Classifications

• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D7/00—Rotors with blades adjustable in operation; Control thereof
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/18—Lubricating arrangements
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D17/00—Regulating or controlling by varying flow
  • F01D17/10—Final actuators
  • F01D17/12—Final actuators arranged in stator parts
  • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
  • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/18—Lubricating arrangements
  • F01D25/20—Lubricating arrangements using lubrication pumps
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
  • F05D2260/79—Bearing, support or actuation arrangements therefor
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/98—Lubrication

Definitions

• the invention relates to the field of oil tanks for aircraft turbine engines. More particularly, the invention relates to the field of oil tanks for flight phases during which the gravitational force is zero (0g condition) or negative (negative g condition).
• a turbomachine for an aircraft comprises, from upstream to downstream, at least a first rotor, also called propeller rotor, such as a propeller when the turbomachine is a turboprop, or even an unducted fan when the turbomachine is of the "open rotor" type. or a ducted fan when the turbomachine is a turbojet, a compressor, a combustion chamber and a turbine.
• the compressor rotor is connected to the turbine rotor and the first rotor by a drive shaft.
• a flow of air is compressed within the compressor then the compressed air is mixed with fuel and burned within the combustion chamber.
• the gases formed by the combustion pass through the turbine which drives the compressor rotor and the thruster rotor.
• the propeller or the fan of the propulsion rotor as well as the rotor of the compressor are equipped with vanes which make it possible to exert an action on the flow of air.
• the turbine engine comprises a system for controlling the blades with variable pitch angle which comprises a control unit connected to a hydraulic actuator to move the blades in rotation with respect to a longitudinal axis of the blades according to the orientation of the air flow .
• the turbomachine In order to supply oil to the control system and in particular the hydraulic actuator as well as other elements of the turbomachine such as bearings and reducers, the turbomachine typically comprises a main oil supply system.
• This supply system comprises, for example, a main reservoir connected to a first supply circuit for lubricating the bearings and to a second supply circuit for supplying oil to the hydraulic actuator.
• a supply pump is mounted on the second supply circuit and allows the suction of oil from the main tank and the circulation of this oil to the hydraulic actuator.
• the main tank typically comprises an enclosure having a lower and upper wall connected by transverse walls. The lower wall includes an orifice connected to the pump for oil suction.
• the oil contained in the main tank finds itself stuck on the upper wall of the tank opposite the orifice in negative g conditions where the oil and the air form a suspension charged with bubbles of air in 0g condition.
• the pump therefore no longer sucks the oil from the reservoir but air or oil heavily laden with air bubbles, which degrades the oil supply to the control system and can even cause the pump to stop. feed pump.
• an auxiliary oil tank for supplying a blade pitch control system of an aircraft turbine engine, comprising an enclosure comprising: a lower wall and a wall upper connected by transverse walls, a first outlet port intended to be connected to a main oil reservoir, a second outlet port intended to be connected to the control system by a second oil supply circuit, a first port input intended to be connected to the control system by an auxiliary recovery circuit.
• the enclosure is characterized in that it further comprises: a first internal volume in fluid communication with the first outlet port, a second internal volume in fluid communication with the second outlet port, and separated from the first internal volume by a baffle, the baffle including a first end wall extending from the top wall to the bottom wall and a second end wall extending from the bottom wall toward the top wall, the first and second end walls being substantially parallel, the first end wall and the bottom wall defining a first fluid passage, and the second end wall and the top wall defining a second fluid passage.
• the tank according to the invention therefore comprises a baffle which makes it possible to separate the first internal volume from the second internal volume.
• the air entering through the first outlet port circulates within the enclosure of the first internal volume towards the second internal volume.
• the circulation of air between the two volumes is slowed down by the baffle which allows the oil which is contained in the second internal volume to remain in communication with the second outlet port to supply the second circuit .
• the air does not reach the second outlet port.
• the auxiliary tank is capable of supplying the control system during such a phase of flight. The blades are therefore not feathered and the aircraft turbine engine maintains maximum thrust during this phase of flight.
