• 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 servitude crossing arm for a turbomachine, the arm (11) having in cross section a profile shape with respect to a longitudinal direction (X) substantially parallel to a flow of air intended to flow around said arm and having at least one opening (12) for sampling said air flow, characterized in that said profiled shape has on at least one of its flanks a recess (17) transverse to said longitudinal direction (X) and in that said opening (12) is located at said recess (17). The invention also relates to an easement passage system comprising this arm and a turbine engine that is equipped with it.
    公开号:FR3025843A1
    申请号:FR1458684
    申请日:2014-09-16
    公开日:2016-03-18
    发明作者:Pierrick Mouchoux；Thierry Kohn；Jonathan Langridge
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] Field of the Invention: The present invention relates to the field of turbomachines and in particular to a turbomachine comprising a cooling circuit and adjustment of the games of the turbomachine, such as radial clearances between a rotor and a stator of the turbomachine.
    [0002] STATE OF THE ART: The value of the radial clearance between a rotor and a stator of the turbomachine, and in particular between the tops of the vanes of the rotor and a stator casing extending around said vanes, is of fundamental importance for the performance of the rotor. the turbomachine. In a known manner, this type of clearance is controlled preferentially by using a cooling circuit of the casing by air taken from an air flow, such as the secondary flow in a double-flow turbomachine. The flow rate of the air flow taken is regulated to control the cooling of the housing, in order to control its expansion and therefore the clearance with the vanes of the turbine.
    [0003] A first way to regulate the flow of air taken to control the cooling of the housing is to install a control valve in the sampling circuit. This solution has the disadvantage that an open scoop is permanently installed in the flow vein of the secondary flow, which generates significant pressure drops. According to the solutions described, for example, in the documents US-B2-7765788 and US-B28092153, it is advantageous to have arms passing through the secondary flow vein to install an opening in the upstream part of these arms in order to to form a scoop. In these solutions, the flow is taken from the middle of the vein, where it is the fastest, driven by the blowers and outside the boundary layer of the housing. In addition, the opening is made on the upstream face of the arm, which allows to take advantage of a dynamic pressure for sampling. Furthermore, the opening and closing of the scoop are controllable, which eliminates the use of a valve in the game control circuit, which can represent a significant gain in mass. However, the previously described solutions, presenting the opening of the scoop to the most energetic air flow attacking the profile of the arm, exposes it to receive small objects (hail, insects, small birds ..) entrained in the secondary air flow and 3025843 2 impacting the arm with an incidence in the longitudinal direction. These small objects can enter the scoop and may accumulate in the control circuit by plugging its pipes upstream of the exchangers. The object of the present invention is in particular to provide an answer to this problem while preserving the dynamic advantages of taking a flow of air through an arm of servitude passage of a turbomachine. SUMMARY OF THE INVENTION For this purpose, the invention relates to a servitude crossing arm for a turbomachine, the arm having in cross section a shape profiled with respect to a longitudinal direction substantially parallel to a flow of air intended for flowing around said arm and comprising at least one sampling aperture of said air flow, characterized in that said profiled shape has on at least one of its flanks a recess transverse to said longitudinal direction and in that said opening is located at said recess. The easement passage arm extends generally between two walls, in a radial direction, for example between two ferrules materializing the vein of passage of the air flow. A section transverse to this direction of extension may in this case be parallel to the direction of the air flow intended to flow around the arm. The fact that the opening is at the recess causes it to be obscured by the upstream part of the arm in a longitudinal direction parallel to that of the flow of air flow. This upstream portion intercepts or deflects most of the small entrained objects while guiding the flow along the arm surface toward the opening.
    [0004] Furthermore, the placement of the opening on the arm makes it possible to find local dynamic properties at the sampling site similar to those of previously described solutions. Advantageously, the upstream edge in the longitudinal direction of the opening is itself located at the recess, the main extension of the opening 30 downstream of the maximum recess position.
    [0005] The terms upstream and downstream in the document are assessed with respect to the direction of flow in the longitudinal direction. Preferably, the arm further comprises a movable flap between a closed position and an open position of said opening.
