• 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 (1) comprising: - a turbine shaft (8, 9) supported by at least one bearing (8b), - at least one enclosure (E3), housing the bearing (8b) of the shaft turbine (8, 9), - an oil cooling circuit of the enclosure (E3) comprising at least one nozzle (G1-G5) configured to inject oil from the cooling circuit into the enclosure (E3) , and - a regulator (14) configured to regulate the flow rate of the oil in the cooling circuit as a function of an oil temperature (Tmax) at the outlet of the enclosure (E3) and / or a pressure difference (AP) at the nozzle (G1-G5).
    公开号:FR3050761A1
    申请号:FR1653748
    申请日:2016-04-27
    公开日:2017-11-03
    发明作者:Serge Rene Morreale
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The present invention relates to an oil cooling device for a turbomachine and a turbomachine equipped with such a device.
    BACKGROUND
    A turbomachine comprises equipment that must be lubricated and / or cooled, such as bearings, reducers, electrical machines and their respective enclosures. For this, the turbomachine comprises a lubricating unit supplying an oil circuit in which the oil acts as lubricant and heat transfer fluid. The thermal power transmitted by the equipment to the oil is then removed via fuel-oil and / or air-oil type heat exchangers.
    The lubrication group comprises in particular a pump which is driven by an accessory drive box, well known to those skilled in the art under its English name "Accessory Gear Box" (AGB). The AGB is connected via a transmission shaft to a shaft of the turbomachine, generally the high pressure shaft, to supply energy to these various accessories.
    At present, equipment cooling is sized at take-off as it is the flight phase that generates the most thermal power. For the other phases of flight, the cooling of the equipment varies according to the speed of rotation of the high pressure shaft insofar as it drives the pump of the lubricating group via the AGB.
    However, it turns out that, apart from the take-off phase, the cooling of the different equipment is greater than necessary, which generates significant heat losses and pressure drops in the exchangers and substantially reduces the efficiency of the turbomachine. The cooling of the equipment is therefore not adapted to the flight phase of the turbomachine or the type of equipment to be cooled.
    SUMMARY OF THE INVENTION
    An object of the invention is therefore to provide a system for adjusting the cooling of the equipment of a turbomachine as a function of the flight phases in order to reduce the heat losses and to improve the efficiency of the turbomachine.
    For this, the invention proposes a turbomachine comprising: - a turbine shaft assembly supported by at least two bearings, - at least one enclosure, housing at least one of the bearings of the turbine shaft assembly, and - an oil cooling circuit of the enclosure, said cooling circuit comprising at least one nozzle configured to inject oil from the cooling circuit into the enclosure, and - a flow regulator, configured to regulate the flow rate of oil in the cooling circuit according to a temperature of the oil at the outlet of the enclosure and / or a pressure difference at the nozzle.
    Some preferred but not limiting characteristics of the turbomachine described above are the following, taken individually or in combination: the flow regulator is configured to regulate the flow of oil in the cooling circuit as a function of the temperature of the oil at the outlet of the enclosure and the pressure difference at the nozzle, - the turbine shaft assembly comprises a low pressure shaft and a high pressure shaft, the housing housing a rear bearing of the shaft high pressure, - the turbomachine further comprises a combustion chamber, the chamber being positioned under said combustion chamber, - the flow regulator is configured to regulate the flow rate of the oil in the cooling circuit so that the difference nozzle pressure is greater than or equal to a predefined pressure difference, said predefined pressure difference being equal to 0.9 bars, - the flow regulator is configured to regulate the flow rate of the oil in the cooling circuit so that the temperature at the outlet of the enclosure is less than or equal to a predefined maximum permissible temperature, maximum permissible temperature being 180 ° C, the turbine shaft assembly comprises a low pressure shaft and a high pressure shaft, the turbomachine further comprising a fan shaft and a reduction mechanism coupling the low shaft. pressure and the fan shaft, the reduction mechanism comprising an epicyclic or planetary reduction gear and having a reduction ratio of between 2.5 and 5; the turbomachine has a dilution ratio greater than 10, for example between 12 and 18, the fan shaft is supported by at least one fan bearing, the low pressure shaft is supported by at least one front bearing and one rear bearing and the high pressure shaft is supported by at least one front bearing and a rear bearing, the turbomachine further comprising: a first enclosure housing the at least one blower bearing, the reduction mechanism and a front bearing of the low pressure shaft, a second chamber housing the front bearing of the high pressure shaft and optionally a bevel gear between the high pressure shaft and a transmission shaft of an accessory drive housing and a third enclosure housing the rear bearing of the low pressure shaft, the first, the second and the third enclosures being cooled by the cooling system, - the flow regulator is configured to regulate the flow of oil in the cooling circuit so that: a difference between the inlet temperature and the outlet temperature of the reduction mechanism is between 30 ° C and 70 ° C, and / or a difference between e the inlet temperature and the outlet temperature at the bearings is between 70 ° C and 80 ° C, and / or a difference between the inlet temperature and the outlet temperature at the level of the enclosures is between 70 ° C and 80 ° C; ° C and 80 ° C, and / or a maximum temperature at the outlet of the reduction mechanism is less than or equal to 150 ° C, and / or a maximum temperature at the outlet of the bearings is less than or equal to 180 ° C, and / or a maximum temperature at the speaker output is less than or equal to 180 ° C, - each chamber is associated with a nozzle and the flow controller is configured to regulate the flow of oil in the cooling circuit according to the difference pressure at each nozzle, and / or - the flow controller comprises a variable geometry oil feed pump or a bypass.
