• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an air and fire seal (30) designed to be fixed on a first tubular member (31) of a turbomachine, such as a discharge duct, and to bear against a second member (32) of the turbomachine, such as an intermediate casing hub. This seal comprises: an annular fixing plate (300) around a reference axis (Y); a first fire-type annular lip (301) extending from the fastening flange to a first length (L1); and a second annular airtight lip (302) extending from the fastening soleplate to a second length (L2) smaller than the first length, opposite the first lip (301). .
    公开号:FR3064029A1
    申请号:FR1752096
    申请日:2017-03-15
    公开日:2018-09-21
    发明作者:Alexandre Didier Jacon Bruno；Clement Didier Cordier Damien；Marie Come Jacques Andre Elluin Gonzague；Benjamin Kevin Lacroix Florian；Didier Edmon Andre Liberal Nabias Philippe；Julien Vitra
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN AIRCRAFT ENGINES.
    Extension request (s)
    Agent (s): CABINET CAMUS LEBKIRI Limited liability company.
    (txy AIR-FIRE SEAL AND ASSEMBLY INCLUDING SUCH A SEAL.
    FR 3 064 029 - A1 _ The invention relates to an air and fire seal (30) designed to be fixed to a first tubular member (31) of a turbomachine, such as a discharge duct , and to bear against a second member (32) of the turbomachine, such as an intermediate casing hub. This seal includes:
    - a fixing sole (300) of annular shape around a reference axis (Y);
    - a first annular lip (301) of fire stop type extending from the fixing sole over a first length (L1); and
    - A second annular air tightness lip (302) extending from the fixing sole over a second length (L2) less than the first length, opposite the first lip (301).

    i
    AIR-FIRE SEAL AND ASSEMBLY COMPRISING SUCH A SEAL
    TECHNICAL AREA
    The present invention relates generally to the field of aircraft turbomachines, such as turbofan engines with double flow and double body. The invention relates more particularly to a seal ensuring airtightness and fire between two members of a turbomachine, such as a discharge duct and an intermediate casing hub.
    STATE OF THE ART
    A double-flow turbojet engine conventionally comprises a fan streamlined by a nacelle, an annular space for primary flow and an annular space for secondary flow. The mass of air sucked in by the blower is divided into a primary flow, which circulates in the primary flow space (also called aerodynamic vein of the primary flow), and in a secondary flow, which is concentric with the primary flow and flows in the secondary flow space (also called aerodynamic vein of the secondary flow). The primary flow space passes through a primary body comprising, from upstream to downstream in the direction of gas flow, one or more compression stages, for example a low pressure compressor and a high pressure compressor, a combustion, one or more turbine stages, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
    This turbojet engine also comprises an intermediate casing, the hub of which is arranged between the casing of the low pressure compressor and the casing of the high pressure compressor. The hub of the intermediate casing can include relief valves or VBV (for “Variable Bleed Valve” in English), whose role is to regulate the flow rate at the inlet of the high pressure compressor, by evacuating part of the air outside the primary flow space.
    Figure 1 shows, in partial axial sectional view, an example of a hub 10 of an intermediate casing 11 belonging to a turbofan engine with double flow and double body. This hub 10 comprises two coaxial annular ferrules, respectively internal 12 and external 13, mutually connected by an upstream transverse flange 14 and by a downstream transverse flange 15. The upstream flange 14 is arranged downstream of the low pressure compressor 16 while the downstream flange 15 is arranged upstream of the high pressure compressor 17. The high pressure compressor 17 generally comprises a succession of rotors and stators with variable setting, making it possible to control the flow rate of the air passing through it.
    The internal annular ferrule 12 delimits the primary flow space 18 of the primary flow F1 of the turbojet engine and comprises air inlet orifices 19 distributed circumferentially around an axis X of the hub 10, this axis X being coincident with the axis of rotation of the turbojet engine. Each of the inlet orifices 19 is closed by a corresponding discharge valve 20 intended for regulating the flow rate of the high pressure compressor 17. The external annular ring 13 delimits the secondary flow space 21 of the secondary flow F2, and comprises air outlet orifices 22 arranged downstream of the downstream transverse flange 15 and distributed circumferentially around the axis X.
