the same amount of air so a further reduction of the temperature in the interior of the heat shield element is reached (or the same temperature with less cooling air). A reduction in temperature has a positive effect on other components of the heat shield element, which are less thermally stressed.
  • cooling air inlets are provided on an outer side of the fastening device.
  • the fastening device is centrally located on the wall of the heat shield element and is therefore the ideal location for feeding the cooling air into the cooling air channels.
  • second cooling air outlets are provided on the inside of the fastening device.
  • the cooling function can be extended to the fastening means of the heat shield element.
  • internally cooled mounting screws are used for the attachment of heat shield elements.
  • fourth cooling air outlets are provided on the hot side in the region of the fastening device. This allows additional film cooling of the heat shield element in the region of the attachment, so that a protective boundary layer is formed between the hot combustion chamber gases and the attachment means.
  • the passage opening of the fastening device has a contact surface for a screw head, so that the screw is sunk in the installed state in the heat shield element, so that it is not acted upon at exposed point with hot gas.
  • the heat shield element is substantially metallic, i. it consists essentially of a metal or a metal alloy, e.g. High temperature resistant alloys based on iron, chromium, nickel or cobalt. Compared to ceramics metals have a lower brittleness and a more favorable thermal and thermal conductivity.
  • the heat shield element is used to protect and cool a hot gas carrying combustor, preferably an annular combustor of a gas turbine having a support structure to which such heat shield elements are attached.
  • the heat shield element is preferably arranged with a fastening means, for example a screw, on the support structure.
  • a heat shield element having a wall which has a hot side which can be acted upon by a hot medium and a cold side which is opposite to the hot side, and an edge which adjoins the wall and extends beyond the plane of the cold side with an inner edge. and an outer side and a fastening device arranged substantially in the middle of the cold side of the wall, which extends substantially perpendicularly away from the wall, with cooling channels being arranged in the fastening device, wall and edge, which extend over at least two of the three a metallic material having a suitable local distribution in powder form is remelted in layers on a substrate by means of laser radiation, so that in each case a further solid layer is formed upon solidification of the molten powder.
  • a three-dimensional CAD model is created in a first step, which is divided into layers in a second step.
  • the actual production of the heat shield element is carried out in the following steps, wherein in the third step, a powder layer is applied to a substrate, in the fourth step, the applied powder is exposed or remelted by a laser and in the fifth step, the pad to the layer thickness of the second step is lowered. The third to fifth steps are repeated until the heat shield element is completely made.
  • heat shield elements with comparatively small numbers of pieces are to be produced sensibly using this method. Also, in the case of service can respond quickly to the needs, so that downtime of the equipment can be reduced.
  • the FIG. 1 shows a gas turbine 21, the 21 is shown partially cut longitudinally.
  • the gas turbine 21 has a compressor, an annular combustion chamber (20) with a plurality of burners for a liquid or gaseous fuel, a turbine for driving the compressor and a in FIG. 1 Not shown generator.
