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
  • 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
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01M—LUBRICATING OF MACHINES OR ENGINES IN GENERAL; LUBRICATING INTERNAL COMBUSTION ENGINES; CRANKCASE VENTILATING
  • F01M1/00—Pressure lubrication
  • F01M1/16—Controlling lubricant pressure or quantity
• • 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
  • F05D2220/00—Application
  • F05D2220/30—Application in turbines
  • F05D2220/32—Application in turbines in gas turbines
  • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
• • 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
  • F05D2260/20—Heat transfer, e.g. cooling
  • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
• • 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
  • F05D2260/40—Transmission of power
• • 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
  • F05D2260/60—Fluid transfer
  • F05D2260/606—Bypassing the fluid
• • 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
• • 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
  • F05D2270/00—Control
  • F05D2270/30—Control parameters, e.g. input parameters
  • F05D2270/301—Pressure
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16N—LUBRICATING
  • F16N2210/00—Applications
  • F16N2210/02—Turbines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
  • F16N—LUBRICATING
  • F16N2210/00—Applications
  • F16N2210/12—Gearings
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the invention relates to the general technical field of aircraft turbomachines such as turbojets and turboprops. More specifically, the invention belongs to the technical field of turbomachine lubrication systems.
• Some turbomachines include a reduction gear to drive a fan of the turbomachine.
• This reducer is for example an epicyclic reducer. It is in particular mechanically connected to a shaft of the low-pressure body which comprises a low-pressure compressor and a low-pressure turbine of the turbomachine.
• turbomachines comprise a lubrication system which comprises heat exchangers for cooling the lubricant, lubrication enclosures for the bearings of the turbomachine, and a gearbox lubrication enclosure.
• Lubricant is supplied to the gearbox lubrication enclosure both to cool the gearbox and to lubricate the gearbox teeth.
• the pressure and the flow rate of the lubricant in the lubrication system can be made to be very low.
• the gearbox may be insufficiently supplied with lubricant, which is likely to damage it.
• the invention aims to at least partially solve the problems encountered in the solutions of the prior art.
• the subject of the invention is a lubrication system for a turbomachine which comprises a reduction gear for driving a module of the turbomachine.
• the lubrication system comprises a main branch and a bypass branch which is arranged in parallel with the main branch.
• the main branch includes a heat exchanger.
• the branch branch includes a hydraulic resistance that is less than the hydraulic resistance of the main branch.
• the reducer is located downstream of the main branch and the bypass branch.
• the lubrication system includes at least one bypass device which is configured to supply the bypass branch with lubricant when a pressure value of the lubricant is lower than a threshold value.
• the reduction gear is supplied with lubricant in a privileged manner, via the branch branch, compared to the rest of the turbomachine when the flow rate of lubricant and the pressure of the lubricant are too low. to supply the entire turbomachine with lubricant.
• the reduction gear is for example supplied is supplied with lubricant by the bypass branch when the turbomachine is operating at low speed. It is in particular supplied with lubricant by the main branch when the flow rate and the pressure of the lubricant are sufficient to supply the whole of the turbomachine, for example when the turbomachine is operating at high speed.
• the lubricant is typically oil.
• the invention may optionally include one or more of the following features, combined or not.
• the bypass device is configured to supply the main branch with lubricant when the pressure value of the lubricant is strictly greater than the threshold value.
• the bypass device is mechanically and/or hydraulically controlled by lubricant pressure.
• the bypass device comprises a lubricant inlet, a first lubricant outlet which is fluidly connected to the bypass branch, a second lubricant outlet which is fluidly connected to the main branch, an obturator configured to at least partially obturate the first outlet and/or the second outlet, and an elastic biasing means of the obturator which is configured to elastically bias the obturator so that it obturates the second exit.
• the shutter is configured to allow lubricant to flow to the first outlet when a lubricant pressure is below the threshold value.
• the bypass device comprises a first bypass valve and/or a second bypass valve.
• the shutter of the first diverter valve comprises a spool.
• the shutter of the second diverter valve comprises a spool.
• the first diverter valve is bistable.
• the first bypass valve comprises a first stable open position in which the first bypass valve supplies the bypass branch with lubricant and a second stable open position in which the first bypass valve supplies the main branch with lubricant. lubricant.
• the second diverter valve is bistable.
• the second diverter valve comprises a first stable open position in which the second diverter valve supplies the diverter branch with lubricant and a second stable open position in which the second diverter valve is configured to supply the main branch in lubricant.
• the diverter device comprises a first diverter valve and a second diverter valve which is fluidly connected in series to the first diverter valve so that the first diverter valve and the second diverter valve supply the branch lubricant bypass when the lubricant pressure value is lower than the threshold value.
• the first diverter valve is configured to fluidically supply directly the main branch when the lubricant pressure value is strictly greater than the threshold value.
• the first diverter valve comprises a lubricant inlet, a first lubricant outlet, a second lubricant outlet which is fluidly connected to the main branch upstream of the heat exchanger, a shutter configured to close the first outlet or the second outlet, and a resilient biasing means of the shutter which is configured to resiliently bias the shutter to shut off the second outlet.
• the shutter of the first diverter valve is configured to allow lubricant to flow to the first outlet when a lubricant pressure is below the pressure threshold value.
