EP0928396B1 - Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds - Google Patents

Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds Download PDF

Info

Publication number
EP0928396B1
EP0928396B1 EP97944734A EP97944734A EP0928396B1 EP 0928396 B1 EP0928396 B1 EP 0928396B1 EP 97944734 A EP97944734 A EP 97944734A EP 97944734 A EP97944734 A EP 97944734A EP 0928396 B1 EP0928396 B1 EP 0928396B1
Authority
EP
European Patent Office
Prior art keywords
heat
component
wall
heat shield
shield
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.)
Expired - Lifetime
Application number
EP97944734A
Other languages
German (de)
English (en)
Other versions
EP0928396A1 (fr
Inventor
Heinz-Jürgen GROSS
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
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP0928396A1 publication Critical patent/EP0928396A1/fr
Application granted granted Critical
Publication of EP0928396B1 publication Critical patent/EP0928396B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F23R3/005—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
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/222—Improvement of heat transfer by creating turbulence
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S165/00—Heat exchange
    • Y10S165/908—Fluid jets

Definitions

  • the invention relates to a heat shield component with a hot gas wall to be cooled and a heat shield arrangement which a hot gas-carrying component, in particular a combustion chamber a gas turbine plant, and a plurality of Has heat shield components.
  • EP 0 224 817 B1 describes a heat shield arrangement, in particular for structural parts of gas turbine systems.
  • the heat shield arrangement serves to protect a supporting structure against a hot fluid, especially for Protection of a hot gas duct wall in gas turbine plants.
  • the Heat shield assembly has an inner liner made of heat resistant Material, which is assembled across the board is made of heat shield elements anchored to the supporting structure. These heat shield elements are left with Columns for the flow of cooling fluid arranged side by side and heat-mobile.
  • Each of these heat shield elements has a hat part and a shaft part in the manner of a mushroom on.
  • the hat part is a flat or spatial, polygonal Panel body with straight or curved edge lines.
  • the shaft part connects the central area of the plate body with the support structure.
  • the hat part preferably has a triangular shape, which creates an inner lining thanks to identical hat parts almost any geometry can be produced
  • the hat parts and possibly other parts of the heat shield elements are made of a heat-resistant material, especially a steel.
  • the supporting structure has holes through which a cooling fluid, in particular air, into a Flow in the space between the hat part and the supporting structure can uno from there through the column to flow through the Cooling fluids in one surrounded by the heat shield elements Area, for example a combustion chamber of a gas turbine system, can flow in. This cooling fluid flow diminishes the penetration of hot gas into the gap.
  • U.S. Patent 5,216,886 is a metallic liner for described a combustion chamber. This lining is made from a large number of cubes arranged side by side Hollow components (cells) on a common metal plate are attached. The common metal plate faces an opening is assigned to each cube-shaped cell for the inflow of cooling fluid. The cube-shaped cells are arranged side by side, leaving a gap. They included on each side wall near the common metal plate a respective opening for the outflow of cooling fluid. The cooling fluid therefore enters the column between neighboring cube-shaped cells, flows through them Column through and forms at a hot gas exposed surface parallel to the metallic plate of the cells from a cooling film.
  • Cooling system defines, in which cooling air over a wall structure through the cells into the interior of the combustion chamber. The cooling air is therefore for further cooling purposes lost.
  • DE 35 42 532 A1 describes a wall, in particular for gas turbine systems, described, which has cooling fluid channels.
  • the wall is preferably between one in gas turbine plants Hot room and a cooling fluid room arranged. she is off individual wall elements put together, each of the wall elements a plate body made of heat-resistant material is. Each plate body has its base distributed, parallel cooling channels on one End with the cooling fluid space and at the other end with the Communicate the hot room. The flowing into the hot room Cooling fluid guided through the cooling fluid channels forms on the the surface of the wall element facing the hot room and / or adjacent wall elements a cooling fluid film.
  • GB-A-849 255 there is a cooling system for cooling one Combustion chamber wall shown.
  • the combustion chamber wall is through Wall elements formed.
  • Each wall element has one Hot gas wall with a hot gas and outside with an inside on. Nozzles are perpendicular to the inside arranged. Cooling fluid comes out of these nozzles in the form of a concentrated electricity and hits the inside. This cools the hot gas wall.
  • the cooling fluid is in collected in a collecting chamber and out of the collecting chamber dissipated.
