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WO2016062581A1 - 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

Info

Publication number
WO2016062581A1
WO2016062581A1 PCT/EP2015/073661 EP2015073661W WO2016062581A1 WO 2016062581 A1 WO2016062581 A1 WO 2016062581A1 EP 2015073661 W EP2015073661 W EP 2015073661W WO 2016062581 A1 WO2016062581 A1 WO 2016062581A1
Authority
WO
WIPO (PCT)
Prior art keywords
heat shield
shield element
wall
cooling air
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.)
Ceased
Application number
PCT/EP2015/073661
Other languages
German (de)
English (en)
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to CN201580056784.2A priority Critical patent/CN107076414B/zh
Priority to EP15778966.0A priority patent/EP3183497B1/fr
Publication of WO2016062581A1 publication Critical patent/WO2016062581A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

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.
  • Impact cooling of the wall to be cooled but this is not an optimum with regard to the cooling air consumption nor to the achievable effect. Impact cooling essentially acts locally and the cooling of the hot gas acted parts takes place only on the back.
  • WO 2006/064038 proposes the AI before a heat shield element, which includes within its wall cooling air channels on ⁇ . This allows a nearly optimal cooling of the heat shield element with low cooling air consumption. The cooling takes place in the cooling channels and causes a Tempe ⁇ raturverring réelle in the wall of the heat shield element to be cooled itself.
  • the edge region of the heat shield element can be insufficiently cooled by the inner cooling air ducts.
  • the object of the invention is to provide a heat shield element of the type mentioned that allows the same to minimize the consumption of cooling air in an advantageous cooling and at the same time as simple and kos ⁇ -effectively to manufacture and to assemble. Furthermore, it is an object of the invention to provide a method for
  • 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 differs from the
  • Hot side over which extends beyond the plane of the cold side.
  • 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.
  • cooling air inlets are arranged in the cooling air ducts, where ⁇ be arranged at cooling air outlets from the cooling air ducts in the region of the edge.
  • ERS te cooling air outlets on the outside of the rim angeord ⁇ net, so that there is an exit of the cooling air into 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 at the edge in the gap between two heat shield elements in the combustion chamber and blocks advantageous against the gap Induction 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 outlet 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 homogeneously at a constant temperature, since a protective de boundary layer between the hot combustion chamber gases and the heat shield element is formed.
  • cooling air inlets are provided on an outer side of the fastening device.
  • the fastening device is arranged centrally on the wall of the heat shield element ⁇ and is therefore the ideal place for the supply of cooling air into the cooling air ducts.
  • 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 its mountings ⁇ constriction device. This allows additional film cooling of the heat shield element in the region of the fastening, so that a protective boundary layer is formed between the hot combustion chamber gases and the fastening means.
  • the second cooling air outlets and / or the fourth cooling air outlets are supplied by the cooling air ducts leading to the edge or if further cooling air ducts lead from the fastening device to the second and / or fourth cooling air outlets. It is advantageous if the through-opening its mountings ⁇ constriction device has a bearing surface for a screw head, so that the screw is sunk ⁇ zeschildelement in the installed state in the hit, so that it is not subjected to exponier ⁇ th position with hot gas.
  • the heat shield member is substantially metal ⁇ lisch, ie it consists essentially of a metal or a metal alloy, such as high temperature resistant alloy coins ⁇ stanchions on iron, chromium, nickel or cobalt base. Compared to ceramics metals have a lower brittleness ⁇ as a more favorable thermal and thermal conductivity.
  • the heat shield element is used as protection and for cooling a hot gas leading combustion chamber, preferably an annular combustor of a gas turbine comprising a support structure attached to the heat shield elements are such ⁇ introduced.
  • the heat shield element is preferably provided with a loading attachment means, such as a screw, arranged on the supporting structure ⁇ .
  • a loading attachment means such as a screw
  • a metallic material with a suitable local distribution in powder form is remelted in layers on a substrate by means of laser radiation, so that in solidification of the molten powder in each case forms a further solid layer.
  • a three-dimensional CAD model is created in a first step, which is decomposed into a two- ⁇ th step in layers.
  • the actual manufacturing of the heat shield element is in the following Schrit ⁇ th, whereby a layer of powder is applied to a Un ⁇ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step.
  • Schrit ⁇ th whereby a layer of powder is applied to a Un ⁇ terlage in the third step, the fourth step, the applied powder is irradiated by a laser or remelted and in the fifth step, the base to the layer thickness is lowered from the second step.
  • 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 quickly to the needs reacts ⁇ the so system downtimes are reduced servicing.
  • FIG. 1 shows a half section through a gas turbine with combustion chambers
  • FIG. 2 shows a heat shield element according to the prior art
  • Figure 3 shows an embodiment of an inventive
  • Figure 4 shows an embodiment with an extension of
  • FIG. 3 shows an embodiment of an inventive
  • Figure 7 shows a section of the combustion chamber with film-cooled
  • FIG. 1 shows a gas turbine 21, which is shown partly in longitudinal section.
  • 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 generator not shown in FIG.
  • the combustion chamber wall is lined with heat shield elements 1, or the heat shield elements 1 are attached to 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 combustion chamber 20 the greater part of the air from the compressor is combined with the liquid or gaseous fuel and burnt. This creates a hot gas that drives the gas turbine 21.
  • a relaxation and Ab ⁇ cooling of the hot gas In the turbine, a relaxation and Ab ⁇ cooling of the hot gas.
  • FIG. 2 schematically shows a heat shield element 30 according to the prior art.
  • the heat shield element 30 has a wall 2, which 2 has a hot side 3 (in FIG. 2 on the opposite side) which can be acted upon by a hot medium and a cold side 4 opposite the hot side 3, as well as an encircling wall bordering the wall 2, extending over the wall Furthermore, an attachment device 8, which extends substantially perpendicularly away from the wall 2, is arranged substantially in the middle of the cold side 4 of the wall 2, at the level of the cold side 4.
  • the heat shield element 30 is fixed by the fixing device 8 through a screw or bolt to the support structure 22nd
  • FIG. 3 a first exemplary embodiment of a heat shield element 1 according to the first embodiment of the invention is schematically shown, are arranged in the wall 2 to the edge 5 cooling channels 9 in which, starting from its mountings ⁇ constriction device. 8
  • cooling air entries 10 on one
  • FIG. 5 shows dung an exemplary embodiment of a heat shield element 1 according to the second embodiment of the inventions, 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 Hitzeschildele ⁇ ment 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 exemplary embodiment of a heat shield element 1 according to the invention. This is initially designed analogously to the example from FIG. 3 and has a cooling air channel 9 extending from the fastening device 8 via the wall 2 to the edge 5. For this purpose, within the heat shield element in alternation with the
  • Cooling air ducts 9 further cooling air ducts 29 are arranged, wel ⁇ che also extending starting from the outside of the fastening ⁇ generating device 8 to the wall 2 extend. There, 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.
  • Figures 2 to 6 show the attachment device 8, 8 extends from the wall 2 of the heat shielding member 1 via the cold side 4 addition, and has a substantially perpendicular ⁇ rights oriented to the wall 2 through opening 16, which is adapted 16 to 16 a fastener 17 can accommodate. Furthermore, in FIGS. 3 to 6, it can be seen that bar, that 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, can be seen