    [0006] The presence of the movable flap makes it possible to control the flow of air taken at the opening and thus to avoid the use of a valve in a regulation circuit connected to the sampling duct fed by the opening. In addition, by closing the opening when there is no sampling, significantly reduces the pressure losses in this case.
    [0007] Advantageously, the flap is pivotally movable about an axis extending substantially at the maximum recess position. Preferably, the pivot axis of the flap is substantially parallel to an axis of elongation of said recess. Thus, during opening, the flap can retract inside the arm, without creating aerodynamic disturbances due to any part that would exceed in the flow. Advantageously, the movable flap forms a tangent continuity in the longitudinal direction with the surface of the arm at the opening, when it closes. In this way, the profile of the arm being designed to limit the pressure drop, when the opening is closed, the flap follows the general profile of the arm and does not introduce disturbances. Advantageously, the recess corresponds to a throttling of the arm. profiled cross sectional shape, said throat separating an upstream portion of the arm, having a maximum thickness of between one and a half times and three and a half times a minimum thickness of the constriction, and a downstream portion of the arm having a maximum thickness between three and a half times and six times the maximum thickness of the upstream part. The term thickness refers here to the extension of the arm in the direction perpendicular to the longitudinal and radial directions.
    [0008] According to the findings of the Applicant, these proportions correspond to advantageous profile geometries for flow and pressure conditions at the opening. Advantageously, the arm further comprises an inner mounting housing 5 of a bailer whose inlet is connected to said opening. Preferably, said opening is located in a concave curved wall of the arm. Preferably, the flap pivots about an axis passing substantially through its most upstream point.
    [0009] Advantageously, the surface portion where the opening is made has a concave curved profile in the longitudinal direction. This brings several benefits. On the one hand, this region of the flow corresponds to an aspiration and then a re-compression taking place continuously of the flow, which makes it possible to optimize the flow sucked by the opening by minimizing the detachments . On the other hand, the movable flap following this shape guides the flow to the sampling duct. Furthermore, the opening of the bailer is preferably spaced apart from the ends of the arm in a direction perpendicular to the housing. More preferably, when the arm passes through a flow vein, in particular a secondary flow vein, the scoop is located substantially midway between said ends of the arm. The invention also relates to a turbomachine comprising a cooling circuit, for example a circuit for regulating the play of a turbine casing around the blades of the turbine, supplied by such a scoop on a service arm and whose efficiency is driven by the position of the bailer's door.
    [0010] Advantageously, said turbomachine comprises a flow vein of a secondary air flow and the arm passes through the vein in said radial direction. The invention also relates to a system of passage of servitudes and air intake for a turbomachine, comprising two coaxial shrouds, respectively internal and external, connected together by radial arms, at least one of which is as defined above.
    [0011] The invention also relates to a turbomachine comprising at least one arm or a system as described above. In such a turbomachine, said opening of the arm can be connected to a cooling circuit and adjustment I games of the turbomachine.
    [0012] BRIEF DESCRIPTION OF THE FIGURES: The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the description of a non-limiting example which follows, with reference to the accompanying drawings of FIG. which: - Figure 1 schematically shows a longitudinal section of a turbomachine according to the invention; FIG. 2 shows a perspective view of an embodiment of a service crossing arm according to the invention; FIG. 3 shows, in section along a plane P of FIG. 2, a schematic diagram of the operation of an arm according to the invention, of which a movable flap is in the open position; FIG. 4 shows, in section along a plane P of FIG. 2, a schematic diagram of the operation of an arm according to the invention, of which a movable flap is in the closed position, and FIGS. an alternative embodiment of an easement passage arm according to the invention in the operating configurations respectively corresponding to FIGS. 3 and 4, according to a plane of section similar to the plane P of FIG. 2.