  • the object of the invention is a heat shield component that is coolable with cooling fluid, and a heat shield arrangement specify with heat shield components so that when cooling a small loss at most of a heat shield component of cooling fluid and / or a slight pressure drop occurs.
  • a heat shield component Task solved by one that has an interior, a hot gas wall to be cooled, adjacent to the interior, an inlet channel and an outlet channel for cooling fluid has, the inlet channel facing the hot gas wall is and widens towards the hot gas wall, and that Outlet channel for a return of the cooling fluid with a Discharge channel is connectable.
  • Inlet duct, outlet duct and the closed hot gas wall cause a complete Cooling fluid return, so that by cooling the heat shield component no loss of cooling fluid occurs.
  • the inlet duct is preferably provided with a cover wall, e.g. a baffle cooling plate, which is adjacent to the hot gas wall and passages for the flow guidance of the cooling fluid having.
  • a cover wall e.g. a baffle cooling plate
  • An expansion of the inlet channel through a cover wall with openings is closed, causes an impact cooling of the hot gas wall over its entire Inner surface.
  • the heat shield component is preferably made made of a heat-resistant material, a metal or one Metal alloy, which is especially cast with high precision (Investment casting).
  • Hot gas wall has cooling fins on its inner surface. This flows through the cover plate along these cooling fins cooling fluid reached the hot gas wall.
  • the cooling fins can be connected to the cover plate, the baffle cooling plate.
  • the inlet duct is preferably air from a compressor can be fed to a gas turbine system. That through the heat shield component led air preferably passes through the outlet duct into a combustion chamber, into one or more burners and / or a compressor of the gas turbine system.
  • the supply of the heat shield component with cooling air and the Return of the heated cooling air to a burner of the gas turbine system preferably takes place via axially parallel supply channels.
  • the channels can be set in the radial direction expand as required and their cross sections of the required Adjust the cooling air volume. All heat shield components therefore have essentially identical cooling air entry conditions.
  • the flow path to the heat shield components or the heated ones Cooling air to the burner is due to its brevity only low pressure losses.
  • the supply the one on the outside of a rotationally symmetrical hot gas Component, in particular a combustion chamber Gas turbine system, arranged heat shield components takes place preferably over the guide vanes of the first row of guide vanes the gas turbine. If through the guide vanes feasible amount of cooling air is not sufficient Cooling the heat shield components is sufficient, it goes without saying possible, supply channels on the hot gas Component, especially the combustion chamber, past their Outside.
  • the return of the heated cooling air is preferably done via separate discharge channels that lead directly to a burner a gas turbine plant. It is also possible to use the Outlet duct of the heat shield components directly into one Main duct in which the compressor air is fed to the burner will let out. This can cause the heat shield components absorbed heat again particularly cheap be fed to the gas turbine process.
  • the one extending from the hot gas wall in the direction of the support structure Outer wall of the heat shield component can in the Surrounding the hot gas wall, at least in regions, undulating be trained. This allows the transition of the outer wall from the hot gas area to that of the Support structure adjacent cold area to reduce stress be formed.
  • the inlet duct is preferably inside the heat shield component is surrounded by the outlet duct. He can expand in a funnel shape towards the cover plate.
  • the heat shield component Fastener On which the inlet channel and the outlet channel surrounds.
  • This fastening part preferably has one Foot area, which runs parallel to the support structure and is fastened there for example by screws.
  • the heat shield component preferably has one that conforms to the Hot gas wall adjoining outer wall, which at least in some areas has a holding level.
  • a fastening component for example with a Head part, can be arranged, with the fastening component with a support structure of a combustion chamber can be connected.
  • the fastening component thus causes the heat shield component to be held on the support structure and allows that the heat shield component due to the thermal load can expand freely.
  • the fastening component a cooled screw, which is cast with high precision, his.
  • the hot gas wall preferably has a wall thickness of below 10 mm on.
  • the wall thickness is preferably in a range between 3 to 5 mm, due to a small temperature difference between inside and outside surface high load change resistance of the heat shield components achievable is.
  • the on a heat shield arrangement for lining a hot gas Component, in particular a combustion chamber Gas turbine plant, task directed through a heat shield arrangement solved that a plurality of heat shield components with cooling fluid return.