    Between the ferrules 12 and external 13, and between the upstream 14 and downstream 15 transverse flanges, intermediate spaces 23 are provided distributed around the axis X of the hub 10. The intermediate spaces 23 are located upstream of an inter25 vein zone ZC, commonly known as the “core zone” or “core compartment”.
    The turbojet engine further comprises discharge veins, which extend between the inlet orifices 19 and the outlet orifices 22. Each discharge vein is made upstream and downstream between the inlet orifice 19 and l 'corresponding outlet orifice 22, through one of the intermediate spaces 23 then through a discharge conduit 24. Each discharge conduit 24 comprises an intermediate orifice 25, which opens into the intermediate space 23 at the level of the upstream surface of the flange downstream transverse 15, and extends to a discharge grid 26 called "VBV grid", disposed at the outlet orifice 22. When a discharge valve 20 is in the open position, a flow of the air F3 scooped by the latter and called the discharge flow passes through the intermediate space 23, the discharge conduit 24 and then joins the secondary flow space 21 by passing through the discharge grid 26.
    Thus, when the air flow that can enter the high pressure compressor 17 is reduced, excess air in the primary flow space 18 can be evacuated in the secondary flow space 21 by these discharge veins. , thus avoiding pumping phenomena which could lead to deterioration or even complete destruction of the low pressure compressor 16.
    In the example of FIG. 1, the discharge conduits 24 are fixed on the one hand to the external shell 13 and on the other hand to the downstream transverse flange 15. They are located in the inter-vein zone ZC of the turbojet engine which has a risk of fire, due to the numerous equipment inside. It is therefore necessary to avoid any supply of fresh air to a fire contained in this zone, coming from the primary flow or the secondary flow. To achieve this, an air and fire seal can be placed between the discharge duct 24 and the external annular shell 13 on the one hand, and between the discharge duct 24 and the downstream transverse flange 15 d 'somewhere else.
    Patent application FR3036136 describes an O-ring air-fire seal arranged between the discharge conduit and the external annular ferrule of an intermediate casing hub. This seal is made of silicone and may include a superposition of different folds of fabrics, in particular glass and / or ceramic.
    However, this O-ring quickly loses its effectiveness when exposed to flame. Indeed, the temperature alters the properties of the materials constituting the seal, in particular silicone, which can lead to failure of the seal and to a rupture of the air seal.
    SUMMARY OF THE INVENTION
    The invention aims to guarantee a durable and reliable air and fire tightness, at least during the first fifteen minutes of a fire, between a first tubular member of a turbomachine and a second member of the turbomachine.
    According to a first aspect of the invention, this objective is achieved by providing an air and fire tightness seal designed to be fixed on the first tubular member and to bear against the second member, this seal comprising:
    - an annular fixing base around a reference axis;
    - a first annular lip of firebreak type extending from the fixing sole over a first length; and
    - a second annular airtightness lip extending from the fixing sole over a second length less than the first length, opposite the first lip.
    Thus, by dissociating the air-tightness function from the fire-tightness function by means of two lips arranged facing one another, the efficiency and longevity of the solution d greatly improves. sealing. The first flame-type lip acts as a barrier or shield against the flame, protecting the second air-tightening lip located behind. The second airtight lip is not exposed to the flame until the first fire-resistant lip has failed, extending its life in the event of a fire.
    In a particular embodiment, the first fire-stop type lip is located radially outermost relative to the reference axis and the second airtightness lip is located radially the most inside with respect to the reference axis. This embodiment of the seal finds particular application in a turbofan with double flow and double body between a discharge duct and an intermediate casing hub. The seal is then mounted around the discharge pipe.
    In a preferred embodiment, the seal comprises a third annular lip of the firebreak type extending from the fixing sole over a third length less than the first length and disposed radially between the first lip of the firebreak type and the second airtightness lip. The third fire-type lip constitutes an additional obstacle for the flame, which further improves the longevity of the seal.
    The device according to the invention can also have one or more of the characteristics below, considered individually or in all technically possible combinations:
    - The first lip of the fire stop type has plies of ceramic fibers coated with an elastomeric material, such as silicone;
    - The number of plies of ceramic fibers in the first lip of fireproof type is between 1 and 3;
    - The first lip of the fireproof type has a metal frame coated with an elastomeric material, such as silicone; and
    - the second airtightness lip is coated with an anti-friction fabric.