  • the combustion chamber wall is lined with heat shield elements 1, or the heat shield elements 1 are mounted on a support structure 22 on the combustion chamber wall.
  • air is sucked in from the environment.
  • the compressor the air compressed and thereby partially heated.
  • a small portion of the air is removed from the compressor and supplied as a coolant to the heat shield elements 1, the greater part of the air is supplied to the burners for combustion.
  • the combustor 20 the greater part of the air from the compressor is contacted with the liquid or gaseous fuel and burned. This creates a hot gas that drives the gas turbine 21.
  • a relaxation and cooling of the hot gas takes place.
  • the heat shield element 30 has a wall 2, which 2 has a hot side 3 (in FIG FIG. 2 on the opposite side) and one of the hot side 3 opposite cold side 4, and one adjacent to the wall 2, circumferential, extending beyond the plane of the cold side 4 also out edge 5 with an inner 6 and an outer side 7. Furthermore, is substantially in the middle of the cold side 4 of the wall 2, a fastening device 8 is arranged, which 8 extends substantially perpendicularly away from the wall 2.
  • the heat shield member 30 is fixed to the support structure 22 by the fastener 8 with a screw or a bolt.
  • FIG. 3 is schematically shown a first embodiment of a heat shield element 1 according to the first embodiment of the invention, in which, starting from the fastening device 8 in the wall 2 to the edge 5 cooling channels 9 are arranged.
  • cooling air inlets 10 are provided on an outer side 11 of the fastening device 8 and corresponding first cooling air outlets 12 on the outer side 7 of the edge 5.
  • FIG. 4 is an embodiment of the heat shield element 1 from Fig.1 1, which further comprises second cooling air outlets 13.
  • the second cooling air outlets 13 are provided in this example on the inside 14 of the fastening device 8.
  • a more complex, internally cooled fastening screw can be replaced by a simple screw for fastening the heat shield element 1 to the support structure 22.
  • FIG. 5 shows an embodiment of a heat shield element 1 according to the second embodiment of the invention, after which third cooling air outlets 15 are provided on the hot side 3 in the region of the edge 5.
  • the hot side of the heat shield element 1 is kept homogeneous at a constant temperature.
  • a protective boundary layer forms between the hot combustion chamber gases and the heat shield element 1.
  • the arrangement of the third cooling air openings 15 in the region of the edge 5 also protects the gap between adjacent heat shield elements 1 before a hot gas intake.
  • FIG. 6 shows a further embodiment of an inventive heat shield element 1.
  • This is initially analogous to the example Fig. 3 has executed and has a extending from the fastening device 8 on the wall 2 to the edge 5 cooling air channel 9.
  • 9 further cooling air channels 29 are arranged within the heat shield element in alternation with the cooling air ducts, which also extend starting from the outside of the fastening device 8 to the wall 2.
  • the further cooling air channels 29 open into fourth cooling air outlets 25, which are arranged near the fastening device 8 on the hot side 3 of the wall 2.
  • FIGS. 2 to 6 Figure 8 shows the fastening device 8 which extends from the wall 2 of the heat shield element 1 beyond the cold side 4 and has a through opening 16 oriented substantially perpendicular to the wall 2, which is designed to receive a fastening means 17. Furthermore, in the FIGS. 3 to 6 recognizable the passage opening 16 has a contact surface 18 for a screw head 19.
  • FIG. 7 shows a section of a combustion chamber with heat shield elements 1 according to the invention.
  • the hot side 3 with the third cooling air outlets 15 for film cooling and the fastening of the heat shield elements 1 by fastening means 17, for example screws, can be seen.