• the second bypass valve comprises a lubricant inlet, a first lubricant outlet which is fluidly connected to the bypass branch, a second lubricant outlet which is fluidically connected to the main branch upstream of the heat exchanger, a shutter configured to close the first outlet or the second outlet, and a means for elastically urging the shutter which is configured to elastically urge the shutter so that it closes the second outlet.
• the shutter of the second diverter valve is configured to allow lubricant to flow to the first outlet when a lubricant pressure is below the pressure threshold value.
• the first outlet of the first diverter valve is in particular fluidly connected to the lubricant inlet of the second diverter valve.
• the lubrication system comprises a non-return device which is configured to limit/prevent the circulation of lubricant from the reducer to the main branch.
• the non-return device comprises a non-return valve.
• the lubrication system comprises a shutter position monitoring device which is configured to monitor the position of the shutter of the bypass device.
• the monitoring device is configured to determine a lubricant pressure in the main branch, for example by means of a first pressure sensor, and to determine a lubricant pressure in the branch branch, for example by means of a second pressure sensor.
• the monitoring device can monitor the position of the shutter of at least one bypass valve by comparing the lubricant pressure value in the main branch and the lubricant pressure value in the bypass branch.
• the main branch comprises the heat exchanger, a filter, a reservoir, a pump and/or a valve.
• the main branch comprises a lubricant distributor.
• the main branch and/or the bypass branch are configured to supply lubricant to an accessory drive unit for a turbomachine which comprises a fuel pump, a lubricant pump, an electric generator and/or a starter to start the turbomachine.
• the starter includes a gear train.
• the invention also relates to a turbomachine comprising a reduction gear, a module and a lubrication system as defined above.
• the turbomachine module includes a fan and/or a propeller, a compressor and a turbine.
• the reducer is configured to be driven by the turbine.
• the turbine is a low pressure turbine of the turbomachine.
• the turbomachine is preferably a turbojet.
• the turbomachine is in particular an aircraft turbomachine.
• FIG. 1 represents a turbomachine comprising a lubrication system according to a first embodiment of the invention
• Figure 2 is a partial schematic representation of a lubrication system according to the first embodiment at low speed
• Figure 3 is a partial schematic representation of the lubrication system according to the first embodiment at high speed
• Figure 4 is a partial schematic representation of a lubrication system according to a second embodiment at low speed
• FIG. 1 represents a turbomachine comprising a lubrication system according to a first embodiment of the invention
• Figure 2 is a partial schematic representation of a lubrication system according to the first embodiment at low speed
• Figure 3 is a partial schematic representation of the lubrication system according to the first embodiment at high speed
• Figure 4 is a partial schematic representation of a lubrication system according to a second embodiment at low speed
• FIG. 1 represents a turbomachine comprising a lubrication system according to a first embodiment of the invention
• Figure 3 is a partial schematic representation of the
• FIG. 5A is a partial schematic representation of a lubrication system according to a third embodiment at low speed
• Figure 5B is a partial schematic representation of the lubrication system according to the third embodiment at high speed
• FIG. 5C is a partial schematic representation of the lubrication system according to the third embodiment at high speed and in the event of untimely blocking of the first bypass valve in its first open position
• FIG. 5D is a partial schematic representation of the lubrication system according to the third embodiment at high speed and in the event of untimely blocking of the second bypass valve in its first open position
• FIG. 6A is a schematic representation of the diverter valve of the lubrication system according to the first embodiment when the diverter valve is in the first open position
• FIG. 6A is a schematic representation of the diverter valve of the lubrication system according to the first embodiment when the diverter valve is in the first open position
• FIG. 6B is a schematic representation of the diverter valve of the lubrication system according to the first embodiment when the diverter valve is in the second open position;
• FIG. 7 illustrates the pressure drop of the diverter valve according to the first embodiment compared to the pressure drop of a valve of conventional structure;
• FIG. 8 illustrates a turbomachine lubrication method, by means of a lubricating device according to one of the embodiments of the invention.
• FIG. 1 represents a turbomachine 1 with double flow and double body.
• the turbomachine 1 is a turbojet which has a shape of revolution around a longitudinal axis AX.
• the turbomachine 1 comprises, in this order on the path of a primary stream 11 of a primary flow, an air intake sleeve 2, a fan 3, a low pressure compressor 4, a high pressure compressor 6, a combustion chamber 7, a high pressure turbine 8 and a low pressure turbine 9.
• air designates any gas capable of serving as an oxidizer in the turbomachine 1.
• the low-pressure compressor 4, the high-pressure compressor 6, the high-pressure turbine 8 and the low-pressure turbine 9 define a secondary vein 13 for the flow of a secondary flow which bypasses them.
• the high pressure compressor 6 and the high pressure turbine 8 are mechanically connected by a drive shaft of the high pressure compressor 6, so as to form a high pressure body of the turbomachine 1.
• the low pressure compressor 4 and the low-pressure turbine 9 are mechanically connected by a turbomachine shaft 1, so as to form a low-pressure body of the turbomachine 1.
• the fan 3 is mechanically connected by a reducer 152 to the low-pressure turbomachine body.
• the low pressure compressor 4, the high pressure compressor 6, the combustion chamber 7, the high pressure turbine 8 and the low pressure turbine 9 are surrounded by an internal fairing which extends from the inlet sleeve 2 to the low pressure turbine 9.
