• 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:
    Is concerned a connection assembly comprising an air distribution housing (15) from an air inlet passage (155) to at least one duct connected to the housing (15) by at least one socket (19) mounted on an orifice (21) of a wall of the housing. This wall of the housing and an inner wall of the socket are connected by a fillet having a radius which is maximum on an angular sector (273).
    公开号:FR3058460A1
    申请号:FR1660784
    申请日:2016-11-08
    公开日:2018-05-11
    发明作者:Jean Laurent Prestel Sebastien；Marie Aubin Pierre Jouy Baptiste
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    Holder (s): SAFRAN AIRCRAFT ENGINES Simplified joint-stock company.
    Extension request (s)
    Agent (s): ERNEST GUTMANN - YVES PLASSERAUD SAS.
    CONNECTION ASSEMBLY FOR COOLING A TURBOMACHINE TURBINE.
    ) 5 /) Is concerned a connection assembly comprising a housing (15) for distributing air from an air inlet passage (155) to at least one duct connected to the housing (15) by at least one socket (19) mounted on an orifice (21) of a wall of the housing. This wall of the housing and an internal wall of the socket are connected by a connection leave having a radius which is maximum over an angular sector (273).
    FR 3 058 460 - A1
    TECHNICAL AREA
    The invention provides an assembly for connecting at least one duct with an air distribution unit.
    The invention more particularly proposes such an assembly for a clearance control system in the turbine of a turbomachine improving the connection of each duct with the housing.
    PRIOR STATE OF THE ART
    In the following, and except in special cases (such as when we talk about the socket):
    - axis or axial has the direction parallel to the axis of the turbomachine, axis around which rotates the rotary blades of this turbomachine,
    - radial has a radial direction to this axis,
    - upstream and downstream define respectively the inlet and outlet sides of the gases, including the air, which circulate in the turbomachine, generally axially,
    - interior and exterior define respective radial positions.
    Game control in a turbomachine turbine consists in controlling the distance between the ends of the movable blades of the turbine and the fixed outer casing of the turbine in order to optimize the efficiency of the turbine.
    This game control mainly consists of injecting cold air into the outer casing in a controlled manner, in order to control its expansion.
    The air is supplied to the casing via a plurality of conduits which are connected to an air distribution box.
    According to a known embodiment, the fluid connection of each duct with the distribution box is made at a side wall of the box, which comprises a socket to which one end of the pipe is fixed. The seal between the end of the conduit and the associated socket is typically provided by brazing.
    Thus, a connection assembly is known comprising sockets and an air distribution unit from an air inlet passage from the unit to ducts, each duct of this assembly being connected to the unit by a said socket mounted on an orifice in a first wall of the housing towards which the air arrives., Each socket has an axis along which extends an internal wall in contact with which air can circulate in the socket.
    In WO2013001246, the connection of the interior volume of the housing with each duct is carried out by means of an internal tube comprising a passage arranged in its cylindrical wall and which is open in the interior volume of the housing, for the circulation of air . In addition, each side wall concerned is shaped so that the edge of each orifice is curved towards the outside of the housing, to form the corresponding socket to which the internal tube is fixed, for example by soldering.
    In another situation, the sockets can be fitted into the holes in the housing.
    Problems with the air supply to the ducts arise anyway, while the air supply to the distribution box appears to be correct.
    Pressure losses have been noted. Studies attribute these pressure drops to the connections between conduits and housing.
    In existing solutions, the passage of the orifices in the side walls of the air distribution box generates pressure losses, which reduces the cooling efficiency of the outer casing. This can be explained by the fact that the cooling ramps formed by the conduits are tangential while the distribution box is generally axial. At the interface between the housing and the ramps, the elbows created tend to produce detachment of the air which reduces the cross-section of this air. The resulting increase in speed induces a large pressure drop, therefore a decrease in the total pressure in the ramps. However, this pressure is useful for efficient cooling of the outer casing. Indeed, a decrease in the total pressure in the ramps negatively impacts the air flow intended for the outer casing. The heat exchange coefficient in the housing suffers.
    The object of the invention is in particular to minimize the risks of occurrence of such a situation and more generally to promote the cooling of the outer casing, which must be favorable to the clearance control between the ends of the movable blades of the turbine and the outer casing.
