EP3256783B1 - Carter guidant des gaz chauds - Google Patents

Carter guidant des gaz chauds Download PDF

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Publication number
EP3256783B1
EP3256783B1 EP16721373.5A EP16721373A EP3256783B1 EP 3256783 B1 EP3256783 B1 EP 3256783B1 EP 16721373 A EP16721373 A EP 16721373A EP 3256783 B1 EP3256783 B1 EP 3256783B1
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EP
European Patent Office
Prior art keywords
casing
wall
hot gas
slot
slots
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.)
Active
Application number
EP16721373.5A
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German (de)
English (en)
Other versions
EP3256783A1 (fr
Inventor
Milan Schmahl
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
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Siemens AG
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Publication of EP3256783A1 publication Critical patent/EP3256783A1/fr
Application granted granted Critical
Publication of EP3256783B1 publication Critical patent/EP3256783B1/fr
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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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • 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
    • F23R2900/03342—Arrangement of silo-type combustion chambers

Definitions

  • the present invention relates to a hot gas-carrying housing comprising a hot gas duct having an annular cross-section, wherein the hot gas duct is bounded inside by a housing inner wall and externally by a housing outer wall provided with at least one hot gas inlet opening is closed at its one end by a housing end wall connecting the housing inner wall and the housing outer wall together and on its other end face has an annular H disclosegasauslassö réelle, projecting from the housing inner wall, an annular fastening web radially inwardly.
  • the present invention relates to a gas turbine plant comprising a gas turbine housing accommodating a compressor and a turbine, a shaft passing through the gas turbine housing and interconnecting the compressor and the turbine, and at least one combustion chamber located outside the gas turbine housing and via a hot gas carrying housing disposed in the gas turbine housing mentioned type fluidly connected to the gas turbine housing, wherein the shaft is enclosed by the housing inner wall of the hot gas-carrying housing and between the housing inner wall and the shaft is a hollow cylindrical shaft protection jacket having an outwardly projecting and provided with a fastening web of the hot gas-carrying housing receiving circumferential groove annular shoulder, which is spaced by a predetermined amount in the radial direction of the housing inner wall of the hot gas-carrying housing.
  • Gas turbine plants with hot gas-carrying housings of the type mentioned are in the prior art, for example from the EP 1 170 464 A2 , already known. They usually include a gas turbine housing in which a compressor and a turbine are accommodated, wherein the compressor and turbine are interconnected by a shaft. Furthermore, a plurality of combustion chambers are provided, for example arranged in the form of Silobrennhuntn on both sides of the gas turbine housing and are fluidically connected via an inserted into the gas turbine housing hot gas-carrying housing with the interior of the gas turbine housing.
  • the hot gas-carrying housing comprises a hot gas channel having an annular cross section, which is bounded on the inside by a housing inner wall and on the outside by a housing outer wall which is provided with a plurality of hot gas inlet openings, the number of which normally corresponds to the number of combustion chambers.
  • an annular mounting web radially inwardly from the housing inner wall, which engages in a circumferential groove of a ring heel of a hollow cylindrical wave protection jacket, which is disposed between the housing inner wall of the hot gas-conducting housing and the shaft, of the housing inner wall of the hot gas-carrying housing is enclosed.
  • a fuel-air mixture is burned in the combustion chambers, whereupon the hot and pressurized combustion exhaust gases are introduced from the combustion chambers via the hot gas-carrying housing in the gas turbine plant and guided to the turbine, in which they set the shaft in rotation ,
  • the thermal energy of the combustion exhaust gases is converted into mechanical energy.
  • the compressor provides the combustion air required for combustion.
  • part of the compressed air emerging from the compressor is mostly used as cooling fluid for cooling thermally stressed components of the gas turbine plant.
  • a thermally stressed component is, inter alia, the housing inner wall of the hot gas-carrying housing. This is cooled by passing compressed ambient air through a cooling channel, which is defined between the wave protective jacket and the housing inner wall of the hot gas-carrying housing.