Claims (9)

  1. Elément (1) de bouclier thermique, notamment pour revêtir une paroi de chambre de combustion, comprenant une paroi (2), qui a un côté (3) chaud pouvant être soumis à un fluide chaud et un côté (4) froid opposé, et comprenant un bord (5), qui s'étend, en faisant le tour, du côté (03) chaud au-delà du côté (4) froid et qui (5) a une face (6) intérieure, voisine du côté (04) froid, et une face (7) extérieure, voisine du côté (03) chaud, et comprenant un dispositif (8) de fixation, qui est disposé sensiblement au milieu de la paroi (2), qui s'étend de la paroi (2) au-delà du côté (4) froid, et qui a une ouverture (16) traversante de réception d'un moyen (17) de fixation,
    dans lequel une pluralité de conduits (9) de refroidissement s'étendent du dispositif (8) de fixation jusqu'au bord (5) en traversant la paroi (2), caractérisé en ce que de premières sorties (12) pour de l'air de refroidissement des conduits (9) de refroidissement sont prévues, sur la face (7) extérieure du bord (5) et/ou des troisièmes sorties (15) d'air de refroidissement sont prévues du côté (3) chaud du bord (5).
  2. Elément (1) de bouclier thermique suivant la revendication 1,
    caractérisé
    en ce que les entrées (10) d'air de refroidissement sont prévues sur une face (11) extérieure du dispositif (8) de fixation.
  3. Elément (1) de bouclier thermique suivant la revendication 1 ou 2,
    caractérisé
    en ce que les deuxièmes sorties (13) d'air de refroidissement sont prévues sur une face (14) intérieure du dispositif (8) de fixation.
  4. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 3,
    caractérisé
    en ce que des quatrièmes sorties (25) d'air de refroidissement sont prévues du côté (3) chaud dans la région du dispositif (8) de fixation au milieu.
  5. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 4,
    caractérisé
    en ce que l'ouverture (16) traversante a une surface (18) d'application d'une tête (19) de vis.
  6. Elément (1) de bouclier thermique suivant l'une des revendications 1 à 5,
    caractérisé
    en ce que l'élément (1) de bouclier thermique est essentiellement métallique.
  7. Chambre de combustion (20) d'une turbine (21) à gaz, ayant une structure (22) porteuse et plusieurs éléments (1) de bouclier thermique suivant l'une des revendications précédentes, qui y sont mis.
  8. Turbine (21) à gaz ayant une chambre de combustion (20) suivant la revendication 7.
  9. Procédé de fabrication d'un élément (1) de bouclier thermique suivant l'une des revendications précédentes, caractérisé
    en ce que faire refondre, au moyen d'un faisceau laser, un matériau métallique ayant des couches sous forme de poudre sur un support, de manière à constituer, à la solidification de la poudre fondue, respectivement une autre couche solide.
EP15778966.0A 2014-10-20 2015-10-13 Élément formant bouclier thermique et procédé de fabrication de celui-ci Active EP3183497B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014221225.1A DE102014221225A1 (de) 2014-10-20 2014-10-20 Hitzeschildelement und Verfahren zu seiner Herstellung
PCT/EP2015/073661 WO2016062581A1 (fr) 2014-10-20 2015-10-13 Élément formant bouclier thermique et procédé de fabrication de celui-ci

Publications (2)

Publication Number Publication Date
EP3183497A1 EP3183497A1 (fr) 2017-06-28
EP3183497B1 true EP3183497B1 (fr) 2018-07-18

Family

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Application Number Title Priority Date Filing Date
EP15778966.0A Active EP3183497B1 (fr) 2014-10-20 2015-10-13 Élément formant bouclier thermique et procédé de fabrication de celui-ci

Country Status (4)

Country Link
EP (1) EP3183497B1 (fr)
CN (1) CN107076414B (fr)
DE (1) DE102014221225A1 (fr)
WO (1) WO2016062581A1 (fr)

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DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
US10663168B2 (en) * 2017-08-02 2020-05-26 Raytheon Technologies Corporation End rail mate-face low pressure vortex minimization
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
US11022307B2 (en) 2018-02-22 2021-06-01 Raytheon Technology Corporation Gas turbine combustor heat shield panel having multi-direction hole for rail effusion cooling
DE102018116682A1 (de) * 2018-07-10 2020-01-16 Elringklinger Ag Wärmeabschirmvorrichtung, insbesondere an lokal unterschiedlich auftretende Wärmeeinträge pro Fläche anpassbare Wärmeabschirmvorrichtung
GB201813753D0 (en) * 2018-08-23 2018-10-10 Rolls Royce Plc A combustion chamber, a combustion chamber tile and a method of manufacturing a combustion chamber tile
DE102019212039A1 (de) * 2019-08-12 2021-02-18 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerbaugruppe mit segmentierter Wandstruktur und Entlastungskanal im Bereich eines Segmentierungsschlitzes sowie Herstellungsverfahren
WO2021121862A1 (fr) * 2019-12-17 2021-06-24 Siemens Energy Global GmbH & Co. KG Carreau de protection thermique pour une chambre de combustion, et chambre de combustion
SE544235C2 (en) * 2020-07-09 2022-03-08 Valmet Oy Cooling shield for a liquor injection pipe, a liquor gun system and a method for cooling a liquor injection pipe
CN112923398B (zh) * 2021-03-04 2022-07-22 西北工业大学 一种加力燃烧室防振隔热屏

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Also Published As

Publication number Publication date
DE102014221225A1 (de) 2016-04-21
WO2016062581A1 (fr) 2016-04-28
CN107076414A (zh) 2017-08-18
EP3183497A1 (fr) 2017-06-28
CN107076414B (zh) 2019-06-14

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