    [0013] DESCRIPTION OF AN EMBODIMENT With reference to FIG. 1, a double-flow turbomachine generally comprises, from upstream to downstream in the direction of the gas flow, one or more blowers 1 and then an engine part comprising one or several compressor stages, low pressure 2 then high pressure 3, a combustion chamber 4, one or more turbine stages, high pressure 5 and then low pressure 6, and an exhaust nozzle 7 of the primary gases. Rotors, rotating around the main axis LL of the turbomachine and can be coupled together by different transmission systems and gears, correspond to these different elements. Here, the flow of air driven by the blowers is separated into a part F1 entering the primary circuit corresponding to the motor part and a part F2 of secondary flow, participating predominantly in the thrust provided by the turbomachine. The secondary flow F2 passes around the motor part in a secondary vein 8. Generally, a turbomachine is equipped with at least one system for passing 10 servitudes such as air ducts, oil ducts, cables electrical, etc., so that they can pass through a vein, such as the flow vein 8 of the secondary flow F2, minimizing the disturbances of this flow. The easements make it possible to connect a first equipment located radially inside the vein to a second equipment located radially outside the vein 15 (the expression radially appreciating with respect to the main axis LL of the turbomachine ). A system of passage of servitudes (commonly called kit engine), shown in Figure 1 in the secondary vein 8, generally comprises an annular body having two rings annular and coaxial, respectively internal 10 and external 9.
    [0014] These two ferrules are connected by substantially radial and tubular arms 11 which comprise internal housings for the passage of the servitudes. This system can be mounted downstream of an intermediate casing of the turbomachine, the ferrules 8, 10 forming the continuity of the walls of the vein 8 at the level of the easement passage system.
    [0015] Generally, the arms 11 of the easement passage system are profiled and aligned in the direction of the main flow of the air stream in the vein 8 to limit the disturbances of this flow and reduce the pressure drops. Radial stator vanes may be installed upstream, for example rectifiers. In this case, the arms of the easement passage system extend downstream of these vanes so as not to disturb the flow flowing between these vanes.
    [0016] Here one of the arms 11 of the easement passage system further comprises an air intake opening 12 located near its leading edge 13. The inside of the arm 11 also contains the inlet of a duct 14 which forms an air bleed scoop in the secondary flow F2, connected to the opening 12. The duct 14 passes into the arm 11 and passes through the shell 10 to bring the cold air, taken from the stream secondary F2, to cooling devices. Preferably, but not necessarily, the air taken by the duct 14 is used by means 15 for cooling an outer casing 16 of the low pressure turbine 6, in order to regulate the clearance between the casing 16 and the vanes of the rotor of the turbine 6.
    [0017] In a first embodiment, with reference to FIG. 2, the service passage arm 11 comprises a main portion 11a, intended for the passage of the servitudes, and having a profile shape in a longitudinal direction X substantially parallel to the flow of secondary flow F2 at the level of the arm 11. This main part 11a passes through the secondary flow vein 8 F2 and has a substantially constant shape between the two rings 10, 9, in a direction of extension of the arm Z, substantially radial and perpendicular to the longitudinal direction X. The profile of the surface of this main part lla in a plane P perpendicular to the direction Z generally has a maximum thickness El significant with respect to its length D1.
    [0018] A profiled fairing 11b, also passing through the stream 8 of flow of the secondary stream and of constant profile in the radial direction Z, is placed at a distance in front of the main part 11a, in its extension in the longitudinal direction X. The profiled fairing 11b has a profiled section along a plane P perpendicular to the radial direction Z, preferably with a rounded leading edge 13 and a rear portion tending to form a trailing edge with an acute angle. The profile of this fairing IIb in a plane P perpendicular to the radial direction Z has a maximum thickness E2, lower than the thickness E1 of the main portion 11a. In addition, it is generally shorter, relative to its length D2, than the main part 11a. The length D2 of this profiled fairing 11b is here substantially of the same order of magnitude as the distance D3 to which it is located in front of the main part 11a.
    [0019] This profiled fairing 11b forms an upstream part of the arm, connected continuously to the main part 11a. Indeed, the fairing of the arm 11 is completed by plates 11c, 11d on each side which join the two parts 11a, 11b previously described. The profile of these plates in a plane P perpendicular to the radial direction Z 5 is concave and is connected, with a continuity of slope along the longitudinal direction X, to the profile of the profiled shroud IIb in the region of its trailing edge, and to profile of the main part 11a in an area upstream of its maximum thickness D1. The outer surface of all these different parts 11a, 11b, 11c, 11d, 10 forms a continuous outer surface of the service arm 11 which comprises, after its leading edge 13, a bulge corresponding to the upstream portion profile 11b, then a curved portion 11c, 11d connecting to the thicker profile of the main portion 11a. This bent portion comprises a throat 17, corresponding to a minimum thickness E3 of the arm 11 in its upstream portion.