• the invention may include one or more of the following characteristics, taken separately from each other or in combination with each other:
• the first end wall and the second end wall delimit an intermediate volume, the sum of the first volume and the intermediate volume being equal to the second internal volume;
• the first end wall and the second end wall delimit an intermediate volume, the sum of the first volume and the intermediate volume being less than the second internal volume;
• the baffle comprises a first intermediate wall and a second intermediate wall which are arranged substantially parallel to and between the first and second end walls, the first intermediate wall defining with the upper wall a third fluid passage and the second intermediate wall delimiting with the lower wall a fourth fluid passage, the first intermediate wall being arranged between the first end wall and the second intermediate wall;
• the upper wall of the enclosure comprises a first portion substantially parallel to the lower wall and a second portion inclined towards the inside of the enclosure, the first and second portions forming a vertex directed towards the outside of the enclosure;
• the first internal volume is between 1 L and 50 L and the second internal volume is between 1 L and 50 L;
• the enclosure further comprises a second inlet port intended to be connected to a valve.
• the invention also relates to a turbine engine for an aircraft comprising: blades with variable pitch angle, a blade control system comprising a control unit connected to at least one hydraulic actuator, an oil supply system comprising: a main supply comprising: a second supply circuit for the control system, a main tank connected to the second supply circuit, and an oil supply pump mounted on the second supply circuit and comprising an inlet and an outlet connected to the control system, an auxiliary supply device comprising: an auxiliary oil reservoir according to any one of the preceding characteristics, the first outlet port being connected to the main reservoir, the second outlet port being connected to the second circuit supply and the first input port being connected to the control system.
• the turbomachine may include one or more of the following characteristics, taken separately from each other or in combination with each other:
• the auxiliary supply device further comprises a valve comprising a body having a first inlet connected to the main reservoir, a second inlet connected to the second outlet port of the auxiliary reservoir and an outlet connected to the inlet of the supply pump , the valve further comprising a movable member in the body and configured to move between a first position in which the first inlet of the valve is in fluid communication with the outlet of the valve and a second position in which the second inlet of the valve is in fluid communication with the valve outlet;
• the auxiliary reservoir comprises a second inlet port
• the auxiliary supply device comprises a valve comprising a body having an inlet connected to the auxiliary reservoir and a first outlet connected to the second inlet port of the auxiliary reservoir, and a second outlet connected to the control system, the valve further comprising a moveable member in the body and configured to move between a first position in which the valve inlet is in fluid communication with the first valve outlet and a second position wherein the valve inlet is in fluid communication with the second valve outlet;
• Figure 1 is a schematic representation in longitudinal section of an aircraft half-turbomachine according to a first embodiment of the invention
• Figure 2 is a schematic representation in perspective of an aircraft turbine engine according to a second embodiment of the invention
• Figure 3 is a schematic representation in longitudinal section of an aircraft turbine engine according to a third embodiment of the invention
• FIG.4 Figure 4 is a schematic representation of an oil supply system according to a first embodiment of the invention.
• FIG.5 is a schematic representation of an oil supply system according to a second embodiment of the invention.
• FIG.6 Figure 6 is a schematic representation in section of an auxiliary oil tank according to the invention.
• Figure 7 is a partial schematic representation in section of the auxiliary oil tank according to an embodiment of the invention.
• a turbomachine 1, 1′,1′′ for an aircraft is represented for example in FIGS. 1 to 3.
• the turbomachine 1, 1, 1′′ comprises a first rotor 2 connected to a motor M extending around a longitudinal axis X.
• the engine M comprises, from upstream to downstream in the flow direction of a main air flow F along the longitudinal axis X, a compressor such as a low pressure compressor 3 and a high pressure compressor 4, a combustion chamber 5, a turbine such as a high pressure turbine 6 and a low pressure turbine 7, and a nozzle 8.
• the high pressure turbine rotor 6 is connected to the high pressure compressor rotor 4 by a high pressure shaft 9.
• the low pressure turbine rotor 7 is connected to the low pressure compressor rotor 3 by a low pressure shaft 10.
• the low pressure 10 and high pressure 9 shafts are supported by bearings 12a.
• the bearings 12a are contained in a lubrication chamber 12 for their lubrication.
• an upstream bearing 120a is arranged radially between an upstream end of the low pressure shaft 10 and a upstream bearing support 120b and a downstream bearing 120a' is arranged downstream of the upstream bearing 120a and radially between the low-pressure shaft 10 and a downstream bearing support 120b'.
• the lubrication chamber 12 is annular.
• the upstream and downstream bearings 120a, 120a' are arranged in the lubrication enclosure 12.
