EP4409115B1 - Auxiliary oil tank for an aircraft turbine engine - Google Patents

Auxiliary oil tank for an aircraft turbine engine

Info

Publication number
EP4409115B1
EP4409115B1 EP22789961.4A EP22789961A EP4409115B1 EP 4409115 B1 EP4409115 B1 EP 4409115B1 EP 22789961 A EP22789961 A EP 22789961A EP 4409115 B1 EP4409115 B1 EP 4409115B1
Authority
EP
European Patent Office
Prior art keywords
valve
oil
inlet
wall
auxiliary
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP22789961.4A
Other languages
German (de)
French (fr)
Other versions
EP4409115A1 (en
Inventor
Sébastien ORIOL
Mohammed-Lamine Boutaleb
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4409115A1 publication Critical patent/EP4409115A1/en
Application granted granted Critical
Publication of EP4409115B1 publication Critical patent/EP4409115B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • 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 turbomachinery. 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 one first rotor, also called the propulsion rotor, such as a propeller when the turbomachine is a turboprop, or an unshod fan when the turbomachine is an open rotor type, or a shod 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. An airflow is compressed within the compressor, then the compressed air is mixed with fuel and burned in the combustion chamber. The gases produced by the combustion pass through the turbine, which drives the compressor rotor and the propulsion rotor.
  • the propeller or fan of the propulsion rotor, as well as the compressor rotor, are equipped with blades that influence the airflow.
  • the turbomachine includes a variable pitch blade control system which includes a control unit connected to a hydraulic actuator to rotate the blades relative to a longitudinal axis of the blades according to the orientation of the airflow.
  • the turbomachine typically includes a main oil supply system.
  • This supply system comprises, for example, a main reservoir connected to a first supply circuit for bearing lubrication and a second supply circuit for supplying oil to the hydraulic actuator.
  • a feed pump is mounted on the second supply circuit and draws oil from the main reservoir and circulates it to the hydraulic actuator.
  • the main reservoir typically consists of a housing with a lower and upper wall connected by transverse walls. The lower wall includes an opening connected to the pump for oil intake.
  • Certain flight phases of the aircraft disrupt the oil supply to the hydraulic actuator.
  • the aircraft may experience flight phases during which the gravitational force is zero or negative. These flight phases are referred to in the field of this invention as “0g conditions” when the gravitational force is zero, or “negative g conditions” when the gravitational force is reversed.
  • 0g conditions when the gravitational force is zero
  • negative g conditions when the gravitational force is reversed.
  • the oil in the main reservoir becomes trapped against the upper wall of the reservoir opposite the opening in negative g conditions, or the oil and air form a suspension laden with air bubbles in 0g conditions. Consequently, the pump no longer draws oil from the reservoir but rather air or oil heavily laden with air bubbles, which degrades the oil supply to the control system and can even cause the supply pump to stop.
  • the hydraulic actuator of the control system is no longer properly supplied with oil.
  • the tank according to the invention therefore includes a baffle that separates the first internal volume from the second internal volume.
  • a baffle that separates the first internal volume from the second internal volume.
  • a turbomachine 1, 1', 1" for an aircraft is represented for example on the figures 1 to 3
  • the turbomachine 1, 1, 1" comprises a first rotor 2 connected to an engine M extending around a longitudinal axis X.
  • the engine M comprises, from upstream to downstream in the direction of flow of a main airflow 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 rotor of the high-pressure turbine 6 is connected to the rotor of the high-pressure compressor 4 by a high-pressure shaft 9.
  • the rotor of the low-pressure turbine 7 is connected to the rotor of the low-pressure compressor 3 by a low-pressure shaft 10.
  • the low-pressure shaft 10 and high-pressure shaft 9 are supported by bearings 12a.
  • the bearings 12a are contained within a lubrication housing 12 for 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' are arranged downstream of upstream bearing 120a and radially between the low-pressure shaft 10 and a downstream bearing support 120b'.
  • the lubrication chamber 12 is annular. Upstream and downstream bearings 120a, 120a' are arranged within the lubrication chamber 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 drives the rotor shaft 100 in rotation.
  • the low-pressure shaft 10 is connected to the rotor shaft 100 by a speed reducer 11. This allows the first rotor 2 to be driven at a speed lower than the rotational speed of the low-pressure shaft 10.
  • the speed reducer 11 is, for example, arranged in the lubrication chamber 12 between the upstream bearing 120a and the downstream bearing 120a'.
  • the main airflow F passes through the turbomachine 1, 1', 1" and splits into a primary airflow F1 which passes through the engine M within a primary channel and a secondary airflow F2 which passes through the first rotor 2 in a secondary channel surrounding the primary channel.
  • the turbomachine 1, 1', 1" includes blades 2a which act on the main airflow F, or primary F1, or the secondary airflow F2.
  • the rotors of the low-pressure 3 and high-pressure 4 compressors include blades 2a which compress the primary airflow F1 upstream of the combustion chamber 5.
  • the 2a blades 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 shrouded fan arranged upstream of the engine M.
  • the fan comprises blades 2a.
  • the fan blades 2a are rotatable about the longitudinal axis X. They are, for example, supported by a disk centered on the longitudinal axis X.
  • the 2a blades are arranged inside a blower housing 2b.
  • the housing 2b is surrounded by a nacelle (not shown).
  • the turbomachine 1' is a turbojet engine with an unfaired fan.
  • the first rotor 2 is an unfaired fan comprising blades 2a.
  • the fan is arranged downstream of the engine M (not visible in this figure).
  • the fan is rotatable about the longitudinal axis X.
  • the fan blades 2a are supported by a disk that rotates about the longitudinal axis X.
  • a straightener 2' is optionally arranged downstream of the fan 2 to straighten the secondary airflow F2.
  • the straightener 2' forms a fixed blade about the longitudinal axis X. It comprises blades 2a that may have variable pitch.
  • the blades 2a are mounted outside the nacelle.
  • the turbomachine 1" is a turboprop.
  • the first rotor 2 is a propeller arranged upstream of the engine M.
  • the propeller rotates about a propeller axis H parallel to the longitudinal axis X, and comprises blades 2a.
  • the blades 2a are supported by a disk centered on the propeller axis H.
  • the blades 2a are, for example, at least two in number and evenly distributed on the disk.
  • the blades 2a extend radially with respect to the longitudinal axis X. They typically comprise a blade and a mounting element for attaching to the disk.
  • the mounting element is, for example, a foot or a platform.
  • the blades 2a have a variable pitch angle. By variable pitch angle, it is understood that the blades 2a are free to rotate about a transverse axis Z that is substantially perpendicular to the longitudinal axis X.
  • the turbomachine 1, 1', 1" includes a control system 13 for the variable pitch-angle blades 2a.
  • the control system 13 includes a unit control unit 13a and at least one hydraulic actuator 13b supplied with oil.
  • the control unit 13a is, for example, fixed in rotation about 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".
  • the hydraulic actuator 13b is, for example, a hydraulic cylinder comprising a rod movable in translation connected to the blade 2a, possibly via a motion transformation mechanism.
  • the translational movement of the rod allows the blade 2a to be rotated about its axis.
  • the translational movement of the rod is controlled by the control unit 13a, which supplies oil to the hydraulic actuator 13b.
  • the hydraulic actuator 13b is movable in rotation about the longitudinal axis X or about an axis parallel to the longitudinal axis X.
  • the hydraulic actuator 13b is, for example, rotationally fixed to the blades 2a.
  • the hydraulic actuator 13b is arranged upstream of the control unit 13a.
  • the control system 13 advantageously includes an oil transfer device 13c from the control unit 13a to the hydraulic actuator 13b.
  • the oil transfer device 13c ensures the transfer of oil from the stationary control unit 13a to the rotating hydraulic actuator 13b.
  • the oil transfer device 13c is known by the acronym OTB for "Oil Transfer Bearing.”
  • the oil transfer device 13c is, for example, arranged within the lubrication chamber 12.
  • the turbomachine 1, 1', 1" further includes an electrical control unit 24.
  • the electrical control unit 24 allows the control unit 13a to be operated.
  • the electrical control unit 24 is, for example, a FADEC (for "Full Authority Digital Engine Control").
  • turbomachine 1, 1', 1" includes an oil supply system comprising a main supply system 14 and an auxiliary supply device 14', shown in the figures 4 And 5 .
  • the main supply system 14 provides lubrication of the bearings 12a within the lubrication enclosure 12 and of the reducer 11 and supplies oil to the control system 13 during a first phase of operation of the turbomachine 1, 1', 1".
  • the auxiliary supply device 14' provides 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 (0g condition) or reversed (negative g condition).
  • the main oil supply system 14 comprises a first supply circuit 14a for the lubrication chamber 12 and a second supply circuit 14b for the control system 13.
  • the main supply system 14 advantageously includes a metering valve 19 with a variable diaphragm.
  • the metering valve 19 supplies oil to the speed reducer 11.
  • this metering valve 19 can also function as a distribution valve for the oil distributed between the lubrication chamber 12 and the speed reducer 11.
  • the main supply system 14 advantageously includes an oil recovery circuit 14a' from the lubrication chamber 12 and an oil recovery circuit 14b' from the control system 13.
  • the main supply system 14 also includes a main oil reservoir 15 connected to the first supply circuit 14a and the second supply circuit 14b.
  • the first supply circuit 14a includes a first supply pump 16a which draws oil from the main reservoir and circulates it through the first supply circuit 14a to supply... oil the lubrication chamber 12.
  • the first supply circuit 14a includes 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 oil recovery circuit 14a' from the lubrication chamber 12 includes a second recovery pump 16b connected to the lubrication chamber 12 and to the main reservoir 15.
  • the pump 16b allows the oil to be recovered from the lubrication chamber 12 and returned to the main reservoir 15 through the recovery circuit 14a'.
  • the main supply system 14 includes a supply pump 18 dedicated to supplying oil to the control system 13.
  • the supply pump 18 is, for example, mounted on the secondary supply circuit 14b.
  • the supply pump 18 is, for example, a positive displacement pump.
  • the positive displacement pump is, for example, of fixed or variable displacement.
  • the supply 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 reservoir 15 and allows the oil to circulate in the first supply circuit 14a to 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 conveys the oil in the second supply circuit 14b to the control system 13.
  • the invention proposes an auxiliary supply device 14'.
  • the auxiliary supply device 14' is mounted on the second supply circuit 14b.
  • the auxiliary supply device 14' includes an auxiliary oil reservoir 20, optionally an auxiliary pump 22 and a valve 21.
  • the auxiliary pump 22 has an inlet 22a and an outlet 22b.
  • the valve 21 is, for example, a 3/2 hydraulic distributor, i.e., having three ports and two positions.
  • the auxiliary pump 22 is arranged between the valve 21 and the auxiliary reservoir 20.
  • the inlet 22a of the pump 22 is connected to the auxiliary reservoir 20.
  • the auxiliary pump 22 is a fixed-displacement hydraulic pump.
  • the auxiliary power supply device 14' advantageously includes 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 hydraulically actuated, spring-return 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 includes a movable member in the body 21a configured to move between a first position in which the inlet of the valve 21 is in fluidic communication with the first outlet of the valve 21 and a second position in which the inlet of the valve 21 is in fluidic communication with the second outlet of the valve 21.
  • the valve 21 includes, for example, a return spring enabling the movable member to be returned from the second position to the first position.
  • the auxiliary pump 22 draws oil from the auxiliary reservoir 20 and the oil is redirected to the auxiliary reservoir 20.
  • the control system 13 is supplied with oil by the supply pump 18 which draws oil from the main reservoir 15.
  • the auxiliary pump 20 draws oil from the auxiliary reservoir 20, and the oil is delivered to the control system 13 via the second supply circuit 14b, for example.
  • the valve 21 is in the first position.
  • the turbomachine 1, 1', 1" is in the second operating phase, particularly when the aircraft is in a flight phase in which the gravitational force is zero (referred to as "0g") or negative (referred to as "negative g"), the valve 21 is in the second position. This ensures the oil supply to the control system 13 from the auxiliary reservoir 20 and prevents any interruption in the oil supply to the control system 13.
  • auxiliary pump 22 is active both when the moving part of the valve 21 is in the first and second positions. This eliminates the need for priming time for the auxiliary pump 22 and guarantees a rapid oil supply to the control system 13 during the second operating phase of the turbomachine 1, 1', 1".
  • the valve 21 includes a hydraulic actuating chamber connected to the inlet 18a of the feed pump 18.
  • the pressure in the first feed circuit 14a drops because the first pump 16a draws air or an air-oil mixture from the main reservoir 15.
  • the pressure at the inlet 18a of the feed pump 18 connected to the first feed circuit 14a then falls below a threshold pressure, which causes the moving part of the valve 21 to move into the second position under the action of the valve spring.
  • This configuration simplifies the control of the valve 21.
  • the valve does not require a special sensor since its actuation is triggered by the sharp drop in pressure at the inlet 18a of the feed pump 18.
  • valve 21 is directly sensitive to gravitational force.
  • the auxiliary supply device 14' further includes 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 chamber 12.
  • the metering valve 19 is mounted between the main heat exchanger 17a, which in this embodiment is an oil/fuel heat exchanger, and the second heat exchanger 17b.
  • the metering valve 19 functions as a distribution valve for the oil supplied between the lubrication chamber 12 and the speed reducer 11. It is a two-outlet valve.
  • the first outlet of the metering valve 19 is connected to the lubrication chamber 12, and the second outlet of the metering valve 19 is connected to the speed 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 includes a check valve 25b to ensure that all the oil delivered by the auxiliary pump 22 supplies the control system 13.
  • the valve 21 has a body 21a with a first inlet connected to the main tank 15 and a second inlet connected to the auxiliary tank 20.
  • the valve 21 further includes an outlet connected to the inlet 18a of the feed pump 18.
  • the valve 21 also includes a movable element within 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 outlet.
  • the valve 21 includes, for example, a return spring allowing the movable element to return from the second position to the first position.
  • the outlet 18b of the feed pump 18 is connected to the control circuit 13.
  • the feed pump 18 draws oil from the main reservoir 15, and in the second position, the feed pump 18 draws oil from the auxiliary reservoir 20.
  • the valve 21 thus controls the oil flow in the second circuit 14b.
  • the valve 21 When the turbomachine 1, 1', 1" is in a second operating phase, particularly when the aircraft is in a flight phase in which the gravitational force is zero (called the 0g condition) or negative (called the negative g condition), the valve 21 is in the second position and the main pump 18 draws oil from the auxiliary reservoir 20 to supply oil to the control system 13.
  • the valve 21 is electrically controlled.
  • the turbomachine 1, 1', 1" includes a sensor configured to deliver a signal to the electrical control unit 24.
  • the sensor is configured to detect the second operating phase of the turbomachine 1, 1', 1".
  • the sensor is, for example, an accelerometer.
  • the moving part of the valve 21 is directly sensitive to the gravitational force acting on the turbomachine 1, 1', 1". When the gravitational force exceeds a given threshold, i.e., in the first operating state, the moving part is in the first position. During the second operating state, the moving part detects the second operating state and moves to 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 valve 21.
  • the auxiliary pump 22 is therefore arranged between valve 21 and the feed pump 18.
  • the inlet 18a of the pump is thus connected to the outlet of valve 21 via the auxiliary pump 22.
  • a second air/oil heat exchanger 23 is arranged between valve 21 and the feed pump 18. More specifically, the second air/oil heat exchanger 23 is arranged between the centrifugal pump 22 and the feed pump 18.
  • the centrifugal pump 22 and the second air/oil heat 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 feed pump 18 and the reducer 11, and comprises a single outlet connected to the lubrication chamber 12.
  • the metering valve 19 does not have a flow distribution function between two outlets.
  • the feed pump 18 is mounted in parallel on the second circuit. 14b between valve 21, and in particular the second air/oil exchanger 23 when present, and metering valve 19.
  • the metering valve 19 is able to open when the valve 21 is in the first position, thus supplying oil to the gearbox 11 from the main reservoir 15, and is able to remain open and/or close when the valve 21 is in the second position.
  • the metering valve 19 is able to close when the valve 21 is in the second position. This avoids supplying oil to the gearbox 11 from the auxiliary reservoir 20, so that the control system 13 is supplied exclusively from the auxiliary reservoir 20.
  • the auxiliary reservoir 20 is sized to supply only the control system 13, making it less bulky.
  • the variable opening of the metering valve 19 is controlled by the electrical control unit 24.
  • the electrical control unit 24 sends a signal to the metering valve 19 to open or close it according to the operating phase.
  • the auxiliary tank 20 according to the invention is, for example, shown on the 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 a housing 200.
  • the housing 200 is, for example, metallic.
  • the housing 200 is, for example, polygonal. It comprises an upper wall 200a and a lower wall 200b connected by opposing transverse walls 200c, 200d.
  • the transverse walls 200c, 200d may 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 the outside of the enclosure 200.
  • Such a configuration optimizes the oil flow in the second supply circuit 14b during the second operating phase of the turbomachine 1, 1', 1".
  • the vertex O represents a high point for the recovery of the oil, which normally eliminates the risk of air being present at this level in a negative severity 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 valve 21 or auxiliary pump 22, an inlet port 203 connected to the control system by the oil recovery circuit 14b' of the control system 13, and optionally a second inlet port 206 connected to valve 21.
  • the first outlet port 201 is, for example, provided on the transverse wall 200c
  • the first inlet port 203 is, for example, provided on the opposite transverse wall 200d.
  • the second outlet port 202 is, for example, provided on the upper wall 200a, for example, at the apex O.
  • the enclosure 200 defines a total volume, for example, between 2 L and 100 L, advantageously between 2 L and 40 L, and preferably between 4 L and 30 L.
  • the enclosure 200 comprises a first internal volume V1 in fluidic communication with the first output port 201 and a second internal volume V2 in fluidic communication with the second output 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 smaller than the second internal volume V2.
  • the auxiliary tank 20 further includes a baffle 204 arranged within the enclosure 200, which separates the first internal volume V1 from the second internal volume V1.
  • the baffle 204 comprises a first end wall 204a extending from the upper wall 200a to the lower wall 200b and a second end wall 204b extending from the lower wall 200b to the upper 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 The first outlet port 201 and the second outlet port 202.
  • the first end wall 204a and the lower wall 200b define a first fluid passage P1
  • the second end wall 204b and the upper wall 200a define a second fluid passage P2.
  • the fluid is, for example, air and/or oil.
  • the first end wall 204a and the second end wall 204b define an intermediate volume V3.
  • the sum of the first volume V1 and the intermediate volume V3 equals the second internal volume V2. This ensures that the internal volume V2 will contain exclusively oil during the second phase of operation.
  • the sum of the volume of the pipeline 201a connecting the first inlet port 201 to the main tank 15, the first volume V1, and the intermediate volume V3 is equal to the second internal volume V2. Therefore, the sum of the first volume V1 and the intermediate volume V3 is less than the second internal volume V2 in this example.
  • the volume of the pipeline 201a can be sized to be equal to the volume of oil consumed during the second operating phase of the turbomachine 1, 1', 1".
  • the baffle 204 further comprises a first intermediate wall 204c and a second intermediate wall 204d which are arranged parallel 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 reservoir 20 is supplied with oil by the control system 13. Excess oil is transferred to the main reservoir 15. This Communication is ensured by pipeline 201a.
  • the control system 13 is supplied with oil from the main reservoir 15.
  • the auxiliary tank 20 During the second operating phase of the turbomachine 1, 1', 1", air enters the auxiliary tank 20 via the first outlet port 201. This is because the oil flow rate exiting the tank is lower than the incoming flow rate. However, thanks to the baffle 204, the passage of air from the first internal volume V1 to the second internal volume V2 is slowed. Thus, the feed pump 18 or the auxiliary pump 22 draws oil and not air or oil heavily laden with air, which allows the control system 13 to be supplied during the second operating phase.
  • the volume of the pipe 201a and the baffle 204a is equal to the volume of oil exiting through the second outlet port 202 during the second operating phase.
  • Such an auxiliary tank 20 has the advantage of being simple and reliable.
  • such an auxiliary tank 20 does not use any moving parts in managing the air intake from the main tank 15.
  • the first outlet port 201 can remain open and no closing mechanism is used.
  • the baffle 204 is fixed, which is easily designed and improves reliability compared to a moving part such as a piston.