    [0020] Preferably, the ratio between the maximum thickness E1 of the arm 11 and the maximum thickness E2 of the upstream portion 11b, E1 / E2 is between the values 3.5 and 6. Still with reference to FIG. opening 12 is made on one side of the arm 11 relative to the median plane, here in the plate 11c forming the connection between the upstream portion 11a and the main portion 11b.
    [0021] If we consider a median plane H in the direction X passing through the leading edge 13 of the arm 11, the outer surface of the arm 11 having the opening 12 is formed, on each side of said median plane H, of a first surface portion which deviates from the median plane H to a distance corresponding to the maximum thickness E2 of the upstream portion 11a, of a second surface portion which is close to the median plane H up to the a throat 17 of minimum thickness E3, and a third surface portion which moves away from the median plane to the zone of maximum thickness E1 of the arm 11. In the longitudinal direction X, the opening 12a an upstream edge 12a straight parallel to the axis Z, located near the point corresponding to the smallest thickness D3 of the profile of the arm 11. The downstream edge 12b of the opening 12 is also straight parallel to the axis 302 Z, at a point where the thickness of the arm between the plates 11c and 11d leaves a gap sufficient ssage to the secondary air flow. The edges 12c, 12d delimiting the opening 12 in the radial direction Z are situated in two planes P perpendicular to this direction, placed respectively at distances H1 and H2 of the inner shell 10 of the secondary vein 8, at the intersection with the arm 11. These distances H1, H2 place the scoop away from the inner ferrule 10 and the outer ferrule 9, in the vein 8 of the secondary flow F2. Preferably, the opening 12 is outside the boundary layers on the walls of the secondary vein 8. It may for example be substantially in the middle of the ends 10 of the arm 11 in the radial direction Z. The opening 12 is equipped with a flap 18 rotatable about an axis 19 parallel to the radial direction Z, on the corresponding upstream edge of the opening. The shape of this flap 18 corresponds to the surface of the plate 11c that would have been cut to practice the opening 12. In other words, when the flap 18 is placed so that its downstream edge, parallel to the direction Z, connected to the downstream edge 12b of the opening 12, the profile of the flap 18 in a plane P is the same as that of the plate 11c on either side of the opening 12. The air has an inlet 14a which connects to the downstream edge 12b of the opening 12 so as to form an air bleed scoop. The inlet 14a of the duct 14 extends in the direction Z over the height range H1, H2 of the opening 12. The extension of the inlet 14a of the duct 14 according to the thickness of the profile of the arm 11 in a plane P goes from the plate 11c to the end position of the downstream edge of the flap 18 when it is pivoted in order to free the opening 12 of the bailer as much as possible.
    [0022] The operation of the scoop between its open position and its closed position will be better understood with reference to FIGS. 3 and 4 respectively. Referring to FIG. 3, the flap 18 is pivoted as much as possible around the pivot axis 19. Here the downstream edge of the flap 18 touches the inside of the plate 11d forming the profile of the arm 11, on the other side of the median plane H with respect to the plate 11c where the opening 12 is made.
    [0023] The pivot axis 19 is placed substantially at the level of the constriction 17. It forms the upstream edge 12a of the opening 12 in the plate 11c of the profile of the arm 11. Preferably, the ratio between the maximum thickness E2 of the upstream portion 11b and the minimum thickness E3 of the arm 11 at the throat 17, E2 / E3 is between the values 1.5 and 3. Here, the downstream edge 12b of the opening 12 is is located substantially at the same distance from the median plane H as the thickest part of the upstream portion 11b. The inlet 14a of the sampling duct 14, which starts at the downstream edge 12b of the opening of the scoop 12, extends over substantially the entire width of the profile of the arm 11 at this point, to the position of the downstream edge of the flap 18, pressed against the opposite plate 11 d of the profile of the arm 11. In this way, the opening 12 of the scoop and, therefore, the inlet 14a of the sampling duct 14, are hidden in the direction longitudinal X by the bulge of the upstream portion 11b. Thus, a small object in the longitudinal direction X will generally be either stopped by the upstream portion 11b or deflected by it and will not enter the withdrawal conduit 14. On the other hand, the profiled shape of the upstream part 11b and then the continuous shape of the flap 18 in the open position guide the gas flow 20 towards the inlet 14a of the sampling duct 14.
