EP4409115B1 - Hilfsöltank für ein flugzeugturbinentriebwerk - Google Patents

Hilfsöltank für ein flugzeugturbinentriebwerk

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
English (en)
French (fr)
Other versions
EP4409115A1 (de
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/de
Application granted granted Critical
Publication of EP4409115B1 publication Critical patent/EP4409115B1/de
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)
  • Pressure Vessels And Lids Thereof (AREA)
  • General Details Of Gearings (AREA)

Claims (11)

  1. Hilfsöltank (20) zur Versorgung eines Steuerungssystems (13) zum Einstellen einer Schaufelteilung (2a) eines Turbotriebwerks eines Luftfahrzeugs (1, 1', 1"), der ein Gehäuse (200) umfasst, umfassend:
    eine untere Wand (200b) und eine obere Wand (200a), die durch Querwände (200c, 200d) verbunden sind,
    eine erste Auslassöffnung (201), die dazu bestimmt ist, an einen Hauptöltank (15) angeschlossen zu werden,
    eine zweite Auslassöffnung (202), die dazu bestimmt ist, durch einen zweiten Ölversorgungskreis (14b) an das Steuerungssystem (13) angeschlossen zu werden, eine erste Einlassöffnung (203), die dazu bestimmt ist, durch einen Rückgewinnungskreis (14b') an das Steuerungssystem (13) angeschlossen zu werden,
    dadurch gekennzeichnet, dass das Gehäuse (200) weiter umfasst:
    ein erstes Innenvolumen (V1) in strömungstechnischer Kommunikation mit der ersten Auslassöffnung (201),
    ein zweites Innenvolumen (V2) in strömungstechnischer Kommunikation mit der zweiten Auslassöffnung (202), und durch eine Schikane (204) vom ersten Innenvolumen (V1) getrennt, wobei die Schikane (204) eine erste Abschlusswand (204a) umfasst, die sich von der oberen Wand (200a) zur unteren Wand (200b) erstreckt, und eine zweite Abschlusswand (204b), die sich von der unteren Wand (200b) zur oberen Wand (200a) erstreckt, wobei die erste und zweite Abschlusswand (204a, 204b) im Weentlichen parallel sind, die erste Abschlusswand (204a) und die untere Wand (200b) einen ersten Fluiddurchlass (P1) begrenzen, und die zweite Abschlusswand (204b) und die obere Wand (200a) einen zweiten Fluiddurchlass (P2) begrenzen.
  2. Tank nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass die erste Abschlusswand (204a) und die zweite Abschlusswand (204b) ein Zwischenvolumen (V3) begrenzen, wobei die Summe des ersten Volumens (V1) und des Zwischenvolumens (V3) gleich dem zweiten Innenvolumen (V2) ist.
  3. Tank nach Anspruch 1, dadurch gekennzeichnet, dass die erste Abschlusswand (204a) und die zweite Abschlusswand (204b) ein Zwischenvolumen (V3) begrenzen, wobei die Summe des ersten Volumens (V1) und des Zwischenvolumens (V3) kleiner als das zweite Innenvolumen (V2) ist.
  4. Tank nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die Schikane (204) eine erste Zwischenwand (204c) und eine zweite Zwischenwand (204d) umfasst, die im Wesentlichen parallel und zwischen der ersten und zweiten Zwischenwand (204a, 204b) angeordnet sind, wobei die erste Zwischenwand (204c) mit der oberen Wand (200a) einen dritten Fluiddurchlass (P3) begrenzt, und die zweite Zwischenwand (204d) mit der unteren Wand (200b) einen vierten Fluiddurchlass (P4) begrenzt, wobei die erste Zwischenwand (204c) zwischen der ersten Abschlusswand (204a) und der zweiten Zwischenwand (204d) angeordnet ist.
  5. Tank nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass die obere Wand (200a) des Gehäuses (200) einen ersten Abschnitt (200a1) im Wesentlichen parallel zur unteren Wand (200b), und einen zweiten Abschnitt (200a2), ins Innere des Gehäuses (200) geneigt umfasst, wobei der erste und zweite Abschnitt (200a1, 200a2) einen (O) nach außerhalb des Gehäuses (200) geführten Scheitelpunkt bildet.
  6. Tank nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass das erste Innenvolumen (V1) zwischen 1 L und 50 L umfasst ist, und das zweite Innenvolumen (V2) zwischen 1 L und 50 L umfasst ist.
