EP1533574A1 - Chambre de combustion pour turbine à gaz avec des éléments de revêtement et procédé pour appliquer ou enlever ces éléments - Google Patents

Chambre de combustion pour turbine à gaz avec des éléments de revêtement et procédé pour appliquer ou enlever ces éléments Download PDF

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Publication number
EP1533574A1
EP1533574A1 EP03026911A EP03026911A EP1533574A1 EP 1533574 A1 EP1533574 A1 EP 1533574A1 EP 03026911 A EP03026911 A EP 03026911A EP 03026911 A EP03026911 A EP 03026911A EP 1533574 A1 EP1533574 A1 EP 1533574A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
cladding element
housing part
attachment
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.)
Withdrawn
Application number
EP03026911A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
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
Priority to EP03026911A priority Critical patent/EP1533574A1/fr
Publication of EP1533574A1 publication Critical patent/EP1533574A1/fr
Withdrawn legal-status Critical Current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
    • F23M5/04—Supports for linings
    • 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
    • F23R3/42—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
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components

Definitions

  • the invention relates to a gas turbine and a gas turbine combustor with a housing part and a cladding element, the means of a releasable attachment to the one Combustion chamber facing inside of the housing part attached is.
  • the invention also relates to a cladding element for a gas turbine combustion chamber and a clamping element for a Attachment combination for holding a trim element in a gas turbine combustor.
  • the invention leads to a method of attachment and / or removal a cladding element of a gas turbine combustor, with a housing part, wherein the cladding element by means of a releasable attachment to a combustion chamber facing Inside the housing part is releasably attached.
  • the combustion chamber of a gas turbine combustion chamber of a gas turbine is usually provided with a lining, which the Housing parts of the gas turbine before the prevailing in the combustion chamber Combustion chamber conditions d. H. especially high temperatures and pressures and the oxidizing effects of the hot gas, protects and isolates.
  • the area of the Housing having the attachment, in particular the attachment self, protect.
  • the panel protects the housing parts before a progressively with time Material fatigue, the higher, the more common and greater temperature and pressure fluctuations in the combustion chamber are. This problem of material loading is also with the Term "Low Cycle Fatigue" (LCF problem) named.
  • a cladding element with a on the combustion chamber side attached to the housing part claw i. one one-sided hook, to hold, with at the claw one Screw is provided, with which a first cladding element be screwed from the gas turbine combustor forth can.
  • This second type of attachment of a trim element Although the interchangeability of a cladding element allows from the side of the gas turbine combustor, since the Screw in the combustion chamber side claw from the combustion chamber ago accessible, but this second type of attachment, especially the screw, directly the combustion chamber conditions the combustion chamber exposed, in particular the high temperatures and temperature fluctuations in the gas turbine combustor.
  • Object of the present invention is therefore a gas turbine and a gas turbine combustor, a trim element and an attachment for a cladding element as well a method for attaching and / or removing a cladding element indicate a gas turbine combustor, the interchangeability of the cladding element from the combustion chamber a gas turbine combustor ago and LCF problems with regard to the mounting area keeps as low as possible.
  • the cladding element in the attached Condition facing away from the combustion chamber rear side the one Distance from the combustion chamber facing the inside of the Housing part has. That in the attached state of a Cladding element is between the panel and the housing part practically formed a cavity system for a Air cooling of the panel and the housing can be used can. Such cooling leads to a leveling of the otherwise sometimes strongly fluctuating combustion chamber conditions towards the cavity system and thus to a large extent Avoidance of strong fluctuations in temperature-pressure and other environmental conditions for those in the cavity system arranged fasteners of the cladding elements.
  • a cladding element in a gas turbine combustor above type be replaced by over any opening in the trim element on the behind the Rear of the cladding element on the inside of the housing part attached fortification is accessed.
  • the cladding element is aligned with the attachment openable and closable opening, in particular in the combustion chamber side wall of the cladding element, on.
