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EP1443275A1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP1443275A1
EP1443275A1 EP03001890A EP03001890A EP1443275A1 EP 1443275 A1 EP1443275 A1 EP 1443275A1 EP 03001890 A EP03001890 A EP 03001890A EP 03001890 A EP03001890 A EP 03001890A EP 1443275 A1 EP1443275 A1 EP 1443275A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
wall
coolant
heat shield
turbine
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.)
Granted
Application number
EP03001890A
Other languages
German (de)
English (en)
Other versions
EP1443275B1 (fr
Inventor
Paul-Heinz Jeppel
Wilhelm Schulten
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 DE50310313T priority Critical patent/DE50310313D1/de
Priority to ES03001890T priority patent/ES2307834T3/es
Priority to EP03001890A priority patent/EP1443275B1/fr
Priority to CNB2004100020853A priority patent/CN100393997C/zh
Priority to JP2004013771A priority patent/JP2004340564A/ja
Priority to US10/767,677 priority patent/US7082771B2/en
Publication of EP1443275A1 publication Critical patent/EP1443275A1/fr
Application granted granted Critical
Publication of EP1443275B1 publication Critical patent/EP1443275B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies

Definitions

  • the invention relates to a combustion chamber for a gas turbine, the combustion chamber of an annular outer wall on the one hand and an annular inner wall disposed therein on the other hand is limited.
  • the combustion chamber walls are on the inside with one of a number of heat shield elements formed liner provided, the or each heat shield element an interior to which a coolant can be applied forms.
  • the invention further relates to a gas turbine with such a combustion chamber.
  • 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 burned in the downstream combustion chambers, whereby compressed air is supplied by an air compressor.
  • the combustion of the fuel turns it into a low Pressurized working medium generated at a high temperature. This working medium is in one of the combustion chambers downstream turbine unit guided where it is working relaxed.
  • a separate combustion chamber can be assigned to each burner be, the flowing out of the combustion chambers Working medium merged before or in the turbine unit can be.
  • the combustion chamber can also be in a so-called annular combustion chamber design, at the majority, especially all, the burner into a common, usually annular combustion chamber open.
  • the the combustion chamber in the direction of flow of the working medium subsequent turbine unit usually comprises one Turbine shaft with a number of rotating blades connected, the ring-shaped rows of blades form.
  • the turbine unit further comprises a number of fixed guide vanes, which are also ring-shaped below the formation of vane rows on the inner casing of the Turbine are attached.
  • the blades are used for Drive of the turbine shaft by pulse transmission of the turbine unit flowing medium while the guide vanes to flow the working medium between seen two in the flow direction of the working medium successive rows of blades or blade rings serve.
  • the combustion chamber is one annular outer wall on the one hand and one arranged therein annular inner wall on the other hand limited.
  • the inner wall of the combustion chamber usually consists of two or several individual parts on their the turbine shaft facing side are screwed together.
  • 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 inside of the combustion chamber wall can do this with heat shield elements be lined with particularly heat-resistant Protective layers can be provided, and the be cooled through the actual combustion chamber wall.
  • a cooling method also known as "impact cooling” can be used for this purpose be used.
  • impingement cooling a Coolant, usually cooling air, through a variety of Holes in the combustion chamber wall fed to the heat shield elements, so the coolant is essentially perpendicular their outer surface facing the combustion chamber wall rebounds. The coolant heated by the cooling process becomes then from the interior that the combustion chamber wall with forms the heat shield elements, dissipated.
  • the structure of the annular combustion chamber described above also has some additional maintenance work Disadvantages. These are usually carried out regularly Maintenance and repair work must be carried out due to the high thermal and mechanical stress parts of the combustion chamber such as the heat shield elements or that used cooling system and in particular also components of the downstream turbine unit repaired or replaced become.
  • a disadvantage of the structure of the combustion chamber is that Turbine shaft not removed from the combustion chamber during maintenance work is accessible from. For maintenance work on the Turbine shaft in the area of the ring combustion chamber or for repairs to the one immediately following the combustion chamber the first guide vanes and moving blades, as a rule all subsequent ones Turbine unit guide vanes and vanes removed become.
  • the invention is therefore based on the object of a combustion chamber of the type mentioned above, which at comparative simple design for a particularly high system efficiency is suitable and in which the inner wall of the Combustion chamber can be removed comparatively quickly and easily is.
  • the object is achieved according to the invention solved by in the assigned to the respective heat shield element Interior each have a number of coolant distributors is arranged, and by the inner wall of the combustion chamber from a number of attached to a support structure of the inner wall Wall elements is formed, the support structure of a number of each other on a horizontal parting line abutting sections is formed in the area of Parting line over a number of diagonally aligned to the inner wall surface Screw connections are interconnected.
