• 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 a cooling device (2) by air jets of the casing of a turbine, preferably a low-pressure turbine engine, comprising a supply box (3) in air under pressure and at least two cooling tubes (40) curved, arranged on either side of said housing (3), around and at a distance from a portion of the housing and being provided with air injection orifices (41), said housing comprising including a bottom (31), and two longitudinal side walls (32, 33), and this bottom being pierced with air injection orifices. This device is remarkable in that each of said side walls extends outwardly by at least one tubular monobloc sleeve and to which a cooling tube is connected, the bottom of the sleeve being at the same level as said bottom of the case at the place where they meet.
    公开号:FR3050228A1
    申请号:FR1653418
    申请日:2016-04-18
    公开日:2017-10-20
    发明作者:Jacques Marcel Arthur Bunel；Emeric D'herbigny；Pierre Tincelin
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    The invention is in the field of cooling a turbine casing.
    The present invention more specifically relates to an air jet cooling device of the casing of a turbine, preferably low pressure, a turbomachine. The invention also relates to a turbomachine, equipped with such a device.
    STATE OF THE ART
    As can be seen in Figures 1 and 2 attached, which represent the state of the art, the low-pressure turbine of a turbomachine is protected by a housing C generally flared, substantially frustoconical. This housing is cooled using impact cooling technology.
    The casing C is equipped with one or more box (es) B of pressurized air supply, each of them being connected to several cooling ramps R.
    In the embodiment shown in these figures, the housing C is equipped with two housings B, positioned at about 180 ° from each other (only one being visible in Figure 2). In addition, each box B is equipped with five R ramps, with two T tubes per ramp, each tube extending about 90 °.
    As shown in the bottom view of the housing B of Figure 4 attached, the tubes T and the housing B are pierced with a series of small orifices O opening to the right of the outer surface of the housing. The pressurized air passing through these orifices O ensures an impact ventilation of the casing C.
    Moreover, and as can be seen in Figure 3 attached and in Figure 4, each tube T is connected to the housing B via a cylindrical sleeve D. Each tube T is soldered in the sleeve D and each socket D is soldered in housing B.
    However, as can be seen in Figure 4, the housing B does not have orifices O at both ends and the sleeves D either. On each side of the housing B, there is therefore a zone ZI, between the last orifice O of the housing B and the first orifice 0 of the tube T, in which there are no orifices, so no injection of air and therefore no cooling of the skin of the housing located opposite.
    In addition, the T tubes have, over most of their length, a curved (curved) shape that substantially matches the curvature of the casing C. However, in order to ensure proper brazing of the tube T in the sleeve D, the end the tube is rectilinear on an area 11, (see Figure 3).
    Consequently, the air gap between the tube T of the ramp R and the skin (outer surface) of the casing C is not constant over the entire circumference of the casing and especially the ramp moves away from the casing skin, which has a negative impact on cooling. It can thus be seen that the gap E1 desired between the tube and the casing can take on ever higher values E2 or even E3, the closer one is to the sleeve D. For example, for an air gap E1 of 3 , 5 mm, the values of E2 and E3 can reach respectively 4.8 mm and 8.5 mm.
    The variation of the gap is also found between the bottom of the case B which is closer to the skin of the casing C (gap E4) and the end of the tube T where it is brazed in the sleeve D (gap E3).
    However, for air jet impact cooling to be effective, this gap must not only be constant but also of low value, determined by the crankcase specifications, (generally of the order of 2 mm to 3.5 mm).
    To summarize, there is therefore close to each case B, an absence of cooling of the casing C on two zones Z1 of a length of the order of 25 mm, or 50 mm and poor cooling on two zones Z2 of a length of the order of 60 mm, or 120 mm.
    These areas not or slightly cooled are to be multiplied by the number of boxes B arranged around the casing C, which number in some embodiments can be four.
    Finally, the assembly and maintenance of the cooling ramps R on the casing C can potentially strongly stress the solder between the bushes D and the housing B or between the bushes D and the ramps R. There is therefore a risk of damage premature of said ramps.
    PRESENTATION OF THE INVENTION The invention therefore aims to solve the aforementioned drawbacks of the state of the art. The invention therefore particularly aims to provide an air jet cooling device of the casing of a turbine which provides a uniform cooling of the housing, that is to say which ensures a gap as constant as possible between the cooling ramp and the outer surface of the housing.