  • the said opening could be through a plug, in particular be closed by a screw-in stopper. When opened, the opening is from the combustion chamber forth, over the distance between the cladding element and the housing part away, a direct way to fortification free, so that the attachment from the combustion chamber loosened or attached can be.
  • the cladding element have an arbitrarily profiled shape, as long as the back of the trim element of the spaced from the combustion chamber inside of the housing part is and a stop behind the back of the trim element is formed.
  • the attack could also be direct be attached to the back. In any case, it's up This way a mounting area, ie in particular the Fixing itself and the stop, before the combustion chamber conditions and therefore also against early material fatigue protected.
  • the stop in Shape of an undercut is formed.
  • the basis forms a combustion chamber side wall, the legs side walls.
  • This form of cladding element allows cladding elements to a complete panel of the gas turbine combustor to put together.
  • the attacks are adjacent lying lining elements on each other. That's it Housing part by the insulating effect of over the distance behind the back of the housing part formed cavity protected against the combustion chamber conditions.
  • a stop can, in principle, via any attachment be held on a housing part.
  • the fastening combination has a releasable from the combustion chamber fastener and a clamping element.
  • the fastener engages from the side of the combustion chamber in the housing part. On In this way, a clamping force is exerted on the clamping element.
  • This clamping force is the cladding element by the clamping element, in particular to a stop of the cladding element, transfer.
  • the fastener could be formed for example in the form of a screw and the Clamping element in the form of a clamping ring.
  • the attachment combination by a separate from the cladding element fastener and clamping element is formed.
  • Particularly advantageous insulation protects the entire Fastening area, in particular the attachment itself and the stop.
  • An insulation according to this development is already given by having a number of cladding elements for forming a lining of the gas turbine combustor be arranged side by side. It is about the Distance between the rear side facing away from the combustion chamber and the combustion chamber facing the inside of the housing part from the combustion chamber isolated cavity formed by the aggressive Combustor conditions is isolated, preferably can be cooled in addition, and thus particularly favorable Conditions for the mounting area arranged in the cavity creates. That the attachment area, in particular the attachment and the stop, is of the aggressive ones Combustion chamber conditions separated and isolated, anyway not directly exposed to the combustion chamber conditions. A further improvement of the above insulation against the combustion chamber conditions can be achieved in particular by that a seal between adjacent parts of adjacent Cladding elements, in particular in the field of Leg or stops, is provided.
  • the above-mentioned clamping element is annular, with the first nose from an upper side of the cover of the clamping element over an annular circumference of the Clamping elements radially extends, so that a lower Side of the first nose rests against an upper side of the stop.
  • a middle ring opening of the clamping element a fastener, such as a screw record.
  • An internal, circumferential balcony is advantageous provided as a stop for the fastener, for example, the screw head, serves.
  • a ring-shaped clamping element is advantageous a corresponding recess, in this case a circular Recess, provided on the inside of the housing part.
  • this is Clamping element formed rotatable, wherein a second Nose from a lower cover side of the clamping element over the extends radially outward annular circumference of the clamping element, so that one side of the second nose is a Vermosbegrenzung causes, i. the nose beats with one of their sides when twisting against another component. It has Moreover, proved to be particularly advantageous in the provided here clamping element by arrangement or molding the nose a Vermosbegrenzung exactly to predetermine. The occasional turning away of an annular clamping element The present training can be done this way namely predetermined during installation and removal of a trim element and thus the installation and removal easier become.
  • the present invention particularly relates to a gas turbine with a gas turbine combustion chamber of the above type.
  • the invention leads to a cladding element for a gas turbine combustor, wherein the trim element According to the invention designed as a U-shaped hollow profile Form having a base, wherein the base a has closable opening, and with legs of different Length, wherein at each of the legs a stop is formed in the form of a balcony.
