EP3781794B1 - Turbinenringanordnung mit zwischensektordichtung - Google Patents

Turbinenringanordnung mit zwischensektordichtung Download PDF

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Publication number
EP3781794B1
EP3781794B1 EP19722665.7A EP19722665A EP3781794B1 EP 3781794 B1 EP3781794 B1 EP 3781794B1 EP 19722665 A EP19722665 A EP 19722665A EP 3781794 B1 EP3781794 B1 EP 3781794B1
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EP
European Patent Office
Prior art keywords
groove
sealing
ring
downstream
upstream
Prior art date
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EP19722665.7A
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English (en)
French (fr)
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EP3781794A1 (de
Inventor
Clément Jarrossay
Sébastien Serge Francis Congratel
Antoine Claude Michel Etienne Danis
Clément Jean Pierre Duffau
Lucien Henri Jacques Quennehen
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP3781794A1 publication Critical patent/EP3781794A1/de
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Classifications

    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Definitions

  • a turbine ring assembly for a turbine engine includes a plurality of one-piece ring sectors of ceramic matrix composite material or metallic material and a ring support structure.
  • the field of application of the invention is in particular that of aeronautical gas turbine engines.
  • the invention is however applicable to other turbomachines, for example industrial turbines.
  • Ceramic matrix composite materials are known for their good mechanical properties which make them suitable for constituting structural elements, and for their ability to retain these properties at high temperatures.
  • the use of CMCs for various hot parts of aeronautical engines has already been envisaged, especially since CMCs have a lower density than that of refractory metals traditionally used.
  • the production of a turbine ring assembly from CMC ring sectors is described in particular in the document WO 2017/060604 .
  • the ring sectors comprise an annular base whose internal face defines the internal face of the turbine ring and an external face from which extend two parts forming legs whose ends are engaged in housings of a structure metal ring support.
  • CMC ring sectors make it possible to significantly reduce the ventilation required to cool the turbine ring.
  • seal between the gas flow stream on the inside of the ring sectors and the outside of the ring sectors remains a problem.
  • sealing tabs are arranged in grooves formed in the faces of adjacent ring sectors in order to establish a seal between the ring sectors.
  • the sealing tabs generally have small dimensions, in particular in thickness, to be easily made of CMC.
  • the invention aims to allow high temperature use of CMC turbine rings and proposes for this purpose a turbine ring assembly comprising a plurality of adjacent ring sectors forming a turbine ring extending circumferentially around in an axial direction, each ring sector having a first part forming a platform with, in a radial direction of the turbine ring, an internal face defining the internal face of the turbine ring and an external face starting from which extend in the radial direction an upstream leg and a downstream leg, each ring sector comprising a first groove in the platform present in the vicinity of the internal face of the said platform, a second groove in the platform present in the vicinity of the external face of said platform, the first and the second groove extending in the axial direction of the turbine ring, an upstream groove extending radially in the upstream leg and a downstream groove extending radially in the downstream leg, a first sealing tongue extending into the first groove, a second sealing tongue extending into the second groove, a sealing tongue upstream extending into the upstream groove and
  • the opening or openings present in the second sealing tongue namely the tongue closest to the external face of the platform of each ring sector which is intended to receive a cooling flow, allow the cooling flow to pass through this second sealing tab and impact the first sealing tab, namely the sealing most exposed to thermal fluxes. It is thus possible to cool the first sealing tongue which can then be exposed to flows of higher temperatures. Additionally, the airflow used to impact the first sealing tab also recharges the pressure in the area between the first and second sealing tabs. The risk of reintroduction of hot air from the vein into this area is thus reduced. The opposite faces of the adjacent ring sectors and the sealing tabs are therefore better protected from high temperature flows.
  • angled sealing elements makes it possible to plug the leaks which may occur at the level of the contact portions between the sealing tongues, that is to say at the level of the junctions between the grooves.
  • each of the sealing tabs and each of the bent sealing elements has a thickness of between 0.1 mm and 1 mm.
  • each of the sealing tongues and each of the bent sealing elements is made of a material chosen from one of the following materials: alloy based on cobalt, nickel and tungsten.
  • sealing tongues comprising two continuous portions forming an angle between them, it is possible to prevent leaks at the junction of two grooves, and this without having to use additional elbow joints.