    Another object of the invention is to propose a device which makes it possible to cool a portion of the outer surface (skin) of said casing larger than that which can be cooled with the devices of the state of the art and thus of increase the life of the crankcase.
    Finally, another objective of the invention is to simplify the method of manufacturing the cooling ramps and to obtain a cooling device of greater mechanical strength. For this purpose, the invention relates to an air jet cooling device of the casing of a turbine, preferably a low pressure turbine engine, comprising a pressurized air supply box and at least one pressure ramp. cooling comprising two cooling tubes disposed on either side of said housing, said housing comprising a bottom, two longitudinal side walls, two upstream and downstream end walls and an upper wall, and said bottom of the housing being pierced with orifices; of air injection arranged to open towards the housing around which said cooling device is intended to be arranged, each cooling tube being curved, disposed around a part of the housing and at a distance from it and being provided with air injection orifices opening towards the housing.
    According to the invention, each of said side walls is extended outwardly by at least one tubular sleeve integral with said side wall, each sleeve is disposed on said side wall so that its bottom is at the same level as said case bottom at their junction and each sleeve is configured and dimensioned so that one of the cooling tubes can be connected to it.
    Thanks to these features of the invention, the air gap between the housing and the bottom of the housing and between the housing and the tubes of the cooling ramp is almost constant, which ensures better cooling. In addition, the fact that the housing is integral with the sleeves structurally reinforces the assembly.
    According to other advantageous and nonlimiting features of the invention, taken alone or in combination: the bottom of the sleeve is pierced, over at least a part of its length, with air injection orifices arranged so as to lead to the housing around which said device is intended to be arranged; - The air injection orifices formed in the bottom of the housing are aligned with the air injection orifices in the sleeves and with the air injection orifices formed in the cooling tubes; the bottom of the housing and the sleeves are curved on either side of a median longitudinal axis of the housing, so as to match the shape of the contour of the housing around which said cooling device is intended to be arranged and in such a way that there is a constant or substantially constant gap between the outer surface of said housing on the one hand and the bottom of the housing and the bottom of the sleeves on the other hand; - Each sleeve has a junction zone with the side wall of the housing and this junction zone is flared from the sleeve to the side wall of the housing and the portion of its circumference other than that of the bottom of the sleeve; said upper wall of the housing is constituted by an attached cover and fixed to the side and end walls of said housing; the cover is fixed to the side and end walls of said case by soldering or brazing; - The tubes of the cooling ramps are introduced into the free end of the sleeves and connected thereto by soldering. The invention also relates to a turbomachine comprising a turbine, in particular a low-pressure turbine, surrounded by a casing, which comprises a cooling device by air jets of said casing, as mentioned above.
    PRESENTATION OF THE FIGURES Other features and advantages of the invention will appear from the description which will now be made, with reference to the accompanying drawings, which represent, by way of indication but not limitation, a possible embodiment.
    In these drawings: FIG. 1 is a perspective view of a portion of a casing of a turbine of a turbomachine, equipped with cooling ramps according to the state of the art, FIG. in perspective of an air supply box and cooling ramps according to the state of the art, - Figure 3 is an elevational view of an air supply box and a portion of the ramps of according to the state of the art, FIG. 4 is a perspective view from below of an air supply box and a part of the cooling ramps according to the state of the art, FIG. is a perspective view in elevation of part of the cooling ramps and an air supply box according to the invention, - Figure 6 is a detailed view of the box of the inside of the box marked A in FIG. 5; FIG. 7 is a view similar to FIG. 5, but on which the cover of the b FIG. 8 is a view in perspective and from below of part of the cooling ramps and of an air supply box according to the invention, and FIG. detail view of Figure 8.
    DETAILED DESCRIPTION
    As can be seen in FIG. 5, the cooling device 2 according to the invention makes it possible to cool the casing 1 of a turbine. This casing 1 has a flared shape, generally comprising several successive frustoconical portions. It has an upstream end 11 and a downstream end 12, with respect to the direction of flow of the gases in the turbine. Its outer surface (skin) is referenced 13.
    The cooling device 2 comprises a pressurized air supply box 3 and at least one cooling ramp 4.
    Each ramp 4 comprises two tubes 40.
    Preferably, the cooling device 2 comprises several ramps 4, for example five in number in Figures 5, 7 and 8, distributed around the housing 1 between the upstream and downstream thereof.