• This internal fairing is surrounded by an external casing which delimits the turbomachine radially outwards with respect to the longitudinal axis AX.
• the outer casing delimits the secondary stream 13 radially outwards, in particular at the level of the fan 3.
• the turbine engine 1 comprises an accessory drive unit 170 which comprises a fuel pump, a lubricant pump, an electric generator and a starter to start the turbine engine 1.
• the starter comprises a gear train.
• the accessory drive unit 170 is connected by a mechanical power take-off to the shaft of the high-pressure body of the turbomachine 1.
• FIG. 2 represents a lubrication system 100 according to a first embodiment of the invention.
• the lubricant is typically oil.
• the lubrication system 100 comprises an upstream branch 110, a main branch 120 and bypass branch 140 which are each downstream of the upstream branch 110, a priority branch 150 and a secondary branch 160 which are each located downstream of the main branch 120 and branch branch 140, and a lubricant return circuit 180.
• upstream and downstream are used with reference to the general direction of flow from upstream to downstream of the lubricant in the lubrication system 100.
• the upstream branch 110 comprises a reservoir 111 of lubricant, a pump assembly 112, a first hydraulic resistance 114 and a bypass device 200.
• the pump assembly 112 comprises at least one lubricant supply pump in the lubrication system 100 and in particular at least one lubricant return pump which is designed to circulate lubricant towards the reservoir 111.
• Each of these pumps is for example a centrifugal pump which can be part of the accessory drive box 170.
• the flow of lubricant pumped by the pump assembly 112 depends in particular on the speed of the turbine engine 1, with a maximum flow rate of pumped lubricant which increases as a function of the operating speed of the turbine engine 1.
• the lubricant return pump is connected to a third lubricant return branch 186 which returns lubricant from pump assembly 112 to reservoir 111.
• a hydraulic resistance of an element of the lubrication system 100 is defined, by analogy with the field of electricity, as the magnitude of the ratio between the pressure drop through this element on the flow rate of lubricant passing through this element.
• a hydraulic resistance corresponds to an element of the lubrication system 100 which is characterized by the value of its hydraulic resistance.
• the first hydraulic resistor 114 comprises for example an oil filter.
• the bypass device 200 comprises at least a first bypass valve 210.
• the bypass device 200 is mechanically and/or hydraulically controlled by lubricant pressure.
• the bypass device 200 is designed to distribute lubricant to the bypass branch 140 when the pressure and the flow rate of lubricant in the lubrication system 100 risk being insufficient to correctly supply the whole of the turbomachine 1 More specifically, the bypass device 200 is configured to supply lubricant to the main branch 120 when a pressure value of the lubricant is strictly greater than a threshold value. It is configured to supply the bypass branch 140 with lubricant when the pressure value of the lubricant is lower than the threshold value.
• the bypass device 200 includes the first bypass valve 210, a lubricant inlet conduit 212, a pressurization conduit 218, a first outlet conduit 214 of lubricant and a second outlet duct 216 of lubricant.
• the first bypass valve 210 includes a lubricant inlet 211, a pressurization inlet 217, a first lubricant outlet 213, a second outlet 215 of lubricant, a shutter 202 and a spring which forms an elastic biasing means 204 of the shutter.
• the lubricant inlet 211 is fluidly connected to the lubricant inlet conduit 212.
• the pressurization inlet 217 is fluidically connected to the pressurization conduit 218.
• the first lubricant outlet 213 is fluidically connected to the branch branch 140.
• the second outlet 215 is fluidically connected to the main branch 120.
• the pressurization conduit 218 is fluidically connected on the one hand to the inlet conduit and to the pressurization inlet 217 on the other hand.
• the pressurization conduit 218 makes it possible to supply lubricant to the pressurization inlet 217 which has a pressure substantially identical to that of the fuel at the lubricant inlet 211 .
• the first diverter valve 210 is bistable. It comprises a first stable open position and a second stable open position.
• the first bypass valve 210 is in the first stable open position when the pressure of the lubricant at the inlet 211 of the first bypass valve 210 is lower than the threshold value. In the first stable open position, the first bypass valve 210 supplies lubricant to the bypass branch 140.
• the first bypass valve 210 is in the second stable open position when the pressure of the lubricant at the inlet 211 of the first bypass valve 210 is greater than the threshold value. In the second stable open position, it supplies lubricant to the main branch 120.
• the shutter 202 comprises a spool which slides in a casing 201 which delimits the outside of the first diverter valve 210.
• the spool of the shutter 202 delimits inside the casing 201 a first chamber 207 and a second chamber 209 which are each located on either side of the shutter 202 and which are each of variable volume.
• the shutter slide 202 is traversed by a first channel 206 and by a second channel 208 which is distinct and fluidically separated from the first channel 206.
• the spring of the elastic biasing means 204 of the shutter is a compression spring which is located in the first chamber 207 in the embodiment shown. It is configured to request the shutter 202 so that the first diverter valve 210 is in the first open position.
• the elastic biasing means 204 of the shutter is configured to elastically urge the shutter 202 so that it closes the second outlet 215 of the first bypass valve 210.
• the shutter 202 closes the second outlet 215 when the lubricant pressure is below the threshold value under the action of the spring of the elastic biasing means 204.
• the second channel 208 is blocked by the housing 201
• the lubricant inlet 211 then opens into the first channel 206.