  • a problem with the cooling of the housing inner wall of the hot gas-conducting housing is that in the transition region between the housing inner wall and the fastening web due to thermal stresses often cracks mainly in the housing inner wall arise that regularly involve extensive and expensive maintenance and repair work.
  • the thermal stresses are due to large temperature differences between the fastening web and the inside of the housing inner wall, since the fastening web is arranged close to the cooling described above, while the inside of the housing inner wall is exposed to the very high temperatures of the combustion gases.
  • the present invention provides a hot gas-carrying housing of the type mentioned, which is characterized in that the fastening web is provided along its circumference with a plurality of the fastening web in the axial direction severing slots, each having at least a first slot portion, starting from extends outwardly from the free end of the fastening web.
  • Such slots which are preferably produced according to the invention by means of water jet cutting, act as relief cuts and compensate for thermally induced stresses in the transition region between the housing inner wall and the fastening web. Investigations have shown that the slot load change number can be improved many times thanks to the arrangement of such slots. If the slots are provided with a very small slot width, an additional variable cooling air consumption and a reduced wearing surface of the fastening web are also effectively avoided.
  • the slots are arranged at uniform intervals from each other in the circumferential direction, in particular in pitches in the range of 4 ° to 10 °, preferably 5 °. With such divisions, a very good relief effect was achieved.
  • the first slot sections preferably extend at least partially in the radial direction, preferably completely in the radial direction.
  • the width of the first slot sections is advantageously in the range of 0.05 and 1.5 mm, in particular in the range of 0.1 to 0.5 mm.
  • At least some of the slots in particular all slots, have a second slot section which is connected to the first slot section and in particular intersects this slot.
  • Such additional second slot sections can also have a positive effect on the Anglie load cycle number.
  • the second slot portions extend at least partially in the circumferential direction.
  • At least some of the slots, in particular all slots are formed substantially T-shaped.
  • curved slot end sections can be connected to the free ends of the second slot sections, which in particular are bent in a hook-like manner, the free ends of the slot end sections of a slot advantageously being substantially mutually facing each other.
  • recesses Preferably close to the free ends of the second slot sections recesses, in particular circular recesses. Such recesses also serve to reduce the notch effect.
  • the second slot sections and / or the slot end sections advantageously have a width of between 0.05 and 1.5 mm, in particular in the range of 0.1 to 0.5 mm.
  • the fastening web is provided with a plurality of elongated passage openings, the number of which, in particular, the number of slots corresponds, wherein the passage openings preferably cross the slots, wherein crossing through openings and slots in particular form a T-shape.
  • Such passage openings serve to guide a cooling fluid through the attachment web.
  • the fastening web is thus cooled directly.
  • the passage openings preferably extend substantially in the circumferential direction.
  • the passage openings have a width in the range of 3 to 10 mm, in particular in the range of 4 to 6 mm.
  • the free end regions of the passage openings are advantageously rounded in order to reduce the notch effect, wherein the radially outer portions of the free end regions in particular each describe the shape of a parabola half. Investigations have shown that the provision of a parabola-shaped rounding in relation to the notch effect gives better results than, for example, an arched curve.
  • the present invention further provides a gas turbine plant with a compressor and a turbine receiving gas turbine housing, a gas turbine housing passing through the compressor and the turbine interconnecting shaft and at least one arranged outside of the gas turbine housing combustion chamber, via a in the Gas turbine housing arranged hot gas-carrying housing according to the present invention is fluidly connected to the gas turbine housing, wherein the shaft is enclosed by the housing inner wall of the hot gas-conducting housing and between the housing inner wall and the shaft a hollow cylindrical shaft protection jacket is arranged, which has an outwardly projecting and with a fastening web of the hot gas-conducting housing having receiving circumferential groove provided annular shoulder, which is spaced by a predetermined amount in the radial direction of the housing inner wall of the hot gas-carrying housing.
