EP1467151A1 - Bouclier thermique - Google Patents

Bouclier thermique Download PDF

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Publication number
EP1467151A1
EP1467151A1 EP03008367A EP03008367A EP1467151A1 EP 1467151 A1 EP1467151 A1 EP 1467151A1 EP 03008367 A EP03008367 A EP 03008367A EP 03008367 A EP03008367 A EP 03008367A EP 1467151 A1 EP1467151 A1 EP 1467151A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
combustion chamber
shield element
elements
shield elements
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Withdrawn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
EP03008367A
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 EP03008367A priority Critical patent/EP1467151A1/fr
Priority to PCT/EP2004/003073 priority patent/WO2004090423A1/fr
Publication of EP1467151A1 publication Critical patent/EP1467151A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23M5/00—Casings; Linings; Walls
    • F23M5/02—Casings; Linings; Walls characterised by the shape of the bricks or blocks used
    • 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

Definitions

  • the invention relates to a heat shield element for the inner lining of combustion chambers.
  • the invention further relates to a combustion chamber with such heat shield elements.
  • Combustion chambers are part of gas turbines, which in many Areas for driving generators or work machines be used.
  • the energy content becomes one Fuel for generating a rotational movement of a turbine shaft used.
  • the fuel is used by burners in the combustion chambers connected to them burned, whereby from compressed air is supplied to an air compressor. By the combustion of the fuel becomes one under high pressure standing working medium with a high temperature. This working medium is downstream of the combustion chambers Turbine unit guided where it is working relaxed.
  • a separate combustion chamber can be assigned to each burner be, the working medium flowing out of the combustion chambers can be brought together in front of or in the turbine unit.
  • the combustion chamber can also be installed in a so-called Annular combustion chamber design, in which one Majority, especially all, of the burners in a common, usually annular combustion chamber open.
  • An increase in efficiency can basically be used for thermodynamic reasons by increasing the outlet temperature, with which the working medium from the combustion chamber and into the Turbine unit flows. Therefore temperatures of around Desired 1200 ° C to 1500 ° C for such gas turbines and also achieved.
  • the combustion chamber wall is usually on the inside lined with heat shield elements that with special heat-resistant protective layers can be provided, and cooled through the actual combustion chamber wall become.
  • heat shield elements that with special heat-resistant protective layers can be provided, and cooled through the actual combustion chamber wall become.
  • impingement cooling is a coolant, usually cooling air, through a number of holes in the combustion chamber wall of the heat shield elements fed so that the coolant essentially perpendicular to the outside of the combustion chamber wall lying surface bounces. That heated up by the cooling process Coolant is then from the interior, the forms the combustion chamber wall with the heat shield elements.
  • the heat shield elements can do so on their side walls be formed that there are two adjacent heat shield elements overlap at their edges or a heat shield element forms an overhang, so that with a number of Screw connections on a heat shield element two adjacent Attach the heat shield elements to the combustion chamber wall to let. Alternatively, one screw is replaced by two led adjacent heat shield elements.
  • the inner lining A combustion chamber alternates with these arrangements made of heat shield elements with fastening screws and heat shield elements without mounting screws.
  • This screw connection of the heat shield elements can be cooled Side of the heat shield elements are made.
  • the heat shield elements can also come from the interior of the combustion chamber are screwed to the combustion chamber wall.
  • This attachment is due to the high temperatures cooling of the fastening screws in the combustion chamber interior from the cooled side of the heat shield elements provided from.
  • a disadvantage of the screw connections from the cooled side of a Heat shield element is that the screw connections are very difficult to access because they are only accessible from the interior reached between the combustion chamber wall and the heat shield element can be. The frequently occurring assembly and Maintenance work on the heat shield elements is therefore very much time-consuming because in particular parts of the combustion chamber wall must be removed.
  • a disadvantage of the screw connection from the combustion chamber interior is that a cooling system is ready for cooling the screws must be asked.