    A second aspect of the invention relates to an assembly comprising:
    - an air and fire seal according to the first aspect of the invention;
    - a first tubular member of a turbomachine, such as a discharge conduit, provided with a flange on which is fixed the joint fixing sole; and
    - A second turbomachine member, such as an intermediate casing hub, comprising a first support surface for the first fire-type lip and a second support surface for the second air-tight lip.
    Preferably, the first bearing surface of the first fire-stop type lip is perpendicular to the reference axis and the second bearing surface of the second airtightness lip is parallel to the axis reference.
    Finally, a third aspect of the invention relates to a turbomachine, such as a turbofan engine with double flow and double body, comprising an assembly according to the second aspect of the invention.
    BRIEF DESCRIPTION OF THE FIGURES
    Other characteristics and advantages of the invention will emerge clearly from the description which is given below thereof, by way of indication and in no way limiting, with reference to the appended figures, among which:
    - Figure 1, previously described, is a partial axial sectional view of an intermediate casing hub according to the prior art;
    - Figure 2 is an axial sectional view of an air-fire seal according to a preferred embodiment of the invention;
    - Figure 3 illustrates a first embodiment of the air-fire seal according to the invention; and
    - Figure 4 illustrates a second embodiment of the air seal gasket according to the invention.
    For the sake of clarity, identical or similar elements are identified by identical reference signs in all of the figures.
    DETAILED DESCRIPTION OF AT LEAST ONE EMBODIMENT
    Figure 2 shows in axial section view an air-fire seal 30 according to a preferred embodiment of the invention. The seal 30 is housed between a first member 31 of a turbomachine, such as a turbofan engine with double flow and double body, and a second member 32 of the turbomachine. It is designed to ensure air and fire tightness between a first enclosure 33a and a second enclosure 33b arranged on either side of the seal 30 and delimited, at least in part, by the first and second organs 31-32. In the example shown in FIG. 2, the first enclosure 33a is a zone of the fire risk turbojet engine and the second enclosure 33b is likely to be traversed by a flow of air.
    The first member 31, of tubular shape, occupies an orifice 34 of corresponding shape arranged in a first wall 321 of the second member 32. This orifice 34 being of dimensions slightly greater than the external dimensions of the first tubular member 31, there is a clearance 35 between the first and second organs 31-32. The seal 30 is located in the immediate vicinity of this set 35.
    The seal 30 is advantageously symmetrical about a reference axis Y, which merges with the axis of symmetry of the first tubular member 31. It comprises an annular fixing sole 300, of axis Y, and at least two lips 301 302, annular and coaxial with the fixing sole 300. The two lips 301-302 extend opposite one another from the fixing sole 300 to the second member 32.
    Preferably, the fixing sole 300 rests against a flange 310 of the first tubular member 31 and extends in a radial direction, that is to say perpendicular to the reference axis Y. The fixing sole 300 can be glued to the flange 310 prior to the assembly of the first and second members 31-32, for example by means of a silicone elastomer crosslinking at room temperature, or "RTV" (acronym for "Room Temperature Vulcanizing" in English) .
    The first lip 301, arranged in this example radially outermost with respect to the reference axis Y, is a lip of fire-stop type, that is to say that it is designed to resist a fire which rages in the first enclosure 33a and to stop the progression of this fire towards the second enclosure 33b, at least temporarily. The first lip 301 is dimensioned to come into abutment against the first wall 321 of the second member 32. The first lip 301 thus protects from fire other parts of the seal 30, in particular the second lip 302. The first wall 321 of the second member 32 is preferably oriented perpendicular to the reference axis Y.
    The second lip 302, arranged radially inward relative to the reference axis Y, constitutes an airtightness lip. Its role is to keep the second enclosure 33b under pressure by preventing the flow of air from entering the first enclosure 33a and supplying the fire contained in this zone. The second lip 302 is of length L2 less than the length L1 of the first lip 301, so as not to come into contact with the first wall 321, which would increase the mounting force of the first member 31 (fitted with the seal d sealing 30) with the second member 32. For example, the length L1 of the first lip 301 is approximately 9 mm and the length L2 of the second lip 302 is approximately 8 mm
    To ensure airtightness, the second lip 302 comes to bear against a second wall 322 of the second member 32, preferably oriented parallel to the reference axis Y. For example, this second wall 322 is constituted by an annular rib (of axis Y) set back with respect to the orifice 34 and projecting with respect to the first wall 321 in the direction of the flange 310 of the first member 31.