Landscapes

  • 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)
  • General Details Of Gearings (AREA)
  • Pressure Vessels And Lids Thereof (AREA)

Description

Domaine technique de l'inventionTechnical field of the invention

L'invention concerne le domaine des réservoirs d'huile pour les turbomachines d'aéronef. Plus particulièrement, l'invention concerne le domaine des réservoirs d'huile pour les phases de vol durant lesquelles la force gravitationnelle est nulle (condition de 0g) ou négative (condition de g négatif).The invention relates to the field of oil tanks for aircraft turbomachinery. 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).

Arrière-plan techniqueTechnical background

L'état de la technique est illustré par les documents US-A1-2020116048 , FR-A1-3105296 et US-A1-2015060206 .The state of the art is illustrated by the documents US-A1-2020116048 , FR-A1-3105296 And US-A1-2015060206 .

Une turbomachine pour un aéronef comprend d'amont en aval, au moins un premier rotor, également appelé rotor propulseur, tel qu'une hélice lorsque la turbomachine est un turbopropulseur, ou encore une soufflante non carénée lorsque la turbomachine est de type « open rotor » ou une soufflante carénée lorsque la turbomachine est un turboréacteur, un compresseur, une chambre de combustion et une turbine. Le rotor du compresseur est relié au rotor de la turbine et au premier rotor par un arbre d'entrainement. Un flux d'air est comprimé au sein du compresseur puis l'air comprimé est mélangé à un carburant et brulé au sein de la chambre de combustion. Les gaz formés par la combustion traversent la turbine qui permet d'entrainer le rotor du compresseur et le rotor propulseur.A turbomachine for an aircraft comprises, from upstream to downstream, at least one first rotor, also called the propulsion rotor, such as a propeller when the turbomachine is a turboprop, or an unshod fan when the turbomachine is an open rotor type, or a shod 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. An airflow is compressed within the compressor, then the compressed air is mixed with fuel and burned in the combustion chamber. The gases produced by the combustion pass through the turbine, which drives the compressor rotor and the propulsion rotor.

L'hélice ou la soufflante du rotor propulseur ainsi que le rotor du compresseur, sont équipés d'aubes qui permettent d'exercer une action sur le flux d'air. Afin d'adapter la turbomachine aux conditions de vols, il est connu d'équiper d'aubes à angle de calage variable le rotor propulseur ou encore le rotor du compresseur d'aubes à angle de calage variable. A cet effet, la turbomachine comprend un système de commande des aubes à angle de calage variable qui comprend une unité de commande reliée à un actionneur hydraulique pour déplacer en rotation les aubes par rapport à un axe longitudinal des aubes selon l'orientation du flux d'air.The propeller or fan of the propulsion rotor, as well as the compressor rotor, are equipped with blades that influence the airflow. To adapt the turbomachine to flight conditions, it is common practice to equip the propulsion rotor or the compressor rotor with variable-pitch blades. In effect, the turbomachine includes a variable pitch blade control system which includes a control unit connected to a hydraulic actuator to rotate the blades relative to a longitudinal axis of the blades according to the orientation of the airflow.

