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
  • 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
  • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
• • 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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/02—Blade-carrying members, e.g. rotors
  • F01D5/08—Heating, heat-insulating or cooling means
• • 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
• • 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
  • F01D25/08—Cooling; Heating; Heat-insulation
  • F01D25/12—Cooling
• • 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
  • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
  • F01D5/02—Blade-carrying members, e.g. rotors
  • F01D5/08—Heating, heat-insulating or cooling means
  • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
  • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/12—Cooling of plants
  • F02C7/16—Cooling of plants characterised by cooling medium
  • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
  • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
  • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
• • 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
• • 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
  • F05D2240/00—Components
  • F05D2240/10—Stators
  • F05D2240/12—Fluid guiding means, e.g. vanes
• • 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
  • F05D2240/00—Components
  • F05D2240/20—Rotors
• • 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
• • 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
  • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
• • 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
  • F05D2270/3015—Pressure differential pressure
• • 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

• TITLE Double-flow turbine comprising a device for regulating the flow of cooling fluid
• the present invention relates to the field of turbomachines, and in particular the cooling of a turbine rotor of a turbomachine.
• the present invention relates to the regulation of the flow of a fluid through a rotor element of said turbomachine.
• turbomachines of the bypass turbojet type comprising an inlet sleeve receiving the air which is drawn in by a low-pressure compressor to then be divided into a central primary flow and a secondary flow surrounding the primary flow.
• the low-pressure compressor is similar to a blower in that part of the air flow that it compresses supplies a secondary flow.
• the secondary flow circulates in a space called the secondary flow which is delimited externally by a secondary flow casing also called the motor hull, and internally by an envelope surrounding the primary flow.
• the primary flow circulates in a space called the primary vein bounded on the outside by the casing and inside by a succession of fixed and rotating internal elements.
• the fixed internals include rectifier and valve platforms, and inner case ferrules, and the rotating internals include rotor bladed wheel platforms.
• the primary flow circulates between an internal casing and an external casing of a high pressure compressor to be compressed in this high pressure compressor before being burned in a combustion chamber. It is then expanded in a high pressure turbine to drive the high pressure compressor, then in a low pressure turbine to drive the low pressure compressor, before being expelled backwards by generating a thrust.
• the outer casing delimiting the primary stream is thus formed by a series of casings comprising a high pressure compressor casing, a casing at the level of the combustion chamber and a high pressure turbine casing, as well as by an outer casing of the casing. 'exhaust.
• Each turbine and each compressor is formed of stages each comprising a series of rotating blades regularly spaced around a longitudinal central axis of the engine, possibly preceded by a distributor in the case of a turbine or possibly followed by a rectifier. in the case of a compressor.
• Distributors and rectifiers consist of a series of fixed vanes.
• the rear part of such an engine comprises, downstream of the low pressure turbine, an exhaust casing which carries a bearing supporting a rear end of the engine rotor.
• This exhaust casing comprises an internal ferrule and an external ferrule and radial arms joining the ferrules to one another, radially crossing the primary stream.
• Aircraft turbomachines are also known, of the double-flow and double-body turbojet type.
• the turbomachine comprises, from upstream to downstream in the direction of flow of the gas flows in the turbomachine, a fan, coupled to a gas turbine engine comprising a low pressure compressor, a high pressure compressor, a annular combustion chamber, a high pressure turbine and a low pressure turbine.
• the rotors of the high pressure compressor and the high pressure turbine are connected by a high pressure (HP) shaft and form with it a high pressure body.
• the rotors of the low pressure compressor and the low pressure turbine are connected by a low pressure (LP) shaft and form with it a low pressure body.
• the HP and LP shafts extend along a longitudinal axis of the turbomachine.
• the fan has blades which are connected to a fan shaft. It is advantageous to make the fan turn at a speed of rotation lower than that of the LP shaft, in particular when the latter is very large, in order to better adapt it aerodynamically.
• the fan shaft is connected in rotation to the LP shaft by means of a reduction gear, for example of the epicyclic gear type.
• the fan shaft can be directly linked to the LP shaft.
• the turbomachinery also includes a fan housing that extends around the blades which is carried by aerodynamic arms, and which defines an inlet stream of air flow. Some of this air enters an internal annular flow vein of a primary flow and the other part feeds an external annular flow vein of a secondary flow.
• the flow passes through the LP and HP compressors, the combustion chamber, and the HP and LP turbines.