  • the invention is based on the consideration that for one a particularly high system efficiency a reliable and in particular area-wide application of the heat shield elements should be guaranteed with coolant. Also at the apparatus can consistently comply with this requirement Effort and in particular the manufacturing effort kept low by the multitude of the previously provided Coolant holes replaced by a simplified system become. To keep the cooling effect high to maintain and on the other hand to simplify the supply, is a division of the coolant flow path into individual partial paths only as close as possible to the one to be cooled Heat shield element, i.e. particularly far at the end of the flow path, intended.
  • the coolant distributors fulfill these functions.
  • the invention relates to maintenance work from the consideration that the attachment of the various Wall elements of the combustion chamber inner wall to each other should be accessible from the combustion chamber and the combustion chamber inner wall so that it can also be dismantled from it.
  • Horizontal force component resulting from the screw connection two connected by the screw connection Compensating for structural elements is every screw connection expediently assigned a key.
  • the Key prevents the screwed together Support structure elements on the horizontal parting line through the horizontal force component of the screw connection to each other move.
  • the feather key advantageously runs for this along the horizontal parting line and is in grooves the adjoining supporting structure elements are precisely fitted, so that they don't move against each other can, and preferably only those for attachment the vertical force component of the screw connection Screw connection occurs on the horizontal parting line.
  • a coolant supply line with a number of coolant outlet openings connected. This allows them to immediately heat shields in front of the coolant distributors be cooled by impingement cooling.
  • the coolant heated up after the cooling process becomes expedient through holes in the combustion chamber wall from the interior between the heat shields and the combustion chamber wall in derived a coolant discharge system.
  • the coolant distributor By the shape and one suitable arrangement of the coolant distributor, the one ensures sufficient distance between the coolant distributors, the heated cooling air can pass through the gaps between the coolant distributors to the openings of the bores located on the combustion chamber wall stream.
  • Relationship to the number of coolant distributors over the the entire length of the combustion chamber is preferably evenly distributed, so the coolant in all the return holes evenly with an approximately the same return temperature can be derived.
  • the coolant distributors on the wall, the To position return bores and the joint joints are expediently using a system with Tongue and groove attached to the inner wall of the combustion chamber.
  • there heat shield elements are preferred at their edges shaped in such a way that it is directed towards the combustion chamber by a double bend form an anchoring that is in a Anchor the recess in the combustion chamber wall that forms the groove and can be attached with it.
  • This is expediently Recess in the combustion chamber wall for adjacent heat shield elements summarized so that they are contiguous Heat shield elements on theirs caused by the bend Front side, butt together and create a seal for the Represent the combustion chamber and the working medium flowing in it.
  • the above-mentioned combustion chamber is preferably a component a gas turbine.
  • the advantages achieved with the invention are in particular in that through the use of coolant manifolds a large area even with only a small manufacturing effort and comprehensive application of the heat shield elements is made possible with coolant.
  • the coolant pressure drop kept low when cooling the combustion chamber so that the system efficiency of the combustion chamber elevated.
  • the low coolant pressure drop can in particular can also be achieved because the cooling air distributor only need few feed holes in the combustion chamber wall.
  • the Using a number of coolant manifolds can be one ensure uniform cooling with low coolant pressure loss, since the coolant supply via a coolant distributor the coolant is only shortly before the impingement cooling on the heat shield elements from a larger coolant supply line into several smaller coolant outlet openings branched. This ensures that the coolant only a short distance with a relatively small one Cross-section flows, so that the coolant pressure loss is limited.
  • the above-mentioned combustion chamber is preferably a component a gas turbine.
  • 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 as a turbine rotor designated turbine shaft 8 arranged with the the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • a turbine rotor designated turbine shaft 8 arranged with the the generator or the working machine is also connected, and which is rotatably mounted about its central axis 9.
  • the type of an annular combustion chamber designed combustion chamber 4 with a number of burners 10 for burning a liquid or gaseous fuel is the type of an annular combustion chamber designed combustion chamber 4 with a number of burners 10 for burning a 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 or other housing components 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.