    Because it is significantly shorter than the first lip 301, the second lip 302 is free to slide along the second wall 322. This allows it not to be impacted by dimensional variations of the housing taking into account the axial tolerances manufacturing and compensate for any axial movements between the first and second members 31-32 during operation of the turbojet engine.
    Thanks to these arrangements, the second air sealing lip 302 is constrained radially rather than axially. The stresses are low since they are essentially due to the air pressure in the second enclosure 33b, and not to the mounting of the first and second members 31-32. The rate of deformation of the second lip 302 is therefore low in comparison with the sealing solutions of the prior art, which minimizes the risks of damage or premature aging.
    Advantageously, the second air-sealing lip 302 is inclined towards the outside by an angle a of between 5 ° and 7 ° relative to the reference axis Y and extends over its entire length. in parallel with the first lip 301 of fire stop type. In addition, as shown in FIG. 2, the free end of the first lip 301, projecting from the second lip 302, can be inclined more towards the outside, for example by an angle β between 7 ° and 16 ° (always relative to the reference axis Y). These inclinations facilitate the mounting of the first and second members 31-32 and guarantee better air-fire tightness.
    The seal 30 comprises, in this preferred embodiment of FIG. 2, a third lip 303 of the fire stop type disposed radially between the first lip 301 and the second lip 302. The length of this third lip 303 is less the length L1 of the first lip 301, for example equal to the length L2 of the second lip 302. The third lip 303 thus constitutes an additional fire barrier, which will slow down the propagation of the fire after the first lip 301 has become faulty, by forming a baffle with the second wall 322 of the second member 32. Since it is not intended to bear on one or the other of the walls of the second member 32, this third lip 303 does not increase the 'mounting effort. The third lip 303 preferably extends in parallel with the first lip 301. In other words, it is inclined towards the outside of the angle oc.
    The seal 30 can be constructed in different ways. In a first exemplary embodiment represented by FIG. 3, the seal 30 comprises ceramic fibers 40 coated with a matrix 41 in a self-extinguishing silicone elastomer. The ceramic fibers 40 are preferably in the form of a fabric, such as that sold by the company "3M" under the reference "Nextel ™ 312". Such fibers are known to confer great fire resistance but have a high stiffness, which can increase the compressive force of the joint during assembly (the first lip 301 being more or less compressed depending in particular on the dimensioning of the members 31- 32). The fixing sole 300, the first lip 301 of fire type and the third lip 303 of fire type, which are all liable to be exposed to fire, advantageously have a number of plies of ceramic fibers between 1 and 3. This range offers an excellent compromise between fire resistance and assembly effort. The second air sealing lip 302 advantageously has a lower number of plies of ceramic fibers 40, for example a single ply, in order to give it more flexibility.
    In a second exemplary embodiment, the seal 30 comprises a metal frame 42 coated with the matrix 41 in self-extinguishing silicone elastomer 3064029 ίο. The metal frame 42, for example steel, Hastelloy® or titanium, constitutes an effective fire barrier. It preferably extends in the fixing sole 300, the first lip 301 of the fire stop type (except its free end, so that the latter can flex in contact with the second member 32) and the third lip 303 of the cut type. -fire. The second air tightness lip 302 is preferably devoid of metal reinforcement in order to be able to accommodate more easily the movements and vibrations of the organs 31-32.
    In each of these exemplary embodiments, the second air sealing lip 302 can be coated with an anti-friction fabric 43 at its bearing surface, in order to slide more easily on the second wall 322 of the second organ 32. The antifriction fabric 43 is also resistant to high temperatures (up to 1100 ° C. in the event of fire) and antistatic (so as not to create sparks). The anti-friction fabric 43 is, for example, that sold by the company "DuPont" under the designation "Nomex®".