• the first rotor 2 is driven in rotation by a rotor shaft 100.
• the rotor shaft 100 is connected to the low pressure shaft 10.
• the low pressure shaft 10 rotates the rotor shaft 100.
• the low pressure shaft 10 is connected to the rotor shaft 100 by a speed reducer 11. This makes it possible to drive the first rotor 2 to a speed lower than the speed of rotation of the low pressure shaft 10.
• the speed reducer 11 is for example arranged in the lubrication enclosure 12 between the upstream bearing 120a and the downstream bearing 120a'.
• the main air flow F crosses the turbomachine 1, 1 ', 1 ” and is divided into a flow of primary air F1 which crosses the engine M within a primary stream and into a flow of secondary air F2 which passes through the first rotor 2 in a secondary stream surrounding the primary stream.
• the turbomachine 1, 1′, 1′′ comprises vanes 2a which make it possible to exert an action on the main air flow F, or primary F1 or the secondary air flow F2.
• the rotors of the low pressure 3 and high pressure 4 compressors include blades 2a which make it possible to compress the flow of primary air F1 upstream of the combustion chamber 5.
• the blades 2a can be fixed in rotation around the longitudinal axis X, or can be mobile in rotation around the longitudinal axis X or an axis parallel to the longitudinal axis X.
• the turbomachine 1 is a turbofan engine.
• the first rotor 2 is a ducted fan which is arranged upstream of the motor M.
• the fan comprises blades 2a.
• the blades 2a of the fan are rotatable around the longitudinal axis X. They are for example carried by a disk centered on the longitudinal axis X.
• blades 2a are arranged inside a fan casing 2b.
• the casing 2b is surrounded by a nacelle (not shown).
• the turbomachine 1′ is a turbojet with an unducted fan.
• the first rotor 2 is an unducted fan which comprises blades 2a.
• the fan is arranged downstream of the motor M (not visible in this figure).
• the fan is rotatable around the longitudinal axis X.
• the blades 2a of the fan are carried by a disc rotatable around the longitudinal axis X.
• a rectifier 2' is optionally arranged downstream of the fan 2 in order to straighten the secondary air flow F2.
• the stator 2' forms a fixed blading around the longitudinal axis X. It comprises vanes 2a which can be variable-pitch.
• the blades 2a are mounted outside the nacelle.
• the turbomachine 1 is a turboprop.
• the first rotor 2 is a propeller which is arranged upstream of the motor M.
• the propeller is rotatable around a propeller axis H parallel to the longitudinal axis X, and comprises blades 2a.
• the vanes 2a are carried by a disc centered on the propeller axis H.
• the vanes 2a are for example at least two in number and regularly distributed over the disc.
• the blades 2a extend radially with respect to the longitudinal axis X. They typically comprise a blade and an element for fixing to the disk.
• the fixing element is for example a foot or a platform.
• the vanes 2a have a variable pitch angle. By variable pitch angle, it is understood that the blades 2a are rotatable around a transverse axis Z substantially perpendicular or perpendicular to the longitudinal axis X.
• the turbomachine 1, 1', 1” comprises a control system 13 of the blades 2a with variable pitch angle.
• the control system 13 comprises a unit control 13a and at least one hydraulic actuator 13b supplied with oil.
• the control unit 13a is for example fixed in rotation around the longitudinal axis X.
• the control unit 13a is for example connected to a stator of the turbomachine 1, 1', 1”.
• the control unit 13a is known in the field of the invention by the acronym PCU for “Pitch Control Unit” in English.
• the hydraulic actuator 13b is for example a hydraulic cylinder comprising a rod movable in translation connected to the blade 2a optionally via a motion transformation mechanism.
• the translational movement of the rod makes it possible to move the blade 2a in rotation around its axis.
• the translational movement of the movable rod is controlled by the control unit 13a which supplies oil to the hydraulic actuator 13b.
• the hydraulic actuator 13b is rotatable around the longitudinal axis X or around an axis parallel to the longitudinal axis X.
• the hydraulic actuator 13b is for example integral in rotation with the blades 2a.
• the hydraulic actuator 13b is for example arranged upstream of the control unit 13a.
• the control system 13 advantageously comprises an oil transfer device 13c from the control unit 13a to the hydraulic actuator 13b.