  • a heat shield component each has a hot gas wall to be cooled, the its outer surface one that can be guided through the combustion chamber Hot gas is facing.
  • the heat shield component enables closed routing of cooling air without loss of cooling air, wherein the cooling air through an inlet duct that extended to the hot gas wall, feedable and via one Exhaust duct is removable.
  • the inlet channel becomes cooling fluid via a feed channel which, for example, with the compressor is connected to a gas turbine system.
  • the heated cooling fluid flowing out of the outlet channel becomes one Discharge channel fed and from there into the burner a gas turbine plant.
  • Each heat shield component has one for guiding the Hot gas designed flow area with its outer Surface facing hot gas wall, to which via an inlet channel Cooling fluid can be supplied according to the principle of impingement cooling and the cooling fluid bouncing off the hot gas wall via a Outlet channel can be brought out of this again.
  • Cooling fluid flowing in a heat shield component in particular Air, thus completely comes out of it out and is thus available for feeding into the thermodynamic Cyclic process available in the gas turbine plant.
  • the heat shield component preferably faces an outer wall a holding step on which a fastening component with a head part.
  • the fastening component is via a shaft part connected to the head part on a Support structure attached, creating the heat shield component is arranged movably on the support structure.
  • the shaft part is preferably elastic, for example over a spring assembly attached to the support structure so that a heat-mobile yet firm connection between given the fastening component and the heat shield component is.
  • the fastening component preferably has one of cooling fluid through which the cooling channel flows and is thus also sufficiently coolable.
  • the cooling duct can be in the interior be open to the hot gas-carrying component, so that cooling fluid flows into this interior in small quantities. Even in this case, the loss of cooling fluid extremely low.
  • FIG. 1 shows a gas turbine system 10, which is partially longitudinal is shown cut open.
  • the gas turbine system 10 has a shaft 26 and is connected in series in the axial direction a compressor 9, an annular combustion chamber 11 and the blading (guide vanes 18, moving blades 27).
  • Combustion air is compressed and heated in the compressor 9, which partially as a cooling fluid 4 (see FIG. 2, 3, 4)
  • Heat shield assembly 20 is supplied.
  • the compressed air is supplied to a plurality of burners 25 which are circular are arranged around the annular combustion chamber 11.
  • One in the Burners 25 not shown burned with the compressor air Fuel forms a hot gas in the combustion chamber 11 29, which from the combustion chamber 11 in the blading of the Gas turbine system 10 (guide blade 18, blade 27) flows in and thus causes rotation of the shaft 26.
  • Combustion chamber 11 shown has a heat shield arrangement 20, which consists of a multiplicity of heat shield components 1 is constructed.
  • the compressor air compressed in the compressor 9 is in a feed channel 12 along the combustion chamber 11 led to each heat shield component 1.
  • a part of Compressor air is used as cooling air 4 in each heat shield component 1 introduced.
  • a partial flow of the compressor air is through the guide vanes 18 of the first row of guide vanes Gas turbine system 10 out.
  • the compressor air as well as the in the heat shield components 1 are heated cooling air 4 Burner 25 supplied in the fuel, not shown is burned. By burning the fuel in the Burner 25 creates a hot gas 29 which passes through the combustion chamber 11 flows to the guide vane 18. Any heat shield component 1 is acted upon by the hot gas 29 on a hot gas wall 2.
  • the interior 6 of each heat shield component 1 is from the hot gas wall 2 and an adjoining one to the supply duct 12 directed outer wall 14 limited.
  • FIG 3 is a longitudinal section through a section Combustion chamber 11 shown in the area of a support structure 17.
  • a heat shield arrangement 20 is provided on the support structure 17 a plurality of heat shield components 1 arranged.
  • Each Heat shield component 1 is directed along a main axis 32, which are essentially perpendicular to the supporting structure 17 is arranged.
  • the heat shield component 1 essentially has one parallel to the support structure 17, the Hot gas 29 exposed hot gas wall 2 on an interior 2A adjacent.
  • One directed along the major axis 32 Inlet channel 3 for cooling fluid 4 widens in the direction the hot gas wall 2 into the interior 2A. He is with one Cover wall 7 completed, which passages 8 to Has flow of cooling fluid 4.
  • the cover wall 7 is directed and extends substantially parallel to the hot gas wall 2 essentially over their entire extent.
  • the cooling fluid 4 flowing through the passages 8 impacts the inner surface 16 and there causes impingement cooling.