  • a hollow cylindrical trained and provided with cooling air openings blast protective jacket is arranged between the shaft protection casing and the housing inner wall, which is fastened to the shaft protection casing.
  • a protective radiation jacket serves to prevent a transfer of heat from the housing inner wall in the direction of the shaft.
  • an impact air cooling of the housing inner wall of the hot gas-conducting housing is provided via the cooling air openings, which achieves a very effective cooling effect.
  • the jet shield is immediately adjacent to or directly attached to the annular shoulder.
  • the impingement air cooling also cools the transition region between the housing inner wall of the housing carrying the hot gas and the fastening web projecting therefrom.
  • the figures show a gas turbine plant 1 according to an embodiment of the present invention or components thereof.
  • the gas turbine plant 1 comprises a gas turbine housing 2, which accommodates a compressor 3 and a turbine 4, which are connected to one another via a shaft 5. Further includes the gas turbine plant 1 two in FIG. 1 Not shown combustion chambers, which are arranged as Silobrennhuntn side of the gas turbine housing 2 and connected via a corresponding piping 6 with a recorded in the gas turbine housing 2 hot gas-carrying housing 7 fluidly connected.
  • the hot gas-carrying housing 7 comprises a hot gas channel 8 with a substantially annular cross-section.
  • the hot gas channel 8 is bounded on the inside by a housing inner wall 9 and the outside by a housing outer wall 10, wherein on the housing outer wall 10, two hot gas inlet openings 11 are provided, which are fluidly connected to one of the piping 6 and thus to one of the combustion chambers.
  • At its one end face of the hot gas channel 8 is closed by a housing inner wall 9 and the housing outer wall 10 interconnecting housing end wall 12, and at its other end an annular H thoroughlygasauslassö réelle 13 is provided, the housing end wall 12 in the direction of the compressor 3 and the hot gas outlet 13 in the direction the turbine 4 has. From the housing inner wall 9 is adjacent to the hot gas outlet 13, a radially inwardly projecting annular attachment web 14 before.
  • the fastening web 14 is provided along its circumference with a plurality of these slitting in the axial direction slots 15 which are arranged at equal intervals, wherein a pitch t in the present case is 5 °.
  • the slots 15 are substantially T-shaped and include a radially extending first slot portion 16 which extends radially outwardly from the free end of the attachment web 14 and a second slot portion 17 connected to and intersecting the first slot portion 16 each circular recesses 18 connect to the free ends of the second slot portion 17.
  • the first slot portions 16 and the second slot portions 17 of each slot 24 presently have a width B in the range of 0.1 to 0.5 mm and are made by water jet cutting.
  • a circumferential recess 19 is formed, which makes it possible to To bring a water jet nozzle very close to the mounting bar 14.
  • the fastening web 14 is held in a circumferential groove 20 which is formed on a spaced by a predetermined amount in the radial direction of the housing inner wall 9 arranged annular shoulder 21 of a hollow cylindrical shaft protection jacket 22 which surrounds the shaft 5 in the region of the hot gas-carrying housing 7 and between the shaft 5 and the housing inner wall 9 of the hot gas-carrying housing 7 is arranged.
  • the annular recess 25 is according to FIG.
  • a first annular cooling air channel 27 is defined, through which during the normal operation of the gas turbine plant 1 cooling air is passed from the compressor 3 in the direction of the turbine 4.
  • the cooling air passage 27 is continued by cooling air holes 28 which extend axially through the annular shoulder 21 and are formed radially inwardly of the circumferential groove 15.
  • Another annular cooling air channel 29 is defined between the wave protection jacket 22 and the jet protection jacket 24 and fluidly connected via the cooling air openings 23 with the first cooling air channel 27.
  • a fuel-air mixture is burned in the combustion chambers, wherein the combustion chambers are supplied by the compressor 3 with compressed ambient air.
  • the hot and pressurized combustion gases generated in the combustion chambers are transmitted via the piping 6 and the hot gas inlet openings 11 introduced into the hot gas-carrying housing 7, then flow through the hot gas channel 8 and are introduced through the hot gas outlet 13 in the direction of the turbine 4 in the gas turbine housing 2.