    As previously described with the device of the state of the art, the housing 1 may be equipped with two cooling devices 2, for example with two housings 3, positioned at about 180 ° from each other and whose tubes 40 cooling ramps extend on each side of this housing, about 90 °. The casing 1 can also be equipped with four cooling boxes 3, the tubes 40 of the cooling ramps then extending on a smaller angular surface.
    The housing 3 is connected to a pressurized air supply source, not shown in the figures.
    As shown in Figure 5, this housing 3 is disposed outside the outer surface 13 of the housing 1 and at a distance therefrom. This housing 3 and the ramps 4 are fixed to the casing 1 for example by means of flanges not shown in the figures. Other methods of fixing the housing are possible.
    The housing 3 comprises a bottom 31, two longitudinal side walls 32, 33, disposed on either side of the bottom 31 and two upstream end 35 and downstream end walls 34.
    Each of said upstream 35 and downstream walls 34 respectively joins the bottom 31 with the upstream ends, respectively downstream of the two longitudinal side walls 32, 33. Finally, the housing 3 is closed by an upper wall 36, not visible in Figure 5.
    In the exemplary embodiment shown in FIG. 7, this upper wall 36 is in the form of an attached lid, fixed to the side walls 32, 33 and to the upstream and downstream walls 35, preferably by welding or brazing. .
    However, according to another embodiment not shown in the figures, the upper wall 36 could be made of material and thus be in one piece with the other walls 32, 33, 34 and 35.In this case, the housing 3 can advantageously be obtained by a casting process or by direct manufacture (for example additive manufacturing).
    The bottom 31 is designed to be disposed at a short distance from the housing 1, which is flared, and with a gap as constant as possible. As a result, the bottom 31 is inclined from upstream to downstream to conform to the frustoconical or substantially frustoconical shape of the casing 1.
    The bottom 31 of the housing 3 has a median longitudinal axis X-X '(shown only in FIG. 7).
    In the embodiment shown in the figures and as it appears best in Figures 5 and 7, the upstream end 35 and downstream end walls 34 are parallel to each other or approximately parallel to each other. Due to the inclination of the bottom 31, the upstream wall 35 forms an acute angle with it and the downstream wall 34, an obtuse angle.
    As can be seen in FIG. 7, the cover 36 comprises an upper wall 361, two longitudinal lateral walls 362, 363, of triangular shape and disposed on either side of the upper wall 361, and two end walls. upstream 365, respectively downstream 364 joining the two walls 362, 363.
    An orifice 366 is pierced in one of the side walls, for example the wall 362. It makes it possible to connect the housing 3 to the source of supply of air under pressure. Other forms of lids are conceivable without departing from the scope of the invention. The connection to the pressurized air supply source could be provided on any face of the housing 3 except the bottom 31.
    According to the invention, each of said side walls 32, 33 of the housing 3 extends outwardly, by at least one tubular sleeve integrally formed (monobloc) with said side wall.
    There are as many sleeves as ramps 4.
    In the example shown in the figures where there are five ramps 4, there is therefore on each side wall 32, respectively 33, five sleeves referenced from upstream to downstream, 321, 322, 323, 324 and 325 for those formed on the wall 32 and respectively 331, 332, 333, 334 and 335 for those formed on the wall 33.
    The sleeves are thus monoblock with the housing 3. This eliminates the soldering that existed between the bushings and the housing in cooling devices of the state of the art. Thus, the casing 3 of the invention provides a structural reinforcement of the entire ramp since the solderings between the casing and the sockets which constituted weak points have been eliminated.
    The housing 3 provided with sleeves 321 to 325 and 331 to 335 is advantageously obtained by casting or by an additive manufacturing process, such as laser melting, because these manufacturing processes are well suited to complex geometry parts.
    The tubes 40 are fitted into each of said sleeves 321 to 325 and 331 to 335 and attached thereto preferably by brazing. The outlet diameters of said sleeves are adapted accordingly.
    In addition, each sleeve is disposed on the side wall 32, 33, so that a portion of its circumference, called "bottom of the sleeve" (in other words its lower part intended to be placed facing the outer surface 13 of the housing 1 when the cooling device is in place), at the same level as the bottom 31 of the housing, at the point of their junction.
    The bottoms of the sleeve are visible in the bottom view of FIG. 8. They are respectively referenced 3210, 3220, 3230, 3240 and 3250 for the sleeves 321 to 325 and 3310, 3320, 3330, 3340 and 3350 for the sleeves 331 to 335.