  • the hot gas wall 2 has cooling fins on the inner surface 16 15 on which an increase in heat transfer from the Condition hot gas wall 2 on the cooling fluid 4. From the inside surface 16, the heated cooling fluid 4 passes through an outlet channel running essentially parallel to the main axis 32 5 out of the interior 2A of the heat shield component 1. That used to cool the heat shield component 1 Cooling fluid 4 thus comes completely out of the heat shield component 1 out again.
  • the outlet duct 5 closes a discharge duct 13, which is designed, for example, as a pipe can be and is welded to the support structure 17.
  • the Discharge channel 13 preferably leads to a burner 25 Gas turbine plant 10 are supply duct 14 and discharge duct 13 directed parallel to the shaft 26.
  • the outer wall 14 is at least in some areas in an environment the hot gas wall 2 is wavy, which makes a Voltage reduction between heated by the hot gas 29 Areas and cooled areas of the heat shield component 1 is reached.
  • the outer wall 14 goes into a fastening part 19 above, which is at least partially parallel to the support structure 17 is directed and directed parallel to this Area with the support structure 17, for example not over shown screws is attached.
  • the feed channel 12 tapers in the transition to the inlet duct 3, accordingly the discharge duct 13 widens when it exits the outlet duct 5 out.
  • FIG 4 is a section through a Combustion chamber 11 shown in the area of a support structure 17.
  • a heat shield arrangement 20 is provided on the support structure 17 a plurality of heat shield components 1 and the heat shield components 1 fastening fastening components 21, in the form of chilled screws.
  • the heat shield component 1 is directed along a major axis 32 which is substantially perpendicular to the support structure 17.
  • the heat shield component 1 has a substantially parallel to Support structure 17 extending hot gas wall exposed to the hot gas 29 2, which has an interior 2A at least in regions limited.
  • An inlet duct directed along the main axis 32 3 for cooling fluid 4 widens in the interior 2A in Direction of the hot gas wall 2. It is closed with a cover wall 7, which passages 8 for the flow of cooling fluid 4 has.
  • the cover wall 7 is essentially parallel directed to the hot gas wall 2 and extends substantially over their entire extent. That through the culverts 8 flowing cooling fluid 4 bounces on the inner surface 16 of the hot gas wall 2 and causes impingement cooling there.
  • the hot gas wall 2 has cooling fins on the inner surface 16 15 or similar elements that improve heat transfer on which is an increase in heat transfer from the hot gas wall 2 condition on the cooling fluid 4. From the inner surface 16 the heated cooling fluid 4 passes through an essentially Exhaust duct 5 running parallel to the main axis 32 from the Interior 2A of the heat shield component 1 out. That for cooling of the heat shield component 1 used cooling fluid 4 arrives thus complete, i.e. without loss, from the heat shield component 1 out again.
  • the outlet duct 5 is preferably executed concentrically.
  • the hot gas wall 2 has one Wall thickness between 3 mm to 5 mm, so that due to less Temperature differences in it from the heat shield components 1 constructed heat shield arrangement 20 a high load cycle resistance having.
  • the heat shield components 1 can also be attached individually due to the simple attachment assemble and disassemble from the combustion chamber 11. Because of their simple geometry also makes them easy to use coat.
  • a discharge duct is connected to the outlet duct 5 13, which can be designed, for example, as a tube and is welded to the support structure 17.
  • the discharge channel 13 preferably leads to a burner 25 of the gas turbine system 10.
  • the discharge channel 13 can also be a cast component the support structure 17.
  • the heat shield component has for attachment to the support structure 17 1 on a substantially parallel to the main axis 32 extending outer wall 14 a holding stage 19A. At this Holding stage 19A is located along a main axis 33 Fastening component 21 with a head part 22. A head part 23 adjoins the head part 22, which the support structure 17 penetrates and on this with disc springs 31 is elastically attached.
  • the fastening component 21, which is preferably produced as an investment casting, has a cooling channel 24 which extends along the main axis 33 extends and leads into the combustion chamber 11. The cooling channel 24 becomes from a running along the support structure 17 Supply channel 12 fed with cooling fluid 4. That through the Fastening component 21 flowing cooling fluid 4 cools it and thus offers adequate protection against the Hot gas 29.
  • the invention is characterized by a heat shield component , which is preferably designed as a precise casting (investment casting) and a complete return of cooling fluid guaranteed. Bounces inside the heat shield component Cooling fluid on the entire inner surface of the hot gas exposed hot gas wall, making this an effective Experiences cooling.
  • the heated cooling fluid in particular compressor air, is through an outlet channel from the heat shield component led out and preferably a burner fed to the gas turbine plant.
  • the heat shield element is complete Return of cooling fluid diverted from the compressor air back into the main stream of compressor air. this leads to a significant increase in the efficiency of the gas turbine system.