  • the thermally heavily loaded by the contact with the hot combustion gases housing inner wall 9 of the hot gas-carrying housing 7 is cooled by cooling air, which, while it flows through the first cooling air channel 27, absorbs heat from the housing inner wall 9 and, after receiving the annular shoulder 21 of the wave protection jacket 22nd trained cooling air holes 28 has happened, is discharged in the direction of the turbine 4.
  • a supplementary cooling of the housing inner wall 9 is achieved by an impingement air cooling, which is caused by a cooling air flow, which is passed through the second cooling air channel 29 and directed through the cooling air openings 23 directly against areas of the housing inner wall 9.
  • FIGS. 6 to 8 show views of the mounting web 14 with alternatively formed slots.
  • the slots 30 according to FIG. 6 each comprise a first slot portion 31 and a second slot portion 32, the formation of which substantially corresponds to that of the slot portions 16 and 17 of the slots 15.
  • To the free ones Ends of the second slot sections 32 are each followed by hook-shaped bent slot end sections 33, the free ends of which face each other substantially.
  • the slots 34 comprise a first slot portion 35 which extends radially outwardly from the free end of the attachment web 14, a second slot portion 36 connected to and crossing the first slot portion 35, two hook-shaped transition slot portions 37 adjacent to the free ends of the second slot portion 36 and two third slot portions 38 which adjoin the transition slot portions 37 and extend substantially parallel to the first slot portion 35.
  • the slits 39 according to FIG. 8 comprise a first slot portion 40 which extends radially outwardly from the free end of the attachment web 14, a second slot portion 41 connected to and crossing the first slot portion 40, and slot end portions 42 adjacent and hook-like bent to the free ends of the second slot portion 41 Whose free ends are substantially facing each other, wherein the rounding or the radius of the Schlitzendabête 42 substantially larger than that of in FIG. 6 shown Schlitzendabterrorisme 33 is selected.
  • FIGS. 9 and 10 show an alternative embodiment of the invention in FIG. 4 shown area. Shown is the housing inner wall 9, which is provided adjacent to the H thoroughlygasauslassö réelle with a radially inwardly projecting annular attachment web 43.
  • the fastening web 43 is provided along its periphery with a plurality of these axially dividing slots 44 which extend radially outwardly from the free end of the fastening web 43 and are arranged at regular intervals at a predetermined pitch.
  • the attachment web 43 is provided with a plurality of elongate passage openings 45, the number of which corresponds to the number of slots 44, wherein the through holes 45, the slots 44 intersect and form together with these substantially a T-shape.
  • the width B of the slots 44 is present in the range of 0.1 to 0.5 mm, the width b of the through holes 45 in the range of 3 to 10 mm and the length l of the through holes 45 in the range of 20 to 40 mm.
  • the free end portions of the through holes 45 are formed rounded, each rounding present describes the shape of a semicircle.
  • the fastening web 43 is held in a circumferential groove 46, which is formed at a spaced by a predetermined amount in the radial direction of the housing inner wall 9 arranged annular shoulder 47 of a hollow cylindrical shaft protection jacket 48 which surrounds the shaft 5 in the region of the hot gas-carrying housing 7 and between the shaft 5 and the housing inner wall 9 of the hot gas-carrying housing 7 is arranged.
  • a first annular cooling air channel 52 is defined, through which cooling air is conducted from the compressor 3 in the direction of the turbine 4 during the normal operation of the gas turbine plant 1.
  • the cooling air channel 52 is continued by the passage 45 provided on the attachment web 43 in the direction of the turbine 4.
  • Another annular cooling air channel 53 is defined between the wave protection jacket 48 and the jet protection jacket 50 and fluidly connected via the cooling air openings 49 with the first cooling air channel 52.
  • FIG. 9 illustrated variant has the advantage over the variant shown in Figure 4, that the fastening web 43 is better cooled thanks to the formed thereon through holes 45. Furthermore, the impingement air cooling also acts in an area near the transition area Housing inner wall 9 and fastening web 43, since the blast protective jacket 50 is fixed directly on the annular shoulder 47.
  • FIG. 11 shows an alternative embodiment of formed on the mounting web 43 through holes 54.
  • the through holes 54 differ from the in FIG. 10 represented passage openings 45, that the curves of the free end portions of the through holes 54 in the region of their radially outer portions each describe the shape of a parabolic half. Such rounding is advantageous in terms of reducing the notch effect.