  • the assembly of inter-sector ring sealing systems is thus simplified and the production cost reduced. Checking the placement of the sealing tongues is also simplified because they no longer need to cooperate with angled seals as in the prior art.
  • each of the sealing tabs has a thickness of between 0.1 mm and 1 mm.
  • each of the sealing tongues is made of a metal alloy based on nickel, cobalt or tungsten.
  • each opening present in the second sealing tab has a surface of between 0.1 mm 2 and 10 mm 2 .
  • each opening present in the second sealing tongue is completely surrounded by the material of said second sealing tongue.
  • each ring sector is made of ceramic material with a composite matrix.
  • the figure 1 shows a ring assembly for a high pressure turbine comprising a turbine ring 1, here made of ceramic matrix composite material (CMC) comprising a plurality of adjacent ring sectors each having an annular base or platform 12, an upstream leg 14 and a downstream leg 16 which each extend radially projecting outwards from the platform 12.
  • the turbine ring 1 surrounds a set of rotating blades 5.
  • the ring set of the invention may also be formed by other turbine ring assemblies such as, for example, a turbine ring assembly comprising stationary gas turbine nozzle sector vanes.
  • the platform is a platform of a distributor and the upstream and downstream tabs 14, 16 can carry sealing means and/or fixing means in order to come into leaktight contact with the casing.
  • the turbine ring 1 is formed from a plurality of adjacent ring sectors 10, the figure 1 being a view in radial section along a plane passing between two contiguous ring sectors.
  • the arrow D A indicates the axial direction with respect to the turbine ring 1 while the arrow D R indicates the radial direction with respect to the turbine ring 1.
  • Each ring sector 10 has a section substantially in the shape of an inverted Pi ( ⁇ ) with an annular base or platform 12, the internal face 12a of which may be coated with a layer of abradable material and/or with a thermal barrier (not shown on the figure 1 ).
  • the inner face 12a defines the gas stream flow path in the turbine.
  • Upstream and downstream tabs 14, 16 extend from the outer face 12b of the platform 12 in the radial direction D R .
  • upstream and downstream are used here in reference to the direction of flow of the gas stream in the turbine (arrow F).
  • the ring support structure 3 which is integral with a turbine casing 30 comprises an annular upstream radial flange 32 comprising a lip 34 on its face facing the upstream tabs 14 of the ring sectors 10, the lip 34 being in support on the external face 14a of the upstream tabs 14.
  • the ring support structure comprises an annular downstream radial flange 36 comprising a lip 38 on its face facing the downstream tabs 16 of the ring sectors 10, the lip 38 both resting on the outer face 16a of the downstream legs 16.
  • each ring sector 10 The lugs 14 and 16 of each ring sector 10 are mounted between the annular flanges 32 and 36 and held therebetween by locking pins. More specifically and as illustrated in the figure 1 , pins 50 are engaged both in the annular upstream radial flange 32 of the ring support structure 3 and in the upstream lugs 14 of the ring sectors 10. For this purpose, the pins 50 each respectively pass through an orifice 33 formed in the annular upstream radial flange 32 and an orifice 15 formed in each upstream lug 14, the orifices 33 and 15 being aligned when mounting the ring sectors 10 on the ring support structure 3.
  • pins 51 are engaged both in the annular downstream radial flange 36 of the structure of ring support 3 and in the downstream lugs 16 of the ring sectors 10.
  • the pins 51 each pass respectively through an orifice 37 made in the annular downstream radial flange 36 and an orifice 17 made in each downstream lug 16, the orifices 37 and 17 being aligned when mounting the ring sectors 10 on the ring support structure 3.
  • each ring sector 10 is provided with a first sealing tongue 21 which here extends horizontally over almost the entire length of the platform 12, with a second sealing tongue 20 arranged above the first horizontal in the radial direction D R and which here extends horizontally over part of the length of the platform 12, an upstream sealing tab 22 which extends mainly along the upstream tab 14 and a tab d downstream seal 23 which extends mainly along the downstream leg 16.
  • each sealing tab is housed in grooves facing each other in the facing edges of two neighboring ring sectors.