• the external duct envelops the casings of the compressors and the turbines and joins the internal duct at the level of a nozzle of the turbomachine.
• it is known to increase the size of the turbomachine which has the drawback of increasing the mass and the size of the turbomachine.
• the various elements of the turbine, and in particular the rotor subjected to high temperatures are traversed by a cooling fluid, such as air from the turbine. ventilation.
• a cooling fluid such as air from the turbine. ventilation.
• the blades of the high pressure turbine are ventilated in order to be able to accept very high temperatures.
• cooling or ventilation air must be used at a pressure higher than that of the primary stream in the high pressure turbine. This air is generally taken from the outlet of the high pressure compressor and will not enter the combustion chamber, which has the effect of reducing the quantity of air available for the combustion chamber of the turbomachine, and thus of reducing the efficiency. thermal of the turbomachine.
• some include an active system for controlling the ventilation flow of a high pressure turbine configured to draw the air flow required for ventilation according to the needs of the turbomachine.
• a system generally comprises a plurality of open tubes located in front of the outlet of the high pressure compressor and the opening of which is controlled by means of one or more actuators in order to take air at the outlet of the high pressure compressor for. inject it into the high pressure turbine disc.
• FR 2 943 094 discloses a closure element configured to deform under the action of a centrifugal force induced by the rotation of the rotor.
• the shutter member is angularly movable about a transverse axis perpendicular to the axis of rotation of the rotor. In the rest position, the shutter element is noticeably flared from upstream to downstream.
• the shutter member deforms under the force of downstream upstream so as to block the passage of cooling air flow in the turbomachine.
• Such a closure element does not allow the increase in the temperature. flow of cooling air when increasing the rotational speed of the rotor, which does not meet the cooling needs of the turbomachine.
• the object of the present invention is therefore to alleviate the drawbacks of the aforementioned systems and to provide a device for regulating the flow of air circulating in a turbomachine rotor as a function of the air requirements necessary to cool at least one element of the turbomachine and this , without adding actuators and control system, in order to optimize the overall performance of the turbomachine.
• the subject of the invention is therefore a turbomachine, with a longitudinal axis comprising a primary stream in which a primary flow circulates at a primary pressure and a secondary stream radially surrounding the primary stream and in which a secondary flow circulates at a secondary pressure, said primary duct comprising at least one compressor configured to compress the primary flow, a turbine driving said compressor in rotation and a combustion chamber intended to receive at the inlet the flow of primary air compressed by the compressor.
• Said turbomachine further comprises a cooling circuit extending between the compressor and the turbine and in which circulates a flow of cooling air taken from the outlet of the compressor and having the primary pressure as pressure.
• the cooling circuit comprises a device for regulating the air flow arranged upstream of the turbine and comprising at least one valve movable between an open position and a closed position as a function of the pressure difference between the pressure in the primary duct located between the compressor and the combustion chamber and the pressure in the secondary stream.
• valve is movable between a position open and closed position as a function of the pressure difference between the pressure of the cooling air flow circulating in the cooling circuit and the pressure in the secondary stream.
• the pressure is almost homogeneous up to the nozzle. It is thus possible to approximate the pressure to a secondary stream pressure, in particular the pressure located between the downstream side of the fan rectifier upstream of the ejection nozzle.
• the air flow control device thus makes it possible to passively regulate the flow of air circulating in the turbine rotor elements by modulating the air bleed according to the cooling needs of the turbomachine.
• the turbomachine can be a double-flow turbojet or a double-flow and double-body turbojet comprising a fan.
• the air flow regulator may be intended to regulate the air flow in a blade of a high pressure or low pressure turbine.
• the device for regulating the air flow is configured to ensure a minimum air flow when the pressure difference between the primary pressure and the secondary pressure is less than a threshold value and to ensure a flow of flow of maximum air when the pressure difference between the primary pressure and the secondary pressure is greater than or equal to the threshold value.
• the threshold value from which the pressure difference increases the air flow can be between 10 and 40 bars.
• this threshold value depends on the general parameters of the turbomachine and particularly on its maximum compression ratio, acronym “OPR” and its compression ratio of the secondary flow, acronym “FPR”.
• OCR maximum compression ratio
• FPR compression ratio of the secondary flow
• the threshold value may be greater than 30, for example 40 bars.
• the threshold value may be less than 20 bars, for example equal to 10 bars.