• the oil transfer device 13c transfers oil from the control unit 13a which is fixed to the hydraulic actuator 13b which is rotatable.
• the oil transfer device 13c is known by the acronym OTB for "Oil Transfer Bearing” in English.
• the oil transfer device 13c is for example arranged in the lubrication chamber 12.
• the turbomachine 1, T, 1” further comprises an electrical control unit 24.
• the electrical control unit 24 makes it possible to control the control unit 13a.
• the electrical control unit 24 is for example a FADEC (for "Full Authority Digital Engine Control" in English).
• the turbomachine 1, T, 1” includes an oil supply system comprising a main supply system 14 and an auxiliary supply device 14', shown in Figures 4 and 5.
• the main supply system 14 ensures the lubrication of the bearings 12a within the lubrication enclosure 12 and of the reducer 11 and the oil supply of the control system 13 during a first phase of operation of the turbomachine 1, 1 ' , 1”.
• the auxiliary supply device 14' ensures the lubrication of the control system 13 during a second phase of operation of the turbomachine 1, '1, 1' during which the gravitational force is zero (condition of 0g) or reversed (condition of g negative).
• the main oil supply system 14 comprises a first supply circuit 14a for the lubrication chamber 12 and a second oil supply circuit 14b for the control system 13.
• the main supply system 14 advantageously comprises a metering valve 19 with variable diaphragm.
• the metering valve 19 makes it possible to supply the speed reducer 11 with oil. the speed reducer 11 .
• the main supply system 14 advantageously comprises an oil recovery circuit 14a' from the lubrication enclosure 12 and an oil recovery circuit 14b' from the control system 13.
• the main supply system 14 also comprises a main oil reservoir 15 connected to the first supply circuit 14a and to the second supply circuit 14b.
• the first supply circuit 14a comprises a first supply pump 16a allowing the suction of oil from the main tank and its circulation in the first supply circuit 14a to supply oil the lubrication chamber 12.
• the first supply circuit 14a comprises a main exchanger 17a, for example air/oil or oil/fuel, and optionally a second exchanger 17b, for example oil/fuel which are arranged between the first pump 16a and the lubrication chamber 12.
• the circuit 14a' for recovering the oil from the lubrication enclosure 12 comprises a second recovery pump 16b connected to the lubrication enclosure 12 and to the main tank 15.
• the pump 16b makes it possible to recover the oil from the lubrication enclosure 12 to return it to the main tank 15 through the recovery circuit 14a'.
• the main supply system 14 comprises a supply pump 18 dedicated to supplying oil to the control system 13.
• the supply pump 18 is for example mounted on the second supply circuit 14b.
• the feed pump 18 is for example a volumetric pump.
• the volumetric pump is, for example, fixed displacement or variable displacement.
• the feed pump 18 includes an inlet 18a and an outlet 18b connected to the control system 13.
• the second supply circuit 14b may include a filter 26 arranged between the supply pump 18 and the control system 13.
• the first pump 16a draws oil from the main tank 15 and allows the circulation of the oil in the first supply circuit 14a until the lubrication chamber 12.
• the supply pump 18 also draws oil from the main reservoir 15, for example upstream or downstream of the first pump 16a and routes the oil into the second supply circuit 4b up to control system 13.
• the oil is plated in the upper part of the main tank 15 while the lower part connected to the first pump 16a is occupied by air.
• an air-oil mixture is in suspension in the tank 15 and in case of reverse gravity of the air occupies the lower part of the main tank 15 connected to the first pump 16a.
• the supply pump 18 is indirectly connected to the lower part of the main tank 15, and therefore risks sucking in air from the main tank 15, or oil heavily laden with air bubbles. This is not acceptable because the control system 13 must be supplied with oil relatively free of air bubbles, so as not to compromise the operation of the control unit 13a and therefore of the hydraulic actuator 13b which controls the pitch. blades 2a.
• the invention provides an auxiliary power supply device 14'.
• the auxiliary power supply device 14' is mounted on the second power supply circuit 14b.
• the auxiliary supply device 14' comprises an auxiliary oil tank 20, optionally an auxiliary pump 22 and a valve 21 .
• the auxiliary pump 22 includes an inlet 22a and an outlet 22b.
• the valve 21 is for example a 3/2 hydraulic distributor, that is to say having three orifices and two positions.
