Classifications

• • 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
  • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
  • F02C9/16—Control of working fluid flow
  • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
  • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
  • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
  • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
  • B64C11/02—Hub construction
  • B64C11/04—Blade mountings
  • B64C11/06—Blade mountings for variable-pitch blades
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
  • B64C11/30—Blade pitch-changing mechanisms
  • B64C11/38—Blade pitch-changing mechanisms fluid, e.g. hydraulic
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/64—Reversing fan flow
  • F02K1/66—Reversing fan flow using reversing fan blades
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
  • F02K1/54—Nozzles having means for reversing jet thrust
  • F02K1/76—Control or regulation of thrust reversers
  • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
• • 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
  • F05D2220/36—Application in turbines specially adapted for the fan of turbofan 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
  • F05D2260/30—Retaining components in desired mutual position
• • 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
  • F05D2260/50—Kinematic linkage, i.e. transmission of position
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
  • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
  • F05D2260/00—Function
  • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades

Definitions

• TITLE TURBOMACHINE MODULE EQUIPPED WITH VARIABLE PITCH BLADES AND AN ANNULAR INTERFACE SHELL
• the present invention relates to the field of aircraft turbine engines. It relates in particular to a turbomachine module comprising variable-pitch blades and a pitch-setting system. It also relates to the corresponding turbomachine as well as a method of assembly or disassembly of the module.
• the prior art includes the following documents US-B2-10907486, FR-A1 -3087233, USAI -2020/141421, US-B2-10533436, US-A1 -2017/066524.
• Turbomachines generally comprise a ducted fan or an unducted propeller fitted with variable-pitch moving blades.
• a ducted fan fitted with pitched or variable-pitch blades makes it possible to adjust the pitch or the orientation of the blades of the blades according to the flight parameters so as to optimize the operation of the fan. This configuration makes it possible to optimize the module in which such a blower is integrated.
• the pitch angle of a blade corresponds to the angle, in a longitudinal plane perpendicular to the axis of rotation of the blade, between the chord of the blade and the plane of rotation of the fan.
• variable-pitch blades can occupy a so-called thrust reversal position (known by the English term "reverse") in which they make it possible to generate counter-thrust to participate in the slowing down of the aircraft and a flag in which, in the event of failure or breakdown, these make it possible to limit their resistance.
• the fan blades are driven in rotation by a motor shaft. Such an example of a fan with variable-pitch blades is described in patent application FR-A1-3087233.
• Turbomachines equipped with unducted propellers are known by the term “open rotor” or “unducted fan”.
• the propeller or propellers forming the propulsion part can be placed at the rear of the gas generator (or engine) so as to be of the pusher type or at the front of the gas generator so as to be of the tractor type.
• turbomachines are turboprops which are distinguished from turbojets by the use of a propeller outside the nacelle (not shrouded) instead of an internal fan presented above. This makes it possible to increase the dilution ratio very significantly without being penalized by the mass of the casings or nacelles intended to surround the blades of the propeller or fan.
• the variable pitch makes it possible for the same purpose to slow down the aircraft or to limit the resistance in the event of a failure.
• the pitch change system comprises a control means which is connected on the one hand, to a fan shaft which is typically driven by the motor shaft via a speed reducer and on the other hand, to a linkage mechanism coupled to the variable-pitch vanes.
• the control means located in a rotating frame of the turbine engine, generally comprises a movable body which, by moving, acts on the position of the blades of the variable-pitch vanes.
• it is necessary to disconnect the connecting means from the control means in order to inspect the latter. This is valid for other elements of the pitch change system and other components of the turbomachine such as an oil transfer device in order to check their correct operation and their state of wear.
• This constraint induces a longer maintenance time, a new adjustment of the kinematics (linkage mechanism and control means), or even additional validation tests to ensure that they are correctly adjusted after each maintenance operation.
• the dismantling of the control means is also complex, or even not possible due to its cooperation with the motor shaft, the restricted zone in which the latter is arranged and its cooperation also with the oil transfer device typically placed downstream of a speed reducer, in a fixed frame. Dismantling the oil transfer device would require dismantling the inlet casing or the low-pressure compressor of the turbomachine, for example.