• the device for regulating the air flow may comprise an annular cover for calibrating the ventilation flow rate mounted in the cooling circuit at the downstream end of said circuit upstream of the turbine rotor and integral with the stator part of the turbomachine, by example the casing of the combustion chamber, the valve being mounted in said cover.
• the cover comprises at least one longitudinal passage opening opening into the cooling circuit, the valve being mounted downstream of said passage opening.
• the passage orifice is, for example, made in an upstream surface of the cover.
• the valve comprises a cylindrical housing, an actuator movable in translation in said housing along an axis parallel to the axis of rotation of the turbine rotor, between the closed position of the valve in which the actuator closes the passage orifice and the open position of the valve in which the cylinder allows the passage of an air flow through the passage orifice.
• Said housing is connected directly or indirectly to a secondary pressure supply tube opening into the secondary vein.
• the jack includes an upstream end having a pointed shape upstream.
• a pointed shape upstream.
• the end of the secondary pressure supply tube opening into the secondary vein is, for example, oriented downstream in order to capture only the static pressure in the secondary vein and not the impurities which may be present in said secondary vein .
• the valve may include sealing elements mounted between the external cylindrical surface of the cylinder and the internal cylindrical surface of the housing.
• the sealing elements can be, for example, O-rings or U-type hydraulic seals or any type of element preventing the passage of fluid to the secondary stream.
• the upstream end of the cylinder includes an axial stop against the end of the housing in the open position of the valve and against the upstream surface of the cover in the closed position of the valve.
• the jack is held in the housing.
• the axial stop has the shape of an annular flange.
• any other shape could be provided forming an axial stop of the jack.
• the valve comprises an elastic member configured to prestress the cylinder in the closed position of the valve, such as for example a spring, housed in said housing and cooperating with a downstream end of the cylinder.
• Said elastic member is dimensioned to prevent the translational movement of the cylinder in the closed position of the valve when the pressure difference between the pressure in the primary stream and the secondary pressure in the secondary stream is below the threshold value, for example when the engine is under little stress.
• the prestressing force of the elastic member is countered and the jack is moved in translation towards the upstream in the open position of the valve.
• elastic member any elastic member, by virtue of the material used and / or its dimensions, capable of deforming elastically, in a reversible manner, under the action of a stress exerted by the pressure difference between the pressure in the primary vein and the secondary pressure in the secondary vein and to return to its initial position after stopping said stress.
• the cover may include an annular chamber into which the secondary pressure supply tube opens.
• the flow control device comprises in besides a secondary pressure supply duct connected to the annular distribution chamber and to the cylindrical housing of the valve, said secondary pressure supply duct being configured to convey the secondary flow into the cylindrical housing of the valve.
• the cover may also include at least one channel extending between the passage orifice and the turbine rotor to allow the passage of an air flow coming from the passage orifice towards said turbine rotor.
• the cover and in particular its upstream surface, comprises a plurality of longitudinal passage orifices, for example, cîrconferentially regularly distributed, opening into the cooling circuit.
• the through holes can be the same sizes or alternatively different sizes to further regulate the air flow.
• the device for regulating the air flow comprises a plurality of valves each configured to be actuated as a function of the pressure difference between the pressure in the primary stream and the pressure in the secondary stream, each valve being mounted in the valve. cover downstream of an associated passage orifice.
• the number of valves may be less than the number of through holes.
• half of the hood passage orifices is associated with a valve.
• the other half of the hood passage openings is therefore permanently open.
• the elastic members of the valves can be identical to each other.
• valve can be non-progressive opening and closing or opening and closing and urep ro gr essive.
• the pressure supply conduit allows the secondary flow to be routed into all of the cylindrical housings of the valves.
• the turbine rotor comprises a turbine disk whose axis of symmetry is coaxial with the axis of rotation, at least one rotor blade mounted radially on the circumference of said turbine disk and a sealing disk having the shape general of an annular part whose axis of symmetry is coaxial with the axis of rotation of the rotor, arranged upstream and integral in rotation with said rotor disc.
• the rotor vanes extend radially outward.
• the cooling circuit opens into a cooling volume formed between the sealing disc and the upstream surface of the turbine disc, the sealing disc comprising at least one ventilation opening opening into the channel.
• the sealing disc comprises a plurality of angularly and regularly distributed ventilation openings.
• the ventilation openings allow the passage of a flow of air taken, for example, by an air injector into the cooling volume.