  • the invention also leads to a clamping element for a fastening combination for holding a trim element in a gas turbine combustor, wherein the clamping element according to the invention an annular formation and a first nose which extends from an upper deck side of the clamping element radially over an annular circumference of the clamping element extends out, and has a second nose, the from a lower deck side of the clamping member over a annular extent of the clamping member extends radially outward.
  • the present invention also leads to a method for Attaching and / or removing a cladding element of a Gas turbine combustor of the aforementioned type, according to the invention over a fortified with the attachment too Opening and closing opening when attaching the following Procedural steps are carried out:
  • the cladding element is facing away from the combustion chamber with a Rear side at a distance from the combustion chamber facing Inside the housing part attached.
  • the attachment is behind the back of the cladding element, on the inside of the body, from the combustion chamber releasably secured and holds the cladding element on the housing part.
  • the attachment When removing, the attachment is behind the back of the Cladding element on the inside of the housing part of The combustion chamber is released and the cladding element is removed from the housing part away.
  • a cladding element can therefore be in a particularly simple manner be replaced from the combustion chamber ago.
  • the advantages of a above-mentioned development of the gas turbine combustor for a cladding element or a clamping element are also for the procedure useful.
  • FIG. 1 The sectional drawing of Figure 1 shows a part of a wall a gas turbine combustor 1 with a housing part 3rd in the area of two adjacent cladding elements 5.
  • the cladding element 5 in the form of a heat shield executed.
  • the juxtaposition of a variety Such heat shields form the inner lining of a Combustion chamber 7 surrounding gas turbine combustor 1.
  • In the combustion chamber 7 prevail during operation of the gas turbine usually temperatures in the range of 1350 ° C or above.
  • high temperature fluctuations may occur, e.g. in the Case of a quick closure of the gas turbine. That the combustion chamber filling fuel gas also attacks, u.a. oxidizing, the combustion chamber boundary.
  • FIG. 1 shows two executed as heat shields Fairing elements 5 in the area of your attachment the housing part 3, which also referred to as combustion chamber structure becomes.
  • the cladding element 5 is by means of a detachable Attachment 9 at the combustion chamber 7 facing inside 11 of the housing part 3 attached.
  • the cladding element 5 has a front side 13 facing the combustion chamber 7 and a rear side 15 facing away from the combustion chamber 7.
  • the Front 13 and the back 15 are part of the combustion chamber 7 facing wall 17 of acting as a heat shield Fairing 5.
  • the cladding element 5 is in the present case shaped that the back 15 a distance 19 from the the combustion chamber 7 facing inside 11 of the housing part. 3 Has.
  • the housing part 3 is an inner housing in the present case a gas turbine, that of another, not here surrounded outer housing of the gas turbine is surrounded.
  • the cladding element 5 in the form of a U-shaped hollow profile formed. It forms the Combustion chamber 7 facing wall 17 of the cladding element fifth the base of the U-shaped hollow profile.
  • the legs of the U-shaped Hollow sections are over a first side wall 21 and a second side wall 23 is formed.
  • the first one Side wall 21 has a shorter length than the second side wall 23 of the cladding element 5.
  • a first stop 25 is formed in the form of a balcony.
  • another stop 27 is also formed in the form of a balcony.
  • the two same trained, adjacent cladding elements 5 can so advantageously be arranged side by side so that the first side wall 21 and the second side wall 23 side by side to come to rest.
  • the first stop 25 rests on it the second stop 27.
  • the one between the first side wall 21 and the second side wall 23 formed gap 29th serves in this embodiment to compensate thermal Length changes of a trim element 5.
  • the isolation of the cavity 31 of the determined by the heating gas Combustion chamber conditions of the combustion chamber 7 is present through the juxtaposed first and second Sidewall 21 and 23 reached as well by the successive overlying stops 25 and 27.
  • the insulation is about it out further improved by a between the first stop 25 and the second stop 27 arranged seal 35th
  • the mounting portion 37 in which the Cladding element 5 through the attachment 9 on the housing part 3 is attached, not only from the hot gas side of the combustion chamber 7 advantageously isolated, but also cooled.
  • These measures cause the combustion chamber conditions the combustion chamber 7, in particular the high temperatures and the temperature fluctuations from the mounting area 37 kept away and are leveled in their extent.