• the auxiliary pump 22 is arranged between the valve 21 and the auxiliary tank 20.
• the inlet 22a of the pump 22 is connected to the auxiliary tank 20.
• the auxiliary pump 22 is a pump fixed displacement hydraulics.
• the auxiliary supply device 14' advantageously comprises a rotary motor to drive the auxiliary pump 22.
• the auxiliary pump 22 is driven by the low pressure shaft 10 or the high pressure shaft 9.
• the valve 21 is a spring-return hydraulically controlled distributor.
• the valve 21 has a body 21a having an inlet connected to the outlet 22b of the auxiliary pump 22 and a first outlet connected to the auxiliary reservoir 20 and a second outlet connected to the second supply circuit 14b, between the supply pump 18 and the control system 13.
• the valve 21 further comprises a movable member in the body 21 a configured to move between a first position in which the inlet of the valve 21 is in fluid communication with the first outlet of the valve 21 and a second position in which the inlet of the valve 21 is in fluid communication with the second outlet of the valve 21 .
• the valve 21 comprises for example a return spring allowing the return of the movable member from the second position to the first position.
• the auxiliary pump 22 draws oil from the auxiliary tank 20 and the oil is redirected towards the auxiliary tank 20.
• the control system 13 is powered in oil by the feed pump 18 which sucks the oil from the main tank 15.
• the auxiliary pump 20 draws oil from the auxiliary tank 20 and the oil is supplied to the control system 13 through the second supply circuit 14b for example.
• the valve 21 is in the first position.
• valve 21 is in the second position. This makes it possible to ensure the oil supply to the control system 13 from the auxiliary reservoir 20 and to avoid any interruption of the oil supply to the control system 13.
• valve 21 comprises a hydraulic actuation chamber connected to inlet 18a of feed pump 18.
• pressure in the first supply circuit 14a drops because the first pump 16a draws air or an air-oil mixture from the main tank 15.
• the pressure at the inlet 18a of the supply pump 18 connected to the first supply circuit 14a then becomes lower than a threshold pressure, which drives the movable member of the valve 21 into the second position under the action of the valve spring.
• a threshold pressure which drives the movable member of the valve 21 into the second position under the action of the valve spring.
• valve 21 is directly sensitive to the gravitational force.
• the auxiliary supply device 14' advantageously further comprises a pressure limiter 25a arranged at the outlet of the auxiliary pump 22, between the auxiliary pump 22 and the valve 21 .
• the pressure limiter 25a is for example a non-return valve.
• the metering valve 19 is mounted on the first supply circuit 14a.
• the metering valve 19 is mounted between the first pump 16a and the lubrication enclosure 12.
• the metering valve 19 is mounted between the main exchanger 17a which is in this mode an oil/fuel exchanger and the second exchanger 17b .
• the metering valve 19 has the function of distribution valve for the oil distributed between the lubrication enclosure 12 and the speed reducer 11 . It is a valve with two outlets.
• the first output of the metering valve 19 is connected to the lubrication enclosure 12 and the second output of the metering valve 19 is connected to the reducer 11 .
• the metering valve 19 is for example controlled by the electrical control unit 24.
• a third exchanger 17c for example air/oil, connects the second outlet of the metering valve 19 and the reducer 11.
• the supply pump 18 comprises a non-return valve 25b in order to guarantee that all the oil delivered by the auxiliary pump 22 supplies the control system 13.
• the valve 21 has a body 21a having a first inlet connected to the main reservoir 15 and a second inlet connected to the auxiliary reservoir 20.
• the valve 21 further comprises an outlet connected to the inlet 18a of the pump supply 18.
• the valve 21 further comprises a movable member in the body configured to move between a first position in which the first inlet is in fluid communication with the outlet and a second position in which the second inlet is in fluid communication with the output.
• the valve 21 comprises for example a return spring allowing the return of the movable member from the second position to the first position.
• Output 18b of feed pump 18 is connected to control circuit 13.
• the feed pump 18 draws oil from the main tank 15 and in the second position, the feed pump 18 draws oil from the auxiliary tank 20.
• the valve 21 thus makes it possible to control the flow of oil in the second circuit 14b.
• the turbomachine 1, 1′, 1′′ is in a first operating phase, in particular when the aircraft is in a so-called “normal” flight phase, the valve 21 is in the first position and the main pump 18 draws in the oil from the main tank 15 to supply the control system 13.