    As can be seen in Figure 9, each tube 40 is pierced with a plurality of orifices 41 of air injection.
    As it appears better in FIGS. 8 and 9, the bottom 31 of the housing 3 is pierced with a series of cooling orifices 37, advantageously arranged in line and preferably over its entire width L. "The entire width L" means from the point where the bottom 31 joins the side wall 32 (or more precisely one of the sleeves 321 to 325) at the point where the bottom 31 joins the wall 33 (or more precisely one of the sleeves 331 to 335).
    The tubes 40 are arranged so that their cooling orifices 41 are aligned with the orifices 37.
    Advantageously, each sleeve 321 to 325 and 331 to 335 is also provided with cooling orifices 38 aligned with the cooling orifices 37 of the housing. These orifices 38 are present over the entire length of the sleeve with the exception of its mouth at which the tube 40 is fitted and brazed. The orifices 38 are formed along the bottoms 3210 to 3250 and 3310 to 3350 of the sleeves.
    On the bottom 31 of the housing 3, there are as many lines of cooling orifices 37 as ramps 4.
    Moreover, each tube 40 is bent, that is to say that it has a circular arc shape whose radius is slightly greater than that of the portion of the housing in front of which it is intended to be positioned. Also preferably, the bottom 31 of the housing is curved on either side of the central axis X-X ', so that its concavity is oriented towards the surface of the housing 1, so as to substantially match the shape of the housing 1 in front of which the housing is intended to be positioned.
    In other words, and as seen in FIG. 7, the bottom sides 31 located to the right and to the left of the median axis X-X 'are lower than the bottom center which extends along said axis X-X '.
    Similarly, advantageously, the sleeves 321 to 325 and 331 to 335 are bent so that their concave part, which corresponds to their bottoms (baselines) respectively 3210 to 3250 and 3310 to 3350 is oriented towards the outer surface 13 of the housing , so as to substantially match the shape of the housing in front of which they are positioned.
    This particular arrangement, combined with the fact that the bottom of each sleeve 321 to 325 and 331 to 335 is at the same height as the bottom 31 of the housing 3 allows for a homogeneous cooling of the housing 1, since the different injection ports air 37 of the bottom 31 and 38 of the sleeves are at a distance (gap E5) constant or almost constant from the outer surface of the housing 1.
    Also preferably, this air gap E5 is calculated to be equal to or substantially equal to the gap E6 existing between a tube 40 (or its cooling orifices 41) and the outer surface 13 of the casing 1. The difference between the two gaps lies in the thickness of the sleeve.
    Preferably, the air gaps E5 and E6 are between 2 mm and 4.5 mm, preferably equal to 3.5 mm.
    On the other hand, the zone Z3 between the last cooling orifice 38 and the first orifice 41, in which there are no cooling orifices, is of less length than the zone ZI of the cooling devices of the state. of the technique (see Figures 4 and 9). A larger part of the casing 1 is thus cooled.
    Finally, advantageously, and as it appears better in FIGS. 5 and 6, each sleeve 321 to 325 and 331 to 335 has a junction zone with the lateral wall 32, 33 of the case 3. This junction zone flares out. from the sleeve towards said side walls 32, 33 except at the bottom of the sleeve. The junction zones of the sleeves 321 to 325 and 331 to 335 are respectively referenced 3211, 3221, 3231, 3241, 3251 and 3311, 3321, 3331, 3341 and 3351 (the reference 3311 being visible only in FIG. 8).
    In other words, the radius R2 of the flared junction zone at the level where it is connected to the side wall 32, 33 is greater than the radius RI of the mouth of the sleeve where it connects to said zone. junction (see Figure 6).
    This greatly reduces the pressure losses between the housing and the tubes of the different ramps, since the dimensions of the junction zone are gradually reduced.
    In addition to the various aforementioned advantages of the invention, it will be noted that the method of manufacturing the cooling device is simplified since there are fewer brazing operations than with the device of the state of the art.
    In addition, the device is more robust, which also reduces the duration and frequency of repair and maintenance operations.
