• 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 turbomachine fluid supply system (200) comprising a fluid reservoir (201), a downstream portion (210) located downstream of the reservoir (201), and a shut-off valve (230). ) located between the reservoir (201) and the downstream portion (210). The shutoff valve (230) is configured to be at least partially open when a rotational speed of a turbomachine shaft is greater than a first threshold and in the absence of fire detected in the turbomachine (1). According to the invention, the shut-off valve (230) is closed when the two following conditions are met: the rotation speed of the shaft is greater than the first threshold, and the speed of rotation of the shaft has been lower than first threshold when a fire was detected in the turbomachine (1) during the flight.
    公开号:FR3019583A1
    申请号:FR1453097
    申请日:2014-04-08
    公开日:2015-10-09
    发明作者:Thomas Lepage；Antoine Laigle；Matthieu Attali
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The invention relates to the technical field of turbomachine fluid supply systems. BACKGROUND OF THE INVENTION More specifically, the invention relates to the isolation of a fuel fluid reservoir, during a fire in a turbomachine. STATE OF THE PRIOR ART Turbomachine lubrication systems are configured, in known manner, to circulate an oil flow sufficient to cool the turbomachine in case of fire. This oil flow circulates under the effect of a lubricant supply pump driven by the natural autorotation of the turbomachine when the aircraft is in flight. However, when this oil flow rate is insufficient to ensure the cooling of the turbomachine during a fire, it is often necessary to limit the flow of oil to turbomachine equipment and / or to provide specific protection for the engine. these equipment against fires. Specific protection against fires have the disadvantage of being detrimental in terms of weight and bulk.
    [0002] In order to limit the flow of fuel fluid circulating in a lubrication system in the event of a fire in a turbomachine, it is known to isolate the oil reservoir from the rest of the lubrication system by a shut-off valve, passive or controlled by a digital control system, as long as the fire is not permanently extinguished.
    [0003] Nevertheless, the use of a passive cut-off valve can be complex to implement since it often results in an absence of lubrication of the turbomachine when the turbomachine is stopped. However, the digital control system of some turbomachines or some aircraft may not be available during a fire to control the opening or closing of a controlled shutoff valve. In addition, the regulations in force require that the engine is able to withstand a fire for a minimum period, while avoiding the fire is fueled during this time.
    [0004] There is therefore a need to isolate a turbomachine fuel fluid reservoir in the event of a fire, while limiting both the availability requirements of a digital control system, the mass and the size of the turbomachine. DISCLOSURE OF THE INVENTION The invention aims to at least partially solve the problems encountered in the solutions of the prior art. In this regard, the subject of the invention is a method for isolating a fuel fluid reservoir relative to a downstream portion of a turbomachine fluid supply system, a shutoff valve configured to limit a fluid flow in direction of the downstream part, being located between the reservoir and the downstream part, the shutoff valve being at least partially open, when a rotational speed of a turbomachine shaft is greater than a first threshold and in the absence of fire detected in the turbomachine. According to the invention, when the rotational speed of the shaft is lower than the first threshold, the shut-off valve closes automatically and the subsequent opening of the shut-off valve is limited / prevented when a fire has been detected during of the flight. More generally, the shut-off valve is closed, when the following conditions are met: the speed of rotation of the shaft is greater than the first threshold, and the speed of rotation of the shaft has been lower than the first threshold. when a fire was detected in the turbomachine during the flight of the turbomachine. In particular, the shut-off valve remains closed, when a fire has been detected in the turbomachine and the speed of rotation of the shaft is likely to be - or to become - insufficient to properly cool the turbomachine equipment to be powered. Thus, the risk of unnecessarily fueling fire with combustible fluid is limited, as well as the need to provide specific fire protection for such equipment.
    [0005] The method and the corresponding supply system therefore make it possible to isolate the fuel fluid reservoir in the event of a fire inside the turbomachine, while limiting the mass and the size of the turbomachine, and in particular respecting the legal requirements for the protection of fires inside a turbomachine.
    [0006] Furthermore, the process can be easily automated by taking mainly into account the presence of a fire or the absence of a fire in the turbomachine. The need for availability of a digital control system is then limited. The combustible fluid is preferably lubricant, especially oil. Alternatively, the fluid is fuel. The invention may optionally include one or more of the following features combined with one another or not. In this configuration, the subsequent opening of the shut-off valve is preferably limited / prevented until the end of the flight of the turbomachine.