Afin d'alimenter en huile le système de commande et notamment l'actionneur hydraulique ainsi que d'autres éléments de la turbomachine tels que des paliers et réducteurs, la turbomachine comprend typiquement un système d'alimentation principal en huile. Ce système d'alimentation comprend par exemple un réservoir principal relié à un premier circuit d'alimentation pour la lubrification des paliers et à un second circuit d'alimentation pour l'alimentation en huile de l'actionneur hydraulique. Une pompe d'alimentation est montée sur le second circuit d'alimentation et permet l'aspiration de l'huile du réservoir principal et la circulation de cette huile jusqu'à l'actionneur hydraulique. Le réservoir principal comprend typiquement une enceinte présentant une paroi inférieure et supérieure reliées par des parois transversales. La paroi inférieure comprend un orifice relié à la pompe pour l'aspiration de l'huile.To supply oil to the control system, including the hydraulic actuator, as well as other turbomachine components such as bearings and gearboxes, the turbomachine typically includes a main oil supply system. This supply system comprises, for example, a main reservoir connected to a first supply circuit for bearing lubrication and a second supply circuit for supplying oil to the hydraulic actuator. A feed pump is mounted on the second supply circuit and draws oil from the main reservoir and circulates it to the hydraulic actuator. The main reservoir typically consists of a housing with a lower and upper wall connected by transverse walls. The lower wall includes an opening connected to the pump for oil intake.

Certaines phases de vol de l'aéronef perturbent l'alimentation en huile de l'actionneur hydraulique. En effet, l'aéronef peut expérimenter des phases de vol durant lesquelles la force gravitationnelle est nulle ou négative. Ces phases de vol sont appelées dans le domaine de l'invention « condition 0g » lorsque la force gravitationnelle est nulle ou « condition de g négatif » lorsque la force gravitationnelle est inversée. Durant de telles phases de vol, l'huile contenue dans le réservoir principal se retrouve plaquée sur la paroi supérieure du réservoir opposée à l'orifice en condition de g négatif ou l'huile et l'air forme une suspension chargée de bulles d'air en condition de 0g. La pompe n'aspire donc plus l'huile du réservoir mais de l'air ou de l'huile fortement chargée de bulles d'air, ce qui dégrade l'alimentation en huile du système de commande et peut même provoquer un arrêt de la pompe d'alimentation. Dans tous les cas, l'actionneur hydraulique du système de commande n'est plus correctement alimenté en huile.Certain flight phases of the aircraft disrupt the oil supply to the hydraulic actuator. Specifically, the aircraft may experience flight phases during which the gravitational force is zero or negative. These flight phases are referred to in the field of this invention as "0g conditions" when the gravitational force is zero, or "negative g conditions" when the gravitational force is reversed. During such flight phases, the oil in the main reservoir becomes trapped against the upper wall of the reservoir opposite the opening in negative g conditions, or the oil and air form a suspension laden with air bubbles in 0g conditions. Consequently, the pump no longer draws oil from the reservoir but rather air or oil heavily laden with air bubbles, which degrades the oil supply to the control system and can even cause the supply pump to stop. In all cases, the hydraulic actuator of the control system is no longer properly supplied with oil.

Une telle dégradation de l'alimentation en huile du système de commande et notamment de l'actionneur hydraulique peut rendre incontrôlable le calage des aubes du rotor propulseur, en particulier les pales de l'hélice ou de la soufflante non carénée, ce qui peut conduire à la mise en drapeau des aubes par un système de sécurité. Ceci a pour conséquence de diminuer significativement la poussée de la turbomachine et d'entrainer une perte de contrôle de celle-ci, ce qui n'est pas acceptable.Such a degradation of the oil supply to the control system, and particularly to the hydraulic actuator, can render the pitch of the propulsion rotor blades uncontrollable, especially the propeller blades or the unshod fan blades, which can lead to the blades being feathered by a safety system. This results in a significant reduction in the turbomachine's thrust and leads to a loss of control, which is unacceptable.

Par conséquent, il existe un besoin de fournir un réservoir d'huile qui permette d'alimenter en huile le système de commande des aubes à angle de calage variable durant les phases de vol pendant lesquelles la force gravitationnelle est nulle ou négative.Therefore, there is a need to provide an oil reservoir that allows oil to be supplied to the variable pitch blade control system during flight phases in which the gravitational force is zero or negative.

Résumé de l'inventionSummary of the invention

A cet effet, l'invention propose un réservoir auxiliaire d'huile pour l'alimentation d'un système de commande de calage de pas d'aubes d'une turbomachine d'aéronef, comprenant une enceinte comprenant :

  • une paroi inférieure et une paroi supérieure reliées par des parois transversales,
  • un premier port de sortie destiné à être raccordé à un réservoir principal d'huile,
  • un second port de sortie destiné à être raccordé au système de commande par un second circuit d'alimentation en huile,
  • un premier port d'entrée destiné à être raccordé au système de commande par un circuit de récupération auxiliaire.
To this end, the invention proposes an auxiliary oil reservoir for supplying a blade pitch control system for an aircraft turbomachine, comprising a housing including:
  • a lower wall and an upper wall connected by transverse walls,
  • a first outlet port intended to be connected to a main oil reservoir,
  • a second output port intended to be connected to the control system via a second oil supply circuit,
  • a first input port intended to be connected to the control system via an auxiliary recovery circuit.

L'enceinte se caractérise en ce qu'elle comprend en outre:

  • un premier volume interne en communication fluidique avec le premier port de sortie,
  • un second volume interne en communication fluidique avec le second port de sortie, et séparé du premier volume interne par une chicane, la chicane comprenant une première paroi d'extrémité s'étendant de la paroi supérieure vers la paroi inférieure et une seconde paroi d'extrémité s'étendant de la paroi inférieure vers la paroi supérieure, les première et seconde parois d'extrémité étant sensiblement parallèles, la première paroi d'extrémité et la paroi inférieure délimitant un premier passage de fluide, et la seconde paroi d'extrémité et la paroi supérieure délimitant un second passage de fluide.
The enclosure is characterized by the fact that it also includes:
  • a first internal volume in fluidic communication with the first output port,
  • a second internal volume in fluidic communication with the second outlet port, and separated from the first internal volume by a baffle, the baffle comprising a first end wall extending from the upper wall to the lower wall and a second end wall extending from the lower wall towards the upper wall, the first and second end walls being substantially parallel, the first end wall and the lower wall delimiting a first fluid passage, and the second end wall and the upper wall delimiting a second fluid passage.

Le réservoir selon l'invention comprend donc une chicane qui permet de séparer le premier volume interne du second volume interne. Lorsque l'aéronef expérimente une phase de vol durant laquelle la force gravitationnelle est nulle ou négative, l'air entrant par le premier port de sortie circule dans l'enceinte du premier volume interne vers le second volume interne. Selon l'invention, la circulation de l'air entre les deux volumes est ralentie par la chicane ce qui permet à l'huile qui est contenue dans le second volume interne de rester en communication avec le second port de sortie pour alimenter le second circuit. Ainsi, l'air n'atteint pas le second port de sortie. Grâce à l'invention, le réservoir auxiliaire est apte à alimenter le système de commande durant une telle phase de vol. Les aubes ne sont donc pas mises en drapeau et la turbomachine d'aéronef maintient une poussée maximale durant cette phase de vol.The tank according to the invention therefore includes a baffle that separates the first internal volume from the second internal volume. When the aircraft experiences a flight phase during which the gravitational force is zero or negative, the air entering through the first outlet port flows from the first internal volume to the second internal volume. According to the invention, the airflow between the two volumes is slowed by the baffle, allowing the oil contained in the second internal volume to remain connected to the second outlet port to supply the second circuit. Thus, the air does not reach the second outlet port. Thanks to the invention, the auxiliary tank is able to supply the control system during such a flight phase. The turbine blades are therefore not feathered, and the aircraft turbomachine maintains maximum thrust during this flight phase.

L'invention peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres :

  • la première paroi d'extrémité et la seconde paroi d'extrémité délimitent un volume intermédiaire, la somme du premier volume et du volume intermédiaire étant égale au second volume interne ;
  • la première paroi d'extrémité et la seconde paroi d'extrémité délimitent un volume intermédiaire, la somme du premier volume et du volume intermédiaire étant inférieure au second volume interne ;
  • la chicane comprend une première paroi intermédiaire et une seconde paroi intermédiaire qui sont agencées sensiblement parallèlement et entre les première et seconde parois d'extrémité, la première paroi intermédiaire délimitant avec la paroi supérieure un troisième passage de fluide et la seconde paroi intermédiaire délimitant avec la paroi inférieure un quatrième passage de fluide, la première paroi intermédiaire étant agencée entre la première paroi d'extrémité et la seconde paroi intermédiaire ;
  • la paroi supérieure de l'enceinte comprend une première portion sensiblement parallèle à la paroi inférieure et une seconde portion inclinée vers l'intérieur de l'enceinte, les première et seconde portions formant un sommet dirigé vers l'extérieur de l'enceinte ;
  • le premier volume interne est compris entre 1 L et 50 L et le second volume interne est compris entre 1 L et 50 L ;
  • l'enceinte comprend en outre un second port d'entrée destiné à être raccordé à une vanne.
The invention may include one or more of the following features, taken individually 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 arranged substantially parallel to each other, and between the first and second end walls, the first intermediate wall, together with the upper wall, delimits 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 peak 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 also includes a second inlet port intended to be connected to a valve.

L'invention concerne également une turbomachine pour un aéronef comprenant :

  • des aubes à angle de calage variable,
  • un système de commande des aubes comprenant une unité commande reliée à au moins un actionneur hydraulique,
  • un système d'alimentation en huile comprenant :
    un système d'alimentation principal comprenant :
    • un second circuit d'alimentation du système de commande,
    • un réservoir principal relié au second circuit d'alimentation, et
    • une pompe d'alimentation en huile montée sur le second circuit d'alimentation et comprenant une entrée et une sortie reliée au système de commande,
    • un dispositif d'alimentation auxiliaire comprenant :
      un réservoir auxiliaire d'huile selon l'une quelconque des caractéristiques précédentes, le premier port de sortie étant relié au réservoir principal, le second port de sortie étant relié au second circuit d'alimentation et le premier port d'entrée étant relié au système de commande.
The invention also relates to a turbomachine for an aircraft comprising:
  • variable angle blades,
  • a blade control system comprising a control unit connected to at least one hydraulic actuator,
  • an oil supply system comprising:
    a main power supply system comprising:
    • a second power supply circuit for the control system,
    • a main reservoir 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 power 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 supply circuit and the first inlet port being connected to the control system.

La turbomachine peut comprendre une ou plusieurs des caractéristiques suivantes, prises isolément les unes des autres ou en combinaison les unes avec les autres :

  • le dispositif d'alimentation auxiliaire comprend en outre une vanne comprenant un corps présentant une première entrée reliée au réservoir principal, une seconde entrée reliée au second port de sortie du réservoir auxiliaire et une sortie reliée à l'entrée de la pompe d'alimentation, la vanne comprenant en outre un organe mobile dans le corps et configuré pour se déplacer entre une première position dans laquelle la première entrée de la vanne est en communication fluidique avec la sortie de la vanne et une seconde position dans laquelle la seconde entrée de la vanne est en communication fluidique avec la sortie de la vanne ;
  • le réservoir auxiliaire comprend un second port d'entrée, et le dispositif d'alimentation auxiliaire comprend une vanne comprenant un corps présentant une entrée reliée au réservoir auxiliaire et une première sortie reliée au second port d'entrée du réservoir auxiliaire, et une deuxième sortie reliée au système de commande, la vanne comprenant en outre un organe mobile dans le corps et configuré pour se déplacer entre une première position dans laquelle l'entrée de la vanne est en communication fluidique avec la première sortie de la vanne et une seconde position dans laquelle l'entrée de la vanne est en communication fluidique avec la deuxième sortie de la vanne ;
  • l'entrée de la pompe d'alimentation est reliée au réservoir principal.
The turbomachine may include one or more of the following features, taken individually or in combination with each other:
  • the auxiliary supply device further includes a valve comprising a body having a first inlet connected to the main tank, a second inlet connected to the second outlet port of the auxiliary tank 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 fluidic communication with the outlet of the valve and a second position in which the second inlet of the valve is in fluidic communication with the outlet of the valve;
  • the auxiliary tank includes a second inlet port, and the auxiliary supply device includes a valve comprising a body having an inlet connected to the auxiliary tank and a first outlet connected to the second inlet port of the auxiliary tank, and a second outlet connected to the control system, the valve further comprising a movable member in the body and configured to move between a first position in which the inlet of the valve is in fluidic communication with the first outlet of the valve and a second position in which the inlet of the valve is in fluidic communication with the second outlet of the valve;
  • The feed pump inlet is connected to the main tank.