    STATEMENT OF THE INVENTION
    The invention therefore proposes that the connection assembly presented above is such that said first wall of the housing and the internal wall of the socket are connected together by a connection leave having a radius which varies over at least part of the perimeter of said internal wall.
    Typically, the sockets will be of the type fitted into the orifices of the housing, one end of the corresponding duct also coming to engage in the socket concerned.
    Due to this connection leave provided on at least part of the perimeter of the internal wall of the sleeve, this internal wall may be devoid of sharp edges, at least on the side of the air inlet.
    In addition, the provision of such a "progressive" connection leave perimeter, rather than in particular a leave with an identical profile perimeter, made it possible to work on another aspect of the quality of cooling by air jets of the outer casing.
    Indeed, it turned out that being able to achieve, thanks to it, and a priori in particular where the radius is the smallest, at least one and preferably several flats located angularly, around said axis, away from 'an area of the perimeter of the socket where the radius of the connection leave tends towards a maximum, has made it possible to bring the ramps considered as close as possible to the casing, which must promote the efficiency of its cooling.
    Providing such flats on the outer wall of each socket will also facilitate the positioning of the sockets on the air distribution box. In particular, three angularly spaced flats can be produced. This will allow a practical, reliable and quick way to visually check the correct positioning of these sockets. In addition, this solution will allow the use of conventional tools for positioning the sockets.
    In particular, two opposite flats may be provided for the direction and an angularly intermediate flat for the direction.
    Given the aforementioned technical field, it is quite naturally that another aspect of the invention relates to an aircraft turbomachine characterized in that it comprises:
    - an assembly as presented above, which includes several said conduits and sockets, and
    - an outer turbine casing around an area of which the air distribution box is arranged, a second wall of which extends adjacent to said area of this outer casing, along it.
    By providing, on this turbomachine, that the radius of the connection leave tends towards a maximum at the location of a zone of the perimeter of said internal wall which is oriented towards the air inlet passage, the risks of detachment of the air, therefore the reductions in the cross-section of the air passage in the sockets, at the change of direction, when the air passes from the housing to the sockets. This will limit the pressure drops.
    And so as to position, as already mentioned, the orifice (s) of the housing, sleeve (s) and conduits concerned as close as possible to the outer turbine casing, for its cooling, the turbomachine could, in another aspect, be such that the sockets:
    - are mounted on the orifices of the housing adjacent to said second wall of the housing, and individually have an external wall provided peripherally with at least one flat which, on at least some of the mounted sockets, will be located (immediately) adjacent to said second wall of the housing.
    Furthermore, if, in addition or as an alternative, the sockets are, on the turbomachine, mounted on the orifices of the housing each having, peripherally, several flats located angularly, around said axis, away from the sector of an area of the perimeter of said internal wall where the radius of the connection leave tends towards a maximum, it will therefore be possible again:
    - facilitate the positioning of the sockets on the air distribution box,
    - increase the possibility of orienting a socket so as to place one of the flats facing said second wall of the housing, thereby reducing the distance between the socket and the outer casing to be cooled,
    - maintain the quality of the air flow entering the sockets.
    If necessary, the characteristics of the solutions presented here will be even better understood and other details and advantages of these may appear further on reading the description which follows, given by way of nonlimiting example and with reference to the appended drawings, in which :
    - Figure 1 is a schematic longitudinal section of an aeronautical turbomachine turbine equipped with an air distribution box as in the invention;
    - Figure 2 is a local external perspective view of the elements shown in Figure 1;
    - Figure 3 is a local reverse perspective view of the air distribution unit;
    - And Figures 4,5 are respectively a section along the line IV-IV of Figure 2 and a corresponding front view of the socket mounted there.
    FIG. 1 represents a part of a low pressure turbine 1 of a turbomachine 10 comprising several turbine stages stepped along the axis X of the turbomachine.
    Each stage comprises a distributor 2 with fixed blades 3 carried by an external casing 4 of the turbine, and a rotor wheel 5 mounted downstream of the distributor 2 and with rotary blades 6.
    The distributors 2 each comprise walls of revolution, respectively internal and external 8 which are connected radially by the blades 3.