    [0007] According to a first configuration, the shut-off valve is closed when the speed of rotation of the shaft is less than the first threshold. The lubrication chambers are then not supplied with lubricant when the rotational speed of the shaft is lower than the first threshold.
    [0008] In this case, the first threshold preferably corresponds to a rotation value of the shaft sufficiently small so that the rotor of the turbomachine does not need to be lubricated, in particular the lubrication chambers. Advantageously, a fluid flow rate sufficient to cool the turbomachine in case of fire flows in the supply system, when the shutoff valve is open and the rotational speed of the shaft is greater than or equal to the first threshold. The invention also relates to a turbomachine fluid supply system comprising a fluid reservoir, a downstream part located downstream of the reservoir and comprising a fluid supply pump, and a shut-off valve located between the reservoir and the reservoir. downstream part, the shutoff valve being configured to be open when a rotational speed of a turbomachine shaft is greater than the first threshold and in the absence of fire detected in the turbomachine.
    [0009] According to the invention, when the rotational speed of the shaft is lower than the first threshold, the shut-off valve closes automatically and the subsequent opening of the shut-off valve is limited / prevented when a fire has been detected during of the flight. According to another advantageous embodiment, the shut-off valve comprises a safety position towards which the shut-off valve is brought back in the absence of control exerted on the shut-off valve, the shut-off valve being closed in the safety position. The shut-off valve is thus closed or closed with limited intervention of a numerical control system of turbomachine or aircraft, or even without intervention of the digital control system, during the critical event that constitutes a fire. The shut-off valve is preferably hermetically closed in the safety position. Nevertheless, a few residual drops may in particular flow downstream of the shut-off valve due to manufacturing tolerances and mounting of the shut-off valve.
    [0010] In addition, it is possible to avoid redoubling the controls of the shut-off valve by the digital control system, since the controls of the shut-off valve by the digital control system are no longer essential to preserve the integrity of the control valve. turbomachine in case of fire.
    [0011] Therefore, the power system and the corresponding method can isolate a turbomachine fuel fluid reservoir in case of fire, while limiting the availability requirements of a digital control system. Preferably, the shut-off valve comprises a locking element movable between a locking position in which the shut-off valve is locked closed, and an unlocking position in which the shut-off valve is configured to be closed or at least partially open, the locking element being in the locked position in the absence of control exerted on the locking element so that the shut-off valve is in the safety position. According to another particular embodiment, the shut-off valve is pneumatically controlled when the locking element is in the unlocking position. In a variant, the opening and / or closing of the shut-off valve is controlled by a numerical control system of the turbomachine and / or the aircraft, when the locking element is in the locked position. A pneumatically controlled shut-off valve is preferably configured to be supplied with air from a turbomachine module selected in particular from a turbomachine compressor or a turbomachine turbine, the shutoff valve being configured to be open when the air pressure coming from the module exceeds a pressure threshold and the locking element is in the unlocking position. The opening and / or closing of the valve can then be performed without intervention of the numerical control system of turbomachine or aircraft, when the locking element is in the unlocking position. The control of the shut-off valve has the advantage of being little energy-consuming.
    [0012] The compressor is preferably a high pressure turbomachine compressor. Similarly, the turbine is preferably a turbomachine high pressure turbine. The shut-off valve preferably comprises a piston and a resilient means mechanically connected to the piston being configured to bias the piston in displacement to a first position in which the shut-off valve is closed, from a second position in which the shut-off valve is at least partially open. The locking member in the locking position preferably forms a stop of the piston, so as to prevent the piston from being in the second position. According to another advantageous embodiment, the locking element is configured to move from the locking position to the unlocking position on command of a digital turbomachine or aircraft control system.
    [0013] The locking member preferably has a bevel shape, so as to promote the movement of the piston from the second position to the first position when the locking member is in the locking position. Furthermore, the bevel shape of the locking element does not prevent the locking element in the locking position from prohibiting the movement of the piston from the first position to the second position. The invention also relates to a turbomachine lubrication system comprising a supply system as defined above in which the supply system is configured to supply at least one turbomachine lubrication chamber, the lubrication system comprising in addition a lubricant return circuit including a lubricant return pump configured to supply the reservoir with lubricant from the lubrication chamber. The invention finally relates to a turbomachine comprising a feed system and / or a lubrication system as described above. The turbomachine is preferably a turbojet or a turboprop. In a variant, the turbomachine is a helicopter engine.