  7. Tank nach einem der vorstehenden Ansprüche, dadurch gekennzeichnet, dass das Gehäuse (200) weiter eine zweite Einlassöffnung (206) umfasst, die dazu bestimmt ist, an ein Ventil (21) angeschlossen zu werden.
  8. Turbotriebwerk (1, 1', 1") für ein Flugzeug, umfassend:
    Schaufeln (2a) mit variablem Einstellwinkel,
    ein Steuerungssystem (13) zum Einstellen der Schaufeln (2a), das eine Steuerungseinheit (13a) umfasst, die mit mindestens einer hydraulischen Betätigungsvorrichtung (13b) verbunden ist,
    ein Ölversorgungssystem, umfassend:
    ein Hauptversorgungssystem (14), umfassend:
    einen zweite, Versorgungskreis (14b) des Steuerungssystems (13),
    einen Haupttank (15), der mit dem zweiten Versorgungskreis (14b) verbunden ist,
    und eine Ölversorgungspumpe (18), die am zweiten Versorgungskreis (14b) montiert ist und einen Einlass (18a) und einen Auslass (18b) umfasst, der mit dem Steuerungssystem (13) verbunden ist,
    eine Hilfsversorgungsvorrichtung (14'), umfassend:
    einen Hilfsöltank (20) nach einem der vorstehenden Ansprüche, wobei die erste Auslassöffnung (201) mit dem Haupttank (15) verbunden ist, die zweite Auslassöffnung (202) mit dem zweiten Versorgungskreis (14b) verbunden ist, und die erste Einlassöffnung (203) mit dem Steuerungssystem (13) verbunden ist.
  9. Turbotriebwerk nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass die Hilfsversorgungsvorrichtung (14') weiter ein Ventil (21) umfasst, das einen Körper (21a) umfasst, der einen ersten Einlass aufweist, der mit dem Haupttank (15) verbunden ist, einen zweiten Einlass, der mit der zweiten Einlassöffnung (202) des Hilfstanks (20) verbunden ist und einen Auslass, der mit dem Einlass (18a) der Versorgungspumpe (18) verbunden ist, wobei das Ventil (21) weiter ein bewegliches Organ im Körper umfasst und konfiguriert ist, um sich zwischen einer ersten Position, in welcher der erste Einlass des Ventils (21) in strömungstechnischer Kommunikation mit dem Auslass des Ventils (21) ist, und einer zweiten Position zu bewegen, in welcher der zweite Einlass des Ventils in strömungstechnischer Kommunikation mit dem Auslass des Ventils (21) ist.
  10. Turbotriebwerk nach Anspruch 8, dadurch gekennzeichnet, dass der Hilfstank (20) eine zweite Einlassöffnung (206) umfasst, und dadurch, dass die Hilfsversorgungsvorrichtung (14') ein Ventil (21) umfasst, das einen Körper (21a) umfasst, der einen Einlass aufweist, der mit dem Hilfstank (20) verbunden ist, und einen ersten Auslass, der mit der zweiten Einlassöffnung (206) des Hilfstanks (20) verbunden ist und einen zweiten Auslass, der mit dem Steuerungssystem (13) verbunden ist, wobei das Ventil (21) weiter ein bewegliches Organ im Körper umfasst und konfiguriert ist, um sich zwischen einer ersten Position, in welcher der Einlass des Ventils (21) in strömungstechnischer Kommunikation mit dem ersten Auslass des Ventils (21) ist, und einer zweiten Position zu bewegen, in welcher der Einlass des Ventils in strömungstechnischer Kommunikation mit dem zweiten Auslass des Ventils (21) ist.
  11. Turbotriebwerk nach dem vorstehenden Anspruch, dadurch gekennzeichnet, dass der Einlass (18a) der Versorgungspumpe (18) mit dem Haupttank (15) verbunden ist.
EP22789961.4A 2021-09-30 2022-09-27 Hilfsöltank für ein flugzeugturbinentriebwerk Active EP4409115B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2110348A FR3127527B1 (fr) 2021-09-30 2021-09-30 Reservoir auxiliaire d’huile pour une turbomachine d’aeronef
PCT/FR2022/051809 WO2023052717A1 (fr) 2021-09-30 2022-09-27 Reservoir auxiliaire d'huile pour une turbomachine d'aeronef

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EP4409124A1 (de) * 2021-09-30 2024-08-07 Safran Aircraft Engines Turbinenmotor mit einem ölversorgungssystem

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

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