  • the Material fatigue in the attachment area 37 due to the low-cycle fatigue (LCF problem) is advantageous in this way reduced.
  • the cladding element 5 but still from Combustion chamber 7 releasably secured to the housing part 3.
  • the cladding element 5 has one with the attachment. 9 aligned opening 39.
  • the orientation is present achieved in that the opening 39 and the attachment. 9 are arranged on an axis 41.
  • the opening 39 is for closed the operating state by a plug 43, the in the present case is designed in the form of an Allen screw. To the Opening the opening 39, the plug 43 is removed, for closing the opening 39, the plug 43 is screwed.
  • the attachment 9 behind the back 15 of the cladding element 5 at the Inside 11 of the housing part 3 from the combustion chamber 7 through which Opening 39 releasably secured, so that as a heat shield acting cladding element 5 held on the housing part 3 is.
  • a gas turbine combustor shown here 1 is the attachment 9 in the form of a fastening combination with a fastener 45, in shape a screw, and a clamping element 47, in the form of a Clamping ring formed.
  • the fastener 45 is through the clamping member 47 through a thread 49 in the housing part 3 screwed and exercises through a clamping element 47 attached first nose 51 a clamping force on the cladding element 5 off.
  • it is the first nose 51 on the first balcony-shaped stop 25, which in turn rests on the second balcony-shaped stop 27.
  • both cladding elements 5 simultaneously held against the inner side 11 of the housing part 3 and further simultaneously via the seal 35 against each other pressed and thus isolate the cavity 31.
  • the adjacent cladding elements 5 relative to each other at a distance from that for thermal expansion provided gap 29 held.
  • the mounted in a recess 53 attachment 9 is in Figure 2 shown in more detail.
  • the recess 53 is more accurate in FIG shown.
  • a three-dimensional view of the Fastener 47 shown in part (b) is a sectional drawing of the fastening element 47.
  • the clamping element 47 is presently designed in the form of a ring and with a Ring opening 61 provided. This ring opening 61 is designed in that it has a fastening element 45 of the fastening 9 can record.
  • the clamping element 47 has a first nose 51, which is from an upper deck side 65 of the clamping member 47 via a indicated in Figure 2, annular circumference 67 of the clamping element 47 extends radially out. As shown in FIG. 1, comes in the installed state, a bottom 69 of the first Nose 51 on an upper side of the stop 25 of a cladding element 5 and transmits a clamping force of Clamping elements 47 on the stop 25, 27 of the adjacent Cladding elements 5.
  • the clamping element 47 is rotatable formed and has a second nose 71, extending from a lower deck side 73 of the clamping member 47 over the extends annular periphery 67 of the clamping member 47 radially out, so that one side 75 of the second nose 71 as a Vermosbegrenzung serves.
  • This has the advantage that despite poor accessibility of the first nose 51 at Ein- and Expansion of a controlled turning back and forth the first Nose 51 is reached, as this is through the second nose 71st is predetermined.
  • the recess 53 on the inside 11 of the housing part. 3 is shown in more detail in FIG.
  • the recess 53 has a milled groove 81 and a drilled recess 83 for receiving of the fastening element 45.
  • the groove 81 forms at one first surface 85 a stop for the bottom 73 of the Clamping elements 47.
  • the opening 83 takes the one shown in FIG Spring 55 on its surface 87 on.
  • the further part 89 of the Recess 83 is provided with a thread 49 shown in FIG provided, in which a correspondingly formed thread 49th the fastener 45 engages.
  • a gas turbine combustion chamber 1 indicated with a housing part 3 and a cladding element 5 been, by means of a releasable attachment 9 at the a combustion chamber 7 facing inside 11 of the housing part 3 is attached.
  • the cladding element 5 in the attached state one from the combustion chamber. 7 remote from the rear side 15, which is a distance 19 from the Has combustion chamber 7 facing inside 11 of the housing part 3.
  • the cladding element 5 is behind the back 15 of the cladding element 5, on the inside 11 of the housing part 3, from the combustion chamber. 7 detachably attached.
  • the detachable from the combustion chamber 7 attached fairing part 5 is in this concept LCF problem with the present gas turbine combustor 1 avoided, since the attachment 9 is isolated from the combustion chamber 7.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03026911A 2003-11-24 2003-11-24 Chambre de combustion pour turbine à gaz avec des éléments de revêtement et procédé pour appliquer ou enlever ces éléments Withdrawn EP1533574A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP03026911A EP1533574A1 (fr) 2003-11-24 2003-11-24 Chambre de combustion pour turbine à gaz avec des éléments de revêtement et procédé pour appliquer ou enlever ces éléments