    [0014] BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be better understood on reading the description of exemplary embodiments, given purely by way of indication and in no way limiting, with reference to the appended drawings in which: FIG. 1 represents a partial diagrammatic sectional view longitudinal turbomachine, according to a first embodiment of the invention; FIG. 2 represents a partial schematic view of a fluid supply system, according to the first embodiment of the invention; FIG. 3 is an enlarged partial schematic view of the shut-off valve of the supply system of FIG. 2 in the open position; Figure 4 is an enlarged partial schematic view of the shutoff valve of the supply system of Figure 3 in the closed position; FIG. 5 schematically illustrates a method of isolating the reservoir of the feed system of FIG. 2. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS Identical, similar or equivalent parts of the different figures bear the same numerical references in order to facilitate the passage from one figure to another. FIG. 1 represents a turbomachine 1 with double flow and double body. The turbomachine 1 comprises in this order on the flow path of a primary flow A fan 2, a low pressure compressor 4, a high pressure compressor 6, a combustion chamber 16, a high pressure turbine 8 and a low turbine pressure 10. The low pressure compressor 4, the high pressure compressor 6, the high pressure turbine 8 and the low pressure turbine 10 delimit a secondary flow stream of a secondary flow B which bypasses them.
    [0015] The high-pressure compressor 6 and the high-pressure turbine 8 are mechanically connected by a driving shaft 3 of the high-pressure compressor 6, so as to form a high-pressure body of the turbomachine 1. Similarly, the low-pressure compressor 4 and the low-pressure turbine 10 are mechanically connected by a turbomachine shaft 1, so as to form a low-pressure body of the turbomachine 1. The turbine engine 1 also comprises an intermediate casing 20 which is traversed by radial structural arms 22. One of the arms structural members 22 comprises a radial shaft 24 whose radially inner end is mechanically connected by gears to the drive shaft 3 of the high pressure compressor 6. The radially outer end of the radial shaft 24 is mechanically connected by gears to a gearbox 30 configured to serve as an accessory box of the turbomachine 1. As a result, the gearbox 30 is t configured to be rotated by the high pressure body.
    [0016] Gearbox 30 is also known as an "accessory gearbox". It comprises a plurality of equipment such as a lubricant supply pump 212, a fuel supply pump, a starter or an electric generator. With reference to FIG. 2, the turbomachine 1 comprises a lubrication system comprising a supply system 200 and a lubricant return circuit 300 to the lubricant reservoir 201. The supply system 200 is configured to supply at least one turbomachine lubricating chamber 122, 124 from a lubricant reservoir 201. The lubrication chambers 122, 124 typically comprise equipment to be lubricated, for a nominal operation of the turbomachine 1. A shutoff valve 230 for supplying lubricant from the tank 201 is located between the tank 201 and the air chambers. Lubrication 122, 124. Between the cut-off valve 230 and the lubrication enclosures 122, 124, the feed system 200 includes the feed pump 212 with lubricant.
    [0017] The lubricant supply pump 212 and the lubricating chambers 122, 124 form a downstream portion 210 of the feed system 200. In the document, the "upstream" and "downstream" directions are defined by the general direction of flow. supply fluid which is lubricant in the first embodiment. The lubricant return circuit 300 includes a lubricant return pump 312 configured to supply the reservoir 201 with lubricant from the lubrication enclosure 122, 124. Between the lubricant return pump 312 and the reservoir 201, the lubricant return circuit 300 includes a heat exchanger 315 configured to cool the lubricant, typically oil, before it returns to the reservoir 201. Heat exchanger 315 thus makes it possible to limit the risks of premature degradation of the lubricant. The shut-off valve 230 comprises a valve 237 configured to limit the flow of fluid 202 from the tank 201 towards the feed pump 212. The valve "T" shaped 237 is connected to one end of an arm 235 of the shutoff valve 230 by a hinge 236. The valve 237 is rotatable about the axis 240 of the valve 237, so as to open and / or close the shutoff valve 230. The valve 237 is movable between an extreme open position in which the shut-off valve 230 is open in FIG. 3, and an extreme closed position in which the shut-off valve 230 is closed in FIG. 4. In the open position, the valve 237 does not It does not limit the flow of lubricant 204 towards the feed pump 212. The shut-off valve 230 may optionally be partially open, in which case the valve 237 is located between the open position and the closed position. Alternatively, the shutoff valve 230 is an "all or nothing" valve, the open position and the closed position are then in particular the only equilibrium positions of the valve 237. The arm 235 is mechanically connected to its opposite end. to that which is the valve 237 to a piston 232 defining the volume of two chambers 234, 236 of the shutoff valve 230. The piston 232 is movable between a first position P1 in which the shutoff valve 230 is closed and the valve 237 in the closed position, and a second position P2 in which the shutoff valve 230 is open and the valve 237 in the open position.