    The vanes 6 rotate around the axis X, in a substantially frustoconical envelope formed by ring sectors 7 carried circumferentially end to end by the outer casing 4 of the turbine.
    The rotor vanes 6 are integral with a turbine shaft, and each comprise respectively external 9 and internal ferrules.
    The internal and external walls of revolution and the external and internal ferrules delimit between them an annular stream 11 of gas flow in the turbine.
    To control the clearance between the ends of the outer shell 9 of the rotary blades 6 of the turbine and the fixed outer casing 4, air is therefore injected onto the outer casing, in order to control its expansion according to the operating conditions of the turbine.
    Relatively cold air is supplied to the outer casing 4 via a plurality of conduits 13 which are connected to an air distribution box 15.
    Before that, the air reaches the housing 15 via a supply tube 17. In the manner of a plenum chamber, the housing 15 distributes this air to the conduits 13.
    The conduits 13 are drilled tubes (some orifices 130 are identified in Figure 2).
    The connection of each conduit 13 with the housing 15 is made at the side walls of the housing, one of which is visible in FIGS. 1,2, the opposite one 153 being visible in FIG. 3.
    The air arriving through the supply tube 17 enters the housing 15 through an air inlet passage 155 formed in one (so-called first wall) of its side walls.
    In the solution presented and illustrated, sockets 19 make it possible to link the conduits 13 and the housing 15, through orifices 21 formed in the side walls 151 or 153 of the housing.
    Each socket 19 is fitted into the corresponding orifice 21 of the housing 15, as shown in FIG. 4.
    And one end of the corresponding conduit 13 is mounted in the sleeve 19, for example by interlocking, as shown. Sealing can be ensured by soldering.
    Each socket has a through passage 190 having an internal wall 191 in contact with which air can circulate, after having reached the orifice 21 concerned.
    Figures 2,4, the arrow 23 shows on this subject the general direction of air circulation from the air inlet passage 155 towards the socket 19 concerned by figure 4. In this figure 4, the arrow 25 indicates, after inflection, the arrival of air to the corresponding orifice 21 and then into the socket.
    The transversality between the axis X1 of elongation of the housing 15 and the axis of the sockets (see axis X2 for the socket in FIGS. 4.5) has induced that, for the quality of the air circulation entering the socket 19, the first wall (here 151) of the housing is connected to the internal wall 191 of the socket by a connection leave 27 having a radius R which varies over at least part of the perimeter of the internal wall 191. This leave of connection is tangent. In FIG. 4, O has been located the position, in the place concerned, of the center of the generating arc of a circle, therefore located outside of the socket 19.
    Thus, this connection leave 27 will ensure, parallel to the axis X2, a greater flaring depth on a sector 273 of the perimeter 275 than elsewhere on this perimeter (see depths H1, H2, H3 Figure 4).
    This flaring depth is defined, parallel to the axis X2, by the radius R established between the two walls 151 and 191, perpendicular to each other, to be connected. The radius R of the connection leave 27 may change as follows, on the perimeter of the orifice 21, between the smallest radius and the largest:
    Internal 0 (D) of conduit 13 (cm)Radius R (cm) 12 to 13 0.5 to 3 15 to 16 0.5 to 4 19 to 20 0.5 to 5 25 to 26 0.5 to 7
    Thus, each conduit 13 will favorably have an internal diameter D of between 12 and 26 cm and the radius R of the connection leave 27 varies accordingly between 0.5 and 7 cm.
    The largest radius R1 can be established and constant over an angular sector (reference 273 Figures 3 and 5) between 90 ° and 135 °, preferably of the order of 120 ° to 10 °. It is in this sector that the greatest depth H1 will then be established.
    In fact, so that the air circulating in the direction 23 (FIGS. 2 and 4) bends its way towards the transverse direction 25 with limited risks of detachment entering the corresponding socket, on passing the orifice 21, the radius connection leave 27 tends towards a maximum (R1) at the location of a zone of the perimeter of the internal wall corresponding to the aforementioned sector 273 and which is oriented towards the air inlet passage 155; see for example direction 230d figures 2 and 3 and leave at the top of the illustration figure 4 or 5.