  • each ring sector 10 comprises a first groove 41 which here extends horizontally in the platform 12 in the vicinity of the internal face 12a thereof and in which is housed the first sealing tongue 21, a second groove 40 which here extends horizontally in the platform 12 in the vicinity of the outer face 12b of the latter and above the groove 41 in the radial direction D R , in which the second sealing tongue 20 is housed, a upstream groove 42 formed in the upstream leg 14 in which is housed the upstream sealing tongue 22 and a downstream groove 43 formed in the downstream leg 16 and in which the downstream sealing tongue 23 is housed.
  • the second sealing tongue 20 is in contact at one end with the tongue of watertight upstream tee 22 and in contact at the other end with the downstream tongue 23.
  • the downstream groove 43 opens into the first groove 41 so that the radially inner end of the sealing tongue downstream 23 is in contact with the first sealing tab 21. Leaks are thus reduced by superimposing the tabs.
  • the figure 1 , 2A and 2B illustrate a single ring sector 10 in which the tongues 20, 21, 22 and 23 are partially inserted respectively into the grooves 40, 41, 42 and 43.
  • the part of the tongues 20, 21, 22 and 23 projecting from the sector ring 10 ( figure 2B ) are introduced into corresponding grooves made in the neighboring ring sector (not shown on the figure 1 , 2A and 2B ).
  • the tabs 20, 21, 22 and 23 are for example metallic and are preferably mounted with cold play in the grooves 40, 41, 42 and 43 in order to ensure the sealing function at the temperatures encountered in service.
  • the sealing tabs can be made of a metal alloy based on nickel, cobalt or tungsten.
  • first sealing element or elbow joint 24 is housed both in the upstream vertical groove 42 and in the second groove 40 while a second sealing element or elbow joint 25 is housed both in the first groove 41 and in the downstream vertical groove 43.
  • Elbow joints 24 and 25 may be formed from bent sheets of metal.
  • the elbow joints can be made of a metal alloy based on nickel, cobalt or tungsten.
  • the elbow joints 24 and 25 are partially introduced respectively into the grooves 42 and 40 and into the grooves 41 and 43.
  • the part of the elbow joints 24 and 25 protruding of the ring sector 10 ( figure 2B ) are introduced into corresponding grooves made in the neighboring ring sector (not shown on the figure 1 , 2A and 2B ).
  • the elbow seals 24 and 25 make it possible to stop the leaks which may occur at the level of the contact portions between the sealing tabs, that is to say at the level of the orthogonal junctions of the grooves.
  • the elbow joint 24 prevents leaks at the level of the contact portion between the second tab 20 and the upstream vertical tongue 22 while the elbow joint 25 prevents leaks at the level of the contact portion between the first tongue 21 and the downstream vertical tongue 23.
  • the second horizontal tab has one or more openings.
  • the second tongue 20 comprises two openings 26 and 27.
  • the first tongue 21 is located closest to the internal face 12a of the platform 12 of the ring sector, that is to say at the most near the vein. Consequently, it is the first horizontal tongue 21 which is subjected to the highest temperatures.
  • the openings 26 and 27 made in the second tongue 20 make it possible to cool the first tongue 21.
  • the outer face 12b of the platform 12 of each ring sector receives a cooling flow F R introduced inside the ring by ventilation elements making it possible to bring the cooling flow to the external face 12b of the platform.
  • the cooling flow F R is introduced through passages 35 present in the annular upstream radial flange 32 of the ring support structure 3, the cooling flow impacting the outer surface 12b of the platform after its inlet into each ring sector 10.
  • the cooling flow can be taken from the compressor stage or come from a combustion chamber bypass airflow . Thanks to the presence of the openings 26 and 27 in the second tab 20 which is located closest to the outer face 12b of the platform 12 receiving the cooling flow F R , a fraction of the cooling flow F R can reach the first tab 21 and cool the latter.
  • the openings present in the second sealing tongue make it possible to create local leakage passages towards the first sealing tongue.
  • each opening present in the second sealing tongue is preferably entirely surrounded by the material of the tongue as illustrated in the figure 2A in order to maintain a continuity of material on the entire length of the tongue and, therefore, to limit leaks at the level of the openings.