  • Such cooling has a particular effect disadvantageous to the overall efficiency of the combustion chamber and the gas turbine because to cool the screws additionally heated a cooling medium such as cooling air becomes. It also affects the space between the recesses and the screw heads recessed therein Flow movement of the working medium because of this depression compared to the smooth inner surface of the heat shield elements an aerodynamic source of interference that leads to turbulence and loss of speed of the flowing along Working medium leads. This affects the movement of the Working medium influence the efficiency of the combustion chamber or the gas turbine also negative.
  • the invention is therefore based on the object of a heat shield element to be specified for the internal lining of combustion chambers, with a particularly high efficiency of the combustion chamber for the simplest possible assembly on the combustion chamber wall is designed. Furthermore, a combustion chamber for Gas turbines with the heat shield elements specified above become.
  • this object is achieved according to the invention solved by on the heat shield element on the Side facing away from the combustion chamber interior over a number of Carrier elements a number of mounting hooks for fastening screws are arranged.
  • the invention is based on the consideration that for one acceptable mounting effort of the system of the heat shield elements from their outside space if possible should be avoided; so the heat shield elements should designed for installation from the interior of the combustion chamber his.
  • the cooling effort for the fastening screws to keep the heat shield element from its back that is, the one facing away from the combustion chamber interior Side, attached to the combustion chamber wall with a bracket be, which also facing the combustion chamber interior Surface of the heat shield elements as aerodynamically as possible designed for the working medium in the combustion chamber interior can be.
  • This function is performed by the hooks, on which the heat shield elements are attached via screws be screwed to the combustion chamber wall. Since the Screws through the mounting hooks arranged over support elements from the area facing the combustion chamber interior the heat shield elements are arranged away, the Heat shield element surface largely uninterrupted be designed.
  • the heat shield element advantageously has one assigned each above a receiving hook Drilling on.
  • a fastening screw can be passed through this hole of the tool and especially a hexagon socket tool reached from the combustion chamber interior and with the combustion chamber wall.
  • the hole has to be only the maximum diameter for the screw connection have used tool.
  • the heat shield elements have the aim of minimizing heat shield elements as much as possible particularly advantageously on their side edges a particularly low depth.
  • To the or each receiving hook of the heat shield element is advantageously by an assigned support element from the outer edge of the heat shield element spaced toward the combustion chamber wall arranged.
  • the heat shield element is preferred shaped such that there are adjacent heat shield elements overlap. To be sufficient in the area of overlap Ensure sealing to the combustion chamber interior and a correspondingly sufficient stability of the screw connection Ensuring both heat shield elements forms the Junction of the support elements provided for the receiving hooks with the heat shield element preferably a support surface for neighboring heat shield elements.
  • the above heat shield element is convenient Part of the inner lining of a combustion chamber.
  • the above-mentioned combustion chamber is preferably a component a gas turbine.
  • the advantages achieved with the invention are in particular in that with the receiving hooks facing the combustion chamber wall for fastening screws of a heat shield element and the associated holes in the heat shield element simple and functional possibility to attach the heat shield elements be provided on the combustion chamber wall can, which is at the same time a streamlined for the working medium Design of the heat shield element surface towards the combustion chamber enables what is beneficial to efficiency the combustion chamber. This is particularly due to the fact that the inner lining of a combustion chamber when using the described heat shield elements with the exception of the holes can be designed. It also improves efficiency positively influenced by the specified heat shield elements, because a separate cooling of the fastening screws is not required. Maintenance and assembly work the heat shield elements, where these from the combustion chamber wall can be removed using the specified heat shield elements time and cost saving.