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03026911A EP1533574A1 (fr) 2003-11-24 2003-11-24 Chambre de combustion pour turbine à gaz avec des éléments de revêtement et procédé pour appliquer ou enlever ces éléments

Publications (1)

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EP1533574A1 true EP1533574A1 (fr) 2005-05-25

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EP03026911A Withdrawn EP1533574A1 (fr) 2003-11-24 2003-11-24 Chambre de combustion pour turbine à gaz avec des éléments de revêtement et procédé pour appliquer ou enlever ces éléments

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1862740A1 (fr) * 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Paroi de chambre de combustion
EP2230454A1 (fr) * 2009-03-18 2010-09-22 Siemens Aktiengesellschaft Dispositif destiné au montage d'un élément de bouclier thermique
EP2261564A1 (fr) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Agencement d'élément d'un bouclier thermique doté d'un moyen de guidance de vis et procédé de montage d'un élément d'un bouclier thermique
WO2014173568A1 (fr) * 2013-04-22 2014-10-30 Siemens Aktiengesellschaft Brique d'écran thermique pour un écran thermique d'une chambre de combustion
EP3309456A1 (fr) * 2016-10-13 2018-04-18 Siemens Aktiengesellschaft Écran thermique avec carreau et support
RU2708760C1 (ru) * 2016-06-28 2019-12-11 Сименс Акциенгезелльшафт Конструкция теплозащитного экрана камеры сгорания с пакетом тарельчатых пружин
EP3540314A4 (fr) * 2016-11-11 2020-06-03 Kawasaki Jukogyo Kabushiki Kaisha Chemise de chambre de combustion
CN113825950A (zh) * 2019-04-04 2021-12-21 安曼瑞士股份公司 用于沥青生产设备的热气发生器的具有空气导板的燃烧室和用于固定空气导板的方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
DE4314160A1 (de) * 1992-05-13 1993-11-18 Siemens Ag Fügeverbindung und Verfahren zu ihrer Herstellung
DE4309200A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Vorrichtung zur Einhängung und Entfernung thermisch hoch belasteter Teile in Turbinenanlagen
GB2298267A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
EP0778408A2 (fr) * 1995-12-05 1997-06-11 United Technologies Corporation Chemise de protection pour tubes chauds permettant un remplacement rapide
US20030021675A1 (en) * 2000-01-28 2003-01-30 Peter Tiemann Thermal shield for a component carrying hot gases, especially for structural components of gas turbines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3956886A (en) * 1973-12-07 1976-05-18 Joseph Lucas (Industries) Limited Flame tubes for gas turbine engines
DE4314160A1 (de) * 1992-05-13 1993-11-18 Siemens Ag Fügeverbindung und Verfahren zu ihrer Herstellung
DE4309200A1 (de) * 1993-03-22 1994-09-29 Abb Management Ag Vorrichtung zur Einhängung und Entfernung thermisch hoch belasteter Teile in Turbinenanlagen
GB2298267A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
EP0778408A2 (fr) * 1995-12-05 1997-06-11 United Technologies Corporation Chemise de protection pour tubes chauds permettant un remplacement rapide
US20030021675A1 (en) * 2000-01-28 2003-01-30 Peter Tiemann Thermal shield for a component carrying hot gases, especially for structural components of gas turbines