• the outlet of the first channel 206 is aligned with the first outlet duct 214.
• the lubricant can flow from the inlet duct 212 to the first outlet duct. outlet 214 through the first diverter valve 210.
• the shutter 202 closes the first outlet 213 when the lubricant pressure is greater than the threshold value by opposing the action of the spring of the elastic biasing means 204.
• the first channel 206 is blocked through the housing 201.
• the lubricant inlet 211 then opens into the second channel 208.
• the outlet of the second channel 208 is aligned with the second outlet duct 216.
• the lubricant can flow from the inlet duct 212 to to the second outlet conduit 216 through the first diverter valve 210.
• the main branch 120 is fluidly connected to a second output 215 of the bypass device 200, by a main conduit 123. It comprises from upstream to downstream a first heat exchanger 121, a second heat exchanger 122, a lubricant distributor 169, a third heat exchanger 124 and a first non-return device 130.
• the main branch 120 supplies the priority branch 150 and the secondary branch 160 with lubricant, when the flow rate and the pressure of lubricant in the lubrication system 100 are sufficient to supply the entire turbomachine 1 with lubricant.
• the main branch 120 supplies by lubricating the downstream of the lubrication system 100 when the speed of the turbomachine 1 is sufficiently high, typically in speeds other than takeoff and landing, for example at cruising speed of the turbomachine 1.
• Each of the heat exchangers 121, 122, 124 may be an air-oil heat exchanger or an oil-fuel heat exchanger.
• Each heat exchanger can be a brick type exchanger or else a surface heat exchanger.
• the heat exchangers 121, 122, 124 can be arranged in series and/or in parallel with each other.
• the lubricant distributor 169 is a lubricant distributor that has a lubricant inlet and several lubricant outlets. It distributes the lubricant that arrives at its inlet between its different outlets.
• the distributor 169 comprises for example several positions and as many outlets as there are lubrication chambers in the lubrication system 100.
• the distributor 169 comprises a lubricant inlet which is located downstream of the second heat exchanger 122, a first lubricant outlet which is fluidly connected downstream of the main branch 120, a second outlet which is fluidly connected to secondary leg 160, and a third outlet which is fluidly connected to reservoir 111.
• the third outlet of distributor 169 is connected to a second lubricant return branch 184 which returns lubricant from lubricant distributor 169 to reservoir 111
• the lubricant distributor 169 is in particular a hydraulic distributor with several channels and several positions of known structure.
• the first non-return device 130 comprises a non-return valve. It is configured to prevent lubricant from flowing from downstream of the main leg 120 through the main leg 120. The first non-return device 130 prevents the flow of lubricant from the priority leg 150 to the main leg 120.
• the bypass branch 140 is arranged in parallel with the main branch 120. It is fluidly connected, via a bypass conduit 141, to a first outlet 213 of the bypass device 200 and downstream of the first non-return device 130 to the main conduit 123.
• the bypass branch 140 includes an overall hydraulic resistance which is lower than the overall hydraulic resistance of the main branch 120, to limit the pressure drops in the bypass branch 140 compared to those in the main branch 120.
• the bypass branch 140 is intended to supply the priority branch 150 with lubricant in a privileged manner with respect to the secondary branch 160 when the flow rate and the pressure of lubricant in the lubrication system 100 risk being insufficient to supply the whole of the turbomachine 1 with lubricant.
• the bypass branch 140 supplies lubricant exclusively to the priority branch 150.
• the priority branch 150 comprises, from upstream to downstream, a cut-off valve 132 and the gearbox lubrication chamber 152.
• the priority branch 150 is connected by a first priority conduit 153 to the main conduit 123, downstream of the first non-return device 130, and to the bypass conduit 141.
• the cut-off valve 132 is configured to stop the supply of lubricant to the lubrication enclosure of the reducer 152 when the pressure of the lubricant supplying this enclosure is too high. It aims to protect the reducer 152 during disturbances in the supply of lubricant to its lubrication enclosure.
• the gearbox lubrication chamber 152 supplies the gearbox 152 with lubricant both to lubricate it and to cool it. In particular, it lubricates the gear teeth of the reducer 152 to limit their wear during the operation of the turbomachine 1.
• the secondary branch 160 includes a fourth heat exchanger 168, a first bearing lubrication enclosure 162, a second bearing lubrication enclosure 164, a third bearing lubrication enclosure 166 and an accessory box lubrication enclosure 170. It is supplied with lubricant exclusively by the distributor 169 in the embodiment shown.
• the fourth heat exchanger 168 may be an air-oil heat exchanger or an oil-fuel heat exchanger. It can be a brick type exchanger or a surface heat exchanger.
• Each of the lubrication enclosures 162, 164, 166 is an enclosure for lubricating a turbomachine shaft bearing, in particular a shaft of the high pressure cops or of the low pressure body of the turbomachine 1.
• Each of the enclosures of lubrication 162, 164, 166 supplies the corresponding bearing to lubricate it and to cool it. In particular, it lubricates the bearings of the bearing during the operation of the turbomachine 1.
• the lubricating chamber of the accessory drive box 170 supplies lubrication to the gears of the accessory drive box 170, in particular the gears of the starter motor of the turbomachine.
• the first lubrication enclosure 162, the second lubrication enclosure 164, the third lubrication enclosure 166 and the accessory drive unit 170 are arranged two by two in parallel. They are each arranged downstream of the fourth heat exchanger 168.