    [0018] The piston 232 is biased towards the first position P1 by elastic means 231 mechanically connected to the piston 232. The resilient means 231 is for example a compression spring which tends to close the shutoff valve 230 or to keep it closed. The piston 232 and the elastic means 231 are located inside a body 239 of the shut-off valve 230, which delimits with the piston the high-pressure chamber 234 and the low-pressure chamber 236 of the shut-off valve 230. high pressure chamber 234 is fed with compressed air from a turbomachine module 1, selected from the high pressure compressor 6, the low pressure compressor 4, the high pressure turbine 8 and the low pressure turbine 10. first embodiment, the high pressure chamber 234 is supplied with compressed air according to the arrow 64 by the high pressure compressor 6. Ambient air feeds the low pressure chamber 236. This air comes in particular from the secondary flow B, so that a pressure difference between the low pressure chamber 236 and the high pressure chamber 234 causes the piston 232 to move against the elastic spring spring 231 so as to balance the pressure at the pressure the chambers 234 and 236, provided that the shutoff valve 230 is not blocked closed. In other words, the shutoff valve 230 is pneumatically controlled, when it is not locked while being closed. The shut-off valve 230 also includes a locking device 40 configured to lock the shut-off valve 230 when the shut-off valve 230 is closed and the shutter 237 is in the closed position. The locking device 40 comprises a locking member 42 movable between a locking position in which the shut-off valve 230 is locked closed, preferably hermetically, and an unlocking position in which the shut-off valve 230 is configured to be closed or at least partially open. In particular, the valve 237 can switch from the closed position to the open position, when the locking element 42 is in the unlocking position. Conversely, the valve 237 remains in the closed position, when the locking element 42 is in the locking position.
    [0019] In the first embodiment, the locking member 42 takes the form of a latch. The locking element 42 preferably serves as a stop for the piston 232, so as to prevent the piston 232 from being in the second position P2, that is to say in particular so as to prevent the shut-off valve 230 from 'open. The locking member 42 has a bevel shape, so as to promote the movement of the piston 232 from the second position P2 to the first position P1 when the locking member 42 is in the locking position. Furthermore, the bevel shape of the locking element 42 does not prevent the locking element 42 in the locking position from preventing the displacement of the piston 232 from the first position P1 to the second position P2.
    [0020] The latch 42 in the locked position is configured to protrude into the low pressure chamber 236 from a through hole 238 formed in the body 239 of the shutoff valve 230. The latch 42 includes a protruding portion 422 configured to engage a flange 233. of the body 239 of the shut-off valve 230, so as to protrude into the low pressure chamber 236, while being designed to prevent movement of the piston 232 to the second position P2. The projecting portion 422 is connected by a rod to a piston 424 of the latch 42 located in a sleeve 41 of the piston 424. The sleeve 41 of the piston 424 comprises a return means 44 of the piston 424 configured to urge the displacement of the piston 424 of so that the locking element 42 is in the blocking position in the absence of control exerted on the locking element 42. In unlocking position, the latch 42 does not protrude into the low pressure chamber 236, so as not to not impede the movement of the piston 232 between the first position P1 and the second position P2. The latch 42 in the unlocking position compresses a return means 44 in the sleeve 41.