  • the gas turbine 1 has a compressor 2 for Combustion air, a combustion chamber 4 and a turbine 6 for Drive the compressor 2 and a generator, not shown or a work machine.
  • a compressor 2 for Combustion air
  • a combustion chamber 4 for Drive the compressor 2 and a generator, not shown or a work machine.
  • the turbine 6 and the compressor 2 on a common, also called Turbine rotor designated turbine shaft 8 arranged with which also connects the generator or the working machine is, and which is rotatably mounted about its central axis 9.
  • the Combustion chamber 4 designed in the manner of an annular combustion chamber is with a number of burners 10 for burning one liquid or gaseous fuel.
  • the turbine 6 has a number of with the turbine shaft 8 connected, rotatable blades 12.
  • the blades 12 are arranged in a ring shape on the turbine shaft 8 and thus form a number of rows of blades.
  • the turbine 6 comprises a number of fixed guide vanes 14, which is also ring-shaped with the formation of Guide vane rows attached to an inner housing 16 of the turbine 6 are.
  • the blades 12 serve to drive the turbine shaft 8 by transfer of momentum from the turbine 6 working medium flowing through M.
  • the guide vanes 14 serve in contrast to the flow of the working medium M between seen two in the flow direction of the working medium M. successive rows of blades or blade rings.
  • a successive pair from a wreath of Guide vanes 14 or a row of guide vanes and from one Wreath of blades 12 or a row of blades is also referred to as the turbine stage.
  • Each guide vane 14 has one which is also referred to as a blade root Platform 18, which is used to fix the respective guide vane 14 on the inner housing 16 of the turbine 6 as a wall element is arranged.
  • the platform 18 is a thermal comparison heavily loaded component that the outer boundary a heating gas channel for the one flowing through the turbine 6 Working medium M forms.
  • Each blade 12 is analog Way over a platform 20 also referred to as a blade root attached to the turbine shaft 8.
  • each guide ring 21 is also hot, flowing through the turbine 6 Working medium M exposed and in the radial direction from the outer end 22 of the blade opposite to it 12 spaced by a gap.
  • the one between neighboring Guide rings 21 arranged guide vane rows serve in particular as cover elements that cover the inner wall 16 or other housing installation parts before a thermal Overuse by the hot flowing through the turbine 6 Working medium M protects.
  • the combustion chamber 4 is so-called in the exemplary embodiment Annular combustion chamber designed in which a variety of in Arranged circumferentially around the turbine shaft 8 Burners 10 open into a common combustion chamber space. To is the combustion chamber 4 in its entirety as an annular Designed structure that positioned around the turbine shaft 8 is.
  • the combustion chamber 4 for a comparatively high temperature of the working medium M from about 1200 ° C to 1500 ° C.
  • This also applies to these operating parameters, which are unfavorable for the materials to enable a comparatively long operating time is the combustion chamber wall 24 on the working medium M facing side with one made of heat shield elements 26 provided inner lining.
  • Any heat shield element 26 is particularly heat-resistant on the working medium side Protective layer. Because of the high Temperatures inside the combustion chamber 4 is also for the Heat shield elements 26 provided a cooling system.
  • FIG 2 To further clarify the internal lining of the combustion chamber 4 is schematically in FIG 2 a section of the inner lining the combustion chamber 4 shown, which consists of a Number of heat shield elements 26 is composed.
  • the heat shield elements 26 are of high efficiency designed for the combustion chamber 4 in particular, if possible time-saving assembly and maintenance. Is to the heat shield element 26 with fastening screws 28 the combustion chamber wall 24 screwed, this with their Screw heads 30 each in a slot Receiving hooks 32 are anchored, as can be seen in FIG. 2 reveals.
  • the receiving hooks 32 are above carrier elements 34 attached to the heat shield elements 26.
  • Heat shield elements 26 without their own fastening screws 28 to attach to the combustion chamber wall 24 form the Joints of the support elements 34 with the heat shield element 26 a support surface for the adjacent heat shield elements 26 out.
  • can do so by using alternating heat shield elements 26 with fastening screws 28 and heat shield elements 26 without fastening screws 28 the inner lining the combustion chamber 4 are formed.
  • a pick-up hook 32 and the associated fastening screw 28 a bore 36 assigned in the heat shield element 26.
  • a recess for holding a hexagon socket tool provided to the fastening screws 28 on the Screw the combustion chamber wall 24.
  • the bores 36 with plug in combustion chamber operation 38 closed to seal the combustion chamber 4 to the outside.