  • each opening has a surface of between 1 mm 2 and 10 mm 2 . It is thus possible to increase the temperature of the gases circulating in the stream on the side of the internal face 12a of the platform of the ring sectors without risking damaging the sealing tongue most exposed to the heat fluxes, namely the first horizontal tab 21.
  • the number and/or the shape of the openings made on the second tongue are defined according to the cooling needs of the first horizontal tongue.
  • the picture 3 shows a turbine ring assembly in accordance with another embodiment of the invention.
  • the ring support metal structure 3 and the ring sectors 10 forming the turbine ring 1, here in ceramic matrix composite (CMC) material are identical to those already described below. before in relation to figure 1 , 2A and 2B and will not be described here again for simplicity.
  • CMC ceramic matrix composite
  • the turbine ring assembly shown in the figure 3 , 4A and 4B differs from the turbine ring assembly previously described in connection with the figure 1 , 2A and 2B in that certain sealing tongues comprise two portions forming an angle between them so as to prevent leaks at the junction of two grooves in the ring sectors, and this without having to use additional elbow joints as in the mode of previous achievement.
  • each ring sector 10 is provided with a first sealing tongue 61 which extends over almost the entire length of the platform 12, with a second sealing tongue 60 arranged above the first tongue in the direction radial D R and which extends over part of the length of the platform 12, an upstream sealing tongue 62 which extends mainly along the upstream leg 14 and a downstream sealing tongue 63 which extends mainly along the downstream leg 16.
  • each sealing tab is housed in grooves facing each other in the facing edges of two neighboring ring sectors.
  • each ring sector 10 comprises a first groove 41 extending here horizontally in the platform 12 in the vicinity of the internal face 12a of the latter, a second groove 40 extending here horizontally in the platform 12 in the vicinity of the external face 12b of the latter and above the groove 41 in the radial direction D R , an upstream groove 42 formed in the upstream leg 14 and a downstream groove 43 formed in the downstream leg.
  • the second groove 40 opens on one side into the radially inner part of the upstream groove 42 and on the other side into the radially inner part of the downstream groove 43.
  • the downstream groove 43 also opens into the first groove 41.
  • the upstream sealing tongue 62 comprises first and second continuous portions 620 and 621 forming an angle between them, the first portion 620 extending into the upstream groove 42 and the second portion 621 extending partially into the second groove 40.
  • the second sealing tongue 60 comprises first and second continuous portions 600 and 601 forming an angle between them, the first portion 600 extending into the second groove 40 and the second portion 601 partially extending into the downstream groove 23, the second portion 621 of the upstream sealing tongue 22 overlapping the first portion 600 of the second sealing tongue 20.
  • the downstream sealing tongue 23 comprises first and second continuous portions 630 and 631 forming an angle between them, the first portion 630 extending into the downstream groove 43 and the second portion 631 extending partially into the first groove 41.
  • the second portion 601 of the second tongue d sealing 20 overlaps the first portion 630 of the downstream sealing tongue 23 while the second portion 631 of the downstream sealing tongue 23 overlaps the first sealing tongue 21.
  • the figure 3 , 4A and 4B illustrate a single ring sector 10 in which the tongues 60, 61, 62 and 63 are partially inserted respectively into the grooves 40, 41, 42 and 43.
  • the part of the tongues 60, 61, 62 and 63 projecting from the sector of ring 10 ( figure 4B ) are introduced into corresponding grooves made in the neighboring ring sector (not shown on the figure 3 , 4A and 4B ).
  • the sealing tabs have very small dimensions. Indeed, the sealing tabs intended to be placed between turbine ring sectors generally have a thickness between approximately 0.1 mm and 1 mm.
  • the tabs 60, 62 and 63 can be produced for example by additive manufacturing or by MIM (Metal Injection Molding) manufacturing, which makes it possible to directly form sealing tabs of very small dimensions with two continuous portions forming an angle.
  • MIM Metal Injection Molding
  • the conformation, for example by bending, of initially flat metallic material tabs having very small dimensions proves difficult, in particular as regards the control of the angle present between the two continuous portions of a tab.
  • a sealing tongue having a thickness of less than 1 mm and comprising two continuous portions forming between them an angle of between 60° and 170° can be produced by laser fusion.