  • combustion chamber 4 2 shows the combustion chamber 4 in section, the continues like a torus around the turbine shaft 8.
  • the combustion chamber 4 has a Beginning or inflow section, in the end of the Outlet of the respectively assigned burner 10 opens.
  • the adjoining Flow profile of the working medium M in this Space area is taken into account.
  • the Combustion chamber 4 has a curvature in longitudinal section through which the outflow of the working medium M from the combustion chamber 4 in one for a particularly high impulse and energy transfer to the first row of moving blades as seen on the flow side is favored.
  • the Combustion chamber 24 of combustion chamber 4 from a combustion chamber wall 25 limited, on the one hand, by an annular combustion chamber outer wall 26 and on the other hand from one arranged therein annular combustion chamber inner wall 28 is formed.
  • the combustion chamber 4 is designed for the combustion chamber inner wall 28 for example for maintenance work on particularly simple Way to be able to access to from the combustion chamber inner wall 28 surrounded turbine shaft 8 and the Combustion chamber 4 immediately following blades 12 and To obtain guide blades 14 of the turbine 6.
  • the combustion chamber 4 is designed in particular for the wall elements 30 of the combustion chamber inner wall 28 from the combustion chamber 24 to be able to disassemble.
  • the wall elements 30 on the formed by them horizontal parting line 31 with oblique to the inner surface of the Combustion chamber inner wall 28 extending screw connections 32 connected.
  • Each screw connection 32 comprises one in Essentially oblique to the wall 28 formed by the combustion chamber Surface guided screw 33, which with a in one of the wall elements 30 incorporated thread 34 cooperates.
  • a key 35 is assigned to the screw connection 32. This runs in a position close to the respective one Screw connection 32 along the horizontal parting line 31 of the wall elements 30 and is in the grooves of the wall elements 30 Combustion chamber inner wall 28 fitted.
  • 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 25, as shown in FIG. 5, on their side facing the working medium M with one Heat shield elements 38 provided lining.
  • each Heat shield element 38 is on the working medium side with a particularly heat-resistant protective layer.
  • a cooling system is also provided for the heat shield elements 38.
  • the cooling system is based on the principle of impact cooling, with the cooling air K as a coolant under sufficient high pressure in a variety of places on the item to be cooled Component is blown.
  • the cooling system is simple in construction for reliable, Comprehensive exposure to the heat shield elements 38 with cooling air and also for a particularly low one Coolant pressure drop designed.
  • the heat shield elements 38 from the outside through the cooling air K cooled by a number of im from each heat shield element 38 and the combustion chamber wall 25 formed interior 40 arranged coolant distributors 42 on the surface of the respective heat shield element 38 is passed.
  • cooling for the heat shield elements 38 is a section in FIG. 5 in section the combustion chamber wall 25 shown. Like this one A number of coolant distributors are visible 42 over the entire area of the respective heat shield element 38 distributed to even cooling guarantee.
  • the coolant K flows through an associated one Coolant supply line 44 in the respective coolant distributor 42.
  • the coolant K is passed through this a number of coolant outlet openings 46 on the surface of the heat shield element 38 passed where this with the Coolant K is cooled by impingement cooling.
  • the holes for the coolant supply lines 44 are in production the combustion chamber 4 easy and time-saving to install because for each coolant distributor 42 only one Coolant supply line 44 is required.
  • coolant outlet openings 46 of the coolant distributor 42 has a smaller cross section than the coolant supply line 44 of the coolant distributor 42. This leads to the flow of the coolant K through the Coolant distributor 42 to a nozzle effect and associated therewith to an increased outlet speed of the coolant K at the coolant outlet openings 46, whereby the effect of the impingement cooling on the heat shield elements 38 increased.
  • the heat shield elements 38 are space-saving for the attached cooling system and the joint screw connection attached to the combustion chamber wall 28.
  • a system with Tongue and groove used.
  • the heat shield elements 38 shaped at its edges so that it is separated by a double Bend anchoring towards the combustion chamber, which in a recess of the combustion chamber wall 25, which the groove forms, anchors and can be fastened with it.
  • the adjacent heat shield elements 38 attached to combined grooves that they touch each other and so the combustion chamber 24 seal the combustion chamber 4.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03001890A 2003-01-29 2003-01-29 Chambre de combustion Expired - Lifetime EP1443275B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE50310313T DE50310313D1 (de) 2003-01-29 2003-01-29 Brennkammer
ES03001890T ES2307834T3 (es) 2003-01-29 2003-01-29 Camara de combustion.
EP03001890A EP1443275B1 (fr) 2003-01-29 2003-01-29 Chambre de combustion
CNB2004100020853A CN100393997C (zh) 2003-01-29 2004-01-12 燃烧室
JP2004013771A JP2004340564A (ja) 2003-01-29 2004-01-22 燃焼器
US10/767,677 US7082771B2 (en) 2003-01-29 2004-01-29 Combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP03001890A EP1443275B1 (fr) 2003-01-29 2003-01-29 Chambre de combustion