• valve 21 When the turbomachine 1, 1', 1” is in a second phase of operation, in particular when the aircraft is in a phase of flight in which the gravitational force is zero (called 0g condition) or negative (called negative g condition), valve 21 is in the second position and the main pump 18 draws oil from the auxiliary tank 20 to supply oil to the control system 13.
• the valve 21 is electrically controlled.
• the turbine engine 1, 1', 1 comprises a sensor configured to deliver a signal to the electrical control unit 24.
• the sensor is configured to detect the second phase of operation of the turbine engine 1, 1', 1 ”.
• the sensor is for example an accelerometer.
• the movable member of the valve 21 is directly sensitive to the gravitational force exerted on the turbomachine 1, 1 ', 1 '. When the gravitational force is greater than a given threshold, therefore in the first operating state, the mobile member is in the first position. During the second operating state, the movable member detects the second operating state and moves into the second position.
• the auxiliary pump 22 in this second embodiment is optional.
• the auxiliary pump 22 is for example a centrifugal pump connected to the outlet of the valve 21.
• the auxiliary pump 22 is therefore arranged between the valve 21 and the supply pump 18.
• the inlet 18a of the pump is therefore connected to the outlet of the valve 21 via the auxiliary pump 22.
• a second air/oil exchanger 23 is arranged between the valve 21 and the supply pump 18. More particularly, the second air/oil exchanger 23 is arranged between the centrifugal pump 22 and the supply pump 18.
• the centrifugal pump 22 and the second air/oil exchanger 23 are mounted on the second supply circuit 14b.
• the metering valve 19 is mounted on the second supply circuit 14b.
• the metering valve 19 is mounted between the supply pump 18 and the reducer 11, and comprises a single outlet connected to the lubrication enclosure 12.
• the metering valve 19 has no function flow distribution between two outlets.
• the supply pump 18 is mounted as a bypass on the second circuit 14b between the valve 21, and in particular the second air/oil exchanger 23 when it is present and the metering valve 19.
• the metering valve 19 is capable of opening when the valve 21 is in the first position, which makes it possible to supply oil to the reducer 11 from the main reservoir 15, and is capable of remaining open and/or to close when the valve 21 is in the second position.
• metering valve 19 is able to close when valve 21 is in the second position. This makes it possible not to supply the reducer 11 with oil from the auxiliary tank 20, in order to exclusively supply the control system 13 from the auxiliary tank 20.
• the auxiliary tank 20 is sized to supply only the control system 13 which makes it less bulky.
• the variable opening of the metering valve 19 is controlled by the electric control unit 24.
• the electric control unit 24 sends a signal to the metering valve 19 to open or close the latter according to the operating phase. .
• the auxiliary tank 20 is for example shown in Figure 6.
• the auxiliary tank 20 is configured to deliver oil during the second phase of operation of the turbomachine 1, 1 ', 1'.
• the auxiliary tank 20 comprises an enclosure 200.
• the enclosure 200 is for example metallic.
• the enclosure 200 is for example polygonal. It comprises an upper wall 200a and a lower wall 200b connected by opposite transverse walls 200c, 200d.
• the transverse walls 200c, 200d can be parallel to each other.
• the upper wall 200a comprises for example a first portion 200a1 parallel to the lower wall 200b and a second portion 200a2 inclined towards the inside of the enclosure 200.
• the first portion 200a1 and the second portion 200a2 meet at a vertex O oriented towards outside the enclosure 200.
• vertex O represents a high point for oil recovery, which normally eliminates the risk of air being present at this level in a negative gravity situation.
• the enclosure 200 has a first outlet port 201 connected to the main reservoir 15 for example by a first pipe 201a, a second outlet port 202 connected to the second supply circuit 14b by the valve 21 or the auxiliary pump 22, a input port 203 connected to the control system by the oil recovery circuit 14b' of the control system 13 and optionally a second input port 206 connected to the valve 21.
• the first output port 201 is for example on the transverse wall 200c and the first entry port 203 and for example made on the opposite transverse wall 200d.
• the second exit port 202 is for example provided on the upper wall 200a, for example on the vertex O.
• the enclosure 200 delimits a total volume for example comprised between 2 L and 100 L, advantageously comprised between 2 L and 40 L and preferentially comprised between 4 L and 30 L.