• the cooling air flow is then distributed to the vanes mounted on the turbine disk.
• the ventilation openings are configured to allow sufficient air flow to cool the turbine blades when the turbomachine is operating at full speed, in particular during the takeoff phases of the aircraft and when the temperature of the gases is very high.
• the air injector makes it possible to drive the cooling air flow in rotation so that said air flow circulates more easily from the stator mark to the rotor mark.
• the air flow from cooling flows along a substantially axial axis at the level of the upstream face of the cover and in the passage orifices.
• this air flow must circulate through the ventilation openings made in a room having a high speed of rotation.
• the air injector which is a part fixed to the stator between said passage and ventilation openings makes it possible, by virtue of the fins, to force the axial air flow to orient itself more naturally towards the rotating ventilation openings.
• FIG. 1 illustrates schematically a half. axial section of a structure of an example of a turbomaehine comprising a device for regulating the air flow according to a first embodiment of the invention
• FIG 2 [Fig 3] very schematically illustrate the upper half of a part of the high pressure body of the turbomaehine of Figure 1 comprising a device for regulating the air flow according to an embodiment of the invention comprising a valve in a closed position and an open position respectively;
• FIG 4 illustrates in detail the air flow control device of Figures 2 and 3;
• FIG 6 are sectional views of the valve in the closed position and the open position, respectively;
• FIG 7 illustrates the downstream face of the air flow regulating device of Figures 2 and 3;
• FIG 8 illustrates very schematically the upper half of a part of the low pressure body of the turbomaehine of Figure 1 in which the device for regulating the air flow according to the invention could be integrated;
• FIG 9 schematically illustrates an axial half-section of a structure of another example of a turbomachine comprising the device for regulating the air flow.
• upstream and downstream are defined with respect to the direction of air circulation in the turbomachine.
• FIG. I is shown very schematically an axial half-section of a turbomachine 10, of longitudinal general axis X-X ', for example of the bypass turbojet type,
• the turbomachine comprises, from upstream to downstream in the direction of flow of the air flow F, an inlet sleeve 11 receiving air, a low pressure compressor 12 (CQPB) configured to suck the air flow F and divide it into a central primary flow F1 at a first variable pressure and a secondary flow F2 at a secondary pressure radially surrounding said primary flow F1.
• the low-pressure compressor 12 can be likened to a fan insofar as part of the air flow that it compresses makes it possible to supply the secondary flow.
• the turbomachine further comprises a high pressure compressor 13 configured to receive the primary air flow Fl from the low pressure compressor 12, an annular combustion chamber 14, a high pressure turbine 15 and a low pressure turbine 16.
• the rotors of the high compressor pressure 13 and the high pressure turbine 15 are connected by a high pressure shaft 17.
• the rotors of the low pressure compressor 12 and of the low pressure turbine 16 are connected by a low pressure shaft 18.
• the secondary stream F2 circulates in a space 19 called the secondary stream delimited on the outside by a casing 19a of the secondary stream or motor shell and internally by a casing 19b radially surrounding the primary stream Fl.
• the primary flow Fl circulates in a space 20 called the primary vein delimited on the outside by the envelope 19b and on the inside. by a succession of fixed and rotating elements.
• the primary flow F1 circulates between an internal casing 21 located downstream of the low pressure compressor 12 and an exhaust casing 22 downstream of the low pressure turbine 16.
• the primary and secondary streams 19, 20 meet downstream of the casing. exhaust 22.
• the turbomachine 10 comprises a first cooling circuit 23 of the high pressure turbine 15 taking air from the high pressure compressor 13 and a second cooling circuit 24 of the low pressure turbine 16 drawing air from the high pressure compressor 13.
• turbomachine could include one or the other of said cooling ducts, or even both.
• the low-pressure compressor 12 or the fan in the case of a double-flow and double-body turbomachine creates a pressure PS called "secondary pressure" in the secondary stream 19.
• FIG. 2 and 3 is shown very schematically an upper half of a part of the high pressure body of a turbomachine 10, for example the turbomachine of Figure 1. It will be noted that the regulating device could also be integrated into the low pressure body of a turbomachine, as illustrated in FIG. 8.
• the high pressure body of the turbomachine of longitudinal general axis X-X ', comprises a casing 19b forming the casing of the secondary stream 19 and enclosing the high pressure compressor 13 of which only the compressor diffuser has been shown, the combustion chamber 14 receiving as input the hot air compressed by said compressor 13, and the high pressure turbine.