    The seal 30 of Figures 2 to 4 can be used in different places of a turbomachine. A preferred application of the seal 30 relates to the discharge conduits of a turbofan engine with double flow and double body. These conduits are intended to redirect part of the primary flow to the flow space of the secondary flow. The discharge conduits may in particular be of the same type as that described in connection with FIG. 1. With reference to this figure, each conduit comprises a first end opening into an intermediate space 23 of the hub 10 of the intermediate casing and a second end opening into the secondary flow space 21. The intermediate space 23 of the hub 10, in fluid communication with the primary flow space 18 via a discharge valve 20, is delimited by the internal annular rings 12 and external 13 on the one hand and by the transverse flanges upstream 14 and downstream 15 on the other hand. Each discharge conduit extends through the inter-vein zone or "core zone" ZC of the turbojet engine, which is reputed to be a zone at risk of fire.
    The seal 30 can thus be mounted around a discharge conduit and cooperate with the downstream transverse flange 15 of the intermediate casing hub.
    π
    In other words, in this application, the first tubular member 31 of FIG. 2 corresponds to the discharge conduit, the second member 32 corresponds to the intermediate casing hub, and more particularly to its downstream transverse flange, the first enclosure 33a corresponds to the zone core ZC of the turbojet engine and the second enclosure 33b corresponds to the intermediate space of the hub.
    The seal 30 has the advantage, by design, of not having a significant impact on the geometries of the discharge conduit and of the intermediate casing hub. Indeed, a profound change in these geometries could increase the mass and the manufacturing costs of the intermediate casing. The use of the seal 30 requires only a repositioning of the existing flange of the discharge conduit and an arrangement of the surface of the downstream transverse flange on which the second sealing lip is supported. The length of this support surface (in the axial direction of Figure 3) is at least 5 mm.
    In certain turbofan engines with double flow and double body, such as that shown partially in FIG. 1, the discharge conduits are parts belonging to the hub of the intermediate casing. They are fixed at their second end to the outer ferrule of the hub.
    In other turbojet engines, the discharge pipes belong to an extension of the intermediate casing, commonly known as a "kit engine". This intermediate casing extension conventionally comprises several shell sectors which reconstitute the secondary flow space and structural link arms allowing the passage of the easements (electrical, mechanical, hydraulic) between the nacelle and the various components of the turbojet engine (core zone especially). The discharge conduits are then pre-assembled on the shell sectors and then mounted by hand without specific tools in the intermediate casing. The seal 30 is particularly suitable for the latter type of turbojet, since it is designed to minimize the mounting effort, as described above.
    Many variants and modifications of the seal according to the invention will appear to a person skilled in the art. For example, in certain places of the turbomachine, the situation of the first and second enclosures 33a-33b can be reversed, that is to say that the first enclosure 33a is traversed by a flow of air and that the second enclosure 33b presents a risk of fire. The positions of the first fire-stop type lip 301 and of the second air-tightness lip 302 will then also be reversed. In other words, the first lip 301 of the fire stop type will be located radially the most on the inside and the second lip 302 of airtightness will be located radially the most on the outside. Finally, the lips 301-302 can be turned in the other direction, i.e. inwards.
    îo Finally, the constitution of the seal 30 is not limited to the examples of materials described above in relation to FIGS. 3 and 4. All or part of the ceramic fibers can in particular be replaced by glass fibers and elastomeric materials other than silicone can be used.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Air and fire seal (30) designed to be fixed to a first tubular member (31) of a turbomachine, such as a discharge duct (24), and to come in
    5 bearing against a second member (32) of the turbomachine, such as an intermediate casing hub (10), characterized in that it comprises:
    - a fixing sole (300) of annular shape around a reference axis (O;
    - a first annular lip (301) of fire stop type extending from the fixing sole plate over a first length (L1); and
    - a second annular lip (302) of air tightness extending from the fixing sole over a second length (L
    [2" id="c-fr-0002]
    2) less than the first length, opposite the first lip (301).
    15 2. Joint (30) according to claim 1, in which the first lip (301) of fire stop type is located radially outermost relative to the reference axis (Y) and the second lip ( 302) airtightness is located radially inward relative to the reference axis.
    20
    [3" id="c-fr-0003]
    3. Joint (30) according to claim 2, in which the first lip (301) of fire stop type and the second lip (302) of air tightness are inclined towards the outside by an angle (oc ) between 5 ° and 7 ° relative to the reference axis (Y).
    [4" id="c-fr-0004]
    4. Joint (30) according to any one of claims 1 to 3, comprising a
    25 third annular lip (303) of fire stop type extending from the fixing sole (300) over a third length less than the first length (L1) and arranged radially between the first lip (301) of fire stop and the second air sealing lip (302).