    BRIEF DESCRIPTION OF THE DRAWINGS Other features, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with reference to the appended drawings given by way of non-limiting examples and in which:
    FIG. 1 is a partial sectional view of an exemplary embodiment of a turbomachine according to the invention, and
    FIG. 2 is a diagram illustrating an exemplary embodiment of a flow regulator that can be implemented in the turbomachine of FIG. 1.
    DETAILED DESCRIPTION OF AN EMBODIMENT
    A turbomachine 1 comprises, in a conventional manner, a fan 2 housed in a fan casing 2, an annular primary flow space and an annular secondary flow space. The primary flow space passes through a primary body comprising one or more stages of compressors, for example a low-pressure compressor 3 and a high-pressure compressor 4, a combustion chamber 5, one or more turbine stages, for example a turbine high pressure 6 and a low pressure turbine 7, and a gas exhaust nozzle.
    Typically, the high pressure turbine 6 rotates the high pressure compressor 4 via a first shaft, said high pressure shaft 8, while the low pressure turbine 7 rotates the low pressure compressor 3 and the fan 2 through a second shaft, said low pressure shaft 9. The low pressure shaft 9 is generally housed in the high pressure shaft 8.
    The fan 2 comprises a fan disk provided with fan blades 2 at its periphery which, when they are rotated, cause the flow of air into the primary and secondary flow spaces of the turbomachine 1. The disk blower is supported by the low pressure shaft 9 which is centered on the axis of the turbomachine 1 by a series of bearings and is rotated by the low pressure turbine 7.
    In order to improve the propulsive efficiency of the turbomachine 1, to reduce its specific consumption as well as the noise emitted by the fan 2, the turbomachine 1 may have a rate of dilution ("bypass ratio" in English, which corresponds to the ratio between the flow rate of the primary flow F1 (cold) and the flow rate of the secondary flow F2 (hot, which passes through the primary body)) high. By high dilution rate, here will be understood a dilution ratio greater than 10, for example between 12 and 18. For this purpose, the fan 2 is decoupled from the low-pressure turbine 7, thus allowing to independently optimize their speed of rotation. respective rotation. For example, the decoupling can be performed using a gear 10, such as a reduction mechanism epicyclic reduction ("star gear reduction mechanics" in English) or planetary gear ("planetary gear reduction mechanics" in English), placed between the upstream end (with respect to the flow direction of the gases in the turbomachine 1) of the low pressure shaft 9 and the blower 2. The blower 2 is then driven by the low pressure shaft 9 via the reduction mechanism 10 and an additional shaft, said fan shaft 11, which is fixed between the reduction mechanism 10 and the fan disk 2.
    This decoupling thus makes it possible to reduce the speed of rotation and the pressure ratio of the fan 2 ("fan pressure ratio" in English), and to increase the power extracted by the low-pressure turbine 7.
    In one embodiment, the reduction mechanism 10 comprises an epicyclic reduction mechanism. The reduction ratio of the reduction mechanism 10 is preferably between 2.5 and 5.
    The diameter of the blower 2 may be between eighty inches (203.2 centimeters) and one hundred inches (254.0 centimeters), preferably between eighty inches (203.2 centimeters) and ninety inches (228.6 centimeters). .