    [0021] The latch-shaped latch member 42 is configured to move from the lock position to the on-demand release position of a turbomachine or aircraft digital control system. In order to limit the risk of failure in the movement of the locking element 42, the control of the locking element 42 by the digital control system 5 is preferably an "all or nothing" control, the locking position and the unblocking position being the only possible end positions of the locking element 42. In this configuration, the locking position is the only equilibrium position at rest of the locking element 42.
    [0022] The displacement of the latch 42 is also effected as a function of the air inlet 60 coming from the high pressure compressor 6. The digital control system 5 is also known by the acronym "FADEC", from the English " Full Authority Digital Engine Control ". Conventionally, the digital control system 5 comprises a two-way engine computer symmetrical, redundant and full authority. This engine calculator is intended to take into account a command from a pilot of the aircraft. In the first embodiment, the digital control system 5 is configured to instruct a priming electromagnet 50 to urge the latch 42 to move from the lock position to the unlock position.
    [0023] The priming electromagnet 50 is configured to pass air under pressure into the liner 41 of the piston 424, so as to allow the latch 42 to move from the lock position to the unlocking position. In the absence of control exerted by the digital control system 5 on the electromagnet 50, the electromagnet 50 is configured to block the inflow of pressurized air according to the arrow 60 in the jacket 41.
    [0024] However, in the absence of control exerted on the latch 42, the return means 44 tends to bring the latch 42 in the locking position in which the return means 44 is at rest. The return means 44 and the resilient means 231 thus form a safety means for closing the shut-off valve 230. This safety means biases the piston 232 to the first position P1, in the absence of control of the element of The stop valve 230 then comprises a safety position PS in which the shut-off valve 230 is closed. The shutoff valve 230 is returned to its safety position PS in the absence of control, pneumatic and / or from the control system 5, exerted on the shutoff valve 230. The locking element 42 is configured to move from the blocking position to the unlocking position by order of the digital control system 5, when starting the aircraft comprising the turbomachine 1 and in the absence of fire. In this case, the shutoff valve 230 opens when the air pressure in the high pressure chamber 234 exceeds a pressure threshold which is greater than the pressure in the low pressure chamber 236. This pressure threshold of the air from the high-pressure compressor 6 is determined as a function of a first threshold S1 of rotational speed vR of a shaft whose movement is related to the rotational movement of the high-pressure body of the turbomachine 1. In the first mode of embodiment, this shaft is the radial shaft 24. Alternatively, it may include the drive shaft 3 of the high pressure compressor 6. The first threshold S1 is determined so that the lubricant flow in the supply system 200 for rotational speed values v R greater than the first threshold S1 allows efficient cooling of the turbomachine 1 during a fire. The first threshold S1 is also determined so that when the rotational speed vR of the radial shaft 24 is smaller than the first threshold S1 in the absence of a fire, the rotor of the turbomachine 1 has little or no need for be lubricated. Furthermore, the lubricant present in the reservoir 201 constitutes a combustible fluid that must not supply fire in the turbomachine 1. Consequently, the shutoff valve 230 is configured to be closed when the rotational speed vR of the shaft radial 24 is smaller than the first threshold Si.
    [0025] The shut-off valve 230 is configured to isolate the lubricant reservoir 201 from the downstream portion 210 of the supply system 200 in the event of fire by the implementation of a method of isolating the reservoir 201 which is described with reference in Figure 5.
    [0026] Firstly, the rotation speed v R of the radial shaft 24 is compared with the first threshold S 1 during a process initialization step 52. When the rotation speed v R is lower than the first threshold S 1, the valve 230 is closed, both in the presence and in the absence of fire detected in the turbine engine 1. When it is detected that the rotational speed v R is greater than the first threshold S 1, the digital control system 5 determines during a step 54 of the isolation process if a fire is detected in the turbomachine 1, for example following a detection of abnormal increase in temperature inside the turbine engine 1 by a temperature sensor. In the absence of a fire detected, the locking element 42 is held in the unlocking position and the shutoff valve 230 is opened in step 64, because of the arrival of compressed air 60 from the compressor high pressure 6 when the rotational speed vR is greater than the first threshold S1. The lubrication enclosures 122, 124 are then substantially properly supplied with lubricant in the absence of fire.