• Each of the bearing lubrication enclosures 162, 164, 166 and the accessory drive housing enclosure 170 are fluidly connected to a first lubricant return leg 182 which returns lubricant from each of the lubrication enclosures 162, 164 , 166 from the landing and from the enclosure of the accessory drive unit 170 to the tank 111.
• the pressure of the lubricant at the inlet 211 of the first bypass valve 210 is lower than the threshold value.
• the turbomachine 1 is for example in a start-up phase.
• the pressure supplied by the pump assembly 112 is insufficient to supply the main branch 120.
• the first bypass valve 210 is in the first open position and it exclusively supplies the bypass branch 140 with lubricant, through the first outlet. 213 lubricant.
• the secondary branch 160 is not supplied with lubricant, due to the absence of lubricant circulation in the main branch 120.
• the lubricant leaving the branch branch 140 supplies the priority branch 150 in the direction of the lubrication of the gearbox 152.
• the gearbox 152 is sufficiently cooled and lubricated despite the low flow rate and low pressure of lubricant in the lubrication system 100.
• the pressure of the lubricant at the inlet 211 of the first bypass valve 210 is greater than the threshold value.
• the turbomachine 1 is for example in cruising speed. Pressure supplied by the pump assembly 112 is sufficient to supply the main branch 120.
• the first diverter valve 210 is in the second open position and it exclusively supplies the main branch 120 with lubricant, through the second outlet 215 of lubricant .
• the lubricant is cooled in the heat exchangers 121, 122, 124 of the main branch 120.
• the priority branch 150 and the secondary branch 160 are each supplied with lubricant, by the main branch 120.
• the lubricant that circulates in the secondary leg 160 is cooled by the fourth heat exchanger 168.
• Each of the bearing lubrication enclosures 162, 164, 166 and the enclosure of the accessory drive box 170 are supplied with lubricant.
• the lubricant leaving the main branch 120 feeds the priority branch 150 in the direction of the lubrication enclosure of the reducer 152.
• the reducer 152 is sufficiently cooled and lubricated despite the pressure drop in the secondary branch 160 and the flow of lubricant in the secondary branch 160.
• FIGS. 7 and 8 each illustrate a method of lubricating 300 the turbine engine 1 during 'flight.
• the turbomachine 1 is first in a start-up phase 302, 304, in which the speed of the turbomachine is low.
• the flow rate and the pressure of lubricant in the lubrication system 100 increase but they are insufficient to supply the secondary branch 160.
• the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is lower than the threshold value.
• the first diverter valve 210 is in the first open position. Only the gearbox lubrication enclosure 152 which is in the priority branch 150 is supplied with lubricant, via the bypass branch 140.
• a first transient state 306 of operation of the turbine engine 1 the flow of lubricant increases and the pressure of the lubricant at the inlet 211 of the first bypass valve 210 exceeds the threshold value.
• the first diverter valve 210 switches to its second stable open position in which it supplies the main branch 120 with lubricant.
• the main branch 120 having a greater hydraulic resistance than that of the bypass branch 140, the pressure drop in the lubrication system 100 increases sharply at a substantially constant flow rate of lubricant.
• the priority branch 150 and the secondary branch 160 are supplied with lubricant.
• Each of the bearing lubricating enclosures 162, 164, 166, the accessory drive housing lubricating enclosure 170, and the reduction gear lubricating enclosure 152 are supplied with lubricant.
• a first cruising speed 308 of the turbomachine 1 the flow of lubricant increases and the pressure of the lubricant in the lubrication system 100 increases.
• the first diverter valve 210 is in its second stable open position in which it supplies lubricant to the main branch 120.
• the priority branch 150 and the secondary branch 160 are supplied with lubricant.
• Each of the bearing lubricating enclosures 162, 164, 166, the accessory drive housing lubricating enclosure 170, and the reduction gear lubricating enclosure 152 are supplied with lubricant.
• the flow of lubricant increases and the pressure of the lubricant in the lubrication system 100 decreases.
• the pressure at the inlet 211 of the first diverter valve 210 is greater than the threshold value.
• the first diverter valve 210 is in its second stable open position in which it supplies lubricant to the main branch 120.
• the priority branch 150 and the secondary branch 160 are supplied with lubricant.
• Each of the bearing lubricating enclosures 162, 164, 166, the accessory drive housing lubricating enclosure 170, and the reduction gear lubricating enclosure 152 are supplied with lubricant.
• a second transient state 314 of operation of the turbine engine 1 the flow of lubricant decreases and the pressure of the lubricant at the inlet 211 of the first bypass valve 210 decreases below the threshold value.
• the first diverter valve 210 swings into its first stable open position in which it supplies lubricant to the diverter branch 140.
• the diverter branch 140 having a lower hydraulic resistance than that of the main branch 120, the loss of The load in the lubrication system 100 decreases sharply at a substantially constant flow rate of lubricant. Only the gearbox lubrication enclosure 152, which is in the priority branch 150, is supplied with lubricant, via the bypass branch 140.
• the flow rate of lubricant circulating in the lubrication system 100 is lower in the second transient state 314 than in the first transient state 306 of operation of the turbomachine.