Brève description des figuresBrief description of the figures

D'autres caractéristiques et avantages ressortiront de la description qui suit d'un mode de réalisation non limitatif de l'invention en référence aux dessins annexés sur lesquels :

  • [Fig.1] la figure 1 est une représentation schématique en coupe longitudinale d'une demi-turbomachine d'aéronef selon un premier mode de réalisation de l'invention ;
  • [Fig.2] la figure 2 est une représentation schématique en perspective d'une turbomachine d'aéronef selon un second mode de réalisation de l'invention;
  • [Fig.3] la figure 3 est une représentation schématique en coupe longitudinale d'une turbomachine d'aéronef selon un troisième mode de réalisation de l'invention;
  • [Fig.4] la figure 4 est une représentation schématique d'un système d'alimentation en huile selon un premier mode de réalisation de l'invention;
  • [Fig.5] la figure 5 est une représentation schématique d'un système d'alimentation en huile selon un second mode de réalisation de l'invention;
  • [Fig.6] la figure 6 est une représentation schématique en coupe d'un réservoir auxiliaire d'huile selon l'invention;
  • [Fig.7] la figure 7 est une représentation schématique partielle et en coupe du réservoir auxiliaire d'huile selon un exemple de réalisation de l'invention;
Other features and advantages will become apparent from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:
  • [ Fig.1 ] there figure 1 is a schematic longitudinal cross-sectional representation of half an aircraft turbomachine according to a first embodiment of the invention;
  • [ Fig. 2 ] there figure 2 is a schematic perspective representation of an aircraft turbomachine according to a second embodiment of the invention;
  • [ Fig.3 ] there figure 3 is a schematic longitudinal cross-sectional representation of an aircraft turbomachine according to a third embodiment of the invention;
  • [ Fig. 4 ] there figure 4 is a schematic representation of an oil supply system according to a first embodiment of the invention;
  • [ Fig. 5 ] there figure 5 is a schematic representation of an oil supply system according to a second embodiment of the invention;
  • [ Fig. 6 ] there figure 6 is a schematic cross-sectional representation of an auxiliary oil reservoir according to the invention;
  • [ Fig. 7 ] there figure 7 is a partial schematic and cross-sectional representation of the auxiliary oil reservoir according to an example of an embodiment of the invention;

Description détaillée de l'inventionDetailed description of the invention

Une turbomachine 1, 1',1" pour un aéronef est représentée par exemple sur les figures 1 à 3. La turbomachine 1, 1, 1" comprend un premier rotor 2 relié à un moteur M s'étendant autour d'un axe longitudinal X. Le moteur M comprend d'amont en aval dans le sens d'écoulement d'un flux d'air principal F le long de l'axe longitudinal X, un compresseur tel qu'un compresseur basse pression 3 et un compresseur haute pression 4, une chambre de combustion 5, une turbine telle qu'une turbine haute pression 6 et une turbine basse pression 7, et une tuyère 8.A turbomachine 1, 1', 1" for an aircraft is represented for example on the figures 1 to 3 The turbomachine 1, 1, 1" comprises a first rotor 2 connected to an engine M extending around a longitudinal axis X. The engine M comprises, from upstream to downstream in the direction of flow of a main airflow 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.

Le rotor de la turbine haute pression 6 est relié au rotor du compresseur haute pression 4 par un arbre haute pression 9. Le rotor de la turbine basse pression 7 est relié au rotor du compresseur basse pression 3 par un arbre basse pression 10.The rotor of the high-pressure turbine 6 is connected to the rotor of the high-pressure compressor 4 by a high-pressure shaft 9. The rotor of the low-pressure turbine 7 is connected to the rotor of the low-pressure compressor 3 by a low-pressure shaft 10.

Les arbres basse pression 10 et haute pression 9 sont soutenus par des paliers 12a. Les paliers 12a sont contenus dans une enceinte de lubrification 12 pour leur lubrification. Par exemple, un palier amont 120a est agencé radialement entre une extrémité amont de l'arbre basse pression 10 et un support palier amont 120b et un palier aval 120a' est agencé en aval du palier amont 120a et radialement entre l'arbre basse pression 10 et un support palier aval 120b'. L'enceinte de lubrification 12 est annulaire. Les paliers amont et aval 120a, 120a' sont agencés dans l'enceinte de lubrification 12.The low-pressure shaft 10 and high-pressure shaft 9 are supported by bearings 12a. The bearings 12a are contained within a lubrication housing 12 for lubrication. For example, 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' are arranged downstream of upstream bearing 120a and radially between the low-pressure shaft 10 and a downstream bearing support 120b'. The lubrication chamber 12 is annular. Upstream and downstream bearings 120a, 120a' are arranged within the lubrication chamber 12.

Le premier rotor 2 est entrainé en rotation par un arbre de rotor 100. L'arbre de rotor 100 est relié à l'arbre basse pression 10. L'arbre basse pression 10 entraine en rotation l'arbre de rotor 100. Avantageusement, l'arbre basse pression 10 est relié à l'arbre de rotor 100 par un réducteur de vitesse 11. Ceci permet d'entrainer le premier rotor 2 à une vitesse inférieure à la vitesse de rotation de l'arbre basse pression 10. Le réducteur de vitesse 11 est par exemple agencé dans l'enceinte de lubrification 12 entre le palier amont 120a et le palier aval 120a'.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 drives the rotor shaft 100 in rotation. Advantageously, the low-pressure shaft 10 is connected to the rotor shaft 100 by a speed reducer 11. This allows the first rotor 2 to be driven at a speed lower than the rotational speed of the low-pressure shaft 10. The speed reducer 11 is, for example, arranged in the lubrication chamber 12 between the upstream bearing 120a and the downstream bearing 120a'.

Le flux d'air principal F traverse la turbomachine 1, 1', 1" et se divise en un flux d'air primaire F1 qui traverse le moteur M au sein d'une veine primaire et en un flux d'air secondaire F2 qui traverse le premier rotor 2 dans une veine secondaire entourant la veine primaire.The main airflow F passes through the turbomachine 1, 1', 1" and splits into a primary airflow F1 which passes through the engine M within a primary channel and a secondary airflow F2 which passes through the first rotor 2 in a secondary channel surrounding the primary channel.

La turbomachine 1, 1', 1" comprend des aubes 2a qui permettent d'exercer une action sur le flux d'air principal F, ou primaire F1 ou le flux d'air secondaire F2. Par exemple, les rotors des compresseurs basse pression 3 et haute pression 4 comprennent des aubes 2a qui permettent de comprimer le flux d'air primaire F1 en amont de la chambre de combustion 5.The turbomachine 1, 1', 1" includes blades 2a which act on the main airflow F, or primary F1, or the secondary airflow F2. For example, the rotors of the low-pressure 3 and high-pressure 4 compressors include blades 2a which compress the primary airflow F1 upstream of the combustion chamber 5.

De manière générales, les aubes 2a peuvent être fixes en rotation autour de l'axe longitudinal X, ou peuvent être mobiles en rotation autour de l'axe longitudinal X ou d'un axe parallèle à l'axe longitudinal X.In general, the 2a blades 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.

Selon un premier mode de réalisation représenté sur la figure 1, la turbomachine 1 est un turboréacteur à double flux. Selon ce mode de réalisation, le premier rotor 2 est une soufflante carénée qui est agencée à l'amont du moteur M. La soufflante comprend des aubes 2a. Les aubes 2a de la soufflante sont mobiles en rotation autour de l'axe longitudinal X. Elles sont par exemple portées par un disque centré sur l'axe longitudinal X. Les aubes 2a sont agencées à l'intérieur d'un carter 2b de soufflante. Le carter 2b est entouré d'une nacelle (non représentée).According to a first embodiment shown on the figure 1 The turbomachine 1 is a turbofan engine. According to this embodiment, the first rotor 2 is a shrouded fan arranged upstream of the engine M. The fan comprises blades 2a. The fan blades 2a are rotatable about the longitudinal axis X. They are, for example, supported by a disk centered on the longitudinal axis X. The The 2a blades are arranged inside a blower housing 2b. The housing 2b is surrounded by a nacelle (not shown).

Selon un second mode de réalisation représenté sur la figure 2, la turbomachine 1' est un turboréacteur à soufflante non carénée. Selon ce mode de réalisation, le premier rotor 2 est une soufflante non carénée qui comprend des aubes 2a. Selon ce mode de réalisation, la soufflante est agencée en aval du moteur M (non visible sur cette figure). La soufflante est mobile en rotation autour de l'axe longitudinal X. Les aubes 2a de la soufflante sont portées par un disque mobile en rotation autour de l'axe longitudinal X. En outre, selon ce mode de réalisation, un redresseur 2' est optionnellement agencé en aval de la soufflante 2 afin de redresser le flux d'air secondaire F2. Le redresseur 2' forme un aubage fixe autour de l'axe longitudinal X. Il comprend des aubes 2a qui peuvent être à calage variable. Les aubes 2a sont montées à l'extérieur de la nacelle.According to a second embodiment shown in the figure 2 The turbomachine 1' is a turbojet engine with an unfaired fan. In this embodiment, the first rotor 2 is an unfaired fan comprising blades 2a. In this embodiment, the fan is arranged downstream of the engine M (not visible in this figure). The fan is rotatable about the longitudinal axis X. The fan blades 2a are supported by a disk that rotates about the longitudinal axis X. In addition, in this embodiment, a straightener 2' is optionally arranged downstream of the fan 2 to straighten the secondary airflow F2. The straightener 2' forms a fixed blade about the longitudinal axis X. It comprises blades 2a that may have variable pitch. The blades 2a are mounted outside the nacelle.

Selon un troisième mode de réalisation représenté sur la figure 3, la turbomachine 1" est un turbopropulseur. Selon ce mode de réalisation, le premier rotor 2 est une hélice qui est agencée en amont du moteur M. L'hélice est mobile en rotation autour d'un axe d'hélice H parallèle à l'axe longitudinal X, et comprend des aubes 2a. Les aubes 2a sont portées par un disque centré sur l'axe d'hélice H. Les aubes 2a sont par exemple au nombre d'au moins deux et régulièrement réparties sur le disque.According to a third embodiment shown in the figure 3 The turbomachine 1" is a turboprop. According to this embodiment, the first rotor 2 is a propeller arranged upstream of the engine M. The propeller rotates about a propeller axis H parallel to the longitudinal axis X, and comprises blades 2a. The blades 2a are supported by a disk centered on the propeller axis H. The blades 2a are, for example, at least two in number and evenly distributed on the disk.

Les aubes 2a s'étendent radialement par rapport à l'axe longitudinal X. Elles comprennent typiquement une pale et un élément de fixation au disque. L'élément de fixation est par exemple un pied ou une plateforme. Selon l'invention, les aubes 2a sont à angle de calage variable. Par angle de calage variable, il est entendu que les aubes 2a sont mobiles en rotation autour d'un axe transversal Z sensiblement perpendiculaire ou perpendiculaire à l'axe longitudinal X.The blades 2a extend radially with respect to the longitudinal axis X. They typically comprise a blade and a mounting element for attaching to the disk. The mounting element is, for example, a foot or a platform. According to the invention, the blades 2a have a variable pitch angle. By variable pitch angle, it is understood that the blades 2a are free to rotate about a transverse axis Z that is substantially perpendicular to the longitudinal axis X.