    As illustrated in FIG. 3, on a housing 15, the sockets 19, and therefore their orifices 21, are typically substantially aligned along an area of the outer casing 4, at different distances from the passage 155. As illustrated in FIG. 3, it is possible by elsewhere consider that the air inlet passage 155 and the orifice 21 of each socket 19 have centers (respectively 155a and 21a to 21d in the illustration) through which pass respective lines (230a to 230d on the illustration) which show that the air coming from the air inlet passage 155 reaches the orifices 21 of the sockets 19 in different directions. The aforementioned direction 23 is one of them.
    Given this embodiment of the housing 15 and the internal distribution of the air, it has been chosen for the purposes already mentioned that the radius (R) of each connection leave 27 is maximum (R1) over an angular sector 273 centered on the corresponding line, open towards the air inlet passage 155 from which the air arrives and between 90 and 135 °, as illustrated for two sockets in FIG. 3. An angular sector of 120 °, to within 10 °, is still preferred.
    The maximum (R1) of the radius R can be constant over the entire sector
    273.
    For their positioning, support on the housing 15 and sealing, the sockets 19 may each have peripherally an external rim 31, at the location of their external wall 29, towards the axial end where they have the connection leave.
    Away from the sector 273 of the perimeter 275 where the flaring depth is the greatest (H1), therefore from the angular zone where the radius R is maximum (R1) and can be constant, the external rim 31 is truncated by one or more flats 33a, 33b, 33c (see FIG. 3) located angularly around the axis X2 of the through passage 190.
    In this way, we will also avoid altering the efficiency in the air flow achieved via the connecting leave. In fact, at the location of this sector 273, the radius (R1) of the connection leave 27 would be truncated (therefore inappropriate) if a flat area was provided there.
    ίο
    There have been provided here two flats 33a, 33c diametrically opposite for the direction, and a flat 33b angularly intermediate between the other two, for the direction.
    Indeed, with the flat 33b located diametrically opposite the angular zone where the radius R is maximum (R1), it is easier, when positioning a socket with respect to its orifice 21, to locate the angular orientation of this socket around the axis X2. Thus, the socket is well positioned relative to the optimal direction materialized by the corresponding straight line 230a-230d and the radius R1 is oriented facing the air inlet 23.
    As for the two other flats 33a, 33c angularly intermediate between the sector 273 and the flat 33b, they can precisely be used to angularly maneuver the sleeve for its positioning, since they are diametrically opposed.
    In addition, such flats can allow the use of conventional tools (such as pliers) for positioning the sockets.
    These flats can finally make it possible to bring the conduits 13 radially closer to the outer casing 4.
    Indeed, as can be noted by comparing FIGS. 2 and 3, a transverse wall 157 (called second wall) elongated from the air distribution box 15 extends generally along the outer casing 4, so (immediately) adjacent to the zone (or part) of this casing which it thus covers, so that the air leaving the passages 130 of the conduits 13 is blown onto the external casing 4, as close as possible to it.
    Overall, the transverse wall 157 of the housing 15 is elongated substantially parallel to the axis X.
    It is therefore in particular to bring the conduits 13 as close as possible to the outer casing 4, that at least one flat has been provided, in this case the flat 33b angularly situated at the diametric opposite of sector 273.
    Thus we see in Figure 3 that, the sockets 19 being mounted on the orifices 21, they are located immediately adjacent to the second transverse wall 157 of the housing 15, one of the flats (33c in this case) being oriented towards the wall 157 to reduce the distance I which separates the wall 157 from the socket considered.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1. Connection assembly comprising sockets (19) and a housing (15) for distributing air from an air inlet passage (155) from the housing to conduits (13), each conduit of said assembly being connected with the housing (15) by a said socket (19) mounted on an orifice (21) of a first wall (151,153) of the housing, said socket (19) having an axis (X2) along which an internal wall extends (191) in contact with which air can circulate in the socket, characterized in that said first wall (151,153) of the housing and the internal wall (191) of the socket are connected to each other by a connection leave (27) having a radius (R) which varies over at least part of the perimeter (275) of said internal wall (191).