• the bypass device 200 operates with hysteresis, which is particularly favorable in the present case. It leads to supplying the priority branch 150 with lubricant for longer when starting the turbomachine 1, which guarantees a reliable supply of lubricant to the lubrication enclosure of the reducer 152 despite any fluctuations in the lubrication system.
• the turbomachine 1 is in a landing and stopping phase 316, in which the speed of the turbomachine is low.
• the flow rate and the pressure of lubricant in the lubrication system 100 decrease further and they are insufficient to supply the secondary branch 160.
• the first bypass valve 210 is in the first open position. Only the gearbox lubrication enclosure 152, which is in the priority branch 150, is supplied with lubricant, via the bypass branch 140.
• FIG. 4 represents a lubrication system 100 according to a second embodiment of the invention.
• the lubrication system 100 according to the second embodiment differs from that according to the first embodiment mainly by the structure of the priority branch 150 and by the structure of the secondary branch 160. Only the differences between the lubrication system 100 according to the second embodiment with respect to the lubrication system 100 according to the first embodiment are described below.
• the accessory drive box lubrication enclosure 170 is part of the priority leg 150 in the second embodiment, instead of being in the secondary leg 160.
• accessories 170 is arranged in parallel with the lubrication enclosure of the reducer 152.
• the priority branch 150 comprises a second non-return device 133 upstream of the lubrication enclosure of the accessory drive unit 170. This second device check valve 133 includes a check valve. It is configured to prevent the circulation of lubricant from the lubrication chamber of the accessory box 170 to the main branch 120.
• the secondary branch 160 comprises the fourth heat exchanger (not shown) and the three bearing lubrication chambers 162, 164, 166 which are each arranged in parallel to each other.
• the hydraulic resistances of the main branch 120 are represented schematically by a block 125 of heat exchanger and lubricant distribution.
• the first non-return device 130 of the main branch is nevertheless represented. It prevents the circulation of lubricant from the lubrication enclosure of the reducer 152 towards the main branch 120.
• Figures 5A, 5b, 5C, 5D represent a lubrication system 100 according to a third embodiment of the invention.
• the lubrication system 100 according to the third embodiment differs from that according to the first embodiment mainly by the structure of the bypass device 200. Only the differences between the lubrication system 100 according to the third embodiment with respect to the system lubrication 100 according to the first embodiment are described below.
• the bypass device 200 of the lubrication system 100 comprises the first bypass valve 210 and a second bypass valve 220.
• Each of the first diverter valve 210 and the second diverter valve 220 is identical in structure to that of the first diverter valve 210 of the lubrication system 100 according to the first embodiment, which has been described with reference to FIGS. 6A and 6b.
• the operation of each of the first valve of bypass 210 and of the second bypass valve 220 during a flight of the turbine engine is similar to that which has been described with reference to FIG. 7.
• the method of lubrication 300 of the turbine engine 1 during its flight is similar to that which has been described with reference to Figure 8.
• Each of the first diverter valve 210 and the second diverter valve 220 is bistable with a first stable open position and a second stable open position.
• Each of the first diverter valve 210 and of the second diverter valve 220 is in its first stable open position when the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is lower than the threshold value, for supply lubricant to the main branch 120.
• the shutter 202 of the first diverter valve 210 When the first diverter valve 210 is in its first stable open position, the shutter 202 of the first diverter valve 210 fluidically connects the inlet 211 of the first diverter valve to the first diverter outlet 213 of the first diverter valve. The shutter 202 of the first diverter valve 210 closes the second lubrication outlet 215 of the first diverter valve 210.
• the shutter 202 of the second diverter valve 220 When the second diverter valve 220 is in its first stable open position, the shutter 202 of the second diverter valve 220 fluidically connects the inlet 221 of the second diverter valve 220 to the first diverter outlet 223 of the second diverter valve. The shutter 202 of the second diverter valve 220 closes the second lubrication outlet 225 of the second diverter valve 220.
• Each of the first diverter valve 210 and of the second diverter valve 220 is in its second stable open position when the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is strictly greater than the threshold value, to supply lubricant to branch branch 140.
• the shutter 202 of the first diverter valve 210 When the first diverter valve 210 is in its second stable open position, the shutter 202 of the first diverter valve 210 fluidically connects the inlet 211 of the first diverter valve to the second bypass outlet 215 of the first bypass valve. The shutter 202 of the first diverter valve 210 closes the first lubrication outlet 213 of the first diverter valve 210.
• the shutter 202 of the second diverter valve 220 When the second diverter valve 220 is in its second stable open position, the shutter 202 of the second diverter valve 220 fluidically connects the inlet 221 of the second diverter valve 220 to the second diverter outlet 225 of the second diverter valve. The shutter 202 of the second diverter valve 220 closes the first lubrication outlet 223 of the second diverter valve 220.
• the first outlet 213 of the first bypass valve 210 is fluidly connected to the lubricant inlet 221 of the second bypass valve 220, by a first bypass conduit 143.
• the second outlet 215 of the first diverter valve 210 is fluidically connected to the main conduit 123, to supply lubricant directly to the main branch 120 when the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is strictly greater than the threshold value.
• the first outlet 223 of the second diverter valve 220 is fluidically connected to the diverter pipe 141 to exclusively supply the priority branch 150, to the detriment of the secondary branch 160, by the diverter branch 140.