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

Claims (18)

  1. Enveloppe (7) conduisant des gaz chauds et comprenant un canal (8) pour des gaz chauds de section transversale annulaire, le canal (8) pour des gaz chauds étant délimité à l'intérieur par une paroi (9) intérieure de l'enveloppe et à l'extérieur par une paroi (10) extérieure de l'enveloppe pourvue d'au moins une ouverture (11) d'entrée des gaz chauds, étant fermée à l'un de ses côtés frontaux par une paroi (12) frontale de l'enveloppe reliant entre elles la paroi (9) intérieure de l'enveloppe et la paroi (10) extérieure de carcasse et à son autre côté frontal ayant une ouverture (13) annulaire de sortie des gaz chauds, dans laquelle, de la paroi (9) intérieure de carcasse, fait saillie vers l'intérieur radialement, une nervure (14; 43) annulaire de fixation, dans laquelle
    la nervure (14; 43) de fixation est pourvue, le long de son pourtour, de plusieurs fentes (15; 30; 34; 39; 44), qui séparent, dans la direction axiale, la nervure (14; 43) de fixation et qui ont chacune au moins une première partie (16; 31; 35; 40) de fente, qui s'étend vers l'extérieur à partir de l'extrémité libre de la nervure (14; 43) de fixation.
  2. Enveloppe (7) suivant la revendication 1, caractérisée en ce que les fentes (15; 30; 34; 39; 44) sont équidistantes les unes des autres, notamment suivant des pas (t) dans la plage de 4° à 10°, de préférence de 5°.
  3. Enveloppe (7) suivant l'une des revendications précédentes, caractérisée en ce que les premières parties (16; 31; 35; 40) de fente s'étendent, au moins en partie, dans la direction radiale.
  4. Enveloppe (7) suivant l'une des revendications précédentes, caractérisée en ce que les premières parties (16; 31; 35; 40) de fente ont une largeur (B) comprise entre 0,05 et 1,5 mm, notamment dans la plage de 0,1 à 0,5 mm.
  5. Enveloppe (7) suivant l'une des revendications précédentes, caractérisée en ce qu'au moins certaines des fentes (15; 30; 34; 39), notamment toutes les fentes, ont une deuxième partie (17; 32; 36; 41) de fente reliée à la première partie (16; 31; 35; 40) de fente, notamment la croisant.
  6. Enveloppe (7) suivant la revendication 5, caractérisée en ce que les deuxièmes parties (17; 32; 36; 41) de fente s'étendent, au moins en partie, dans la direction périphérique.
  7. Enveloppe (7) suivant la revendication 5 ou 6, caractérisée en ce qu'au moins certaines des fentes (15; 30; 34; 39), notamment toutes les fentes, sont sensiblement en forme de T.
  8. Enveloppe (7) suivant l'une des revendications 5 à 7, caractérisée en ce que des parties (33; 42) d'extrémité de fente incurvées, notamment des parties d'extrémité de fente de type en crochet, se raccordent aux extrémités libres des deuxièmes parties (32; 41) de fente.
  9. Enveloppe (7) suivant la revendication 8, caractérisée en ce les extrémités libres des parties (33; 42) d'une fente (30; 39) sont tournées sensiblement l'une vers l'autre.
  10. Enveloppe (7) suivant l'une des revendications 5 à 7, caractérisée en ce qu'aux extrémités libres des deuxièmes parties (17) de fente, se raccordent des évidements (18), notamment des évidements circulaires.
  11. Enveloppe (7) suivant l'une des revendications 5 à 10, caractérisée en ce que les deuxièmes parties (17; 32; 36; 41) de fente et/ou les parties (33; 42) d'extrémité de fente ont une largeur comprise entre 0,05 et 1,5 mm, notamment dans la plage de 0,1 à 0,5 mm.
  12. Enveloppe (7) suivant l'une des revendications 1 à 4, caractérisée en ce que la nervure (43) de fixation est pourvue de plusieurs boutonnières (45; 54), dont le nombre correspond au nombre de fentes (44), les boutonnières (45; 54) croisant de préférence les fentes (44), des boutonnières (45; 54) et des fentes (44) s'entrecroisant l'une l'autre donnant notamment une forme en T.
  13. Enveloppe (7) suivant la revendication 12, caractérisée en ce que les boutonnières (45; 54) s'étendent sensiblement dans la direction périphérique.
  14. Enveloppe (7) suivant la revendication 12 ou 13, caractérisée en ce que les boutonnières (45; 54) ont une largeur (b) dans la plage de 3 à 10 mm, notamment dans la plage de 4 à 6 mm.
  15. Enveloppe (7) suivant l'une des revendications 12 à 14, caractérisée en ce que les régions d'extrémité libre des boutonnières (45; 54) sont arrondies, les parties, disposées à l'extérieur radialement, des régions d'extrémité libre décrivant notamment chacune la forme d'une demie parabole.
  16. Installation (1) de turbine à gaz, comprenant une carcasse (2) de turbine à gaz, recevant un compresseur (3) et une turbine (4), un arbre (5), traversant la carcasse (2) de la turbine à gaz et reliant entre eux le compresseur (3) et la turbine (4) et au moins une chambre de combustion, disposée à l'extérieur de la carcasse (2) de la turbine à gaz et raccordée par une enveloppe (7) conduisant des gaz chauds, disposée dans la carcasse (2) de la turbine à gaz suivant l'une des revendications précédentes, en technique d'écoulement, à la carcasse (2) de la turbine à gaz, l'arbre (5) étant entouré de la paroi (9) intérieure de l'enveloppe (7) conduisant les gaz chauds et il est disposé, entre la paroi (7) intérieure de l'enveloppe et l'arbre (5), une chemise (22; 49) de protection d'arbre en forme de cylindre creux, qui a un ressaut (21; 47) annulaire, pourvu d'une rainure (20; 46) périphérique recevant la nervure (14; 43) de fixation de l'enveloppe conduisant des gaz chauds, et qui est à une distance, d'une valeur définie à l'avance, dans la direction radiale de la paroi (9) intérieure de l'enveloppe (7) conduisant du gaz chaud.
  17. Installation (1) de turbine à gaz suivant la revendication 16, caractérisée en ce qu'entre la chemise (22; 48) de protection d'arbre et la paroi (9) intérieure de l'enveloppe, est disposée une chemise (24; 50) de protection vis-à-vis du rayonnement, qui est constituée sous la forme d'un cylindre creux, qui est pourvue d'ouïes (23; 49) d'air de refroidissement et qui est fixée à la chemise (22; 48) de protection d'arbre.
  18. Installation (1) de turbine à gaz suivant la revendication 17, caractérisée en ce que la chemise (50) de protection vis-à-vis du rayonnement est fixée au voisinage immédiat du ressaut (47) annulaire ou directement sur celui-ci.
EP16721373.5A 2015-04-28 2016-04-21 Carter guidant des gaz chauds Active EP3256783B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102015207760.8A DE102015207760A1 (de) 2015-04-28 2015-04-28 Heißgasführendes Gehäuse
PCT/EP2016/058891 WO2016173920A1 (fr) 2015-04-28 2016-04-21 Carter guidant des gaz chauds