Afin de contrôler l'angle de calage des aubes 2a, la turbomachine 1, 1', 1" selon l'invention comprend un système de commande 13 des aubes 2a à angle de calage variable. Le système de commande 13 comprend une unité de commande 13a et au moins un actionneur hydraulique 13b alimenté en huile. L'unité de commande 13a est par exemple fixe en rotation autour de l'axe longitudinal X. L'unité de commande 13a est par exemple reliée à un stator de la turbomachine 1, 1', 1". L'unité de commande 13a est connue dans le domaine de l'invention sous l'acronyme PCU pour « Pitch Control Unit » en langue anglaise. L'actionneur hydraulique 13b est par exemple un vérin hydraulique comprenant une tige mobile en translation reliée à l'aube 2a éventuellement via un mécanisme de transformation du mouvement. Le mouvement de translation de la tige permet de déplacer en rotation l'aube 2a autour de son axe. Le déplacement en translation de la tige mobile est commandé par l'unité de commande 13a qui alimente en huile l'actionneur hydraulique 13b. L'actionneur hydraulique 13b est mobile en rotation autour de l'axe longitudinal X ou d'un axe parallèle à l'axe longitudinal X. L'actionneur hydraulique 13b est par exemple solidaire en rotation des aubes 2a. L'actionneur hydraulique 13b est par exemple agencé en amont de l'unité de commande 13a.To control the pitch angle of the blades 2a, the turbomachine 1, 1', 1" according to the invention includes a control system 13 for the variable pitch-angle blades 2a. The control system 13 includes a unit control unit 13a and at least one hydraulic actuator 13b supplied with oil. The control unit 13a is, for example, fixed in rotation about 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". The hydraulic actuator 13b is, for example, a hydraulic cylinder comprising a rod movable in translation connected to the blade 2a, possibly via a motion transformation mechanism. The translational movement of the rod allows the blade 2a to be rotated about its axis. The translational movement of the rod is controlled by the control unit 13a, which supplies oil to the hydraulic actuator 13b. The hydraulic actuator 13b is movable in rotation about the longitudinal axis X or about an axis parallel to the longitudinal axis X. The hydraulic actuator 13b is, for example, rotationally fixed to the blades 2a. The hydraulic actuator 13b is arranged upstream of the control unit 13a.

Le système de commande 13 comprend avantageusement un dispositif de transfert d'huile 13c de l'unité de commande 13a vers l'actionneur hydraulique 13b. Le dispositif de transfert d'huile 13c assure le transfert d'huile de l'unité de commande 13a qui est fixe vers l'actionneur hydraulique 13b qui est mobile en rotation. Le dispositif de transfert d'huile 13c est connu sous l'acronyme OTB pour « Oil Transfer Bearing » en langue anglaise. Le dispositif de transfert d'huile 13c est par exemple agencé dans l'enceinte de lubrification 12.The control system 13 advantageously includes an oil transfer device 13c from the control unit 13a to the hydraulic actuator 13b. The oil transfer device 13c ensures the transfer of oil from the stationary control unit 13a to the rotating hydraulic actuator 13b. The oil transfer device 13c is known by the acronym OTB for "Oil Transfer Bearing." The oil transfer device 13c is, for example, arranged within the lubrication chamber 12.

La turbomachine 1, 1', 1" comprend en outre une unité de contrôle électrique 24. L'unité de contrôle électrique 24 permet de piloter l'unité de commande 13a. L'unité de contrôle électrique 24 est par exemple un FADEC (pour « Full Authority Digital Engine Control » en langue anglaise).The turbomachine 1, 1', 1" further includes an electrical control unit 24. The electrical control unit 24 allows the control unit 13a to be operated. The electrical control unit 24 is, for example, a FADEC (for "Full Authority Digital Engine Control").

En outre, la turbomachine 1, 1', 1" comprend un système d'alimentation en huile comprenant système d'alimentation principal 14 et un dispositif d'alimentation auxiliaire 14', représenté sur les figures 4 et 5.In addition, the turbomachine 1, 1', 1" includes an oil supply system comprising a main supply system 14 and an auxiliary supply device 14', shown in the figures 4 And 5 .

Le système d'alimentation principal 14 assure la lubrification des paliers 12a au sein de l'enceinte de lubrification 12 et du réducteur 11 et l'alimentation en huile du système de commande 13 durant une première phase de fonctionnement de la turbomachine 1, 1', 1". Le dispositif d'alimentation auxiliaire 14' assure la lubrification du système de commande 13 durant une seconde phase de fonctionnement de la turbomachine 1, '1, 1" durant laquelle la force gravitationnelle est nulle (condition de 0g) ou inversée (condition de g négatif).The main supply system 14 provides lubrication of the bearings 12a within the lubrication enclosure 12 and of the reducer 11 and supplies oil to the control system 13 during a first phase of operation of the turbomachine 1, 1', 1". The auxiliary supply device 14' provides 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 (0g condition) or reversed (negative g condition).

Le système d'alimentation principal 14 en huile comprend un premier circuit d'alimentation 14a de l'enceinte de lubrification 12 et un second circuit d'alimentation 14b en huile du système de commande 13. Le système d'alimentation principal 14 comprend avantageusement une vanne de dosage 19 à diaphragme variable. La vanne de dosage 19 permet d' alimenter en huile le réducteur de vitesse 11. Dans un premier mode de réalisation, cette vanne de dosage 19 peut avoir une fonction de vanne de répartition de l'huile distribuée entre l'enceinte de lubrification 12 et le réducteur de vitesse 11.The main oil supply system 14 comprises a first supply circuit 14a for the lubrication chamber 12 and a second supply circuit 14b for the control system 13. The main supply system 14 advantageously includes a metering valve 19 with a variable diaphragm. The metering valve 19 supplies oil to the speed reducer 11. In a first embodiment, this metering valve 19 can also function as a distribution valve for the oil distributed between the lubrication chamber 12 and the speed reducer 11.

Le système d'alimentation principal 14 comprend avantageusement un circuit de récupération 14a' d'huile de l'enceinte de lubrification 12 et un circuit de récupération 14b' d'huile du système de commande 13.The main supply system 14 advantageously includes an oil recovery circuit 14a' from the lubrication chamber 12 and an oil recovery circuit 14b' from the control system 13.

Le système d'alimentation principal 14 comprend par ailleurs un réservoir principal 15 d'huile relié au premier circuit d'alimentation 14a et au second circuit d'alimentation 14b.The main supply system 14 also includes a main oil reservoir 15 connected to the first supply circuit 14a and the second supply circuit 14b.

L'huile envoyée aux paliers 12a, par exemple le palier amont 120a et le palier aval 120a', au réducteur 11 et les fuites d'huile du dispositif de transfert 13c, retombent dans le fond de l'enceinte de lubrification 12. Afin d'optimiser la consommation d'huile, cette huile est récupérée et dirigée par exemple dans le circuit de récupération 14a' d'huile de l'enceint de lubrification 12.The oil sent to the bearings 12a, for example the upstream bearing 120a and the downstream bearing 120a', to the reducer 11 and the oil leaks from the transfer device 13c, fall back into the bottom of the lubrication enclosure 12. In order to optimize oil consumption, this oil is recovered and directed for example into the oil recovery circuit 14a' of the lubrication enclosure 12.

Le premier circuit d'alimentation 14a comprend une première pompe 16a d'alimentation permettant l'aspiration de l'huile à partir du réservoir principal et sa circulation dans le premier circuit d'alimentation 14a pour alimenter en huile l'enceinte de lubrification 12. Avantageusement, le premier circuit d'alimentation 14a comprend un échangeur principal 17a par exemple air/huile ou huile/carburant, et optionnellement un second échangeur 17b par exemple huile/carburant qui sont agencés entre la première pompe 16a et l'enceinte de lubrification 12.The first supply circuit 14a includes a first supply pump 16a which draws oil from the main reservoir and circulates it through the first supply circuit 14a to supply... oil the lubrication chamber 12. Advantageously, the first supply circuit 14a includes 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.

Le circuit de récupération 14a' de l'huile de l'enceinte de lubrification 12 comprend une seconde pompe 16b de récupération reliée à l'enceinte de lubrification 12 et au réservoir principal 15. La pompe 16b permet de récupérer l'huile de l'enceinte de lubrification 12 pour la retourner dans le réservoir principal 15 au travers du circuit de récupération 14a'.The oil recovery circuit 14a' from the lubrication chamber 12 includes a second recovery pump 16b connected to the lubrication chamber 12 and to the main reservoir 15. The pump 16b allows the oil to be recovered from the lubrication chamber 12 and returned to the main reservoir 15 through the recovery circuit 14a'.

En outre, le système d'alimentation principal 14 comprend une pompe d'alimentation 18 dédiée à l'alimentation en huile du système de commande 13. La pompe d'alimentation 18 est par exemple montée sur le second circuit d'alimentation 14b. La pompe d'alimentation 18 est par exemple une pompe volumétrique. La pompe volumétrique est par exemple à cylindrée fixe ou à cylindrée variable. La pompe d'alimentation 18 comprend une entrée 18a et une sortie 18b reliée au système de commande 13.Furthermore, the main supply system 14 includes a supply pump 18 dedicated to supplying oil to the control system 13. The supply pump 18 is, for example, mounted on the secondary supply circuit 14b. The supply pump 18 is, for example, a positive displacement pump. The positive displacement pump is, for example, of fixed or variable displacement. The supply pump 18 includes an inlet 18a and an outlet 18b connected to the control system 13.

Le second circuit d'alimentation 14b peut comprendre un filtre 26 agencé entre la pompe d'alimentation 18 et le système de commande 13.The second supply circuit 14b may include a filter 26 arranged between the supply pump 18 and the control system 13.

Durant la première phase de fonctionnement de la turbomachine 1, 1', 1", la première pompe 16a aspire l'huile à partir du réservoir principal 15 et permet la circulation de l'huile dans le premier circuit d'alimentation 14a jusqu'à l'enceinte de lubrification 12. La pompe d'alimentation 18 aspire l'huile également à partir du réservoir principal 15, par exemple en amont ou en aval de la première pompe 16a et achemine l'huile dans le second circuit d'alimentation14b jusqu'au système de commande 13.During the first phase of operation of the turbomachine 1, 1', 1", the first pump 16a draws oil from the main reservoir 15 and allows the oil to circulate in the first supply circuit 14a to 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 conveys the oil in the second supply circuit 14b to the control system 13.

Durant la seconde phase de fonctionnement, typiquement un vol en gravité négative (ou inversée), l'huile est plaquée dans la partie supérieure du réservoir principal 15 tandis que la partie inférieure reliée à la première pompe 16a est occupé par de l'air. En cas de gravité nulle, un mélange air-huile est en suspension dans le réservoir 15 et en cas de gravité inversée de l'air occupe la partie inférieure du réservoir principal 15 reliée à la première pompe 16a. La pompe d'alimentation 18 est indirectement reliée à la partie inférieure du réservoir principal 15, et risque donc d'aspirer de l'air du réservoir principal 15, ou de l'huile fortement chargée de bulles d'air. Ceci n'est pas acceptable car le système de commande 13 doit être alimenté en huile relativement exempte de bulles d'air, afin de ne pas compromettre le fonctionnement de l'unité commande 13a et donc de l'actionneur hydraulique 13b qui commande le pas des aubes 2a. Aussi, la présence d'air peut conduire à l'arrêt de la pompe d'alimentation 18. Par conséquent, afin d'assurer une alimentation en huile convenable pour le système de commande 13 durant la seconde phase de fonctionnement de la turbomachine 1, 1', 1", l'invention propose un dispositif d'alimentation auxiliaire 14'. Le dispositif d'alimentation auxiliaire 14' est monté sur le second circuit d'alimentation 14b.During the second phase of operation, typically a negative (or inverted) gravity flight, oil is trapped in the upper part of the main tank 15 while the lower part, connected to the first pump 16a, is filled with air. In zero gravity, an air-oil mixture is suspended in the tank 15, and in inverted gravity... Air occupies the lower part of the main reservoir 15, which is connected to the first pump 16a. The feed pump 18 is indirectly connected to the lower part of the main reservoir 15 and therefore risks drawing air from the main reservoir 15, or oil heavily laden with air bubbles. This is unacceptable because the control system 13 must be supplied with oil that is relatively free of air bubbles, so as not to compromise the operation of the control unit 13a and thus of the hydraulic actuator 13b, which controls the pitch of the vanes 2a. Also, the presence of air can lead to the shutdown of the feed pump 18. Therefore, in order to ensure a suitable oil supply for the control system 13 during the second operating phase of the turbomachine 1, 1', 1", the invention proposes an auxiliary supply device 14'. The auxiliary supply device 14' is mounted on the second supply circuit 14b.