    30 5. Joint (30) according to any one of claims 1 to 4, in which the first lip (301) of firebreak type comprises plies of ceramic fibers (40) coated with an elastomeric material (41), such as silicone.
    6. Joint (30) according to claim 5, in which the number of plies of ceramic fibers (40) in the first lip (301) of fire stop type is between 1 and 3
    [5" id="c-fr-0005]
    5 7. Joint (30) according to any one of claims 1 to 4, in which the first lip (301) of fire stop type comprises a metal frame (42) coated with an elastomeric material (41), such as silicone.
    [6" id="c-fr-0006]
    8. Seal according to any one of claims 1 to 7, wherein the second air sealing lip is coated with an anti-friction fabric.
    [7" id="c-fr-0007]
    9. Assembly comprising:
    - an air and fire seal (30) according to any one of claims 1 to 8;
    15 - a first tubular member (31) of a turbomachine, such as a discharge duct (24), provided with a flange (310) on which is fixed the fixing sole (300) of the joint; and
    - a second turbomachine member (32), such as a hub (10) of intermediate casing, comprising a first bearing surface (321) of the first
    20 fire-resistant lip and a second support surface (322) of the second airtightness lip.
    [8" id="c-fr-0008]
    10. The assembly of claim 9, wherein the first bearing surface (321) of the first lip (301) of fire stop type is perpendicular to the axis of
    25 reference (Y) and in which the second support surface (322) of the second air sealing lip (302) is parallel to the reference axis (Y).
    [9" id="c-fr-0009]
    11. Turbomachine, such as a turbofan engine with double flow and double body, comprising an assembly according to one of claims 9 and 10.
    1/3
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3064029A1|2018-09-21|JOINT FOR SEALING LIGHT AND ASSEMBLY COMPRISING SUCH A JOINT
    EP1818615B1|2008-08-13|Annular combustion chamber of a turbomachine
    EP2334909B1|2012-12-05|Sealing between a combustion chamber and a turbine distributor in a turbine engine
    EP1607682B1|2016-06-08|Gas turbine
    CA2548905C|2013-09-17|Assembly of a turbine engine annular combustion chamber
    FR3036136B1|2019-07-12|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOREACTOR COMPRISING A COMPOSITE DISCHARGE DUCT
    EP1519009A1|2005-03-30|Turbomachine with cabin bleed air through a tube with ball joint
    FR3051016A1|2017-11-10|DEVICE FOR DEFROSTING AN AERONAUTICAL TURBOMACHINE SEPARATION SPOUT
    WO2016116686A1|2016-07-28|Sealing device between an injection system and a fuel injection nozzle of an aircraft turbine engine
    EP3172411B1|2018-06-20|System for supplying pressurised air installed in an aircraft turbine engine including sealing means
    FR3010154A1|2015-03-06|INTERMEDIATE CASTER SEAL PANEL FOR A DOUBLE FLOW AIRCRAFT TURBOMACHINE
    FR3012846A1|2015-05-08|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOJET AIRBORNE COMPRISING A DEFORMABLE CONDUIT OF AIR AND DEBRIS CANALIZATION
    FR3005991A1|2014-11-28|INTERFACE DEVICE BETWEEN TWO TURBOMACHINE ELEMENTS
    FR3041380B1|2019-08-23|ASSEMBLY FOR AIR CIRCULATION DEVICE FOR TURBOMACHINE
    FR3005098A1|2014-10-31|TURBOMACHINE BEARING SUPPORT COMPRISING ACCESS OPENING FOR ASSEMBLY OF SERVITUDES
    FR3074518A1|2019-06-07|CONNECTION BETWEEN A CERAMIC MATRIX COMPOSITE DISPENSER AND A METAL SUPPORT OF A TURBOMACHINE TURBINE
    FR3109961A1|2021-11-12|Improved CMC distributor for turbomachine turbine
    WO2017144805A1|2017-08-31|Rectifier for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction
    WO2021009430A1|2021-01-21|Seal for an intermediate turbomachine casing
    EP3735527B1|2022-01-12|Outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, comprising improved air-sealing and fire-resistance devices