    [0024] Placing the downstream edge 12b of the opening 12 substantially behind the thickest portion of the bulge of the upstream portion 11b makes it possible to obtain a maximum passage section for the inlet 14a of the sampling duct 14. width of the inlet 14a is thus slightly less than the maximum thickness E2 of the upstream portion 11b.
    [0025] Advantageously, the edges of the duct 14 along the downstream edge 12b of the opening 12 of the bailer are oriented relative to the secondary flow incident flow 20 so as not to have a sharp edge, to avoid disturbances. aerodynamic along the arm 11. Referring to Figure 4, when the flap 18 is pivoted about the axis 19 so as to close the opening 12, its edges are connected to those of the opening 12, in particular regards the downstream edge 12b. Similarly, as is illustrated in FIG. 4, its profile forms a continuity of slope in the longitudinal direction X with the profile of the upstream portion 11b and the plate 11c on the side of the opening 12 of FIG. the scoop. In this way, the flow of gas 20 along the arm 11 follows its profile as if there was no opening 12 and is not disturbed by the scoop. The pressure losses are thus minimal compared to an arm not adapted for a bailer, when the opening 12 is closed. Indeed, with respect to the only main part 11a, the entire arm 11 with the added elements such as the upstream portion 11b and the fairing plates 11c, 11d on each side, form a profiled body in the longitudinal direction X .
    [0026] Advantageously, at least this upstream portion of the arm 11 is symmetrical around a median plane H in the longitudinal direction X and does not introduce lateral forces. However, in an alternative embodiment, the arm 11 may be asymmetrical so as to adapt the leading edge 13 of the arm 11 to the residual gyration of the secondary flow F2, existing after the recovery of the flow downstream of the fan 1 by a device 15 of fixed vanes, placed in a known manner upstream of the arm 11 but not shown in Figure 1. With reference to Figures 5 and 6, the longitudinal direction X corresponding to the incident flow here is slightly in relation to the general orientation of the cross section of the main portion 11a of the arm 11 passing 20 easements. The elements of the variant described in FIGS. 5 and 6 having the same functions as those of the preceding embodiment have identical references to those shown in FIGS. 3 and 4. The arm 11 always has a profiled upstream portion 11b but its cross section is not necessarily aligned with the main part 11a. It is preferably substantially oriented in the longitudinal direction X. In this case, a fairing 11c of convex cross-section makes the connection between the upstream portion 11b and the main portion 11a, on the intrados side with respect to the longitudinal direction X, substantially parallel to the incident flow. This shroud 11c is shaped to form a recess in the cross-section of the arm 11, with a maximum recess point 17 transverse to the longitudinal direction X.
    [0027] As can be seen in FIGS. 5 and 6, the opening 12 is made in the side of the arm 11, in the vicinity of this maximum recess point 17. Preferably, the upstream edge 12a and the pivot axis 19 of the flap 18 are located substantially at this maximum recess point 17. Furthermore, the opening 12 is preferably located in a zone of the fairing 11c which is masked by the upstream portion 11a, in the longitudinal direction X. Here, the cross section of the fairing 11d making the junction between the upstream portion 11b and the main portion 11a, on the other side of the arm 11, has a convex shape, shaped to avoid inflection points on the profile of the arm 11. this way, it is avoided to create recirculation zones on this side of the arm 11, which corresponds to an extrados for the incident flow. As is illustrated in FIGS. 5 and 6, the scoop operates in the same manner as before by pivoting the shutter 18 around an axis 19 situated on the upstream edge of the opening 18, substantially at the level of the maximum recess. 17.