Le dispositif d'alimentation auxiliaire 14' comprend un réservoir auxiliaire 20 d'huile, optionnellement une pompe auxiliaire 22 et une vanne 21. La pompe auxiliaire 22 comprend une entrée 22a et une sortie 22b. La vanne 21 est par exemple un distributeur hydraulique 3/2 c'est-à-dire présentant trois orifices et deux positions.The auxiliary supply device 14' includes an auxiliary oil reservoir 20, optionally an auxiliary pump 22 and a valve 21. The auxiliary pump 22 has an inlet 22a and an outlet 22b. The valve 21 is, for example, a 3/2 hydraulic distributor, i.e., having three ports and two positions.

Selon un premier mode de réalisation représenté sur la figure 4, la pompe auxiliaire 22 est agencée entre la vanne 21 et le réservoir auxiliaire 20. L'entrée 22a de la pompe 22 est reliée au réservoir auxiliaire 20. La pompe auxiliaire 22 est une pompe hydraulique à cylindrée fixe. Le dispositif d'alimentation auxiliaire 14' comprend avantageusement un moteur rotatif pour entrainer la pompe auxiliaire 22. Alternativement, la pompe auxiliaire 22 est entrainée par l'arbre basse pression 10 ou l'arbre haute pression 9.According to a first embodiment shown on the figure 4 The auxiliary pump 22 is arranged between the valve 21 and the auxiliary reservoir 20. The inlet 22a of the pump 22 is connected to the auxiliary reservoir 20. The auxiliary pump 22 is a fixed-displacement hydraulic pump. The auxiliary power supply device 14' advantageously includes a rotary motor to drive the auxiliary pump 22. Alternatively, the auxiliary pump 22 is driven by the low-pressure shaft 10 or the high-pressure shaft 9.

Selon ce mode de réalisation, la vanne 21 est un distributeur à commande hydraulique à rappel par ressort. La vanne 21 présente un corps 21a présentant une entrée reliée à la sortie 22b de la pompe auxiliaire 22 et une première sortie reliée au réservoir auxiliaire 20 et une deuxième sortie reliée au second circuit d'alimentation 14b, entre la pompe d'alimentation 18 et le système de commande 13. La vanne 21 comprend en outre un organe mobile dans le corps 21a configuré pour se déplacer entre une première position dans laquelle l'entrée de la vanne 21 est en communication fluidique avec la première sortie de la vanne 21 et une seconde position dans laquelle l'entrée de la vanne 21 est en communication fluidique avec la seconde sortie de la vanne 21. La vanne 21 comprend par exemple un ressort de rappel permettant le rappel de l'organe mobile de la seconde position vers la première position.According to this embodiment, the valve 21 is a hydraulically actuated, spring-return 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 includes a movable member in the body 21a configured to move between a first position in which the inlet of the valve 21 is in fluidic communication with the first outlet of the valve 21 and a second position in which the inlet of the valve 21 is in fluidic communication with the second outlet of the valve 21. The valve 21 includes, for example, a return spring enabling the movable member to be returned from the second position to the first position.

On comprend ainsi que dans la première position telle qu'illustrée sur la figure 4, la pompe auxiliaire 22 aspire l'huile à partir du réservoir auxiliaire 20 et l'huile est redirigée vers le réservoir auxiliaire 20. Le système de commande 13 est alimenté en huile par la pompe d'alimentation 18 qui aspire l'huile à partir réservoir principal 15.It is thus understood that in the first position as illustrated on the figure 4 The auxiliary pump 22 draws oil from the auxiliary reservoir 20 and the oil is redirected to the auxiliary reservoir 20. The control system 13 is supplied with oil by the supply pump 18 which draws oil from the main reservoir 15.

Dans la seconde position (non illustrée), la pompe auxiliaire 20 aspire l'huile à partir du réservoir auxiliaire 20 et l'huile est acheminée jusqu'au système de commande 13 au travers du second circuit d'alimentation 14b par exemple. Ainsi, lorsque la turbomachine 1, 1', 1" est dans la première phase de fonctionnement, notamment lorsque l'aéronef est dans une phase de vol dite « normale », la vanne 21 est dans la première position. Lorsque la turbomachine 1, 1', 1" est dans la seconde phase de fonctionnement, notamment lorsque l'aéronef est dans une phase de vol dans laquelle la force gravitationnelle est nulle (appelée « 0g ») ou négative (appelée « g négatif »), la vanne 21 est dans la seconde position. Ceci permet d'assurer l'alimentation en huile du système de commande 13 à partir du réservoir auxiliaire 20 et éviter toute interruption d'alimentation en huile du système de commande 13. Aussi, la pompe auxiliaire 22 est active à la fois lorsque l'organe mobile de la vanne 21 est dans la première position et dans la seconde position. Ceci permet de s'affranchir d'un temps d'amorçage de la pompe auxiliaire 22 et de garantir une alimentation rapide en huile du système de commande 13 durant la seconde phase de fonctionnement de la turbomachine 1, 1', 1".In the second position (not shown), the auxiliary pump 20 draws oil from the auxiliary reservoir 20, and the oil is delivered to the control system 13 via the second supply circuit 14b, for example. Thus, when the turbomachine 1, 1', 1" is in the first operating phase, particularly when the aircraft is in a so-called "normal" flight phase, the valve 21 is in the first position. When the turbomachine 1, 1', 1" is in the second operating phase, particularly when the aircraft is in a flight phase in which the gravitational force is zero (referred to as "0g") or negative (referred to as "negative g"), the valve 21 is in the second position. This ensures the oil supply to the control system 13 from the auxiliary reservoir 20 and prevents any interruption in the oil supply to the control system 13. Furthermore, the auxiliary pump 22 is active both when the moving part of the valve 21 is in the first and second positions. This eliminates the need for priming time for the auxiliary pump 22 and guarantees a rapid oil supply to the control system 13 during the second operating phase of the turbomachine 1, 1', 1".

La vanne 21 comprend une chambre d'actionnement hydraulique reliée à l'entrée 18a de la pompe d'alimentation 18. Lorsque la turbomachine 1, 1', 1" est dans la seconde phase de fonctionnement (gravité négative ou nulle), la pression dans le premier circuit d'alimentation 14a chute du fait que la première pompe 16a aspire de l'air ou un mélange air-huile à partir du réservoir principal 15. La pression à l'entrée 18a de la pompe d'alimentation 18 reliée au premier circuit d'alimentation 14a devient alors inférieure à une pression seuil, ce qui entraine l'organe mobile de la vanne 21 dans la seconde position sous l'action du ressort de la vanne. Une telle configuration permet de simplifier le pilotage de la vanne 21. Cette dernière ne nécessite pas de capteur particulier puisque son actionnement est provoqué par la forte baisse de pression à l'entrée 18a de la pompe d'alimentation 18.The valve 21 includes a hydraulic actuating chamber connected to the inlet 18a of the feed pump 18. When the turbomachine 1, 1', 1" is in the second operating phase (negative or zero gravity), the pressure in the first feed circuit 14a drops because the first pump 16a draws air or an air-oil mixture from the main reservoir 15. The pressure at the inlet 18a of the feed pump 18 connected to the first feed circuit 14a then falls below a threshold pressure, which causes the moving part of the valve 21 to move into the second position under the action of the valve spring. This configuration simplifies the control of the valve 21. The valve does not require a special sensor since its actuation is triggered by the sharp drop in pressure at the inlet 18a of the feed pump 18.

Alternativement, la vanne 21 est directement sensible à la force gravitationnelle.Alternatively, valve 21 is directly sensitive to gravitational force.

Par ailleurs, selon ce premier mode de réalisation, avantageusement, le dispositif d'alimentation auxiliaire 14' comprend en outre un limiteur de pression 25a agencé à la sortie de la pompe auxiliaire 22, entre la pompe auxiliaire 22 et la vanne 21. Le limiteur de pression 25a est par exemple un clapet anti-retour.Furthermore, according to this first embodiment, advantageously, the auxiliary supply device 14' further includes 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.

Selon ce premier mode de réalisation, la vanne de dosage 19 est montée sur le premier circuit d'alimentation 14a. La vanne de dosage 19 est montée entre la première pompe 16a et l'enceinte de lubrification 12. Préférentiellement, la vanne de dosage 19 est montée entre l'échangeur principal 17a qui est dans ce mode un échangeur huile/carburant et le second échangeur 17b. Dans ce premier mode de réalisation, la vanne de dosage 19 a pour fonction de vanne de répartition de l'huile distribuée entre l'enceinte de lubrification 12 et le réducteur de vitesse 11. C'est une vanne à deux sorties. La première sortie de la vanne de dosage 19 est reliée à l'enceinte de lubrification 12 et la seconde sortie de la vanne de dosage 19 est reliée au réducteur 11. La vanne de dosage 19 est par exemple pilotée par l'unité de contrôle électrique 24.According to this first embodiment, 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 chamber 12. Preferably, the metering valve 19 is mounted between the main heat exchanger 17a, which in this embodiment is an oil/fuel heat exchanger, and the second heat exchanger 17b. In this first embodiment, the metering valve 19 functions as a distribution valve for the oil supplied between the lubrication chamber 12 and the speed reducer 11. It is a two-outlet valve. The first outlet of the metering valve 19 is connected to the lubrication chamber 12, and the second outlet of the metering valve 19 is connected to the speed reducer 11. The metering valve 19 is, for example, controlled by the electrical control unit 24.

En outre, selon cet exemple, un troisième échangeur 17c, par exemple air/huile relie la deuxième sortie de la vanne de dosage 19 et le réducteur 11.In addition, according to this example, a third exchanger 17c, for example air/oil, connects the second outlet of the metering valve 19 and the reducer 11.

Selon un mode de réalisation préféré de l'invention, la pompe d'alimentation 18 comprend un clapet anti-retour 25b afin de garantir que toute l'huile délivrée par la pompe auxiliaire 22 alimente le système de commande 13.According to a preferred embodiment of the invention, the supply pump 18 includes a check valve 25b to ensure that all the oil delivered by the auxiliary pump 22 supplies the control system 13.

Selon un second mode de réalisation représenté sur la figure 5, la vanne 21 présente un corps 21a présentant une première entrée reliée au réservoir principal 15 et une seconde entrée reliée au réservoir auxiliaire 20. La vanne 21 comprend en outre une sortie reliée à l'entrée 18a de la pompe d'alimentation 18. La vanne 21 comprend en outre un organe mobile dans le corps configuré pour se déplacer entre une première position dans laquelle la première entrée est en communication fluidique avec la sortie et une seconde position dans laquelle la seconde entrée est en communication fluidique avec la sortie. La vanne 21 comprend par exemple un ressort de rappel permettant le rappel de l'organe mobile de la seconde position vers la première position. La sortie 18b de la pompe d'alimentation 18 est reliée au circuit de commande 13.According to a second embodiment shown in the figure 5 The valve 21 has a body 21a with a first inlet connected to the main tank 15 and a second inlet connected to the auxiliary tank 20. The valve 21 further includes an outlet connected to the inlet 18a of the feed pump 18. The valve 21 also includes a movable element within 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 outlet. The valve 21 includes, for example, a return spring allowing the movable element to return from the second position to the first position. The outlet 18b of the feed pump 18 is connected to the control circuit 13.