  • the sealing tabs 60, 61, 62 and 63 can be made of metallic material and are preferably mounted with cold play in the grooves 40, 41, 42 and 43 in order to ensure the sealing function at the temperatures encountered. in service.
  • the sealing tabs can be made of a metal alloy based on nickel, cobalt or tungsten.
  • the second portion 621 which extends axially from the first portion 620 of the upstream sealing tongue 62, overlaps the first portion 600 of the second sealing tongue 60.
  • the second portion 601 which extends axially from the first portion 600 of the second sealing tongue 60, overlaps the first portion 630 of the downstream sealing tongue 63.
  • the second portion 631 which extends axially from the first portion 630 of the downstream sealing tongue 63, overlaps the first sealing tongue 61.
  • a double seal is produced at the base of the ring which reinforces the inter-sector seal in the ring while ensuring a redirection of the air flowing from the outer side of the ring upstream, that is to say in the moving wheel formed by the rotating blades inside the ring.
  • this is preferably made as close as possible to the internal face 12a of the platform 12 of the ring sector so that the first sealing tongue 21 is located as close as possible to the vein. This reduces the inter-sector clearance and its impact on the tip of the blades.
  • the second tab has one or more openings.
  • the second tab 60 comprises two openings 126 and 127.
  • the first tab 61 is located closest to the internal face 12a of the platform 12 of the ring sector, that is to say at the most near the vein. Consequently, it is the first tongue 61 which is subjected to the highest temperatures.
  • the openings 126 and 127 made in the second tongue 60 make it possible to cool the first tongue 61.
  • the outer face 12b of the platform 12 of each ring sector receives a cooling flow F R introduced inside the ring by ventilation elements making it possible to bring the cooling flow to the external face 12b of the platform.
  • the cooling flow F R is introduced through passages 35 present in the annular upstream radial flange 32 of the ring support structure 3, the flow cooling flow impacting the outer surface 12b of the platform after it has entered each ring sector 10.
  • the cooling flow can be taken from the compressor stage or come from combustion chamber bypass airflow. Thanks to the presence of the openings 126 and 127 in the second tab 60 which is located closest to the outer face 12b of the platform 12 receiving the cooling flow F R , a fraction of the cooling flow F R can reach the first tab 61 and cool the latter. It is thus possible to increase the temperature of the gases circulating in the stream on the side of the internal face 12a of the platform of the ring sectors without risking damaging the sealing tongue most exposed to heat fluxes, namely the first tongue 61.
  • the number and/or the shape of the openings made on the second horizontal tongue are defined according to the cooling needs of the first horizontal tongue.
  • Each opening may for example have a square or round shape.
  • the opening or openings are positioned on the second tab to lead to hot spots identified on the first tab.
  • each opening present in the second sealing tongue is preferably entirely surrounded by the material of the tongue and/or has a surface comprised between 1 mm 2 and 10 mm 2 .
  • Comparative temperature simulations were carried out by calculation by the Holder. Simulations were carried out with CMC ring sectors and sealing tabs as defined above. The simulations consisted of exposing the internal face of the ring sector platform to a reference temperature greater than 1000°C while circulating a cooling flow on the external face of the ring sector platform.
  • the second sealing tongue that is to say the sealing tongue closest to the external face of the platform of the ring sectors receiving the cooling flow, does not comprise openings.
  • the second sealing tongue comprises openings as described above.
  • the maximum temperature reached by the first sealing tab was calculated. This is reduced by more than 10° C. when the second horizontal sealing tongue has openings.