• the objective of the present invention is to provide a turbomachine module equipped with variable-pitch blades with easily removable members and/or equipment without penalizing the adjustment of the kinematics necessary for the pitching of the blades and while allowing a gain in compactness. .
• a turbomachine module with a longitudinal axis X comprising: a fan intended to be driven in rotation around the longitudinal axis X by a fan shaft, the fan comprising a plurality of variable pitch fan blades, a system for changing the pitch of the fan blades comprising a link mechanism connected to the blades of the fan and a control means acting on the link mechanism, the control means comprising a fixed body integral with the fan shaft and a mobile body, with respect to said fixed body, which is connected to the link mechanism, the pitch change system comprising an annular part having a portion integral with the mobile body, the annular part having a shape generally bell-shaped and extending at least partly radially outside the fixed body, the module comprising an annular ferrule which is removably fixed to the annular part and which comprises means for attaching the link mechanism.
• this solution achieves the above objective.
• the fact of providing an annular interface ferrule between the annular bell-shaped part and the link mechanism makes it possible to guarantee the maintenance of the adjustment and the configuration of the link mechanism.
• the annular shell fixed on the one hand, to the link mechanism and on the other hand, to the bell-shaped annular part avoids the dismantling of the link mechanism which reduces the intervention time. It also allows an operator to control the angle of the blades, or even to re-adjust them during reassembly.
• the removable fixing to the bell-shaped annular part which is mounted on the movable body of the control means allows a visual inspection of the control means and its easy disassembly/reassembly if necessary as well as for other parts upstream and/or downstream thereof.
• the time saved for a technology comprising between eight and twenty-five, preferably sixteen variable-pitch blades with kinematics for each blade and anti-rotation elements, the time saved on the intervention is several hours. Such a time saving also influences a significant economic gain including the hourly rate of operators and the immobilization of the aircraft at airports.
• the module also includes one or more of the following features, taken alone or in combination:
• the fixed body comprises a ferrule which extends radially outside the fixed body from an outer wall and which comprises a first flange having a free end defining an outer rim, the outer diameter of the outer rim being smaller than the inner diameter of the annular shroud.
• the fixed body extends radially around the mobile body and the mobile body comprises an upstream end to which the annular part is removably fixed.
• the annular ferrule is intended to be mounted at least partly radially on the outside of a cylindrical portion of the annular part, the annular ferrule comprising a radially inner surface of complementary shape at least partly with a radially outer surface of the portion cylindrical.
• the connecting mechanism comprises connecting rods each having a first end secured to the annular shroud via the attachment means and a second end connected to the root of a fan blade.
• the fan shaft is connected to a power shaft of the turbomachine via a mechanical speed reducer, the speed reducer comprising an outer ring integral in rotation with the fan shaft.
• the turbomachine module comprises a fluid transfer device which is mounted upstream of the speed reducer and which is connected to a supply source upstream of the speed reducer, the transfer device comprising an annular stator part integral with a fixed structure of the turbomachine and a rotor part which is engaged in the stator part and which is integral in rotation with the control means, the stator part comprising an internal cylindrical surface and first pipes opening into the internal cylindrical surface, the part rotor comprising an outer cylindrical surface and second pipes opening into the outer cylindrical surface.
• the fluid transfer device extends at least partly inside the fan shaft.
• the fixed body comprises supply means which are coupled to the second pipes of the rotor part of the fluid transfer device.
• the speed reducer comprises an inner sun gear coupled to the power shaft, satellites, a planet carrier which carries the satellites and an outer ring gear which is coupled to the fan shaft.
• the speed reducer is housed in a lubrication enclosure.
• the annular shell has a U-shaped axial section with a first branch and a second branch connected by a bottom.
• the first branch of the ferrule has a surface of complementary shape with a surface of a radial flange of the annular part.
• the annular ferrule is mounted on the annular part following a sliding fit at the level of a cylindrical surface of the annular part.
• at least one rotational guide bearing of a blade root is housed in an internal housing of a ring.
• the movable body and the annular part are integral in movement via coupling means arranged between the movable body and the annular part.
• the rods are adjustable in length.