    [0027] From the moment at which a fire has been detected in the turbomachine 1 during the flight of the turbomachine 1, the shutoff valve 230 is kept open in step 66 only if the rotational speed v R has remained higher than the first threshold Si since the fire was detected. From the moment at which a fire has been detected in the turbomachine 1 and the rotational speed v R becomes at least punctually less than the first threshold Si, the piston 232 tends to move from the second position P2 to the first position P1 when the locking element 42 is in the unlocking position. When the piston 232 has arrived in the first position P1, the locking member 42 switches to the blocking position in step 66, so that the shutoff valve 230 is locked closed. The shut-off valve 230 then remains preferably locked closed by the locking element 42 as a precaution until the end of the flight of the turbomachine 1. In other words, when the rotation speed v R is lower than the first threshold S 1 and a fire is detected in the turbomachine 1, the shutoff valve 230 closes automatically and the subsequent opening of the shutoff valve 230 during the flight is limited / prevented. More generally, the shut-off valve 230 is closed, when the following two conditions are met: the rotation speed v R of the radial shaft 24 is greater than the first threshold S 1, and the rotational speed v R of the radial shaft was lower than the first threshold S1 when a fire was detected in the turbomachine 1 during the flight of the turbomachine 1. The invention makes it easier to comply with the regulatory requirements for fire regulation in a turbomachine 1, in particular by limiting use of specific fire-resistant protections and large mass in the turbomachine 1. In particular, the risk that the shutoff valve 230 does not close in case of fire in the turbomachine 1 is limited by the security means, formed by the return means 44 and the elastic means 231, which tends to bring the shut-off valve 230 to its safety position PS in which the shutoff valve 230 is iron nted. Of course, various modifications may be made by those skilled in the art to the invention which has just been described without departing from the scope of the disclosure of the invention.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A method of isolating a reservoir (201) of fuel fluid relative to a downstream portion (210) of a turbomachine fluid supply system (200) (1), a shutoff valve (230), configured to limit a flow of fluid towards the downstream portion (210), being located between the reservoir (201) and the downstream portion (210), the shutoff valve (230) being at least partially open when a rotational speed (vR) of a turbomachine shaft (3, 24) is greater than a first threshold (S1) and in the absence of a fire detected in the turbomachine (1), characterized in that when the rotation speed (vR) of the shaft (3, 24) is smaller than the first threshold (S1), the shut-off valve (230) closes automatically and the subsequent opening of the shut-off valve (230) is limited / prevented when a fire has been detected during the flight of the turbomachine (1).
    [0002]
    2. Insulating method according to the preceding claim, wherein the shutoff valve (230) is closed when the rotational speed (vR) of the shaft is less than the first threshold (Si).
    [0003]
    3. Insulating method according to any one of the preceding claims, wherein a flow of fluid sufficient to cool the turbomachine (1) in case of fire flows in the supply system (200), when the shutoff valve (230) is open and the rotational speed (vR) is greater than or equal to the first threshold (Si).
    [0004]
    4. A turbomachine fluid supply system (200) comprising a fluid reservoir (201), a downstream portion (210) located downstream of the reservoir (201) and comprising a feed pump (212) in fluid, and a shutoff valve (230) located between the reservoir (201) and the downstream portion (210), the shutoff valve (230) being configured to be at least partially open when a rotational speed (vR) d a turbomachine shaft (3, 24) is greater than a first threshold (S1) and in the absence of a fire detected in the turbomachine (1), characterized in that when the rotational speed (vR) of the shaft (3, 24) is less than the first threshold (S1), the shut-off valve (230) closes automatically and the subsequent opening of the shut-off valve (230) is limited / prevented when a fire has been detected at during the flight of the turbomachine (1).
    [0005]
    5. Power system (200) according to the preceding claim, wherein the shutoff valve (230) comprises a safety position (PS) to which the shutoff valve (230) is brought back in the absence of control exerted on the shut-off valve (230), the shut-off valve (230) being closed in the safety position (PS).
    [0006]
    6. Feeding system (200) according to the preceding claim, wherein the shutoff valve (230) comprises a locking element (42) movable between a locking position in which the shutoff valve (230) is locked closed, and an unlocking position in which the shut-off valve (230) is configured to be closed or at least partially open, the locking member (42) being in the locked position in the absence of control exerted on the shut-off element. locking (42) so that the shut-off valve (230) is in the safety position (PS).