• the second diverter valve 220 is fluidly connected in series to the first bypass valve 210 to supply the bypass branch 140 with lubricant when the pressure value of the lubricant is lower than the threshold value.
• the second outlet 225 of the second diverter valve 220 is fluidically connected to the main conduit 123 to supply lubricant to the main branch 120, in the event of failure of the first diverter valve 210.
• the second outlet 225 of the second diverter valve is in particular connected to the main branch 120 upstream of the first heat exchanger 121 of the main branch
• FIG. 5A the hydraulic resistances of the main branch 120 are represented schematically by a block 125 of heat exchanger and lubricant distribution.
• the first non-return device 130 of the main branch is nevertheless represented. It prevents the circulation of lubricant from the lubrication enclosure of the reducer 152 towards the main branch 120.
• the fourth heat exchanger 168 is not shown in this figure.
• each of the first diverter valve 210 and the second diverter valve 220 is operating normally.
• the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is lower than the threshold value.
• the turbomachine 1 is for example in a start-up phase.
• the pressure supplied by the pump assembly 112 is insufficient to supply the main branch 120.
• Each of the first diverter valve 210 and of the second diverter valve 220 is in the first open position and it exclusively feeds the main branch. diversion 140 with lubricant, through the first lubricant outlet 213 of the first diversion valve 210 and through the first lubricant outlet 223 of the second diversion valve 220.
• the secondary branch 160 is not supplied with lubricant, from due to the absence of circulation of lubricant in the main branch 120.
• the lubricant leaving the bypass branch 140 supplies the priority branch 150 in the direction of the lubrication enclosure of the reducer 152.
• the reducer 152 is sufficiently cooled and lubricated despite the low flow rate and low pressure of lubricant in the lubrication system 100.
• each of the first diverter valve 210 and the second diverter valve 220 is operating normally.
• the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is greater than the threshold value.
• the turbomachine 1 is for example in cruising speed.
• the pressure supplied by the pump assembly 112 is sufficient to supply the main branch 120.
• the first diverter valve 210 is in the second open position and it exclusively supplies the main branch 120 with lubricant, through the second outlet 215 of lubricant.
• the inlet 221 of the second bypass valve 220 is not supplied with lubricant.
• the lubricant is cooled in the heat exchangers 121, 122, 124 of the main branch 120.
• the priority branch 150 and the secondary branch 160 are each supplied with lubricant, by the main branch 120.
• the lubricant that circulates in the secondary leg 160 is cooled by the fourth heat exchanger 168.
• Each of the bearing lubrication enclosures 162, 164, 166 and the enclosure of the accessory drive box 170 are supplied with lubricant.
• the lubricant leaving the main branch 120 feeds the priority branch 150 in the direction of the lubrication enclosure of the reducer 152.
• the reducer 152 is sufficiently cooled and lubricated despite the pressure drop in the secondary branch 160 and the flow of lubricant in the secondary branch 160.
• the first diverter valve 210 is faulty and it is blocked in its first stable open position.
• the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is greater than the threshold value.
• the turbomachine 1 is for example in cruising speed.
• the pressure supplied by the pump assembly 112 is sufficient to supply the main branch 120.
• the failure of the first bypass valve 210 would be likely to lead to the absence of lubrication of the secondary branch 160, in particular of each of the enclosures of lubrication 162, 164, 166 of the bearing and of the accessory drive unit 170. This could result in damage to the bearings of the turbomachine and/or of the accessory drive unit 170.
• the first diverter valve 210 is in the first open position and it supplies lubricant to the inlet 221 of the second diverter valve 220.
• the second diverter valve 220 is operating normally and it is in its second stable open position .
• the inlet 221 of the second diverter valve 220 is fluidically connected to the second outlet 225 of the second diverter valve 220 and to the main branch 120.
• the priority branch 150 and the secondary branch 160 are each supplied with lubricant, by the main branch 120.
• the second diverter valve 220 is faulty and is stuck in its first stable position opening.
• the pressure of the lubricant at the inlet 211 of the first diverter valve 210 is greater than the threshold value.
• the turbomachine 1 is for example in cruising speed.
• the pressure supplied by the pump assembly 112 is sufficient to supply the main branch 120.
• the failure of the second bypass valve 220 could lead to the absence of lubrication of the secondary branch 160, in particular of each of the lubrication enclosures 162 , 164, 166 bearing and the accessory drive unit 170. This could result in damage to the bearings of the turbomachine and/or the accessory drive unit 170.
• the first diverter valve 210 is in the second open position and it exclusively supplies the main branch 120 with lubricant, through the second outlet 215 of lubricant.
• the inlet 221 of the second bypass valve 220 is not supplied with lubricant.
• the second bypass valve 220 therefore cannot abnormally direct the lubricant through the bypass leg 140.
• the lubricant is cooled in the heat exchangers 121, 122, 124 of the main leg 120.
• the priority leg 150 and the secondary 160 are each supplied with lubricant, by the main branch 120.
• the reducer 152 is supplied with lubricant in a privileged manner, via the bypass branch 140, with respect to heat exchangers 121, 122, 124 and to lubrication chambers 162, 164, 166 of bearings when the flow of lubricant and the pressure of the lubricant are too low to supply lubricant to the entire lubrication system 100.