    Finally, the housing is better cooled, its life is increased.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Device (2) for cooling by air jets of the casing (1) of a turbine, preferably a low-pressure turbine engine, comprising a pressurized air supply box (3) and at least one cooling ramp (4) comprising two cooling tubes (40) disposed on either side of said housing (3), said housing (3) comprising a bottom (31), two longitudinal side walls (32, 33), two upstream (35) and downstream (34) end walls and an upper wall (36), and said bottom (31) of the housing being pierced with air injection orifices (37) arranged to open towards the casing around which said cooling device (2) is intended to be arranged, each cooling tube (40) being curved, arranged around a portion of the casing and at a distance from it and being provided with injection orifices of air (41) opening towards the housing, characterized in that each of said side walls (32, 33) extends towards the outside by at least one tubular sleeve (321, 322, 323, 324, 325, 331, 332, 333, 334, 335) integral with said side wall (32, 33), in that each sleeve is disposed on said side wall (32, 33) so that its bottom (3210, 3220, 3230, 3240, 3250, 3310, 3320, 3330, 3340, 3350) is at the same level as said bottom (31) of the housing at the location of their junction and that each sleeve is configured and dimensioned so that one of the cooling tubes (40) can be connected thereto.
    [2" id="c-fr-0002]
    2. Device (2) according to claim 1, characterized in that the bottom (3210, 3220, 3230, 3240, 3250, 3310, 3320, 3330, 3340, 3350) of the sleeve is pierced on at least a portion of its length, of air injection orifices (38) arranged to open towards the housing around which said device (2) is intended to be arranged.
    [3" id="c-fr-0003]
    3. Device (2) according to claim 2, characterized in that the air injection orifices (37) formed in the bottom (31) of the housing (3) are aligned with the air injection orifices ( 38) formed in the sleeves (321, 322, 323, 324, 325, 331, 332, 333, 334, 335) and with the air injection ports (41) in the cooling tubes (40).
    [4" id="c-fr-0004]
    4. Device (2) according to any one of the preceding claims, characterized in that the bottom (31) of the housing (3) and the sleeves (321, 322, 323, 324, 325, 331, 332, 333, 334 , 335) are curved on either side of a median longitudinal axis (X-X ') of the housing, so as to match the shape of the contour of the housing around which said cooling device is intended to be arranged and so there is a constant or substantially constant air gap (E5) between the outer surface (13) of said housing (1) on the one hand and the bottom (31) of the housing (3) and the bottoms (3210, 3220, 3230, 3240, 3250, 3310, 3320, 3330, 3340, 3350) of said sleeves on the other hand.
    [5" id="c-fr-0005]
    5. Device (2) according to one of the preceding claims, characterized in that each sleeve (321, 322, 323, 324, 325, 331, 332, 333, 334, 335) has a junction area (3211, 3221 , 3231, 3241, 3251, 3311, 3321, 3331, 3341, 3351) with the lateral wall (32, 33) of the housing (3) and in that this junction zone is flared from the sleeve towards the side wall (32, 33) of the housing and on the portion of its circumference other than that of the bottom (3210, 3220, 3230, 3240, 3250, 3310, 3320, 3330, 3340, 3350) of the sleeve.
    [6" id="c-fr-0006]
    6. Device (2) according to one of the preceding claims, characterized in that said upper wall (36) of the housing (3) consists of an attached cover and attached to the side walls (32, 33) and end (34, 35) of said housing.
    [7" id="c-fr-0007]
    7. Device (2) according to claim 6, characterized in that the cover (36) is fixed to the side walls (32, 33) and end (34, 35) of said housing by welding or brazing.
    [8" id="c-fr-0008]
    8. Device (2) according to one of the preceding claims, characterized in that the tubes (40) of the cooling ramps (4) are introduced into the free end of the sleeves (321, 322, 323, 324, 325, 331, 332, 333, 334, 335) and connected thereto by brazing.
    [9" id="c-fr-0009]
    9. A turbomachine comprising a turbine, in particular a low-pressure turbine, surrounded by a casing (1), characterized in that it comprises an air jet cooling device (2) of said casing, according to any one of the preceding claims. .