Publications (2)

Publication Number Publication Date
EP1443275A1 true EP1443275A1 (fr) 2004-08-04
EP1443275B1 EP1443275B1 (fr) 2008-08-13

Family

ID=32605266

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03001890A Expired - Lifetime EP1443275B1 (fr) 2003-01-29 2003-01-29 Chambre de combustion

Country Status (6)

Country Link
US (1) US7082771B2 (fr)
EP (1) EP1443275B1 (fr)
JP (1) JP2004340564A (fr)
CN (1) CN100393997C (fr)
DE (1) DE50310313D1 (fr)
ES (1) ES2307834T3 (fr)

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DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung

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EP1398569A1 (fr) * 2002-09-13 2004-03-17 Siemens Aktiengesellschaft Turbine à gaz
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
EP1701095B1 (fr) * 2005-02-07 2012-01-18 Siemens Aktiengesellschaft Ecran thermique
EP2049841B1 (fr) * 2006-08-07 2016-12-28 General Electric Technology GmbH Chambre de combustion d'une installation d'incinération
WO2008017550A1 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation de combustion
EP2119966A1 (fr) * 2008-05-15 2009-11-18 ALSTOM Technology Ltd Chambre de combustion à émissions réduites de monoxyde de carbone
EP2119964B1 (fr) 2008-05-15 2018-10-31 Ansaldo Energia IP UK Limited Procédé pour réduire les émissions d'une chambre à combustion
IT1391548B1 (it) 2008-11-05 2012-01-11 Enel Produzione Spa Turbogas con combustore monocanna e convogliatore dei fumi biforcato a flusso differenziato dell'aria di diluizione
EP2282124A1 (fr) * 2009-08-03 2011-02-09 Alstom Technology Ltd Procédé de modification d'une chambre à combustion d'une turbine à gaz
CN102278155A (zh) * 2011-06-02 2011-12-14 马鞍山科达洁能股份有限公司 燃气和蒸汽轮机系统
US20130086920A1 (en) * 2011-10-05 2013-04-11 General Electric Company Combustor and method for supplying flow to a combustor
CN103115381B (zh) * 2011-11-17 2015-04-01 中航商用航空发动机有限责任公司 一种火焰筒的筒壁结构
EP2642203A1 (fr) * 2012-03-20 2013-09-25 Alstom Technology Ltd Amortisseur de helmholtz annulaire
EP2728255A1 (fr) * 2012-10-31 2014-05-07 Alstom Technology Ltd Agencement de segment de gaz chaud
US9651258B2 (en) 2013-03-15 2017-05-16 Rolls-Royce Corporation Shell and tiled liner arrangement for a combustor
WO2015036430A1 (fr) * 2013-09-11 2015-03-19 Siemens Aktiengesellschaft Bouclier thermique céramique cunéiforme d'une chambre de combustion de turbine à gaz
JP6210810B2 (ja) * 2013-09-20 2017-10-11 三菱日立パワーシステムズ株式会社 デュアル燃料焚きガスタービン燃焼器
DE102014221225A1 (de) * 2014-10-20 2016-04-21 Siemens Aktiengesellschaft Hitzeschildelement und Verfahren zu seiner Herstellung
US10935235B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10935236B2 (en) 2016-11-10 2021-03-02 Raytheon Technologies Corporation Non-planar combustor liner panel for a gas turbine engine combustor
US10655853B2 (en) 2016-11-10 2020-05-19 United Technologies Corporation Combustor liner panel with non-linear circumferential edge for a gas turbine engine combustor
US10830433B2 (en) 2016-11-10 2020-11-10 Raytheon Technologies Corporation Axial non-linear interface for combustor liner panels in a gas turbine combustor
US10739001B2 (en) * 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
US10533747B2 (en) * 2017-03-30 2020-01-14 General Electric Company Additively manufactured mechanical fastener with cooling fluid passageways
DE102017212575A1 (de) * 2017-07-21 2019-01-24 Siemens Aktiengesellschaft Verfahren zur Erhöhung der Leistung einer Gasturbine
DE102020203017A1 (de) * 2020-03-10 2021-09-16 Siemens Aktiengesellschaft Brennkammer mit keramischem Hitzeschild und Dichtung
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
CN112050255B (zh) * 2020-09-18 2022-04-22 中国航发四川燃气涡轮研究院 一种采用间隙旋流冷却的火焰筒

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014204468A1 (de) * 2014-03-11 2015-10-01 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer sowie Verfahren zu deren Herstellung
US9803869B2 (en) 2014-03-11 2017-10-31 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustion chamber and method for manufacturing the same

Also Published As

Publication number Publication date
DE50310313D1 (de) 2008-09-25
EP1443275B1 (fr) 2008-08-13
ES2307834T3 (es) 2008-12-01
CN100393997C (zh) 2008-06-11
US20040182085A1 (en) 2004-09-23
CN1519507A (zh) 2004-08-11
US7082771B2 (en) 2006-08-01
JP2004340564A (ja) 2004-12-02

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