• the reducer 152 is supplied with lubricant by the bypass branch 140 when the turbomachine is operating at low speed. In particular, it is supplied with lubricant by the main branch 120 when the flow rate and the pressure of the lubricant are sufficient to supply the entire lubrication system 100, in particular when the turbomachine 1 is operating at high speed.
• the turbomachine 1 is a turbomachine with a doublet of unducted counter-rotating propellers.
• Such turbomachines 1 are also known in English under the name “Open Rotor”.
• the reducer 152 is for example configured to drive the propellers in rotation, in particular by connecting them to the low-pressure body of the turbomachine.
• the turbomachine 1 is a turboprop engine which comprises a propeller at the inlet of the turbomachine.
• each of the hydraulic resistances of the lubrication system may vary.
• each of these hydraulic resistors can comprise a heat exchanger, a filter, a cut-off valve and/or a flow meter.
• the structure of the bypass device 200 may vary, in particular as long as the bypass device 200 allows lubricant to circulate in the main branch 120 at least for certain operating speeds of the turbomachine 1.
• bypass device 200 is mechanically, electrically and/or pneumatically controlled.
• the bypass device 200 can be controlled electrically, for example by a digital regulation system of the turbomachine.
• a digital control system is also known as "FADEC”.
• the bypass device 200 may comprise a first bypass valve 210 and a second bypass valve 220 which are arranged fluidically in parallel. Nevertheless, the arrangement of the bypass device 200 of the lubrication system 100 according to the third embodiment remains preferred to such a variant embodiment, since it promotes a better distribution of the lubricant in the event of failure of a valve among the first diverter valve 210 and the second diverter valve 220.
• the structure of the first diverter valve 210 and/or that of the second diverter valve 220 can vary.
• the elastic biasing means 204 of at least one diverter valve 210, 220 comprises a tension spring which is located in the second chamber 209 and which biases the shutter 202 towards the first opening position of this valve.
• at least the first diverter valve 210 comprises at least one stable open position between the first stable open position and the second stable open position, in which the shutter 202 of the first diverter valve 210 partially feeds the main branch 120 and partially the bypass branch 140.
• the first bypass valve 210 may comprise a plurality of stable opening positions between the between the first stable opening position and the second stable opening position, for example a continuity of stable opening positions or a sequence of discrete stable opening positions.
• first diverter valve 210 and/or the second diverter valve 220 can be another type of distributor than a three-way, two-position hydraulic distributor.
• the pressurization inlet 215 of the first bypass valve 210 can open into the first chamber 207 of the first bypass valve 210 and/or the pressurization inlet 215 of the second bypass valve 220 can open into the first chamber 207 of the second diverter valve 220.
• the shutter 202 of the first bypass valve 210 comprises a valve and/or the shutter 202 of the second bypass valve 220 comprises a valve.
• the structure of the second diverter valve 220 is for example different from that of the first diverter valve 210.
• the bypass device 200 includes a second bypass valve 220 in addition to the first bypass valve 210, and the bypass device 200 has a structure similar, if not identical, to that of the bypass device. of the lubrication system according to the third embodiment.
• the main branch 120 and the bypass branch 140 are each of variable structure.
• the priority branch 150 and the secondary branch 160 are each of variable structure.
• the arrangement, the number and the nature of the hydraulic resistors in the lubrication system 100 can vary.
• the number of heat exchangers 121, 122, 124 of the branch can vary.
• the main branch 120 can include at least one filter.
• Bypass branch 140 may include at least one heat exchanger.
• the priority branch 150 may have no cut-off valve 132 upstream of the reducer 152 or else have no non-return valve 130, in particular when the cut-off valve 132 also serves as a non-return device.
• the lubrication system 100 may comprise a single non-return valve 130 which is located between the outlet of the main branch 120 and the inlet of the priority branch 150.
• the priority branch 150 may include a lubricant distributor, typically a hydraulic distributor, to distribute the flow of lubricant between the reducer 152 and the accessory drive unit 170.
• a lubricant distributor typically a hydraulic distributor
• the number of lubrication enclosures 162, 164, 166 of the secondary branch 160 can vary.
• the lubrication system 100 includes a shutter position monitoring device 202 of each bypass valve which is configured to monitor the position of the shutter 202.
• This monitoring device is for example configured to determine a lubricant pressure in the main branch 120, for example by means of a first pressure sensor, and to determine a lubricant pressure in the bypass branch 140, for example by means of a second pressure sensor.
• the monitoring device can monitor the position of the shutter 202 by comparing the lubricant pressure value in the main branch 120 and the lubricant pressure value in the bypass branch 140.

Landscapes

• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• General Details Of Gearings (AREA)

Applications Claiming Priority (2)

Publications (1)

Family

ID=74045758

Family Applications (1)

Country Status (5)

Families Citing this family (1)

Family Cites Families (3)

• 2020
  • 2020-10-15 FR FR2010565A patent/FR3115318B1/fr active Active
• 2021
  • 2021-10-12 US US18/249,148 patent/US20230407764A1/en active Pending
  • 2021-10-12 EP EP21807169.4A patent/EP4229279A1/fr active Pending
  • 2021-10-12 WO PCT/FR2021/051768 patent/WO2022079382A1/fr unknown
  • 2021-10-12 CN CN202180074217.5A patent/CN116368291A/zh active Pending

Also Published As

Similar Documents

Legal Events