  • a reduction of approximately 30° C. has been calculated in the areas of the first sealing tongue into which the openings present in the second sealing tongue open. We see here the impact of the openings made in the second sealing tongue on the temperature reduction of the first sealing tongue.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (10)

  1. Turbinenringanordnung, die eine Vielzahl von benachbarten Ringsektoren (10) umfasst, die einen Turbinenring (1) bilden, der sich in Umfangsrichtung um eine axiale Richtung (DA) erstreckt, wobei jeder Ringsektor (10) eine Plattform (12) mit, entlang einer radialen Richtung des Turbinenrings, einer Innenseite, welche die Innenseite des Turbinenrings (1) definiert, und einer Außenseite, ausgehend von der sich entlang der radialen Richtung eine stromaufwärtige Lasche (14) und eine stromabwärtige Lasche (16) erstrecken, wobei jeder Ringsektor (10) eine erste Rille (41), die in der Plattform (12) in der Nachbarschaft der Innenseite (12a) der Plattform vorhanden ist, eine zweite Rille (40), die in der Plattform (12) in der Nachbarschaft der Außenseite (12b) der Plattform vorhanden ist, wobei die erste und die zweite Rille sich entlang der axialen Richtung des Turbinenrings erstrecken, eine stromaufwärtige Rille (42), die sich radial in der stromaufwärtigen Lasche (14) erstreckt, und eine stromabwärtige Rille (43) umfasst, die sich radial in der stromabwärtigen Lasche (16) erstreckt, wobei ein erster Dichtungslappen (21) sich in der ersten Rille (41) erstreckt, ein zweiter Dichtungslappen (20) sich in der zweiten Rille (40) erstreckt, ein stromaufwärtiger Dichtungslappen (22) sich in der stromaufwärtigen Rille (42) erstreckt, und ein stromabwärtiger Dichtungslappen (23) sich in der stromabwärtigen Rille (43) erstreckt,
    dadurch gekennzeichnet, dass der zweite Dichtungslappen (20) eine oder mehrere Öffnungen (26, 27) umfasst.
  2. Ringanordnung nach Anspruch 1, wobei die stromaufwärtige Rille (42) in der zweiten Rille (40) mündet, die stromabwärtige Rille (43) in der ersten und der zweiten Rille (41, 40) mündet und wobei jeder Ringsektor umfasst:
    - ein erstes gekrümmtes Dichtungselement (24), das zugleich in der stromaufwärtigen Rille (42) und in der zweiten Rille (40) aufgenommen ist, und
    - ein zweites gekrümmtes Dichtungselement (25), das zugleich in der ersten Rille (41) und in der stromabwärtigen Rille (43) aufgenommen ist.
  3. Ringanordnung nach Anspruch 1 oder 2, wobei jeder der Dichtungslappen (20, 21, 22, 23) und jedes der gekrümmten Dichtungselemente (24, 25) eine Dicke von zwischen 0,1 mm und 1 mm aufweist.
  4. Ringanordnung nach Anspruch 3, wobei jeder der Dichtungslappen (20, 21, 22, 23) und jedes der gekrümmten Dichtungselemente (24, 25) aus einer metallischen Legierung auf Nickel-, Kobalt- oder Wolframbasis besteht.
  5. Ringanordnung nach Anspruch 1, wobei die stromaufwärtige Rille (42) in die zweite Rille (40) mündet und die stromabwärtige Rille (43) in die erste und die zweite Rille (41, 40) mündet, und wobei:
    - der stromaufwärtige Dichtungslappen (62) einen ersten und einen zweiten ununterbrochenen Abschnitt (620, 621) umfasst, die zueinander einen Winkel bilden, wobei der erste Abschnitt (620) sich in der stromaufwärtigen Rille (42) erstreckt und der zweite Abschnitt (621) sich teilweise in der zweiten Rille (40) erstreckt,
    - der zweite Dichtungslappen (60) einen ersten und einen zweiten ununterbrochenen Abschnitt (600, 601) umfasst, die zueinander einen Winkel bilden, wobei der erste Abschnitt (600) sich in der zweiten Rille (40) erstreckt und der zweite Abschnitt (601) sich teilweise in der stromabwärtigen Rille (43) erstreckt, wobei der zweite Abschnitt (621) des stromaufwärtigen Dichtungslappens (62) den ersten Abschnitt (600) des zweiten Dichtungslappens (60) überlappt,
    - der stromabwärtige Dichtungslappen (63) einen ersten und einen zweiten ununterbrochenen Abschnitt (630, 631) umfasst, die zueinander einen Winkel bilden, wobei der erste Abschnitt (630) sich in der stromabwärtigen Rille (43) erstreckt und der zweite Abschnitt (631) sich teilweise in der ersten Rille (41) erstreckt, wobei der zweite Abschnitt (601) des zweiten Dichtungslappens (60) den ersten Abschnitt (630) des stromabwärtigen Dichtungslappens (63) überlappt und der zweite Abschnitt (631) des stromabwärtigen Dichtungslappens den ersten Dichtungslappen (61) überlappt.