    FR3111964A1|2021-12-31|Assembly of a combustion chamber part by overlapping another part
    FR3107725A1|2021-09-03|Assembly for an aircraft turbomachine stator, with reinforced sealing between an outer shell and a bladed stator ring surrounded by this shell
    WO2021069816A1|2021-04-15|Turbine nozzle having blading made of ceramic matrix composite through which a metal ventilation circuit passes
    FR3018097B1|2019-08-02|TURBOMACHINE ORGAN COMPRISING A METAL PIECE AND A COMPOSITE MATERIAL PART
    FR3109792A1|2021-11-05|Mounting a sealing ring on an aeronautical turbomachine
    同族专利:
    公开号 | 公开日
    FR3064029B1|2021-04-30|
    GB201803990D0|2018-04-25|
    US20180266263A1|2018-09-20|
    GB2562582A|2018-11-21|
    US20200173296A1|2020-06-04|
    US11098607B2|2021-08-24|
    US10598037B2|2020-03-24|
    GB2562582B|2022-01-05|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP2275655A2|2009-07-14|2011-01-19|Rolls-Royce plc|A flow discharge device|
    WO2016047432A1|2014-09-26|2016-03-31|三菱日立パワーシステムズ株式会社|Seal member|
    FR3036136A1|2015-05-15|2016-11-18|Snecma|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOREACTOR COMPRISING A COMPOSITE DISCHARGE DUCT|FR3098550A1|2019-07-12|2021-01-15|Safran Aircraft Engines|GASKET FOR TURBOMACHINE INTERCASE|
    FR3111670A1|2020-06-19|2021-12-24|Safran|Fire barrier between two rooms|US3965066A|1974-03-15|1976-06-22|General Electric Company|Combustor-turbine nozzle interconnection|
    US5249812A|1990-03-12|1993-10-05|John Crane Inc.|Barrier seal systems|
    JP4031590B2|1999-03-08|2008-01-09|三菱重工業株式会社|Combustor transition structure and gas turbine using the structure|
    US6860108B2|2003-01-22|2005-03-01|Mitsubishi Heavy Industries, Ltd.|Gas turbine tail tube seal and gas turbine using the same|
    JP4191552B2|2003-07-14|2008-12-03|三菱重工業株式会社|Cooling structure of gas turbine tail tube|
    US7527469B2|2004-12-10|2009-05-05|Siemens Energy, Inc.|Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine|
    JP4476152B2|2005-04-01|2010-06-09|三菱重工業株式会社|Gas turbine combustor|
    US7797948B2|2007-03-27|2010-09-21|Siemens Energy, Inc.|Transition-to-turbine seal apparatus and transition-to-turbine seal junction of a gas turbine engine|
    JP5384983B2|2009-03-27|2014-01-08|本田技研工業株式会社|Turbine shroud|
    US9322288B2|2012-11-29|2016-04-26|United Technologies Corporation|Pressure seal with non-metallic wear surfaces|
    US9835092B2|2015-06-30|2017-12-05|United Technologies Corporation|Seals for gas turbine engine nacelle cowlings|FR3036136B1|2015-05-15|2019-07-12|Safran|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOREACTOR COMPRISING A COMPOSITE DISCHARGE DUCT|
    FR3088307B1|2018-11-09|2021-03-12|Safran Nacelles|FIRE-TIGHT AIRCRAFT TURBOREACTOR NACELLE|
    US11131406B2|2019-06-24|2021-09-28|Rolls-Royce Deutschland Ltd & Co Kg|Seal for engine firewall|
    法律状态:
    2018-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-09-21| PLSC| Publication of the preliminary search report|Effective date: 20180921 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 5 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1752096A|FR3064029B1|2017-03-15|2017-03-15|AIR-FIRE SEAL AND ASSEMBLY INCLUDING SUCH A SEAL|
    FR1752096|2017-03-15|FR1752096A| FR3064029B1|2017-03-15|2017-03-15|AIR-FIRE SEAL AND ASSEMBLY INCLUDING SUCH A SEAL|
    GB1803990.9A| GB2562582B|2017-03-15|2018-03-13|Air-fire seal and assembly comprising such a seal|
    US15/920,874| US10598037B2|2017-03-15|2018-03-14|Air-fire seal and assembly comprising such a seal|
    US16/784,624| US11098607B2|2017-03-15|2020-02-07|Air-fire seal and assembly comprising such a seal|
    [返回顶部]