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)
EP03008367A 2003-04-10 2003-04-10 Bouclier thermique Withdrawn EP1467151A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03008367A EP1467151A1 (fr) 2003-04-10 2003-04-10 Bouclier thermique
PCT/EP2004/003073 WO2004090423A1 (fr) 2003-04-10 2004-03-23 Element d'ecran thermique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03008367A EP1467151A1 (fr) 2003-04-10 2003-04-10 Bouclier thermique

Publications (1)

Publication Number Publication Date
EP1467151A1 true EP1467151A1 (fr) 2004-10-13

Family

ID=32864992

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03008367A Withdrawn EP1467151A1 (fr) 2003-04-10 2003-04-10 Bouclier thermique

Country Status (2)

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EP (1) EP1467151A1 (fr)
WO (1) WO2004090423A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1712840A1 (fr) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Bouclier thermique avec boulon de fixation
EP1884713A1 (fr) * 2006-07-25 2008-02-06 Siemens Aktiengesellschaft Ensemble écran thermique, en particulier pour une turbine à gaz
WO2009013332A2 (fr) * 2007-07-24 2009-01-29 Continental Automotive Gmbh Turbocompresseur avec un carter de turbocompresseur présentant un vissage à l'aide d'un tirant d'ancrage
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
EP2730843A1 (fr) * 2012-11-13 2014-05-14 Rolls-Royce Deutschland Ltd & Co KG Bardeaux de chambre de combustion d'une turbine à gaz
RU2561957C2 (ru) * 2010-08-27 2015-09-10 Сименс Акциенгезелльшафт Элемент теплозащитного экрана
EP2977678A1 (fr) * 2014-07-25 2016-01-27 Rolls-Royce plc Élément de garniture pour une chambre de combustion
WO2018202407A1 (fr) * 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Chambre de combustion
US11530817B2 (en) 2018-12-12 2022-12-20 Rolls-Royce Plc Combustor, a tile holder and a tile

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2952812B1 (fr) * 2014-06-05 2018-08-08 General Electric Technology GmbH Chambre de combustion annulaire d'une turbine á gaz et segment de manchon

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4773227A (en) * 1982-04-07 1988-09-27 United Technologies Corporation Combustion chamber with improved liner construction
US5069034A (en) * 1989-05-11 1991-12-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Heat protective lining for an afterburner or transition duct of a turbojet engine
DE4314160A1 (de) * 1992-05-13 1993-11-18 Siemens Ag Fügeverbindung und Verfahren zu ihrer Herstellung
GB2298267A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
US5704208A (en) * 1995-12-05 1998-01-06 Brewer; Keith S. Serviceable liner for gas turbine engine
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

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4773227A (en) * 1982-04-07 1988-09-27 United Technologies Corporation Combustion chamber with improved liner construction
US5069034A (en) * 1989-05-11 1991-12-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Heat protective lining for an afterburner or transition duct of a turbojet engine
DE4314160A1 (de) * 1992-05-13 1993-11-18 Siemens Ag Fügeverbindung und Verfahren zu ihrer Herstellung
GB2298267A (en) * 1995-02-23 1996-08-28 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
US5704208A (en) * 1995-12-05 1998-01-06 Brewer; Keith S. Serviceable liner for gas turbine engine
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

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1712840A1 (fr) * 2005-04-13 2006-10-18 Siemens Aktiengesellschaft Bouclier thermique avec boulon de fixation
EP1884713A1 (fr) * 2006-07-25 2008-02-06 Siemens Aktiengesellschaft Ensemble écran thermique, en particulier pour une turbine à gaz
WO2009013332A2 (fr) * 2007-07-24 2009-01-29 Continental Automotive Gmbh Turbocompresseur avec un carter de turbocompresseur présentant un vissage à l'aide d'un tirant d'ancrage
WO2009013332A3 (fr) * 2007-07-24 2009-03-19 Continental Automotive Gmbh Turbocompresseur avec un carter de turbocompresseur présentant un vissage à l'aide d'un tirant d'ancrage
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
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
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
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
RU2516713C2 (ru) * 2009-06-09 2014-05-20 Сименс Акциенгезелльшафт Система теплозащитного экрана с элементами для вхождения винтов и способ монтажа элемента теплозащитного экрана
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
RU2561957C2 (ru) * 2010-08-27 2015-09-10 Сименс Акциенгезелльшафт Элемент теплозащитного экрана
EP2730843A1 (fr) * 2012-11-13 2014-05-14 Rolls-Royce Deutschland Ltd & Co KG Bardeaux de chambre de combustion d'une turbine à gaz
US9683743B2 (en) 2012-11-13 2017-06-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber tile of a gas turbine
EP2977678A1 (fr) * 2014-07-25 2016-01-27 Rolls-Royce plc Élément de garniture pour une chambre de combustion
US9970660B2 (en) 2014-07-25 2018-05-15 Rolls-Royce Plc Liner element for a combustor
WO2018202407A1 (fr) * 2017-05-04 2018-11-08 Siemens Aktiengesellschaft Chambre de combustion
US11530817B2 (en) 2018-12-12 2022-12-20 Rolls-Royce Plc Combustor, a tile holder and a tile

Also Published As

Publication number Publication date
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