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 à effet de bouclier thermique (1) à recyclage du fluide de refroidissement comportant une paroi pour gaz chauds (2) à refroidir, un canal d'admission (3) pour le fluide de refroidissement (4) et un canal de sortie (5) pour le fluide de refroidissement (4). Le canal d'admission (3) est orienté en direction de la paroi pour gaz chauds (2) et s'élargit en direction de ladite paroi pour gaz chauds (2). L'invention concerne en outre un système de bouclier thermique (20) qui revêt un élément (11) guidant les gaz chauds, notamment la chambre de combustion (11) d'une installation de turbine à gaz (10) et une pluralité d'éléments à effet de bouclier thermique (1) à recyclage du fluide de refroidissement.

Claims (16)

  1. Elément (1) formant bouclier thermique et comprenant une chambre (2A) intérieure qui est délimitée, dans certaines parties, par une paroi (2) soumise à du gaz chaud et à refroidir, un canal (3) d'entrée pour l'entrée de fluide (4) de refroidissement dans la chambre (2A) intérieure et un canal (5) de sortie pour le retour du fluide (4) de refroidissement hors de la chambre (2A) intérieure, le canal (5) de sortie pouvant communiquer avec un canal (13) d'évacuation pour un retour du fluide de refroidissement,
       caractérisé en ce que le canal (3) d'entrée est dirigé vers la paroi (2) soumise au gaz chaud et s'élargit en direction de la paroi (2) soumise au gaz chaud.
  2. Elément (1) formant bouclier thermique suivant la revendication 1, à l'intérieur (6) duquel le canal (5) de sortie entoure dans une grande mesure le canal (3) d'entrée.
  3. Elément (1) formant bouclier thermique suivant la revendication 1 ou 2, dans lequel le canal (3) d'entrée est recouvert d'une paroi (7) de couverture, qui est voisine de la paroi (2) soumise à du gaz chaud et qui comporte des traversées (8) pour le passage du fluide (4) de refroidissement.
  4. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, qui est fabriqué et notamment coulé en un métal ou en un alliage métallique.
  5. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, dans lequel il peut être envoyé de l'air (4) provenant d'un compresseur (9) au canal (3) d'entrée et, par le canal (5) de sortie, à la chambre (11) de combustion d'une installation (10) de turbine à gaz.
  6. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, comprenant une paroi (14) extérieure se raccordant à la paroi (2) soumise à du gaz chaud, la paroi (14) extérieure étant au moins par parties ondulée.
  7. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, qui comporte, pour la fixation à une structure (17) portante, une pièce (19) de fixation entourant le canal (2) d'entrée et le canal (4) de sortie.
  8. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, dans lequel la paroi (2) soumise à du gaz chaud comporte des nervures (15) de refroidissement sur sa surface (16) intérieure.
  9. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, dans lequel le canal (3) d'entrée s'évase en forme d'entonnoir.
  10. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, comprenant une paroi (14) extérieure se raccordant à la paroi (2) soumise à du gaz chaud, la paroi (14) extérieure comprenant au moins en certaines parties un épaulement (19A) de maintien.
  11. Elément (1) formant bouclier thermique suivant l'une des revendications précédentes, dans lequel la paroi (2) soumise à du gaz chaud a au moins par parties une épaisseur de paroi inférieure à 10 mm, notamment comprise entre 3 mm et 5 mm.
  12. Dispositif (20) à bouclier thermique, qui revêt un élément (11) dans lequel passe du gaz chaud, notamment une chambre de combustion d'une installation (10) de turbine à gaz et qui comporte une multiplicité d'éléments (1) formant bouclier thermique suivant la revendication 1.
  13. Dispositif (20) à bouclier thermique suivant la revendication 12, dans lequel au moins un canal (12) d'admission passe dans une aube (18) directrice d'une installation (10) de turbine à gaz.
  14. Dispositif (20) à bouclier thermique suivant la revendication 12 ou 13, dans lequel le un canal (12) d'admission et/ou le canal (13) d'évacuation est ou sont dirigé(s) sensiblement perpendiculairement à un arbre (26) d'une installation (10) de turbine à gaz.
  15. Dispositif (20) à bouclier thermique suivant l'une des revendications 12 à 14, dans lequel chaque élément (1) formant bouclier thermique comporte une paroi (14) extérieure ayant un épaulement (19A) de maintien et, pour la fixation sur une structure (17) portante, il est prévu des éléments (21) de fixation ayant respectivement une tête (22) et une tige (23), la tige (23) de chaque élément (21) de fixation étant fixée à la structure (17) portante et respectivement la tête (22) d'un élément (21) de fixation appliquant l'élément (1) formant bouclier thermique à l'épaulement (19A) de maintien en le maintenant.
  16. Dispositif (20) à bouclier thermique suivant la revendication 15, dans lequel chaque élément de fixation peut être refroidi en comportant notamment un canal (24) de refroidissement dans lequel peut passer du fluide (4) de refroidissement.
EP97944734A 1996-09-26 1997-09-24 Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds Expired - Lifetime EP0928396B1 (fr)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
DE19639630 1996-09-26
DE19639630 1996-09-26
DE19639694 1996-09-26
DE19639694 1996-09-26
PCT/DE1997/002168 WO1998013645A1 (fr) 1996-09-26 1997-09-24 Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds

Publications (2)

Publication Number Publication Date
EP0928396A1 EP0928396A1 (fr) 1999-07-14
EP0928396B1 true EP0928396B1 (fr) 2001-11-21

Family

ID=26029819

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97944734A Expired - Lifetime EP0928396B1 (fr) 1996-09-26 1997-09-24 Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds

Country Status (6)

Country Link
US (1) US6047552A (fr)
EP (1) EP0928396B1 (fr)
JP (1) JP2001504565A (fr)
DE (1) DE59706065D1 (fr)
RU (1) RU2190807C2 (fr)
WO (1) WO1998013645A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US8522557B2 (en) 2006-12-21 2013-09-03 Siemens Aktiengesellschaft Cooling channel for cooling a hot gas guiding component

Families Citing this family (40)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE29714742U1 (de) 1997-08-18 1998-12-17 Siemens AG, 80333 München Hitzeschildkomponente mit Kühlfluidrückführung und Hitzeschildanordnung für eine heißgasführende Komponente
SE9801822L (sv) * 1998-05-25 1999-11-26 Abb Ab Förbränningsanordning
US6142734A (en) * 1999-04-06 2000-11-07 General Electric Company Internally grooved turbine wall
DE10003728A1 (de) * 2000-01-28 2001-08-09 Siemens Ag Hitzeschildanordnung für eine Heißgas führende Komponente, insbesondere für Strukturteile von Gasturbinen
EP1245792A1 (fr) * 2001-03-30 2002-10-02 Siemens Aktiengesellschaft Virole de turbine refroidie et procédé pour sa fabrication
EP1247943A1 (fr) * 2001-04-04 2002-10-09 Siemens Aktiengesellschaft Segment de virole réfroidi pour turbine à gaz
EP1271056A1 (fr) 2001-06-20 2003-01-02 Siemens Aktiengesellschaft Chambre de combustion de turbine à gaz et méthode pour y amener de l'air
GB0117110D0 (en) 2001-07-13 2001-09-05 Siemens Ag Coolable segment for a turbomachinery and combustion turbine
DE10233805B4 (de) * 2002-07-25 2013-08-22 Alstom Technology Ltd. Ringförmige Brennkammer für eine Gasturbine
EP1389692A1 (fr) * 2002-08-16 2004-02-18 Siemens Aktiengesellschaft Dispositif de fixation autobloquant
ES2278847T3 (es) * 2002-08-16 2007-08-16 Siemens Aktiengesellschaft Tornillo refrigerable interiormente.
EP1420208A1 (fr) * 2002-11-13 2004-05-19 Siemens Aktiengesellschaft Chambre de combustion
EP1431661A1 (fr) * 2002-12-19 2004-06-23 Siemens Aktiengesellschaft Corps de guidage d'écoulement
ES2307834T3 (es) * 2003-01-29 2008-12-01 Siemens Aktiengesellschaft Camara de combustion.
US7093441B2 (en) * 2003-10-09 2006-08-22 United Technologies Corporation Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume
EP1672281A1 (fr) * 2004-12-16 2006-06-21 Siemens Aktiengesellschaft Elément de protection thermique
JP4453021B2 (ja) * 2005-04-01 2010-04-21 セイコーエプソン株式会社 半導体装置の製造方法及び半導体製造装置
EP1715271A1 (fr) * 2005-04-19 2006-10-25 Siemens Aktiengesellschaft Bouclier thermique, chambre de combustion et turbine à gaz
EP1724526A1 (fr) 2005-05-13 2006-11-22 Siemens Aktiengesellschaft Coquille de turbine à gaz, turbine à gaz et procédé de démarrage et d'arrêt d'une turbine à gaz
US20070245710A1 (en) * 2006-04-21 2007-10-25 Honeywell International, Inc. Optimized configuration of a reverse flow combustion system for a gas turbine engine
EP2049840B1 (fr) * 2006-08-07 2018-04-11 Ansaldo Energia IP UK Limited Chambre de combustion d'une installation de combustion
WO2008017551A2 (fr) * 2006-08-07 2008-02-14 Alstom Technology Ltd Chambre de combustion d'une installation d'incinération
JP4407685B2 (ja) 2006-10-11 2010-02-03 セイコーエプソン株式会社 半導体装置の製造方法および電子機器の製造方法