On comprend ainsi que dans la première position, la pompe d'alimentation 18 aspire l'huile à partir du réservoir principal 15 et dans la seconde position, la pompe d'alimentation 18 aspire l'huile à partir du réservoir auxiliaire 20. La vanne 21 permet ainsi de contrôler le flux d'huile dans le second circuit 14b. Lorsque la turbomachine 1, 1', 1" est dans une première phase de fonctionnement, notamment lorsque l'aéronef est dans une phase de vol dite « normale », la vanne 21 est dans la première position et la pompe principale 18 aspire l'huile à partir du réservoir principal 15 pour alimenter le système de commande 13. Lorsque la turbomachine 1, 1', 1" est dans une seconde phase de fonctionnement, notamment lorsque l'aéronef est dans une phase de vol dans laquelle la force gravitationnelle est nulle (appelée condition de 0g) ou négative (appelée condition de g négatif), la vanne 21 est dans la seconde position et la pompe principale 18 aspire l'huile à partir du réservoir auxiliaire 20 pour alimenter en huile le système de commande 13.It is thus understood that in the first position, the feed pump 18 draws oil from the main reservoir 15, and in the second position, the feed pump 18 draws oil from the auxiliary reservoir 20. The valve 21 thus controls the oil flow in the second circuit 14b. When the turbomachine 1, 1', 1" is in a first operating phase, particularly 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 oil from the main reservoir 15 to supply the control system 13. When the turbomachine 1, 1', 1" is in a second operating phase, particularly when the aircraft is in a flight phase in which the gravitational force is zero (called the 0g condition) or negative (called the negative g condition), the valve 21 is in the second position and the main pump 18 draws oil from the auxiliary reservoir 20 to supply oil to the control system 13.

Selon un premier exemple de réalisation, la vanne 21 est commandée électriquement. Selon cet exemple, la turbomachine 1, 1', 1" comprend un capteur configuré pour délivrer un signal à l'unité de contrôle électrique 24. Le capteur est configuré pour détecter la seconde phase de fonctionnement de la turbomachine 1, 1', 1". Le capteur est par exemple un accéléromètre. Selon un second exemple de réalisation, l'organe mobile de la vanne 21 est directement sensible à la force gravitationnelle s'exerçant sur la turbomachine 1, 1', 1". Lorsque la force gravitationnelle est supérieure à un seuil donné, donc dans le premier état de fonctionnement, l'organe mobile est dans la première position. Lors du second état de fonctionnement, l'organe mobile détecte le second état de fonctionnement et se déplace dans la seconde position.According to a first embodiment, the valve 21 is electrically controlled. In this example, the turbomachine 1, 1', 1" includes a sensor configured to deliver a signal to the electrical control unit 24. The sensor is configured to detect the second operating phase of the turbomachine 1, 1', 1". The sensor is, for example, an accelerometer. According to a second embodiment, the moving part of the valve 21 is directly sensitive to the gravitational force acting on the turbomachine 1, 1', 1". When the gravitational force exceeds a given threshold, i.e., in the first operating state, the moving part is in the first position. During the second operating state, the moving part detects the second operating state and moves to the second position.

La pompe auxiliaire 22 dans ce second mode de réalisation est optionnelle. La pompe auxiliaire 22 est par exemple une pompe centrifuge reliée à la sortie de la vanne 21. La pompe auxiliaire 22 est donc agencée entre la vanne 21 et la pompe d'alimentation 18. L'entrée 18a de la pompe est donc reliée à la sortie de la vanne 21 via la pompe auxiliaire 22. Optionnellement, un second échangeur air/huile 23 est agencé entre la vanne 21 et la pompe d'alimentation 18. Plus particulièrement, le second échangeur air/huile 23 est agencé entre la pompe centrifuge 22 et la pompe d'alimentation 18. La pompe centrifuge 22 et le second échangeur air/huile 23 sont montés sur le second circuit d'alimentation 14b.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 valve 21. The auxiliary pump 22 is therefore arranged between valve 21 and the feed pump 18. The inlet 18a of the pump is thus connected to the outlet of valve 21 via the auxiliary pump 22. Optionally, a second air/oil heat exchanger 23 is arranged between valve 21 and the feed pump 18. More specifically, the second air/oil heat exchanger 23 is arranged between the centrifugal pump 22 and the feed pump 18. The centrifugal pump 22 and the second air/oil heat exchanger 23 are mounted on the second supply circuit 14b.

Selon ce mode de réalisation, la vanne de dosage 19 est montée sur le second circuit d'alimentation 14b. La vanne de dosage 19 est montée entre la pompe d'alimentation 18 et le réducteur 11, et comprend une seule sortie reliée à l'enceinte de lubrification 12. Dans ce mode de réalisation, la vanne de dosage 19 n'a pas de fonction de distribution du débit entre deux sorties. La pompe d'alimentation 18 est montée en dérivation sur le second circuit 14b entre la vanne 21, et notamment le second échangeur air/huile 23 lorsqu'il est présent et la vanne de dosage 19.According to this embodiment, the metering valve 19 is mounted on the second supply circuit 14b. The metering valve 19 is mounted between the feed pump 18 and the reducer 11, and comprises a single outlet connected to the lubrication chamber 12. In this embodiment, the metering valve 19 does not have a flow distribution function between two outlets. The feed pump 18 is mounted in parallel on the second circuit. 14b between valve 21, and in particular the second air/oil exchanger 23 when present, and metering valve 19.

Avantageusement, la vanne de dosage 19 est apte à s'ouvrir lorsque la vanne 21 est dans la première position, ce qui permet d'alimenter en huile le réducteur 11 à partir du réservoir principal 15, et est apte à rester ouverte et/ou à se fermer lorsque la vanne 21 est dans la seconde position. Préférentiellement, la vanne de dosage 19 est apte à se fermer lorsque la vanne 21 est dans la seconde position. Ceci permet de ne pas alimenter en huile le réducteur 11 à partir du réservoir auxiliaire 20, afin d'alimenter exclusivement le système de commande 13 à partir du réservoir auxiliaire 20. Ainsi, le réservoir auxiliaire 20 est dimensionné pour alimenter uniquement le système de commande 13 ce qui le rend moins encombrant. Avantageusement, l'ouverture variable de la vanne de dosage 19 est commandée par l'unité de contrôle électrique 24. L'unité de contrôle électrique 24 envoie un signal à la vanne de dosage 19 pour ouvrir ou fermer cette dernière selon la phase de fonctionnement.Advantageously, the metering valve 19 is able to open when the valve 21 is in the first position, thus supplying oil to the gearbox 11 from the main reservoir 15, and is able to remain open and/or close when the valve 21 is in the second position. Preferably, the metering valve 19 is able to close when the valve 21 is in the second position. This avoids supplying oil to the gearbox 11 from the auxiliary reservoir 20, so that the control system 13 is supplied exclusively from the auxiliary reservoir 20. Thus, the auxiliary reservoir 20 is sized to supply only the control system 13, making it less bulky. Advantageously, the variable opening of the metering valve 19 is controlled by the electrical control unit 24. The electrical control unit 24 sends a signal to the metering valve 19 to open or close it according to the operating phase.

Le réservoir auxiliaire 20 selon l'invention est par exemple représenté sur la figure 6. Le réservoir auxiliaire 20 est configuré pour délivrer de l'huile durant la seconde phase de fonctionnement de la turbomachine 1, 1', 1".The auxiliary tank 20 according to the invention is, for example, shown on the figure 6 The auxiliary tank 20 is configured to deliver oil during the second phase of operation of the turbomachine 1, 1', 1".

Le réservoir auxiliaire 20 comprend une enceinte 200. L'enceinte 200 est par exemple métallique. L'enceinte 200 est par exemple polygonale. Elle comprend une paroi supérieure 200a et une paroi inférieure 200b reliées par des parois transversales 200c, 200d opposées. Les parois transversales 200c, 200d peuvent être parallèles entre elles. La paroi supérieure 200a comprend par exemple une première portion 200a1 parallèle à la paroi inférieure 200b et une seconde portion 200a2 inclinée vers l'intérieur de l'enceinte 200. La première portion 200a1 et la seconde portion 200a2 se rejoignent en un sommet O orienté vers l'extérieur de l'enceinte 200. Une telle configuration permet d'optimiser l'écoulement de l'huile dans le second circuit d'alimentation 14b durant la seconde phase de fonctionnement de la turbomachine 1, 1', 1". En effet, le sommet O représente un point haut pour la récupération de l'huile, ce qui normalement écarte le risque de présence d'air à ce niveau dans une situation de gravité négative.The auxiliary tank 20 comprises a housing 200. The housing 200 is, for example, metallic. The housing 200 is, for example, polygonal. It comprises an upper wall 200a and a lower wall 200b connected by opposing transverse walls 200c, 200d. The transverse walls 200c, 200d may 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 the outside of the enclosure 200. Such a configuration optimizes the oil flow in the second supply circuit 14b during the second operating phase of the turbomachine 1, 1', 1". Indeed, the vertex O represents a high point for the recovery of the oil, which normally eliminates the risk of air being present at this level in a negative severity situation.

L'enceinte 200 présente un premier port de sortie 201 relié au réservoir principal 15 par exemple par une première canalisation 201a, un second port de sortie 202 relié au second circuit d'alimentation 14b par la vanne 21 ou la pompe auxiliaire 22, un port d'entrée 203 relié au système de commande par le circuit de récupération 14b' d'huile du système de commande 13 et optionnellement un second port d'entrée 206 relié à la vanne 21. Le premier port de sortie 201 est par exemple ménagé sur la paroi transversale 200c et le premier port d'entrée 203 et par exemple ménagé sur la paroi transversale 200d opposée. Le second port de sortie 202 est par exemple ménagé sur la paroi supérieure 200a, par exemple sur le sommet O.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 valve 21 or auxiliary pump 22, an inlet port 203 connected to the control system by the oil recovery circuit 14b' of the control system 13, and optionally a second inlet port 206 connected to valve 21. The first outlet port 201 is, for example, provided on the transverse wall 200c, and the first inlet port 203 is, for example, provided on the opposite transverse wall 200d. The second outlet port 202 is, for example, provided on the upper wall 200a, for example, at the apex O.

L'enceinte 200 délimite un volume total par exemple compris entre 2 L et 100 L, avantageusement compris entre 2 L et 40 L et préférentiellement compris entre 4 L et 30 L. L'enceinte 200 comprend un premier volume interne V1 en communication fluidique avec le premier port de sortie 201 et un second volume interne V2 en communication fluidique avec le second port de sortie 202. Le premier volume interne V1 est compris entre 1 L et 50 L, avantageusement entre 1 L et 20 L et encore plus avantageusement entre 2 L et 15 L. Le second volume interne V2 est compris entre 1 L et 50 L, avantageusement entre 1 L et 20 L et encore plus avantageusement entre 2 L et 15 L. Préférentiellement, le premier volume interne V1 est inférieur au second volume interne V2.The enclosure 200 defines a total volume, for example, between 2 L and 100 L, advantageously between 2 L and 40 L, and preferably between 4 L and 30 L. The enclosure 200 comprises a first internal volume V1 in fluidic communication with the first output port 201 and a second internal volume V2 in fluidic communication with the second output 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. Preferably, the first internal volume V1 is smaller than the second internal volume V2.