    [0007]
    7. Feed system (200) according to the preceding claim, wherein the shutoff valve (230) is pneumatically operated when the locking element (42) is in the unlocking position.
    [0008]
    The supply system (200) of any one of claims 6 and 7, wherein the locking member (42) is configured to move from the lock position to the system unlock position of a system digital regulator (5) for turbomachine or aircraft.
    [0009]
    The supply system (200) according to any one of claims 4 to 8, wherein the shutoff valve (230) comprises a piston (232) and a resilient means (231) mechanically connected to the piston (232). being configured to bias the piston (232) to a first position (P1) in which the shutoff valve (230) is closed, from a second position (P2) in which the shutoff valve (230) is at least partially opened.
    [0010]
    10. Turbomachine (1) comprising a power system (200) according to any one of claims 4 to 9.
    类似技术:
    公开号 | 公开日 | 专利标题
    FR3019583B1|2019-09-13|ISOLATION OF A FUEL FLUID RESERVOIR IN RELATION TO A DOWNSTREAM PART OF A TURBOMACHINE FEEDING SYSTEM IN THE EVENT OF A FIRE
    FR3007459A1|2014-12-26|SYSTEM AND METHOD FOR ROTATING A ROTARY MEMBER OF A MECHANICAL DEVICE, IN PARTICULAR A TURBOMACHINE.
    EP2392509A1|2011-12-07|Dual function door for aircraft engine nacelle
    FR2991421A1|2013-12-06|EPICYCLOIDAL TRAIN REDUCER WITH BEARING-BASED SATELLITE AXES
    CA2955739C|2017-07-04|System for supplying pressurised air installed in an aircraft turbine engine including sealing means
    EP3077288B1|2018-01-03|Fluids drainmast for propulsor assembly
    EP2072782B1|2010-11-24|Recirculation valve in an aeronautical engine
    FR2968041A1|2012-06-01|Fuel supply device for turboshaft engine e.g. single or double flow turbojet engine, of aircraft, has branch circuit and bypass valve to prevent fuel bypass of supply circuit through circuit when engine speed is below predetermined value
    WO2012069772A1|2012-05-31|Oil discharge device and turbomachine comprising such a device
    FR3075863B1|2019-11-22|TURBOMACHINE TURBINE HAVING A DEVICE FOR LIMITING OVERSPEED
    EP2949577B1|2017-10-04|Multi-engine power plant with a backup system for injecting fluid, and aircraft
    FR3059718B1|2019-06-21|HYDROMECHANICAL HYSTERESIS CUTTING DEVICE FOR TURBOMACHINE LUBRICATION SYSTEM
    FR3028887B1|2019-09-27|METHOD AND LUBRICATION CIRCUIT FOR TURBOMACHINE USING ELECTRICAL MEANS
    FR3075864B1|2019-11-15|TURBOMACHINE COMPRISING A TURBINE-DISCHARGING BLOWER THROUGH AN ELASTICALLY REMOVABLE CURVIC COUPLING
    FR3003544A1|2014-09-26|DEVICE FOR MONITORING AND CUTTING THE PRESSURIZING AIR SUPPLY OF AN AIRCRAFT FUEL TANK
    EP3329108B1|2021-11-03|Isolation of an aircraft turbine engine tank in case of a fire by closing a valve sensitive to the release of an extinguishant
    WO2011154641A1|2011-12-15|Device for supplying fuel to a gas turbine airplane engine
    EP3601765B1|2021-02-17|Improved device for temporarily increasing turbomachine power
    FR2960906A1|2011-12-09|Control system for turbomachine of engine of aircraft, has closing unit provided to stop sending of control command in response to reception of reinitialization command when overspeed is not detected by detection unit
    FR3109966A1|2021-11-12|CONTROL PROCESS AND CONTROL UNIT TO AVOID PUMPING A CHARGING COMPRESSOR IN AN AUXILIARY POWER UNIT
    FR3101666A1|2021-04-09|Turbomachine oil circuit including a relief valve
    FR3094045A1|2020-09-25|Turbomachine comprising a bypass line for cleaning fluids
    WO2017220881A1|2017-12-28|Method for testing the integrity of a fluid flow regulating system for a turbomachine