    The turbomachine 1 further comprises an AGB 12 which can be fixed to the engine casing, for example in the nacelle 2a surrounding the fan 2 or in the central compartment between the stream of the primary flow Fl and the vein of the secondary flow F2, and which mechanically drives a series of accessories by taking the driving power required on a motor shaft, generally the high pressure shaft 8. The AGB 12 causes including among these accessories, a lubrication group comprising a feed pump oil. An oil circuit connects the pump to the G1-G5 nozzles that target the lubrication and cooling components contained in the E1-E5 enclosures, respectively.
    In the following, the invention will more particularly be described in the case of a turbomachine 1 with a double flow comprising a high degree of dilution and a reducer type epicyclic reduction mechanism. This is however not limiting, the invention applying to any type of turbomachine 1, regardless of its dilution ratio, the presence of a reducer and the type of reducer 10 between the fan 2 and the low shaft pressure 9.
    FIG. 1 illustrates in particular an example of a turbomachine 1 with a double flow comprising an epicyclic reduction gear 10.
    As can be seen, in the case of such an example of a turbomachine 1, the oil circuit generally cools the epicyclic reduction gear 10, enclosures E1-E5 housing equipment and the AGB 12. The E1-E5 enclosures can comprise, from upstream to downstream in the direction of flow of the gases in the turbomachine 1: a first chamber El housing the bearings 7a of the fan 2, the epicyclic reduction gear 10 and the front bearing 9a of the low pressure shaft 9, a second chamber E2, located upstream of the high pressure compressor 4, housing the front bearing 8a of the high pressure shaft 8 and the bevel gear between the high pressure shaft 8 and the transmission shaft 13 of the AGB 12 (Diagrammatically illustrated in FIG. 1), a third enclosure E3 situated under the combustion chamber 11 and the high-pressure turbine 6, generally housing the rear bearing 8b of the high-pressure shaft 8, and a fourth and a fifth enclosure E4 and E5, located below the low pressure turbine 7 and the exhaust casing, respectively, housing the rear bearings 9b of the low pressure shaft 9.
    It will be understood that this configuration of the speakers E1-E5 is only one example of possible embodiment, the turbomachine 1 may comprise one or more additional enclosures (the front bearing 9a of the low pressure shaft 9 may for example be housed in a dedicated enclosure) or the different equipment and bearings that can be distributed differently in the E1-E5 enclosures (the front bearing 9a of the low pressure shaft 9 can for example be housed in the second enclosure E2 with the front bearing 8a of the shaft high pressure 8).
    It is known that the thermal power transmitted to the oil is even greater than its flow rate is important. The invention therefore proposes to deliver the oil flow strictly necessary for the cooling of the various members (gearbox 10, bearings 7a, 8a, 8b, 9a, 9b, etc.) of the turbomachine 1, within the limit of the admissible temperature by each equipment and the oil itself, in order to increase its efficiency.
    It will be noted that the lubrication unit generally comprises only one feed pump, the distribution of the oil in the oil circuit being determined by the outlet diameter of the nozzles G1-G5 at the level of each equipment to be cooled. . Only the flow of the pump can be changed.
    In order to deliver the oil flow rate strictly necessary for cooling, the turbomachine 1 comprises, downstream of the oil reservoir, a flow regulator configured to regulate the flow rate of the pump according to the flight phase. This regulation is operated as a function of: the maximum admissible temperature at the outlet of the third enclosure E3 (which is located under the combustion chamber 5), and the minimum pressure difference APmin at the terminals of the nozzles G1-G5.
    In other words, the flow regulator determines the flow of oil to be supplied to the pump of the lubrication unit so as to ensure that the temperature at the outlet of the third enclosure E3 is less than or equal to its maximum temperature, given that the flow must be sufficient to ensure that the pressure difference ΔΡ at the terminals of the nozzles G1-G5 is greater than the minimum pressure difference APmin.
    The temperature at the outlet of the third enclosure E3 is indeed the most penalizing temperature in the cooling circuit: by determining the oil flow taking into account this maximum temperature, it is thus possible to ensure that the other equipment is necessarily sufficiently cooled.
    The maximum temperature at the outlet of the third enclosure E3 can be 180 ° C.
    Moreover, the minimum pressure difference Δpmin across the nozzles G1-G5 is preferably equal to 0.9 bars.