    [2" id="c-fr-0002]
    2. The assembly of claim 1, wherein the sleeve (12) has an outer wall having several flats (33a, 33b, 33c) located angularly, around said axis (X2), away from an area (273) of the perimeter where the radius (R) of the connection leave (27) tends towards a maximum (R1).
    [3" id="c-fr-0003]
    3. An assembly according to claim 1 or 2, in which:
    - The air inlet passage (155) and the orifice (21) of each socket (19) have centers (155a, 21a ...) through which pass respective lines (230a ... 230c .. .), and
    - the radius (R) of each connection leave (27) is maximum (R1) over an angular sector (273) centered on the corresponding line, open towards the air inlet passage (155) whence the air comes in and between 90 and 135 °.
    [4" id="c-fr-0004]
    4. Assembly according to one of the preceding claims, in which each conduit (13) has an internal diameter (D) of between 12 and 26 cm and the radius (R) of the connection leave (27) varies between 0.5 and 7 cm.
    [5" id="c-fr-0005]
    5. Aircraft turbomachine characterized in that it comprises:
    - an assembly according to claim 1, which comprises several conduits (13) and sockets (19), and
    - a casing (4) outside the turbine of the turbomachine, around a zone 5 of which is disposed the air distribution box (15), a second wall (157) of which extends adjacent to said zone of the casing (4) outside, along it.
    [6" id="c-fr-0006]
    6. Turbomachine according to the preceding claim, in which the radius (R) of the connection leave (27) tends towards a maximum (R1) at the location
    10 of a zone (273) of the perimeter of said internal wall (191) which is oriented towards the air intake passage (155).
    [7" id="c-fr-0007]
    7. Turbomachine according to one of claims 5 or 6, in which the sockets (19) are mounted on the orifices (21) of the housing adjacent to said second wall (157) of the housing (15), and have
    15 individually an outer wall provided peripherally with at least one flat (33a, 33b, 33c) which, on at least some of the mounted sockets, is located adjacent to said second wall of the housing (15), so as to position the orifices (21) of the housing, sockets (19) and conduits (13) concerned as close as possible to the casing (4) outside the turbine.
    20
    [0008]
    8. A turbomachine according to claim 5, in which the sockets (19) are mounted on the orifices (21) of the housing (15) each having, peripherally, several flats located angularly, around said axis (X2), apart of said zone (273) of the perimeter.
    1/2
    类似技术:
    公开号 | 公开日 | 专利标题
    EP3318725B1|2020-03-11|Connection assembly for cooling a turbine of a turbine engine
    EP1818613B1|2018-10-10|Combustion chamber of a turbomachine
    FR2930591A1|2009-10-30|OPTIMIZING THE ANGULAR POSITIONING OF A TURBINE DISPENSER OUTSIDE A TURBOMACHINE COMBUSTION CHAMBER
    WO2013001246A1|2013-01-03|Arrangement for connecting a duct to an air-distribution casing
    CA2891076C|2021-03-09|Air exhaust tube holder in a turbomachine
    FR2902831A1|2007-12-28|Turbojet for aircraft, has heat exchanger arranged in inner volume of nacelle remote from inner wall of nacelle and outer wall of engine to provide lower and upper heat exchanging surfaces contacting discharge of cold air traversing nacelle
    EP2705219B1|2015-01-28|Turbine nozzle guide vane assembly in a turbomachine
    EP3638886B1|2021-01-06|Cooling device for an annular external casing of a turbine
    FR3054000A1|2018-01-19|DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE
    EP3039341B1|2018-12-05|Turbomachine combustion chamber comprising air deflection means for reducing wake created by igniter
    EP3299590B1|2019-07-24|Intermediate casing of a turbine of a turbomachine