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un élément formant bouclier thermique (1) qui comprend une paroi (2), pourvue d'un côté chaud (3) et d'un côté froid (4) opposé, et un bord périphérique (5) pourvu d'un côté intérieur (6) et d'un côté extérieur (7), et un dispositif de fixation (8) disposé sensiblement au milieu du côté froid (4) de la paroi (2) et qui s'étend sensiblement perpendiculairement depuis la paroi (2) ; dans le dispositif de fixation (8), la paroi (2) et le bord (5) sont ménagés des conduits de refroidissement (9) qui s'étendent sur au moins deux des trois. L'invention concerne en outre une chambre de brûleur (20) et une installation de turbine à gaz (24). En outre, l'invention concerne un procédé de fabrication d'un tel élément formant bouclier thermique (1).
PCT/EP2015/073661 2014-10-20 2015-10-13 Élément formant bouclier thermique et procédé de fabrication de celui-ci Ceased WO2016062581A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
CN201580056784.2A CN107076414B (zh) 2014-10-20 2015-10-13 热屏蔽元件和用于其制造的方法
EP15778966.0A EP3183497B1 (fr) 2014-10-20 2015-10-13 Élément formant bouclier thermique et procédé de fabrication de celui-ci

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014221225.1 2014-10-20
DE102014221225.1A DE102014221225A1 (de) 2014-10-20 2014-10-20 Hitzeschildelement und Verfahren zu seiner Herstellung

Publications (1)

Publication Number Publication Date
WO2016062581A1 true WO2016062581A1 (fr) 2016-04-28

Family

ID=54293259

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2015/073661 Ceased WO2016062581A1 (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)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
EP3614051A1 (fr) * 2018-08-23 2020-02-26 Rolls-Royce plc Chambre de combustion, tuile de chambre de combustion et procédé de fabrication d'une tuile de chambre de combustion
US20230076312A1 (en) * 2018-02-22 2023-03-09 Raytheon Technologies Corporation Multi-direction hole for rail effusion