    When the pressure difference ΔΡ at the terminals of the nozzles G1-G5 is smaller than the minimum pressure difference APmin, the flow regulator 14 increases the oil flow in the cooling circuit in order to increase said pressure difference ΔΡ and to reach the predetermined minimum threshold AP min of pressure difference across the nozzles G1-G5 (for example 0.9 bars). This increase in flow then has the effect of increasing the thermal power transmitted to the oil and thus reducing the temperature across the various equipment, including the output temperature of the third enclosure E3.
    Likewise, when the temperature at the outlet of the third enclosure E3 exceeds the maximum permissible temperature, the flow regulator 14 increases the oil flow in order to lower the said temperature, which has the effect of increasing the pressure difference AP to sprinkler terminals G1-G5.
    Thus, in all cases, the regulation of the flow makes it possible to respect the conditions fixed at the terminals of the nozzles G1-G5 and at the output of the third enclosure E3.
    In order for the thermal power reduction to be maximal, the flow regulation must concern all the thermal rejection vector stations. The size of the equipment (ACOC (for Air Cooled ON Cooler), FCOC (for Fuel Cooled ON Cooler), crankcase defroster (if defrosted with oil), fuel pump and recovery pumps) remains unchanged insofar as it remains established from the sizing point (that is, the take-off phase). However, these different jobs are now working under better conditions when lesser flow is required or at least possible.
    In this way, the efficiency of these different stations is improved and the pressure drops of the exchangers are reduced (to iso exchanged power, the air-oil exchanger (ACOC) requiring less air flow).
    Moreover, the ratio between the air flow rate and the oil flow of the recovery pumps of each enclosure E1-E5 is also increased. It should be noted in particular that the increase in the ratio between the air flow rate and the oil flow of the recovery pumps makes it possible to improve the recovery of the oil in the E1-E5 enclosures and thus to reduce the risks of retention. oil (bubbling) in all phases of flight (with the exception of the take-off phase, which remains the dimensioning phase for these positions so that the oil flow during this phase is unchanged).
    The flow control can be effected by means of a flow regulator 14 comprising a conventional variable geometry oil supply pump or a bypass having a valve 15 which returns a fraction of the oil flow to the reservoir 16. Whatever the embodiment, the flow regulator 14 can be controlled by a computer (FADEC type). The temperature information at the output of the third enclosure E3 can be obtained by means of a progressive sensor configured to measure said temperature substantially continuously or in predetermined time intervals. Depending on the temperature, the flow regulator 14 can therefore change the oil flow substantially continuously according to an arithmetic law. The information on the pressure difference ΔΡ can be obtained by means of progressive pressure sensors placed at the terminals of the nozzles G1-G5, or alternatively by means of on-off sensors (TOR type) placed at said terminals and sized to detect the minimum pressure difference APmin. In this variant, the regulation of the flow rate by the flow regulator 14 is not progressive and takes place only when the pressure difference ΔΡ becomes smaller than the minimum pressure difference APmin. The flow regulator 14 can then correct the oil flow by increasing it to a value that can be predefined (and correspond for example to the oil flow during takeoff phase).
    An exemplary embodiment of a flow regulator 14 comprising a bypass is illustrated in FIG. 2. The bypass comprises for example a valve 15, placed between the oil reservoir 16 and the first chamber (in the direction of flow of the oil in the cooling circuit). The valve 15 is in fluid communication on the one hand with the enclosures E1-E5 and on the other hand with the oil reservoir 16. In operation, oil is pumped from the oil reservoir 16 at an initial flow Di , which corresponds to the oil flow required during the take-off phase to cool the equipment. The oil then passes through the valve 15. Part of the oil thus transmitted is then distributed by the valve 15 between the nozzles G1 to G5 associated with the speakers E1-E5, via a main circuit and at a flow rate said to be regulated. , which is less than or equal to the initial flow Di, and the oil reservoir 16, via a bypass secondary circuit and at a so-called bypass flow rate Dbp. The ratio between the controlled flow rate Dr and the bypass flow rate Dbp is determined by the computer as a function of the measured temperature Tt (in real time) at the outlet of the third enclosure E3 and the minimum pressure difference APmin at the terminals of the nozzles G1. -G5. Of course, during the take-off phase, which is dimensioning, the regulated flow rate Dr is equal to the initial flow rate Di. Controlled flow rate Dr is on the other hand lower than the initial flow Di during the other phases of flight.