JP4362834B2 (ja) * 2006-10-11 2009-11-11 セイコーエプソン株式会社 半導体装置の製造方法、電子機器の製造方法および半導体製造装置
EP1998115A1 (fr) * 2007-05-29 2008-12-03 Siemens Aktiengesellschaft Canal de refroidissement destiné à refroidir un composant véhiculant un gaz chaud
FR2921463B1 (fr) * 2007-09-26 2013-12-06 Snecma Chambre de combustion d'une turbomachine
DE102007062699A1 (de) * 2007-12-27 2009-07-02 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerauskleidung
US8240988B2 (en) * 2008-03-26 2012-08-14 Siemens Energy, Inc. Fastener assembly with cyclone cooling
DE102008028025B4 (de) * 2008-06-12 2011-05-05 Siemens Aktiengesellschaft Hitzeschildanordnung
EP2591881A1 (fr) * 2011-11-09 2013-05-15 Siemens Aktiengesellschaft Dispositif, procédé et vis en fonte pour l'échange sécurisé de plaques de bouclier thermique de turbines à gaz
EP2613080A1 (fr) * 2012-01-05 2013-07-10 Siemens Aktiengesellschaft Chambre de combustion d' une chambre de combustion annulaire pour une turbine à gaz
EP2693121B1 (fr) * 2012-07-31 2018-04-25 Ansaldo Energia Switzerland AG Rugosité proche de la paroi pour dispositifs d'amortissement réduisant les oscillations de pression dans les systèmes de combustion
US9322334B2 (en) * 2012-10-23 2016-04-26 General Electric Company Deformable mounting assembly
EP2728255A1 (fr) * 2012-10-31 2014-05-07 Alstom Technology Ltd Agencement de segment de gaz chaud
EP3105425B1 (fr) * 2014-02-13 2019-03-20 United Technologies Corporation Circuit de refroidissement pour composant de moteur à turbine à gaz, pourvu d'un élément de respiration en forme de piédestal
GB201501971D0 (en) * 2015-02-06 2015-03-25 Rolls Royce Plc A combustion chamber
US10101029B2 (en) * 2015-03-30 2018-10-16 United Technologies Corporation Combustor panels and configurations for a gas turbine engine
DE102016211613A1 (de) * 2016-06-28 2017-12-28 Siemens Aktiengesellschaft Hitzeschildanordnung einer Brennkammer mit Tellerfederpaket
RU209216U1 (ru) * 2021-08-30 2022-02-07 Антон Владимирович Новиков Теплозащитный экран для камеры сгорания газовой турбины
RU209161U1 (ru) * 2021-12-01 2022-02-03 Антон Владимирович Новиков Теплозащитный экран для камеры сгорания газовой турбины

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB849255A (en) * 1956-11-01 1960-09-21 Josef Cermak Method of and arrangements for cooling the walls of combustion spaces and other spaces subject to high thermal stresses
GB1283953A (en) * 1969-06-19 1972-08-02 Rolls Royce Wall for hot fluid streams
EP0225527A2 (fr) * 1985-12-02 1987-06-16 Siemens Aktiengesellschaft Paroi refroidie pour turbines à gaz
EP0224817B1 (fr) 1985-12-02 1989-07-12 Siemens Aktiengesellschaft Ecran de protection contre la chaleur pour éléments structuraux d'une turbine à gaz
US4820097A (en) * 1988-03-18 1989-04-11 United Technologies Corporation Fastener with airflow opening
US5216886A (en) 1991-08-14 1993-06-08 The United States Of America As Represented By The Secretary Of The Air Force Segmented cell wall liner for a combustion chamber
JP2792304B2 (ja) * 1992-01-22 1998-09-03 日本電気株式会社 集積回路用冷却装置
EP0597137B1 (fr) * 1992-11-09 1997-07-16 Asea Brown Boveri AG Chambre de combustion pour turbine à gaz
DE4244302C2 (de) * 1992-12-28 2002-08-29 Alstom Vorrichtung zur Prallkühlung
US5363654A (en) * 1993-05-10 1994-11-15 General Electric Company Recuperative impingement cooling of jet engine components
GB2298267B (en) * 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
US5782294A (en) * 1995-12-18 1998-07-21 United Technologies Corporation Cooled liner apparatus