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US10663168B2 (en) 2017-08-02 2020-05-26 Raytheon Technologies Corporation End rail mate-face low pressure vortex minimization
US11248791B2 (en) 2018-02-06 2022-02-15 Raytheon Technologies Corporation Pull-plane effusion combustor panel
US11009230B2 (en) 2018-02-06 2021-05-18 Raytheon Technologies Corporation Undercut combustor panel rail
US10830435B2 (en) 2018-02-06 2020-11-10 Raytheon Technologies Corporation Diffusing hole for rail effusion
DE102018116682A1 (de) * 2018-07-10 2020-01-16 Elringklinger Ag Wärmeabschirmvorrichtung, insbesondere an lokal unterschiedlich auftretende Wärmeeinträge pro Fläche anpassbare Wärmeabschirmvorrichtung
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
EP4372281B1 (fr) * 2022-11-18 2025-12-31 ANSALDO ENERGIA S.p.A. Chambre de combustion pour un ensemble turbine à gaz de centrale électrique comprenant une pluralité de tuiles métalliques de protection thermique présentant une caractéristique de refroidissement par air améliorée

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WO2005049312A1 (fr) * 2003-11-14 2005-06-02 Siemens Aktiengesellschaft Systeme stratifie haute temperature de dissipation thermique et procede de production de ce systeme
EP1672281A1 (fr) * 2004-12-16 2006-06-21 Siemens Aktiengesellschaft Elément de protection thermique
DE102005046731A1 (de) * 2005-04-19 2006-11-02 Siemens Ag Hitzeschildanordnung
EP2549063A1 (fr) * 2011-07-21 2013-01-23 Siemens Aktiengesellschaft Élément d'écran thermique pour une turbine à gaz
WO2014137428A1 (fr) * 2013-03-05 2014-09-12 Rolls-Royce Corporation Tuile de chambre de combustion à effusion, convexion, impact à double paroi

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EP1284390A1 (fr) * 2001-06-27 2003-02-19 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz
ES2307834T3 (es) * 2003-01-29 2008-12-01 Siemens Aktiengesellschaft Camara de combustion.
EP1507116A1 (fr) * 2003-08-13 2005-02-16 Siemens Aktiengesellschaft Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
ATE530505T1 (de) * 2007-05-07 2011-11-15 Siemens Ag Keramisches pulver, keramische schicht sowie schichtsystem aus zwei pyrochlorphasen und oxiden
GB0913580D0 (en) * 2009-08-05 2009-09-16 Rolls Royce Plc Combustor tile
EP2423596A1 (fr) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Elément de bouclier thermique
EP2487006A1 (fr) * 2011-02-14 2012-08-15 Siemens Aktiengesellschaft Traitement au laser multiple sous des angles différents
DE102012204103A1 (de) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Hitzeschildelement für einen Verdichterluftbypass um die Brennkammer
GB201303057D0 (en) * 2013-02-21 2013-04-03 Rolls Royce Plc A combustion chamber

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Publication number Priority date Publication date Assignee Title
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
WO2005049312A1 (fr) * 2003-11-14 2005-06-02 Siemens Aktiengesellschaft Systeme stratifie haute temperature de dissipation thermique et procede de production de ce systeme
EP1672281A1 (fr) * 2004-12-16 2006-06-21 Siemens Aktiengesellschaft Elément de protection thermique
DE102005046731A1 (de) * 2005-04-19 2006-11-02 Siemens Ag Hitzeschildanordnung
EP2549063A1 (fr) * 2011-07-21 2013-01-23 Siemens Aktiengesellschaft Élément d'écran thermique pour une turbine à gaz
WO2014137428A1 (fr) * 2013-03-05 2014-09-12 Rolls-Royce Corporation Tuile de chambre de combustion à effusion, convexion, impact à double paroi

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016224632A1 (de) * 2016-12-09 2018-06-14 Rolls-Royce Deutschland Ltd & Co Kg Plattenförmiges Bauteil einer Gasturbine sowie Verfahren zu dessen Herstellung
US10753612B2 (en) 2016-12-09 2020-08-25 Rolls-Royce Deutschland Ltd & Co Kg Plate-shaped structural component of a gas turbine
US20230076312A1 (en) * 2018-02-22 2023-03-09 Raytheon Technologies Corporation Multi-direction hole for rail effusion
US11725816B2 (en) 2018-02-22 2023-08-15 Raytheon Technologies Corporation Multi-direction hole for rail effusion
EP3614051A1 (fr) * 2018-08-23 2020-02-26 Rolls-Royce plc Chambre de combustion, tuile de chambre de combustion et procédé de fabrication d'une tuile de chambre de combustion

Also Published As

Publication number Publication date
EP3183497A1 (fr) 2017-06-28
DE102014221225A1 (de) 2016-04-21
CN107076414B (zh) 2019-06-14
EP3183497B1 (fr) 2018-07-18
CN107076414A (zh) 2017-08-18

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