    [0028] Here, the inlet 14a of the sampling duct 14 is substantially of the same width as in the previous case. However, it can be seen that the convex shape of the fairing 11d possibly leaves the possibility of designing a wider inlet 14a, allowing a greater sampling of the air flow along the side of the arm 11 where the opening 12 is located.
    [0029] In the case of application to a temperature control circuit such as that presented above in FIG. 1, the rotation of the pivot pin 19 of the flap 18 can be controlled by a continuous angular positioning motor. Such an engine can be installed, for example, in line with the axis 19 outside the arm 11, on the other side of one of the ferrules 9, 10.
    [0030] The regulation of the flow taken by the duct 14 and therefore used by the temperature control circuit, is then done by adjusting the position of the flap 18 in a continuous manner between a closed position, corresponding to FIG. 4, and a position maximum opening, corresponding to Figure 3. In addition, the embodiment of the scoop 12 according to the invention has been presented for a turbojet double flow with sampling in the secondary flow but 3025843 13 can adapt directly for example, to a system of passage of easements in another vein.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Servo passage arm for a turbomachine, the arm (11) having in cross section a profile shape with respect to a longitudinal direction (X) substantially parallel to a flow of air intended to flow around said arm and comprising at least an opening (12) for sampling said air flow, characterized in that said profiled shape has on at least one of its flanks a recess (17) transverse to said longitudinal direction (X) and in that said opening (12) is located at said recess (17).
    [0002]
    2. Arm according to claim 1, characterized in that it further comprises a flap (18) movable between a closed position and an open position of said opening (12).
    [0003]
    3. Arm according to claim 2, wherein the flap (18) is pivotally movable about an axis (19) extending substantially at the maximum recess position (17).
    [0004]
    4. Arm according to claim 3, wherein the pivot axis (19) of the flap (18) is substantially parallel to an axis of extension (Z) of said recess.
    [0005]
    5. Arm according to any one of the preceding claims, wherein the recess (17) corresponds to a constriction of the profiled shape of the cross section, and wherein said constriction separates an upstream portion (11b) of the arm having a thickness. maximum (E2) between one and a half and three and a half times a minimum thickness (E3) of the throat (17), and a downstream portion (11a) of the arm having a maximum thickness (El) of between three times and half and six times the maximum thickness (E2) of the upstream portion (11b). 3025843 15
    [0006]
    6. Arm according to any one of the preceding claims, further comprising an inner housing for mounting a scoop, an inlet (14a) is connected to said opening (12).
    [0007]
    An arm according to any one of the preceding claims, wherein said opening (12) is located in a concave curved wall (11c) of the arm (11).
    [0008]
    8. System of passage of servitudes and air intake for a turbomachine, comprising two coaxial ferrules, respectively internal (10) and outer (9), connected together by radial arms, at least one of which is as defined according to the one of the preceding claims.
    [0009]