Publications (2)

Publication Number Publication Date
EP3256783A1 EP3256783A1 (fr) 2017-12-20
EP3256783B1 true EP3256783B1 (fr) 2019-02-20

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EP16721373.5A Active EP3256783B1 (fr) 2015-04-28 2016-04-21 Carter guidant des gaz chauds

Country Status (5)

Country Link
EP (1) EP3256783B1 (fr)
CN (1) CN209637884U (fr)
DE (1) DE102015207760A1 (fr)
HU (1) HUE043070T2 (fr)
WO (1) WO2016173920A1 (fr)

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* Cited by examiner, † Cited by third party
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DE102017211866A1 (de) * 2017-07-11 2019-01-17 MTU Aero Engines AG Leitschaufelsegment mit gekrümmter Entlastungsfuge

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4413477A (en) * 1980-12-29 1983-11-08 General Electric Company Liner assembly for gas turbine combustor
DE10032454A1 (de) * 2000-07-04 2002-01-17 Man Turbomasch Ag Ghh Borsig Vorrichtung zum Kühlen eines ungleichmäßig stark temperaturbelasteten Bauteiles
EP1512489B1 (fr) * 2003-09-05 2006-12-20 Siemens Aktiengesellschaft Aube pour turbine
US7805946B2 (en) * 2005-12-08 2010-10-05 Siemens Energy, Inc. Combustor flow sleeve attachment system
EP2157284A1 (fr) * 2008-08-21 2010-02-24 Siemens Aktiengesellschaft Dispositif de turbine à gaz avec conduit de transition non cylindrique et procédé pour diriger l'écoulement sur la turbine
US8511089B2 (en) * 2009-07-31 2013-08-20 Rolls-Royce Corporation Relief slot for combustion liner

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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CN209637884U (zh) 2019-11-15
EP3256783A1 (fr) 2017-12-20
HUE043070T2 (hu) 2019-08-28
DE102015207760A1 (de) 2016-11-03
WO2016173920A1 (fr) 2016-11-03

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