• the high pressure turbine 15 comprises a turbine rotor 25, with an axis of rotation X-X ', comprising a turbine disk 25a whose axis of symmetry is coaxial with the axis of rotation X-X'.
• the turbine disk 25a comprises an axial bore (not referenced) from which extends the drive shaft 17 connected to the compressor 13 to drive it in rotation in a primary stream 20.
• the turbine disk 25a further comprises a plurality of rotor blades 25b mounted radially on the circumference of said turbine disk 25a.
• the rotor vanes 25b extend radially outward.
• the turbine 15 further comprises a sealing disc 26 configured to seal between the rotor 25 and the stator upstream of the turbine 15.
• the sealing disc 26 is commonly referred to as a "labyrinth disc”.
• the sealing disc 26 takes the general form of an annular part whose axis of symmetry is coaxial with the axis of rotation X-X ’.
• the sealing disc 26 is mounted upstream of the turbine disc 25a and rotatably secured to the latter.
• the cooling circuit 23 of the turbomachine 10 extends between the high pressure compressor 13 and the high pressure turbine 15.
• the cooling circuit 13 opens into a cooling volume Y formed between the downstream surface of the sealing disc 26 and the upstream surface of the turbine disc 25a.
• an air flow is taken upstream of the combustion chamber 14 at the outlet of the compressor 13 to be introduced into said cooling volume V.
• the sealing disc 26 comprises a plurality of ventilation openings 26a opening out into the thickness of said sealing disc 26.
• the ventilation openings 26a are angularly and regularly distributed over the upstream surface of said sealing disc. 26.
• the ventilation openings 26a allow the passage of a flow of air F1 taken, for example, by an air injector (not shown) in the cooling volume V.
• the cooling air flow is then distributed to the vanes 25b mounted on the turbine disk 25a,
• the ventilation openings 26a are configured to allow sufficient air flow to cool the vanes 25b when the turbomachine is operating at full speed. , in particular during the take-off phases of the aircraft and when the gas temperature is very high.
• the cooling circuit 23 comprises a device for regulating the air flow rate 30.
• the device for regulating the air flow rate 30 comprises an annular cover 31 for calibrating the ventilation flow rate mounted in the cooling circuit 23 at the downstream end of said circuit directly upstream of the disc turbine 25a.
• the cover 31 is integral with the stator, in particular with the casing 14a of the combustion chamber 14.
• the cover 31 is delimited by an upstream radial surface 32, an internal annular surface 33 connected upstream to the upstream radial surface 32 and supporting downstream an internal seal with the sealing disc 26, an intermediate annular surface 34 connected upstream to the upstream radial surface 32 and supporting downstream an external seal with the sealing disc 26 and an external annular surface 35 connected upstream to the upstream radial surface 32 and connected downstream to the stator, in particular to the casing 14a of the combustion chamber 14.
• the upstream radial surface 32 comprises a plurality of longitudinal passage orifices 32a emerging into the thickness of the upstream surface 32.
• the passage orifices 32a may be circumferentially regularly distributed over the upstream surface 32 of the cover 31.
• the cover 31 further comprises a channel 36 located axially between the upstream surface 32 and the downstream end of the sealing disc 26 and radially between the inner annular surface 33 and the intermediate annular surface 34 of the cover 31.
• the channel 36 allows the passage of the air flow F1 coming from the passage openings 32a towards the sealing disc 26 and thus into the cooling volume V through the ventilation openings 26a of said disc 26.
• the device for regulating the air flow 30 further comprises a tube 38 for supplying secondary pressure PS comprising an end 38a opening into the secondary stream 19 and an end 38b connected to the cover 31 and opening in particular into an annular chamber 40 mounted. in said cover 32.
• the end 38a opening into the secondary stream 19 is oriented downstream so as to capture only the static pressure in the secondary stream 19 and not the impurities that may be present.
• the device for regulating the air flow rate 30 further comprises a plurality of valves 42 each configured to be actuated as a function of the pressure difference between the primary stream 20 and the secondary stream 19.
• Each valve 42 is mounted in the cover 31. in ava1 of an associated passage orifice 32a.
• half of the passage orifices 32a of the cover 31 is associated with a valve 42.
• the other half of the passage orifices 32a of the cover 31 is therefore permanently open.