    9. Turbomachine having at least one arm according to one of claims 1 to 7 or a system according to claim 8.
    [0010]
    10. The turbomachine according to the preceding claim, wherein said opening (12) of the arm (11) is connected to a cooling circuit (14, 15) and clearance clearance of the turbomachine.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3025843B1|2019-06-28|SERVITUDE PASSAGE ARM FOR A TURBOMACHINE
    CA2794825C|2018-06-12|Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same
    FR3037617B1|2019-06-28|TURBOMACHINE DISCHARGE VEIN CONDUIT COMPRISING VARIABLE SECTION VBV GRID AND PASSIVE ACTUATION
    CA2721423C|2016-08-30|Injection of air into the flow path of a turbomachine compressor
    EP3204620B1|2018-11-21|Stator of an aircraft turbine engine
    CA2975570A1|2016-08-18|Guide assembly with optimised aerodynamic performance
    WO2015011413A1|2015-01-29|Hub of an intermediate casing for an aircraft turbojet engine comprising doors with contoured geometry
    EP1956226B1|2009-08-19|Discharge device for a jet engine, and jet engine comprising same
    EP3277942B1|2019-02-20|Discharge flow duct of a turbine engine comprising a vbv grating with variable setting
    FR3012846A1|2015-05-08|INTERMEDIATE CASTER HUB FOR AIRCRAFT TURBOJET AIRBORNE COMPRISING A DEFORMABLE CONDUIT OF AIR AND DEBRIS CANALIZATION
    EP3563047A1|2019-11-06|Intermediate housing hub comprising discharge flow guiding channels formed by the discharge fins
    WO2015011392A1|2015-01-29|Intermediate housing hub for an aircraft turbofan, including air guide deflectors
    FR3067387B1|2019-06-28|AIR SUPPLY ECOPE FOR SUPPLYING A COOLING SYSTEM AND CONTROLLING THE GAMES OF A TURBINE
    FR2926337A1|2009-07-17|Outlet guide vane for airplane jet engine, has platforms spaced apart from each other by platform inter-space for defining air passing channel between platforms, where one of platforms is in external position with respect to other platform
    EP3722559A1|2020-10-14|Turbine engine for an aircraft
    FR3059367A1|2018-06-01|DOUBLE FLOW TURBOMACHINE EQUIPPED WITH A DISCHARGE SYSTEM
    BE1028097B1|2022-01-26|Turbomachine compressor blade, compressor and turbomachine fitted therewith
    FR3072127B1|2019-11-01|INTERMEDIATE CASTER HUB DISCHARGE DUCT FOR AN AIRCRAFT AIRCRAFT COMPRISING COOLING CHANNELS
    FR3025564B1|2019-08-16|VARIABLE-TIMING AUB SYSTEM FOR A TURBOMACHINE
    FR3100268A1|2021-03-05|DOUBLE-FLOW TURBOMACHINE FOR AN AIRCRAFT
    FR3059366A1|2018-06-01|DOUBLE FLOW TURBOMACHINE EQUIPPED WITH A DISCHARGE SYSTEM
    FR3093136A1|2020-08-28|INPUT COVER FOR AN AIRCRAFT TURBOMACHINE
    WO2018096239A1|2018-05-31|Bypass turbomachine fitted with bleed system
    同族专利:
    公开号 | 公开日
    FR3025843B1|2019-06-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0469825A2|1990-07-30|1992-02-05|General Electric Company|Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine|
    EP0743434A1|1995-05-15|1996-11-20|Aerospatiale Societe Nationale Industrielle|Precooling heat exchange arrangement integral with mounting structure fairing of gas turbine engine|
    CA2638677A1|2007-08-28|2009-02-28|General Electric Company|Apparatus and method for suppressing dynamic pressure instability in bleed duct|
    EP2224099A2|2009-02-26|2010-09-01|Rolls-Royce Deutschland Ltd & Co KG|Gas turbine active tip clearance control|FR3052823A1|2016-06-20|2017-12-22|Snecma|AERODYNAMIC BOND IN A TURBOMACHINE PART|
    WO2017220881A1|2016-06-20|2017-12-28|Safran Aircraft Engines|Method for testing the integrity of a fluid flow regulating system for a turbomachine|
    FR3057615A1|2016-10-17|2018-04-20|Safran Aircraft Engines|SERVITUDE PASSAGE ARM FOR A TURBOMACHINE|
    US20180355748A1|2017-06-07|2018-12-13|Safran Aircraft Engines|Turbomachine including a cooling and turbine clearance control system having an air supply scoop|
    FR3108939A1|2020-04-03|2021-10-08|Safran Aircraft Engines|Operation of a scoop in a turbomachine|
    法律状态:
    2015-09-16| PLFP| Fee payment|Year of fee payment: 2 |
    2016-03-18| PLSC| Search report ready|Effective date: 20160318 |
    2016-09-02| PLFP| Fee payment|Year of fee payment: 3 |
    2017-05-04| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-08-22| PLFP| Fee payment|Year of fee payment: 5 |
    2019-08-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-08-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-08-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1458684|2014-09-16|
    FR1458684A|FR3025843B1|2014-09-16|2014-09-16|SERVITUDE PASSAGE ARM FOR A TURBOMACHINE|FR1458684A| FR3025843B1|2014-09-16|2014-09-16|SERVITUDE PASSAGE ARM FOR A TURBOMACHINE|
    [返回顶部]