• the enclosure 200 comprises a first internal volume V1 in fluidic communication with the first outlet port 201 and a second internal volume V2 in fluid communication with the second outlet port 202.
• the first internal volume V1 is between 1 L and 50 L, advantageously between 1 L and 20 L and even more advantageously between 2 L and 15 L.
• the second internal volume V2 is between 1 L and 50 L, advantageously between 1 L and 20 L and even more advantageously between 2 L and 15 L.
• the first internal volume V1 is less than the second internal volume V2.
• the auxiliary tank 20 further comprises a baffle 204 arranged in the enclosure 200 which separates the first internal volume V1 from the second internal volume V1.
• Baffle 204 includes a first end wall 204a extending from top wall 200a toward bottom wall 200b and a second end wall 204b extending from bottom wall 200b toward top wall 200a.
• the first and second end walls 204a, 204b are for example parallel to the transverse walls 200c, 200d.
• the first and second end walls 204a, 204b are arranged between the first outlet port 201 and the second outlet port 202.
• the first end wall 204a and the lower wall 200b delimit a first fluid passage P1, and the second end wall 204b and the upper wall 200a delimit a second passage P2 of fluid.
• the fluid is for example air and/or oil.
• the first end wall 204a and the second end wall 204b delimit an intermediate volume V3.
• the sum of the first volume V1 and of the intermediate volume V3 is equal to the second internal volume V2. This ensures that the internal volume V2 will contain oil exclusively during the second phase of operation.
• the sum of the volume of the pipe 201 a connecting the first inlet port 201 to the main reservoir 15, of the first volume V1 and of the intermediate volume V3 is equal to the second internal volume V2.
• the sum of the first volume V1 and of the intermediate volume V3 is therefore less according to this example than the second internal volume V2.
• the volume of the pipe 201 a can be dimensioned to be equal to the volume of oil consumed during the second phase of operation of the turbomachine 1, 1 ', 1 ”.
• the baffle 204 advantageously further comprises a first intermediate wall 204c and a second intermediate wall 204d which are arranged parallel to and between the first and second end walls 204a, 204b, the first intermediate wall 204c delimiting with the upper wall 200a a third fluid passage P3 and the second intermediate wall 204d delimiting with the lower wall 200b a fourth fluid passage P4, the first intermediate wall 204c being arranged between the first end wall 204a and the second intermediate wall 204d.
• the auxiliary tank 20 is supplied with oil by the control system 13.
• the excess oil is communicated to the main tank 15. This communication is ensured by the pipe 201 a.
• the control system 13 is supplied with oil from the main tank 15.
• the auxiliary tank 20 During the second phase of operation of the turbomachine 1, 1 1 ”, air enters the auxiliary tank 20 via the first outlet port 201 . Indeed, the flow of oil leaving the tank is lower than that entering. However, thanks to the baffle 204, the passage of air from the first internal volume V1 to the second internal volume V2 is slowed down. Thus, the supply pump 18 or the auxiliary pump 22 sucks in oil and not air or oil with a high air content, which makes it possible to supply the control system 13 during the second phase of operation. . It is understood that advantageously, the volume of the pipe 201a and the baffle 204a is equal to the volume of oil exiting through the second outlet orifice 202 during the second phase of operation.
• Such an auxiliary tank 20 has the advantage of being simple and reliable.
• such an auxiliary tank 20 does not implement any moving parts in the management of the air inlet coming from the main tank 15.
• the first outlet port 201 can remain open and no closing member is implemented.
• the baffle 204 is fixed, which is easily conceivable and improves reliability compared to a moving part such as a piston.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Lubrication Of Internal Combustion Engines (AREA)
• Supply Devices, Intensifiers, Converters, And Telemotors (AREA)
• Pressure Vessels And Lids Thereof (AREA)
• General Details Of Gearings (AREA)

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• 2021
  • 2021-09-30 FR FR2110348A patent/FR3127527B1/fr active Active
• 2022
  • 2022-09-27 EP EP22789961.4A patent/EP4409115B1/de active Active
  • 2022-09-27 US US18/694,588 patent/US12428977B2/en active Active
  • 2022-09-27 WO PCT/FR2022/051809 patent/WO2023052717A1/fr not_active Ceased
  • 2022-09-27 CN CN202280065449.9A patent/CN118019899A/zh active Pending

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