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007137883A1 (fr) * 2006-05-31 2007-12-06 Siemens Aktiengesellschaft Paroi de chambre de combustion
US8069670B2 (en) 2006-05-31 2011-12-06 Siemens Aktiengesellschaft Combustion chamber wall
CN101460783B (zh) * 2006-05-31 2012-01-04 西门子公司 燃烧室壁
EP1862740A1 (fr) * 2006-05-31 2007-12-05 Siemens Aktiengesellschaft Paroi de chambre de combustion
EP2230454A1 (fr) * 2009-03-18 2010-09-22 Siemens Aktiengesellschaft Dispositif destiné au montage d'un élément de bouclier thermique
WO2010105871A1 (fr) * 2009-03-18 2010-09-23 Siemens Aktiengesellschaft Dispositif pour le montage d'un élément pare-feu
CN102460022B (zh) * 2009-06-09 2015-05-06 西门子公司 带有螺栓穿引器件的热屏元件装置和安装热屏元件的方法
EP2261564A1 (fr) * 2009-06-09 2010-12-15 Siemens Aktiengesellschaft Agencement d'élément d'un bouclier thermique doté d'un moyen de guidance de vis et procédé de montage d'un élément d'un bouclier thermique
WO2010142510A1 (fr) * 2009-06-09 2010-12-16 Siemens Aktiengesellschaft Agencement d'éléments de protection thermique avec un élément permettant d'engager une vis et procédé de montage d'un élément de protection thermique
CN102460022A (zh) * 2009-06-09 2012-05-16 西门子公司 带有螺栓穿引器件的热屏元件装置和安装热屏元件的方法
RU2516713C2 (ru) * 2009-06-09 2014-05-20 Сименс Акциенгезелльшафт Система теплозащитного экрана с элементами для вхождения винтов и способ монтажа элемента теплозащитного экрана
WO2014173568A1 (fr) * 2013-04-22 2014-10-30 Siemens Aktiengesellschaft Brique d'écran thermique pour un écran thermique d'une chambre de combustion
RU2708760C1 (ru) * 2016-06-28 2019-12-11 Сименс Акциенгезелльшафт Конструкция теплозащитного экрана камеры сгорания с пакетом тарельчатых пружин
US10989412B2 (en) 2016-06-28 2021-04-27 Siemens Energy Global GmbH & Co. KG Heat shield assembly of a combustion chamber having a disk spring set
EP3309456A1 (fr) * 2016-10-13 2018-04-18 Siemens Aktiengesellschaft Écran thermique avec carreau et support
WO2018068980A1 (fr) * 2016-10-13 2018-04-19 Siemens Aktiengesellschaft Élément d'écran thermique à carreau et support
EP3540314A4 (fr) * 2016-11-11 2020-06-03 Kawasaki Jukogyo Kabushiki Kaisha Chemise de chambre de combustion
US11543132B2 (en) 2016-11-11 2023-01-03 Kawasaki Jukogyo Kabushiki Kaisha Combustor liner
US11873992B2 (en) 2016-11-11 2024-01-16 Kawasaki Jukogyo Kabushiki Kaisha Combustor liner
CN113825950A (zh) * 2019-04-04 2021-12-21 安曼瑞士股份公司 用于沥青生产设备的热气发生器的具有空气导板的燃烧室和用于固定空气导板的方法
CN113825950B (zh) * 2019-04-04 2024-05-17 安曼瑞士股份公司 用于热气发生器的燃烧室和用于固定空气导板的方法

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