    同族专利:
    公开号 | 公开日
    FR3019583B1|2019-09-13|
    US20170022906A1|2017-01-26|
    WO2015155465A1|2015-10-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2402467A|1944-01-31|1946-06-18|Westinghouse Electric Corp|Lubrication control|
    US2991845A|1959-04-10|1961-07-11|Westinghouse Electric Corp|Lubrication system for a gas turbine engine|
    EP1936122A1|2006-12-21|2008-06-25|Techspace Aero S.A.|Isolation valve for the oil circuit of an airplane engine|
    EP2202387A1|2008-12-23|2010-06-30|Techspace Aero S.A.|Control-free isolation valve for the oil circuit of an airplane engine|
    FR2960022A1|2010-05-11|2011-11-18|Snecma|Oil supplying circuit for pressurized squeeze films in e.g. front ball bearings of ducted-fan turbine engine in aeronautical field, has bypass pipe connecting inlet of pressurizing valve with lubricating chamber for supplying oil to film|
    US2341071A|1942-11-09|1944-02-08|Sutherland Paper Co|Machine for use in setting up cellular cartons|
    US4150654A|1977-08-11|1979-04-24|Caterpillar Tractor Co|Engine and fuel shutdown control|
    JPS55161923A|1979-06-01|1980-12-16|Nissan Motor Co Ltd|Fuel control device for gas turbine engine|
    US4245465A|1979-08-30|1981-01-20|Avco Corporation|Gas turbine engine lubrication system including three stage flow control valve|
    US4367705A|1981-04-30|1983-01-11|Deere & Company|Heat activated fuel shut-off valve actuator|
    US5632297A|1995-09-26|1997-05-27|Amcast Industrial Corporation|Piston-type thermally or pressure activated relief device|
    JP5529676B2|2010-08-20|2014-06-25|三菱重工業株式会社|Fuel supply system for gas turbine combustor and fuel supply method for gas turbine combustor|
    US20140332703A1|2013-05-10|2014-11-13|Hamilton Sundstrand Corporation|Adjustment and locking mechanisms|DE102015112325A1|2015-07-28|2017-02-02|Rolls-Royce Deutschland Ltd & Co Kg|An aircraft engine with a fuel supply device and with at least one hydraulic fluid reservoir comprising a hydraulic fluid circuit with a heat exchanger|
    FR3039591B1|2015-07-31|2017-08-25|Snecma|INSULATION OF AN AIRCRAFT TURBOMACHINE TANK IN THE EVENT OF FIRE BY CLOSURE OF A VALVE SENSITIVE TO THE RELEASE OF AN EXTINGUISHING AGENT|
    FR3059718B1|2016-12-02|2019-06-21|Safran Aircraft Engines|HYDROMECHANICAL HYSTERESIS CUTTING DEVICE FOR TURBOMACHINE LUBRICATION SYSTEM|
    US20180283283A1|2017-03-28|2018-10-04|Pratt & Whitney Canada Corp.|Aircraft fire safety with oil pump deprime valve|
    法律状态:
    2016-04-07| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-06| PLFP| Fee payment|Year of fee payment: 4 |
    2018-03-22| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-03-25| PLFP| Fee payment|Year of fee payment: 6 |
    2020-03-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-03-23| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1453097|2014-04-08|
    FR1453097A|FR3019583B1|2014-04-08|2014-04-08|ISOLATION OF A FUEL FLUID RESERVOIR IN RELATION TO A DOWNSTREAM PART OF A TURBOMACHINE FEEDING SYSTEM IN THE EVENT OF A FIRE|FR1453097A| FR3019583B1|2014-04-08|2014-04-08|ISOLATION OF A FUEL FLUID RESERVOIR IN RELATION TO A DOWNSTREAM PART OF A TURBOMACHINE FEEDING SYSTEM IN THE EVENT OF A FIRE|
    US15/302,571| US20170022906A1|2014-04-08|2015-04-07|Method for isolating a combustible fluid tank from a downstream portion of a turbomachine supply system in case of a fire, and such a supply system|
    PCT/FR2015/050899| WO2015155465A1|2014-04-08|2015-04-07|Method for isolating a combustible fluid tank from a downstream portion of a turbomachine supply system in case of a fire, and such a supply system|
    [返回顶部]