    The regulation of the flow rate of the oil in the circuit causes an increase in the temperature at the crossing of each equipment generating thermal power. However, by determining the oil flow as a function of the maximum permissible temperature Tmax at the outlet of the third enclosure E3, the temperature that can be reached at the different equipment of the turbomachine 1 remains admissible, without risk of damaging this equipment. .
    The control logic can also be configured to limit the oil temperature to 150 ° C at the output of the epicyclic gearbox gearing 10, whatever the case of operation, in order to ensure the presence of a sufficiently viscous film at contact of gear teeth 10.
    The outlet temperature of the oil at each equipment depends on its inlet temperature, which is taken globally at the exchanger outlet.
    For example, for an oil inlet temperature which may be between 80 ° C. and 120 ° C., the difference in temperature at the equipment to be cooled of the turbomachine 1 may remain within the following ranges thanks to the regulator 14: 70 ° C to 80 ° C at the bearings 7a, 8a, 8b, 9a, 9b 30 ° C to 70 ° C at the epicyclic reducer 10, 30 ° C to 70 ° C at the various speakers E1, E2, E4, E5.
    In addition, the flow regulator 14 is also configured so that the maximum permissible temperature is: less than or equal to 150 ° C. at the outlet of the epicyclic reduction gear 10 less than or equal to 180 ° C. at the outlet of the bearings 7a, 8a, 8b, 9a, 9b less than or equal to 160 ° C at the output of the speakers El, E2, E4, E5.
    The decrease in power is even greater than the input temperature is low.
    For example, we obtain a thermal power gain of up to 9 kW over all phases of flight (especially when the inlet temperature is close to 80 ° C), and of the order of 7kW cruise, this which results in a significant increase in the efficiency of the turbomachine 1.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Turbomachine (1) comprising: - a turbine shaft assembly (8, 9) supported by at least two bearings (8b), - at least one enclosure (E3), housing at least one of the bearings (8b) ) of the turbine shaft assembly (8, 9), and - an oil cooling circuit of the enclosure (E3), said cooling circuit comprising at least one nozzle (G1-G5) configured to inject the cooling circuit oil in the enclosure (E3), the turbomachine (1) being characterized in that it further comprises a flow regulator (14), configured to regulate the flow of oil in the cooling circuit; cooling according to an oil temperature (Tmax) at the outlet of the enclosure (E3) and / or a pressure difference (ΔΡ) at the nozzle (G1-G5).
    [2" id="c-fr-0002]
    2. The turbomachine (1) according to claim 1, wherein the flow regulator (14) is configured to regulate the flow of oil in the cooling circuit as a function of the temperature of the oil at the outlet of the enclosure (E3) and the pressure difference (ΔΡ) at the nozzle (G1-G5).
    [3" id="c-fr-0003]
    3. The turbomachine (1) according to one of claims 1 or 2, wherein the turbine shaft assembly (8, 9) comprises a low pressure shaft (9) and a high pressure shaft (8), the enclosure (E3) housing a rear bearing (8b) of the high pressure shaft (8).
    [4" id="c-fr-0004]
    4. The turbomachine (1) according to one of claims 1 to 3, further comprising a combustion chamber (5), the enclosure (E3) being positioned under said combustion chamber (5).
    [5" id="c-fr-0005]
    5. Turbine engine (1) according to one of claims 1 to 4, wherein the flow controller (14) is configured to regulate the flow of oil in the cooling circuit so that the pressure difference (ΔΡ) at the nozzle (G1-G5) is greater than or equal to a predefined pressure difference (APmin), said predefined pressure difference (APmin) may be equal to 0.9 bars.
    [6" id="c-fr-0006]
    6. The turbomachine (1) according to one of claims 1 to 5, wherein the flow controller (14) is configured to regulate the flow of oil in the cooling circuit so that the temperature at the outlet of the enclosure (E3) is less than or equal to a predefined maximum temperature (Tmax), said maximum temperature (Tmax) permissible being equal to 180 ° C.
    [7" id="c-fr-0007]
    7. Turbine engine (1) according to one of claims 1 to 6, wherein the turbine shaft assembly (8, 9) comprises a low pressure shaft (9) and a high pressure shaft (8), the turbomachine (1) further comprising a fan shaft (7) and a reduction mechanism (10) coupling the low pressure shaft (9) and the fan shaft (7), the reduction mechanism (10) comprising a reduction gear epicyclic or planetary and having a reduction ratio of between 2.5 and 5.