    CA2919596A1|2015-01-22|Cover of a turbomachine centrifugal compressor capable of being rigidly connected via the downstream side near to the upstream edge of same, and turbomachine comprising this cover
    FR3055656A1|2018-03-09|TURBINE FOR A TURBOMACHINE, SUCH AS A TURBOREACTOR
    FR3081539A1|2019-11-29|TURBOMACHINE COMBUSTION CHAMBER BOTTOM
    FR3015551A1|2015-06-26|TURBOMACHINE WITH DOUBLE CENTRIER TURBINE
    FR3072127B1|2019-11-01|INTERMEDIATE CASTER HUB DISCHARGE DUCT FOR AN AIRCRAFT AIRCRAFT COMPRISING COOLING CHANNELS
    FR2999277A1|2014-06-13|Annular internal or external wall for e.g. direct flow combustion chamber, of turboshaft engine, has cooling holes whose drilling axes are directed according to direction of air flow so as to maintain supply of air axially across holes
    FR3111666A1|2021-12-24|RECOVERED CYCLE AIRCRAFT TURBOMACHINE
    FR3081927A1|2019-12-06|DEVICE FOR COOLING A TURBOMACHINE HOUSING
    FR3025260B1|2019-08-30|CENTRIFUGAL COMPRESSOR WITH IMPROVED RESISTANCE
    FR3015588A1|2015-06-26|DOUBLE COMPRESSOR CENTRIFUGAL TURBOMACHINE
    EP3824221A1|2021-05-26|Assembly for a turbomachine
    FR3096114A1|2020-11-20|Combustion chamber comprising means for cooling an annular envelope zone downstream of a chimney
    FR3064297A1|2018-09-28|TURBINE FOR A TURBOMACHINE, SUCH AS A TURBOREACTOR
    FR3086341A1|2020-03-27|REDUCING TURBOMACHINE FOR AN AIRCRAFT
    同族专利:
    公开号 | 公开日
    FR3058460B1|2018-11-09|
    CN108071491A|2018-05-25|
    US20180128120A1|2018-05-10|
    EP3318725B1|2020-03-11|
    EP3318725A1|2018-05-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5540547A|1994-06-23|1996-07-30|General Electric Company|Method and apparatus for damping vibrations of external tubing of a gas turbine engine|
    EP1205637A1|2000-11-09|2002-05-15|Snecma Moteurs|Cooling device for stator ring|
    EP1798381A2|2005-12-16|2007-06-20|General Electric Company|Thermal control of gas turbine engine rings for active clearance control|
    US20140109596A1|2011-06-30|2014-04-24|Snecma|Arrangement for connecting a duct to an air-distribution casing|
    DE19957597B4|1999-11-30|2006-05-04|Umfotec Gmbh|Arrangement of flow dampers for turbocharger engines|
    JP5761254B2|2013-05-27|2015-08-12|株式会社デンソー|Rotating electric machine|
    FR3014852B1|2013-12-17|2016-01-15|Sidel Participations|CONTAINER COMPRISING A BACKGROUND WITH AN EVOLVING LENGTH|
    US10408453B2|2017-07-19|2019-09-10|United Technologies Corporation|Dilution holes for gas turbine engines|FR3085719B1|2018-09-06|2021-04-16|Safran Aircraft Engines|PRESSURIZED AIR SUPPLY BOX OF AN AIR JET COOLING DEVICE|
    FR3097008A1|2019-06-04|2020-12-11|Safran Aircraft Engines|Device for cooling by air jets of a turbine and turbomachine casing comprising such a device|
    FR3101104B1|2019-09-23|2021-09-03|Safran Aircraft Engines|Device for cooling by air jets of a turbine housing|
    FR3105983B1|2020-01-08|2022-01-07|Safran Aircraft Engines|Device for cooling a crankcase of a turbomachine|
    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-05-11| PLSC| Publication of the preliminary search report|Effective date: 20180511 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1660784|2016-11-08|
    FR1660784A|FR3058460B1|2016-11-08|2016-11-08|CONNECTION ASSEMBLY FOR COOLING TURBOMACHINE TURBINE|FR1660784A| FR3058460B1|2016-11-08|2016-11-08|CONNECTION ASSEMBLY FOR COOLING TURBOMACHINE TURBINE|
    EP17199386.8A| EP3318725B1|2016-11-08|2017-10-31|Connection assembly for cooling a turbine of a turbine engine|
    US15/804,738| US20180128120A1|2016-11-08|2017-11-06|Connecting assembly for cooling the turbine of a turbine engine|
    CN201711082983.8A| CN108071491A|2016-11-08|2017-11-07|For the connection component of the turbine of cooling turbine engines|
    [返回顶部]