Le réservoir auxiliaire 20 comprend en outre une chicane 204 agencée dans l'enceinte 200 qui sépare le premier volume interne V1 du second volume interne V1. La chicane 204 comprend une première paroi d'extrémité 204a s'étendant de la paroi supérieure 200a vers la paroi inférieure 200b et une seconde paroi d'extrémité 204b s'étendant de la paroi inférieure 200b vers la paroi supérieure 200a. Les première et seconde parois d'extrémité 204a, 204b sont par exemple parallèles aux parois transversales 200c, 200d. Les première et seconde parois d'extrémités 204a, 204b sont agencées entre le premier port de sortie 201 et le second port de sortie 202. La première paroi d'extrémité 204a et la paroi inférieure 200b délimitent un premier passage P1 de fluide, et la seconde paroi d'extrémité 204b et la paroi supérieure 200a délimitent un second passage P2 de fluide. Le fluide est par exemple de l'air et/ou de l'huile.The auxiliary tank 20 further includes a baffle 204 arranged within the enclosure 200, which separates the first internal volume V1 from the second internal volume V1. The baffle 204 comprises a first end wall 204a extending from the upper wall 200a to the lower wall 200b and a second end wall 204b extending from the lower wall 200b to the upper 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 The first outlet port 201 and the second outlet port 202. The first end wall 204a and the lower wall 200b define a first fluid passage P1, and the second end wall 204b and the upper wall 200a define a second fluid passage P2. The fluid is, for example, air and/or oil.

La première paroi d'extrémité 204a et la seconde paroi d'extrémité 204b délimitent un volume intermédiaire V3. Selon un premier exemple, la somme du premier volume V1 et du volume intermédiaire V3 est égale au second volume interne V2. Ceci permet d'assurer que le volume interne V2 contiendra exclusivement de l'huile durant la seconde phase de fonctionnement.The first end wall 204a and the second end wall 204b define an intermediate volume V3. In a first example, the sum of the first volume V1 and the intermediate volume V3 equals the second internal volume V2. This ensures that the internal volume V2 will contain exclusively oil during the second phase of operation.

Selon un autre exemple de réalisation, la somme du volume de la canalisation 201a reliant le premier port d'entrée 201 au réservoir principal 15, du premier volume V1 et du volume intermédiaire V3 est égale au second volume interne V2. La somme du premier volume V1 et du volume intermédiaire V3 est donc inférieure selon cet exemple au second volume interne V2. De plus, le volume de la canalisation 201a peut être dimensionné pour être égal au volume d'huile consommé durant la seconde phase de fonctionnement de la turbomachine 1, 1', 1".According to another embodiment, the sum of the volume of the pipeline 201a connecting the first inlet port 201 to the main tank 15, the first volume V1, and the intermediate volume V3 is equal to the second internal volume V2. Therefore, the sum of the first volume V1 and the intermediate volume V3 is less than the second internal volume V2 in this example. Furthermore, the volume of the pipeline 201a can be sized to be equal to the volume of oil consumed during the second operating phase of the turbomachine 1, 1', 1".

Comme illustré sur la figure 7, avantageusement, la chicane 204 comprend en outre une première paroi intermédiaire 204c et une seconde paroi intermédiaire 204d qui sont agencées parallèlement et entre les première et seconde parois d'extrémité 204a, 204b, la première paroi intermédiaire 204c délimitant avec la paroi supérieure 200a un troisième passage P3 de fluide et la seconde paroi intermédiaire 204d délimitant avec la paroi inférieure 200b un quatrième passage P4 de fluide, la première paroi intermédiaire 204c étant agencée entre la première paroi d'extrémité 204a et la seconde paroi intermédiaire 204d.As illustrated on the figure 7 Advantageously, the baffle 204 further comprises a first intermediate wall 204c and a second intermediate wall 204d which are arranged parallel 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.

Durant la première phase de fonctionnement de la turbomachine 1, 1', 1", le réservoir auxiliaire 20 est alimenté en huile par le système de commande 13. L'huile en excès est communiquée au réservoir principal 15. Cette communication est assurée par la canalisation 201a. Le système de commande 13 est alimenté en huile à partir du réservoir principal 15.During the first phase of operation of the turbomachine 1, 1', 1", the auxiliary reservoir 20 is supplied with oil by the control system 13. Excess oil is transferred to the main reservoir 15. This Communication is ensured by pipeline 201a. The control system 13 is supplied with oil from the main reservoir 15.

Durant la seconde phase de fonctionnement de la turbomachine 1, 1', 1", de l'air pénètre dans le réservoir auxiliaire 20 via le premier port de sortie 201. En effet, le débit d'huile sortant du réservoir est inférieur à celui entrant. Cependant, grâce à la chicane 204, le passage de l'air du premier volume interne V1 vers le second volume interne V2 est ralenti. Ainsi, la pompe d'alimentation 18 ou la pompe auxiliaire 22 aspire de l'huile et non de l'air ou de l'huile fortement chargée en air ce qui permet d'alimenter le système de commande 13 durant la seconde phase de fonctionnement. On comprend qu'avantageusement, le volume de la canalisation 201a et de la chicane 204a est égal au volume d'huile sortant par le second orifice de sortie 202 durant la seconde phase de fonctionnement.During the second operating phase of the turbomachine 1, 1', 1", air enters the auxiliary tank 20 via the first outlet port 201. This is because the oil flow rate exiting the tank is lower than the incoming flow rate. However, thanks to the baffle 204, the passage of air from the first internal volume V1 to the second internal volume V2 is slowed. Thus, the feed pump 18 or the auxiliary pump 22 draws oil and not air or oil heavily laden with air, which allows the control system 13 to be supplied during the second operating phase. Advantageously, the volume of the pipe 201a and the baffle 204a is equal to the volume of oil exiting through the second outlet port 202 during the second operating phase.

Un tel réservoir auxiliaire 20 selon l'invention présente l'avantage d'être simple et fiable. Par exemple, un tel réservoir auxiliaire 20 ne met en œuvre aucune pièce mobile dans la gestion de l'entrée d'air provenant du réservoir principal 15. Par exemple, le premier port de sortie 201 peut rester ouvert et aucun organe de fermeture n'est mis en œuvre. Aussi, la chicane 204 est fixe, ce qui est facilement concevable et permet d'améliorer la fiabilité par rapport à une pièce mobile telle qu'un piston.Such an auxiliary tank 20 according to the invention has the advantage of being simple and reliable. For example, such an auxiliary tank 20 does not use any moving parts in managing the air intake from the main tank 15. For example, the first outlet port 201 can remain open and no closing mechanism is used. Also, the baffle 204 is fixed, which is easily designed and improves reliability compared to a moving part such as a piston.

Claims (11)

  1. An auxiliary oil tank (20) for supplying a control system (13) for controlling the pitch of vanes (2a) of an aircraft turbine engine (1, 1', 1"), comprising an enclosure (200) comprising:
    a lower wall (200b) and an upper wall (200a) connected by transverse walls (200c, 200d),
    a first outlet port (201) intended to be connected to a main oil tank (15),
    a second outlet port (202) intended to be connected to the control system (13) via a second oil supply circuit (14b),
    a first inlet port (203) intended to be connected to the control system (13) via an auxiliary recovery circuit (14b'),
    characterised in that the enclosure (200) further comprises:
    a first internal volume (V1) in fluid communication with the first outlet port (201),
    a second internal volume (V2) in fluid communication with the second outlet port (202), and separated from the first internal volume (V1) by a baffle (204), the baffle (204) comprising a first end wall (204a) extending from the upper wall (200a) towards the lower wall (200b) and a second end wall (204b) extending from the lower wall (200b) towards the upper wall (200a), the first and second end walls (204a, 204b) being substantially parallel, the first end wall (204a) and the lower wall (200b) defining a first fluid passage (P1), and the second end wall (204b) and the upper wall (200a) defining a second fluid passage (P2).
  2. The tank according to the preceding claim, characterised in that 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) being equal to the second internal volume (V2).
  3. The tank according to claim 1, characterised in that the first end wall (204a) and the second end wall (204b) define an intermediate volume (V3), the sum of the first volume (V1) and of the intermediate volume (V3) being less than the second internal volume (V2).
  4. The tank according to any one of the preceding claims, characterised in that the baffle (204) comprises a first intermediate wall (204c) and a second intermediate wall (204d) which are arranged substantially 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).
  5. The tank according to any one of the preceding claims, characterised in that the upper wall (200a) of the enclosure (200) comprises a first segment (200a1) substantially parallel to the lower wall (200b) and a second segment (200a2) inclined towards the inside of the enclosure (200), the first and second segments (200a1, 200a2) forming a top (O) directed towards the outside of the enclosure (200).
  6. The tank according to any one of the preceding claims, characterised in that the first internal volume (V1) is between 1 L and 50 L and the second internal volume (V2) is between 1 L and 50 L.
  7. The tank according to any one of the preceding claims, characterised in that the enclosure (200) further comprises a second inlet port (206) intended to be connected to a valve (21).
  8. A turbine engine (1, 1', 1") for an aircraft comprising:
    variable pitch angle vanes (2a),
    a control system (13) for controlling the pitch of the vanes (2a) comprising a control unit (13a) connected to at least one hydraulic actuator (13b),
    an oil supply system comprising:
    a main supply system (14) comprising:
    a second supply circuit (14b) for supplying the control system (13),
    a main tank (15) connected to the second supply circuit (14b), and an oil supply pump (18) mounted on the second supply circuit (14b) and comprising an inlet (18a) and an outlet (18b) connected to the control system (13),
    an auxiliary supply device (14') comprising:
    an auxiliary oil tank (20) according to any of the preceding claims, the first outlet port (201) being connected to the main tank (15), the second outlet port (202) being connected to the second supply circuit (14b) and the first inlet port (203) being connected to the control system (13).
  9. The turbine engine according to the preceding claim, characterised in that the auxiliary supply device (14') further comprises a valve (21) comprising a body (21a) having a first inlet connected to the main tank (15), a second inlet connected to the second outlet port (202) of the auxiliary tank (20) and an outlet connected to the inlet (18a) of the supply pump (18), the valve (21) further comprising a member movable within the body and configured to move between a first position in which the first inlet of the valve (21) is in fluid communication with the outlet of the valve (21) and a second position in which the second inlet of the valve (21) is in fluid communication with the outlet of the valve (21).
  10. The turbine engine according to claim 8, characterised in that the auxiliary tank (20) comprises a second inlet port (206), and in that the auxiliary supply device (14') comprises a valve (21) comprising a body (21a) having an inlet connected to the auxiliary tank (20) and a first outlet connected to the second inlet port (206) of the auxiliary tank (20), and a second outlet connected to the control system (13), the valve (21) further comprising a member movable within the body and 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).
  11. The turbine engine according to the preceding claim, characterised in that the inlet (18a) of the supply pump (18) is connected to the main tank (15).
EP22789961.4A 2021-09-30 2022-09-27 Auxiliary oil tank for an aircraft turbine engine Active EP4409115B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2110348A FR3127527B1 (en) 2021-09-30 2021-09-30 AUXILIARY OIL TANK FOR AN AIRCRAFT TURBOMACHINE
PCT/FR2022/051809 WO2023052717A1 (en) 2021-09-30 2022-09-27 Auxiliary oil tank for an aircraft turbine engine

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EP4409115A1 EP4409115A1 (en) 2024-08-07
EP4409115B1 true EP4409115B1 (en) 2025-11-05

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US (1) US12428977B2 (en)
EP (1) EP4409115B1 (en)
CN (1) CN118019899A (en)
FR (1) FR3127527B1 (en)
WO (1) WO2023052717A1 (en)

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EP4409124A1 (en) * 2021-09-30 2024-08-07 Safran Aircraft Engines Turbine engine comprising an oil supply system

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FR3127527B1 (en) 2023-09-01
CN118019899A (en) 2024-05-10
EP4409115A1 (en) 2024-08-07
WO2023052717A1 (en) 2023-04-06
FR3127527A1 (en) 2023-03-31
US12428977B2 (en) 2025-09-30
US20240392695A1 (en) 2024-11-28

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