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US7849694B2 (en) 2003-08-13 2010-12-14 Siemens Aktiengesellschaft Heat shield arrangement for a component guiding a hot gas in particular for a combustion chamber in a gas turbine
US8522557B2 (en) 2006-12-21 2013-09-03 Siemens Aktiengesellschaft Cooling channel for cooling a hot gas guiding component

Also Published As

Publication number Publication date
US6047552A (en) 2000-04-11
WO1998013645A1 (fr) 1998-04-02
JP2001504565A (ja) 2001-04-03
EP0928396A1 (fr) 1999-07-14
RU2190807C2 (ru) 2002-10-10
DE59706065D1 (de) 2002-02-21

Similar Documents

Publication Publication Date Title
EP0928396B1 (fr) Element a effet de bouclier thermique a recyclage du fluide de refroidissement et systeme de bouclier thermique pour element de guidage de gaz chauds
EP1005620B1 (fr) Element constitutif d'un bouclier thermique a recirculation du fluide de refroidissement
EP1654495B1 (fr) Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour une chambre de combustion de turbine à gaz
EP1636526B1 (fr) Chambre a combustion
DE60224339T2 (de) Kühleinsatz mit tangentialer Ausströmung
DE69102032T2 (de) Gasturbinenbrennkammer.
DE3200972C2 (fr)
EP0244693B1 (fr) Dispositif protecteur contre le surchauffage à gaz chaud pour les propulseurs à turbine à gaz
CH697920A2 (de) Turbinentriebwerk mit einer Brennkammerauskleidung mit wirbelluftgekühltem hinterem Ende und Kühlverfahren.
DE102005025823A1 (de) Verfahren und Vorrichtung zum Kühlen einer Brennkammerauskleidung und eines Übergangsteils einer Gasturbine
EP2084368B1 (fr) Aube de turbine
DE2844701A1 (de) Fluessigkeitsgekuehlter turbinenrotor
EP2275743A2 (fr) Chambre de combustion d'une turbine à gaz dotée d'un dispositif de démarrage pour un film de refroidissement de la paroi de la chambre de combustion
EP2711630A1 (fr) Dispositif de refroidissement d'une structure porteuse d'un bouclier thermique et bouclier thermique
DE4223733C2 (de) Verbindung von Mischrohr und Flammrohr einer Gasturbine
WO2006064038A1 (fr) Ecran thermique
WO2014177371A1 (fr) Lance de brûleur dotée d'un bouclier thermique, pour brûleur d'une turbine à gaz
EP1250555B1 (fr) Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pieces de structure de turbines a gaz
EP2808611B1 (fr) Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
DE3248439A1 (de) Gasturbinentriebwerk mit gekuehlten schaufelspitzen
EP1306521A1 (fr) Ailette de rotor pour une turbine à gaz et turbine à gaz avec des ailettes de rotor
EP0835996B1 (fr) Turbine à gaz avec combustion séquentielle
EP1507117A1 (fr) Chambre de combustion, notamment chambre de combustion pour turbine à gaz
WO2006072528A1 (fr) Turbine a gaz comportant un generateur de prerotation et procede d'utilisation d'une turbine a gaz
EP1384950B1 (fr) Chambre de combustion annulaire pour une turbine à gaz

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19990319

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): CH DE FR GB IT LI

17Q First examination report despatched

Effective date: 19990827

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE FR GB IT LI

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REF Corresponds to:

Ref document number: 59706065

Country of ref document: DE

Date of ref document: 20020221

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20020216

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020930

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20020930

26N No opposition filed
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20060912

Year of fee payment: 10

Ref country code: FR

Payment date: 20060912

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20060930

Year of fee payment: 10

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20061120

Year of fee payment: 10

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20070924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080401

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20080531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20071001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070924

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070924