• the latter case is particularly advantageous so as not to ventilate the turbine blades when the engine speed is at idle.
• Each valve 42 comprises a cylindrical housing 43, a cylinder 44 movable in translation in said housing 43 along an axis Xl-Xl 'parallel to the axis X-X' of rotation, between a closed position of the valve, visible in the figures 2 and 5 and an open position of the valve, visible in Figures 3 and 6, and a spring 46 housed in said housing 43.
• each valve 42 comprises an elastic member 46, such as for example a spring, configured to pre-stress the cylinder 44 in the closed position of the valve 42,
• the jack 44 comprises an upstream end 44a which opens into the associated passage orifice 32a and a downstream end 44b cooperating with the associated spring 46.
• the upstream end 44a has, in no way limiting, the shape of a point upstream. Such a shape has the advantage of allowing self-centering of the jack 44 in the associated passage orifice 32a.
• Each assembly of actuator 44 and its spring 46 is associated with a conduit 48 for supplying secondary pressure connected to the annular distribution chamber 40 and to the cylindrical housings 43 of each valve 42 in order to convey the secondary flow into all the cylindrical housings. valves 42.
• Each of the cylinders 44 is held in the closed position of the valve 42, visible in Figures 2 and 5, by an associated spring 46. In the closed position of the valve 42, the cylinders 44 block the passage of ventilation air through the 'passage orifice 32a associated in the channel 36 and thus in the cooling volume V.
• the springs 46 are dimensioned to prevent the translational movement of the jack 44 upstream when the pressure difference DR between the pressure P3 in the primary stream and the pressure PS in the secondary stream is less than a first threshold value SI, for example when the turbomachine is idling.
• the pressure P3 is located between the high pressure compressor 13 and the combustion chamber 14.
• the threshold value S 1 above which the pressure difference makes it possible to increase the air flow rate may be between 10 and 40 bars.
• this threshold value depends on the general parameters of the turbomachine and particularly on its maximum compression ratio, acronym "OPR” and its secondary flow compression ratio, acronym "FPR".
• OPR maximum compression ratio
• FPR secondary flow compression ratio
• the threshold value may be greater than 30, for example 40 bars.
• the threshold value may be less than 20 bars, for example equal to 10 bars.
• the opening of the valves could be gradual in the case where the springs 46 are different between the valves in order to start opening a passage orifice 32a from of a first threshold value, then two passage orifices 32a starting from a second threshold value, greater than the first threshold value, and so on until the opening of all the valves starting from a final threshold value.
• These threshold values can be between 10 and 40 bars.
• the first threshold value may be equal to 30 bars
• the second threshold value may be equal to 35 bars.
• the through holes 32a are of identical size. As a variant, one could provide passage orifices 32a of different dimensions to regulate the air flow more finely.
• the springs 46 are identical to each other. Different springs could be provided for each valve and configured so that the valves are actuated in the open position one after the other as the pressure difference DR increases, thus allowing a gradual increase in the air flow of ventilation.
• the valve can be non-progressive opening and closing or progressive opening and closing.
• each valve 42 comprises sealing elements 49 between the external cylindrical surface (not referenced) of the jack 44 and the internal cylindrical surface (not referenced) housing 43. Sealing elements 49 may be, for example, O-rings or U-type hydraulic seals.
• the upstream end 44a of the cylinder comprises an annular flange 44c forming an axial stop against the end of the housing 43 in the open position of the valve 42 and against the upstream surface 32 of the cover 31 in closed position of the valve 42.
• the actuator 44 is held in the housing 43.
• any other shape could be provided forming an axial stop of the actuator 44.
• the device for regulating the air flow thus makes it possible to passively regulate the flow of air circulating in the rotor elements by modulating the air intake according to cooling needs.
• the turbomachine comprises a valve actuated between a closed position and an open position as a function of the pressure difference between the primary stream 20 and the secondary stream 19.
• the turbomachine 10 comprises a low pressure turbine stage 16 comprising a turbine rotor, with an axis of rotation X-X ', comprising a turbine disk 16a of generally annular shape, the axis of which of symmetry is coaxial with the axis of rotation X-X '.
• Turbine disc 16a comprises an axial bore (not referenced) from which extends a drive shaft 18 and a plurality of rotor blades 16b mounted radially around the circumference of said turbine disc 16a. The rotor blades 16b extend radially outward.