    [8" id="c-fr-0008]
    8. Turbomachine (1) according to claim 7, having a dilution ratio greater than 10, for example between 12 and 18.
    [9" id="c-fr-0009]
    9. Turbomachine (1) according to one of claims 7 or 8, wherein the fan shaft (7) is supported by at least one blower bearing (7a), the low pressure shaft (9) is supported by at least one front bearing (9a) and one rear bearing (9b) and the high pressure shaft (8) is supported by at least one front bearing (8a) and one rear bearing (8b), the turbomachine (1) comprising furthermore: - a first enclosure (E1) housing the at least one blower bearing (7a), the reduction mechanism (10) and a front bearing (9a) of the low pressure shaft (9), - a second enclosure (E2) housing the front bearing (8a) of the high pressure shaft (8) and optionally a bevel gear between the high pressure shaft (8) and a drive shaft (13) of a drive housing accessories (12), and - a third enclosure (E4, E5) housing the rear bearing (8b) of the low pressure shaft (9), the first (El), the second (E2) and the third einte (E4, E5) being cooled by the cooling system.
    [10" id="c-fr-0010]
    10. The turbomachine (1) according to claim 9, wherein the flow regulator (14) is configured to regulate the flow of oil in the cooling circuit so that: - a difference between the inlet temperature and the temperature of the reduction mechanism (10) is between 30 ° C and 70 ° C, and / or - a difference between the inlet temperature and the outlet temperature at the bearings (7a, 8a, 8b, 9a, 9b) is between 70 ° C and 80 ° C, and / or - a difference between the inlet temperature and the outlet temperature at the level of the enclosures (E1, E2, E4, E5) is between 70 ° C and 80 ° C, and / or - a maximum temperature at the outlet of the reduction mechanism (10) is less than or equal to 150 ° C, and / or - a maximum temperature at the outlet of the bearings (7a, 8a, 8b, 9a, 9b) is less than or equal to 180 ° C, and / or - a maximum temperature at the speaker output (E1, E2, E4, E5) is less than or equal to e at 180 ° C.
    [11" id="c-fr-0011]
    11. The turbomachine (1) according to one of claims 9 or 10, wherein each chamber (E1-E5) is associated with a nozzle (G1-G5) and the flow regulator (14) is configured to regulate the flow rate. oil in the cooling circuit as a function of the pressure difference (ΔΡ) at each nozzle (G1-G5).
    [12" id="c-fr-0012]
    12. Turbine engine (1) according to one of claims 1 to 11, wherein the flow controller (14) comprises a variable geometry oil feed pump or a bypass.
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    同族专利:
    公开号 | 公开日
    US20170314473A1|2017-11-02|
    GB2551432A|2017-12-20|
    GB2551432B|2021-07-21|
    FR3050761B1|2019-07-05|
    GB201706718D0|2017-06-14|
    US10450959B2|2019-10-22|
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    FR3043714B1|2015-11-16|2017-12-22|Snecma|FRONT AIRCRAFT TURBOMACHINE PART COMPRISING A SINGLE BLOWER CONDUCTED BY A REDUCER, AS WELL AS STRUCTURAL OUTPUT LEAD DIRECTORS FITTED PARTLY BEFORE A SEPARATION SPOUT|
    US10954863B2|2019-04-09|2021-03-23|General Electric Company|Phasing gearbox|
    GB202005028D0|2020-04-06|2020-05-20|Rolls Royce Plc|Gearboxes for aircraft gas turbine engines|
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    2018-09-14| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20180809 |
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    优先权:
    申请号 | 申请日 | 专利标题
    FR1653748|2016-04-27|
    FR1653748A|FR3050761B1|2016-04-27|2016-04-27|CONTROL OF OIL FLOW IN A COOLING CIRCUIT OF A TURBOMACHINE|FR1653748A| FR3050761B1|2016-04-27|2016-04-27|CONTROL OF OIL FLOW IN A COOLING CIRCUIT OF A TURBOMACHINE|
    US15/498,850| US10450959B2|2016-04-27|2017-04-27|Regulation of the oil flow in a cooling circuit of a turbomachine|
    GB1706718.2A| GB2551432B|2016-04-27|2017-04-27|Regulation of the oil flow in a cooling circuit of a turbomachine|
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