  6. Ringanordnung nach einem der Ansprüche 1 bis 3, wobei jeder der Dichtungslappen (60, 61, 62, 63) eine Dicke von zwischen 0,1 mm und 1 mm aufweist.
  7. Ringanordnung nach Anspruch 6, wobei jeder der Dichtungslappen (60, 61, 62, 63) aus einer metallischen Legierung auf Nickel-, Kobalt- oder Wolframbasis besteht.
  8. Ringanordnung nach einem der Ansprüche 1 bis 7, wobei jede Öffnung (26, 27, 126, 127), die in dem zweiten Dichtungslappen (20, 60) vorhanden ist, eine Oberfläche von zwischen 0,1 mm2 und 10 mm2 aufweist.
  9. Ringanordnung nach einem der Ansprüche 1 bis 8, wobei jede Öffnung (26, 27, 126, 127), die in dem zweiten Dichtungslappen vorhanden ist, vollständig von dem Material des zweiten Dichtungslappens umgeben ist.
  10. Turbinenanordnung nach einem der Ansprüche 1 bis 9, wobei jeder Ringsektor (10) aus Keramikmaterial mit Verbundmatrix besteht.
EP19722665.7A 2018-04-16 2019-04-04 Turbinenringanordnung mit zwischensektordichtung Active EP3781794B1 (de)

Applications Claiming Priority (2)

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FR1853302A FR3080142B1 (fr) 2018-04-16 2018-04-16 Ensemble d'anneau de turbine avec etancheite inter-secteurs
PCT/FR2019/050797 WO2019202234A1 (fr) 2018-04-16 2019-04-04 Ensemble d'anneau de turbine avec etancheite inter-secteurs

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WO2023147117A1 (en) * 2022-01-28 2023-08-03 Raytheon Technologies Corporation Cooled vane with forward rail for gas turbine engine
US11773751B1 (en) 2022-11-29 2023-10-03 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating threaded insert
US11713694B1 (en) 2022-11-30 2023-08-01 Rolls-Royce Corporation Ceramic matrix composite blade track segment with two-piece carrier
US11840936B1 (en) 2022-11-30 2023-12-12 Rolls-Royce Corporation Ceramic matrix composite blade track segment with pin-locating shim kit
US11732604B1 (en) 2022-12-01 2023-08-22 Rolls-Royce Corporation Ceramic matrix composite blade track segment with integrated cooling passages
US11885225B1 (en) 2023-01-25 2024-01-30 Rolls-Royce Corporation Turbine blade track with ceramic matrix composite segments having attachment flange draft angles

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FR2869944B1 (fr) * 2004-05-04 2006-08-11 Snecma Moteurs Sa Dispositif de refroidissement pour anneau fixe de turbine a gaz
US8753073B2 (en) * 2010-06-23 2014-06-17 General Electric Company Turbine shroud sealing apparatus
US10316683B2 (en) * 2014-04-16 2019-06-11 United Technologies Corporation Gas turbine engine blade outer air seal thermal control system
US20160053633A1 (en) * 2014-08-22 2016-02-25 Rolls-Royce Corporation Seal with cooling feature
US9874104B2 (en) * 2015-02-27 2018-01-23 General Electric Company Method and system for a ceramic matrix composite shroud hanger assembly
FR3041993B1 (fr) * 2015-10-05 2019-06-21 Safran Aircraft Engines Ensemble d'anneau de turbine avec maintien axial
WO2018004583A1 (en) * 2016-06-30 2018-01-04 Siemens Aktiengesellschaft Stator vane assembly having mate face seal with cooling holes
FR3068071B1 (fr) * 2017-06-26 2019-11-08 Safran Aircraft Engines Ensemble pour la liaison par palonnier entre un carter de turbine et un element annulaire de turbomachine

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CN112004993A (zh) 2020-11-27
WO2019202234A1 (fr) 2019-10-24
US20210164366A1 (en) 2021-06-03
FR3080142B1 (fr) 2020-05-01
CN112004993B (zh) 2023-04-14
EP3781794A1 (de) 2021-02-24
FR3080142A1 (fr) 2019-10-18
US11111823B2 (en) 2021-09-07

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