• the drive shaft 1 8 is intended to be connected to the rotor of a low pressure compressor 12 mounted upstream of the low pressure turbine rotor 16.
• the turbine stage further comprises a sealing disc 50 configured to seal between the rotor and the stator part, for example comprising the casing of the combustion chamber (not shown) upstream of the turbomachine.
• the sealing disc 50 is commonly referred to as a "labyrinth disc”.
• the sealing disc 50 is in the general form of an annular part whose axis of symmetry is coaxial with the axis of rotation X-X ’.
• the sealing disc 50 is mounted upstream of the turbine disc 16a and rotatably secured to the latter.
• the sealing disc 50 comprises a radially inner fixing part 50a connected upstream to an element (not referenced) of the turbine body 10 and downstream to the turbine disc 16a.
• the sealing disc 50 is also axially prestressed so that its radially outer edge 50b bears axially against an upstream surface of the rim of the turbine disc 16a and thus prevent the movement of the blades 16b.
• a cooling volume V is provided between the downstream surface of the sealing disc 50 and the upstream surface of the rotor turbine disc 16a.
• An air flow, illustrated by an arrow F1 in FIG. 8, is taken upstream from the high pressure compressor 13 to be introduced into said cooling volume V.
• the sealing disc 50 comprises a plurality of ventilation openings 50c opening into the thickness of said sealing disc 50.
• the ventilation openings 50c are angularly and regularly distributed over the upstream surface of said disc 50.
• the ventilation openings 50c are angularly and regularly distributed over the upstream surface of said disc 50.
• the ventilation openings 50c are angularly and regularly distributed.
• 50c ventilation openings allow the passage of an air flow taken from the high pressure compressor and conveyed by a cooling circuit 24 to the low pressure turbine casing. The cooling air flow is then distributed to the vanes 16b mounted on the rotor turbine disk 16a.
• the ventilation openings 50c are configured to allow sufficient air flow to cool the turbine blades 16b when the turbomachine is operating at full speed, in particular during the take-off phases of the aircraft and when the gas temperature is very high. .
• the turbomachine 10 comprises the device for regulating the air flow rate 30 illustrated in detail in FIGS. 2 to 7.
• the device for regulating the air flow rate 30 comprises an annular cover 31 for calibrating the ventilation flow rate mounted in the cooling circuit 24 at the downstream end of said circuit directly upstream of the turbine disk 16a.
• the cover 31 is integral with the stator.
• turbomachine structure and could be applied to a turbomachine of different structure, for example to a turbomachine 100 with double flow and double body comprising a fan, as illustrated. in figure 9.
• the turbomachine 100 comprises, from upstream to downstream in the direction of flow of the gas flows in the turbomachine, a fan 101, coupled to a gas turbine engine comprising a low pressure compressor 1 12, a high pressure compressor 113, an annular combustion chamber 114, a high pressure turbine 115 and a low pressure turbine 1 16.
• the rotors of the high pressure compressor and of the high pressure turbine are connected by a high pressure (HP) shaft 117 and form with it a high pressure body.
• the rotors of the low pressure compressor and of the low pressure turbine are connected by a low pressure shaft (LP) 1 18 and form with it a low pressure body.
• the HP and LP shafts extend along a longitudinal axis X-X 'of the turbomachine.
• the fan shaft is rotatably linked to the BP 11 8 shaft directly or indirectly.
• the turbomachine also includes a fan housing which extends around the blades which is carried by aerodynamic arms, and which defines an air inlet stream for the flows. Part of this air enters an internal annular flow stream of a primary flow 120 and the other part feeds an external annular flow stream of a secondary flow 119.
• the flow passes through the LP and HP compressors, the combustion chamber, and HP and LP turbines.
• the outer vein envelops the casings of compressors and turbines and joins the internal vein at the level of a nozzle of the turbomachine.
• the ventilation air flow can be regulated using only the outlet pressure of the high pressure compressor and the pressure in the secondary stream.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)
• Turbine Rotor Nozzle Sealing (AREA)

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• 2020
  • 2020-03-24 FR FR2002873A patent/FR3108655B1/fr active Active
• 2021
  • 2021-03-18 WO PCT/FR2021/050443 patent/WO2021191528A1/fr unknown
  • 2021-03-18 US US17/907,141 patent/US11873729B2/en active Active
  • 2021-03-18 EP EP21718940.6A patent/EP4127406A1/de active Pending

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