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    同族专利:
    公开号 | 公开日
    BR112018071421A2|2019-02-05|
    WO2017182740A1|2017-10-26|
    CN109072712B|2021-09-03|
    US10844789B2|2020-11-24|
    EP3445949B1|2020-04-29|
    RU2018140464A3|2020-06-04|
    EP3445949A1|2019-02-27|
    US20190093559A1|2019-03-28|
    FR3050228B1|2019-03-29|
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4019320A|1975-12-05|1977-04-26|United Technologies Corporation|External gas turbine engine cooling for clearance control|
    US5100291A|1990-03-28|1992-03-31|General Electric Company|Impingement manifold|
    US5540547A|1994-06-23|1996-07-30|General Electric Company|Method and apparatus for damping vibrations of external tubing of a gas turbine engine|
    US6149074A|1997-07-18|2000-11-21|Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma"|Device for cooling or heating a circular housing|
    US20140109596A1|2011-06-30|2014-04-24|Snecma|Arrangement for connecting a duct to an air-distribution casing|WO2019229377A1|2018-05-30|2019-12-05|Safran Aircraft Engines|Device for cooling a turbomachine housing|
    FR3081911A1|2018-06-04|2019-12-06|Safran Aircraft Engines|DEVICE FOR COOLING A TURBINE HOUSING FOR A TURBOMACHINE|
    WO2020049259A1|2018-09-06|2020-03-12|Safran Aircraft Engines|Pressurized-air supply unit for 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|
    FR3101104A1|2019-09-23|2021-03-26|Safran Aircraft Engines|Device for cooling by air jets of a turbine housing|
    FR3105983A1|2020-01-08|2021-07-09|Safran Aircraft Engines|Device for cooling a casing of a turbomachine|
    US11280217B2|2018-09-06|2022-03-22|Safran Aircraft Engines|Pressurized-air supply unit for an air-jet cooling device|US4621492A|1985-01-10|1986-11-11|The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration|Low loss injector for liquid propellant rocket engines|
    US5205115A|1991-11-04|1993-04-27|General Electric Company|Gas turbine engine case counterflow thermal control|
    RU2028463C1|1992-08-05|1995-02-09|Государственное предприятие по организации технической эксплуатации и диагностики энергомеханического оборудования и линейной части магистральных газопроводов "Оргэнергогаз"|Device for cooling gas-turbine set housing|
    US7597537B2|2005-12-16|2009-10-06|General Electric Company|Thermal control of gas turbine engine rings for active clearance control|
    US8661151B2|2011-05-09|2014-02-25|Google Inc.|Dynamic playlist for mobile computing device|
    US9039350B2|2012-01-09|2015-05-26|General Electric Company|Impingement cooling system for use with contoured surfaces|
    US9341074B2|2012-07-25|2016-05-17|General Electric Company|Active clearance control manifold system|
    RU2538985C1|2013-12-30|2015-01-10|Открытое акционерное общество "Авиадвигатель"|High-temperature turbine stator|FR3093129B1|2019-02-25|2021-01-29|Safran Aircraft Engines|Device for holding at least one cooling tube to a turbomachine casing and its mounting method|
    CN110593968A|2019-09-30|2019-12-20|侯志刚|External cooling device of steam turbine and method for installing cooling pipe in cooling device|
    US11255264B2|2020-02-25|2022-02-22|General Electric Company|Frame for a heat engine|
    法律状态:
    2017-04-06| PLFP| Fee payment|Year of fee payment: 2 |
    2017-10-20| PLSC| Search report ready|Effective date: 20171020 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 3 |
    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1653418A|FR3050228B1|2016-04-18|2016-04-18|AIR JET COOLING DEVICE OF A TURBINE HOUSING|
    FR1653418|2016-04-18|FR1653418A| FR3050228B1|2016-04-18|2016-04-18|AIR JET COOLING DEVICE OF A TURBINE HOUSING|
    US16/094,229| US10844789B2|2016-04-18|2017-04-13|Device for cooling a turbine casing with air jets|
    CN201780024221.4A| CN109072712B|2016-04-18|2017-04-13|Device for cooling a turbine housing by means of air jets|
    BR112018071421A| BR112018071421A2|2016-04-18|2017-04-13|device for cooling a turbine housing with air jets and turbocharger|
    EP17722490.4A| EP3445949B1|2016-04-18|2017-04-13|Device for cooling a turbine casing with air jets|
    RU2018140464A| RU2724379C2|2016-04-18|2017-04-13|Turbo crankcase air jet cooling device|
    CA3021023A| CA3021023A1|2016-04-18|2017-04-13|Device for cooling a turbine casing with air jets|
    PCT/FR2017/050893| WO2017182740A1|2016-04-18|2017-04-13|Device for cooling a turbine casing with air jets|
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