• the second pipes of the rotor part are in fluid communication with the first pipes of the stator part.
• the annular part comprises a central portion which has a first end connected to the proximal portion and which extends downstream while widening.
• control means is mounted generally upstream of the fan shaft along the longitudinal axis.
• the fasteners comprise threaded elements.
• the invention further relates to an aircraft turbine engine comprising at least one module having any one of the preceding characteristics.
• the invention further relates to an aircraft comprising at least one turbomachine as mentioned above.
• the invention also relates to a method for assembling a turbomachine module according to any one of the aforementioned characteristics, the method comprising the following steps:
• FIG. 1 is a schematic view, in axial and partial section, of an example of a turbomachine with a ducted fan to which the invention applies;
• FIG. 2 schematically shows, in partial axial section, a moving blade with variable pitch and a system for changing the pitch thereof according to the invention;
• FIG. 3 illustrates in perspective and upstream an annular bell-shaped piece mounted on a control means of the pitch change system and on an annular ferrule integral with a connecting mechanism of the pitch change system according to the invention
• Figure 4 shows a detail view of a fluid transfer device according to Figure 2;
• FIG. 5 schematically represents an axial sectional view of the upstream module of the turbomachine with all the components mounted/assembled according to the invention
• FIG. 6 shows, according to FIG. 5, the bell-shaped annular part disassembled, the connecting mechanism being held in position according to the invention
• FIG. 7 represents, according to FIG. 5, the extraction of the control means and of a fluid transfer device according to the invention.
• FIG. 8 represents steps in a method for dismantling various components of a turbomachine module according to the invention.
• the invention applies to a turbine engine intended to be mounted on an aircraft.
• the aircraft comprises a fuselage and at least two wings extending on either side of the fuselage along the axis of the fuselage.
• At least one turbomachine is mounted under each wing.
• the turbomachine may be a turbojet, for example a turbomachine equipped with a ducted fan (turboblower) or a turboprop, for example a turbomachine equipped with a non-ducted propeller ("open rotor", "USF” for "Unducted Single Fan” or “UDF” for “Unducted Dual Fan”).
• open rotor "USF” for "Unducted Single Fan” or “UDF” for “Unducted Dual Fan”.
• UDF Unducted Dual Fan
• fan is used to denote either a fan or a propeller.
• turbomachine module a module which notably comprises a fan and a fan shaft for driving the fan.
• the turbomachine 1 comprises a gas generator 2 upstream of which a fan 3 is mounted.
• the gas generator 2 typically comprises, from upstream to downstream, a low pressure compressor 4, a high pressure compressor 5, a chamber combustion 6, a high pressure turbine 7 and a low pressure turbine 8.
• the rotors of the low pressure compressor 4 and of the low pressure turbine 8 are mechanically connected by a low pressure shaft 9 so as to form a low pressure body.
• the rotors of the high pressure compressor 5 and of the high pressure turbine 7 are mechanically connected by a high pressure shaft 10 so as to form a high pressure body.
• the high-pressure body is guided in rotation around the longitudinal axis X by a first bearing 11 with rolling bearings upstream and a second bearing 12 with rolling bearings downstream.
• the first bearing 11 is mounted radially between an inter-compressor casing 13 and an upstream end of the high-pressure shaft 10.
• the inter-compressor casing 13 is arranged axially between the low-pressure compressor 4 and the high-pressure compressor 5.
• the second bearing 12 is mounted radially between an inter-turbine casing 14 and a downstream end of the high-pressure shaft 10.
• the inter-turbine casing 14 is arranged axially between the low-pressure 7 and high-pressure 8 turbines. rotation around the longitudinal axis X via a third bearing 15 with bearings and a fourth double bearing 16 with bearings.
• the latter are mounted radially between an exhaust casing 17 and a downstream end of the low pressure shaft 9.
• the exhaust casing 17 is located downstream of the low pressure turbine 8.
• the third bearing 15 is mounted radially between a inlet casing 18 and an upstream end of the low pressure shaft 9.
• the high pressure shaft 10 extends radially at least partly outside the low pressure shaft 9 and are coaxial.
• the low pressure or low pressure body comprises the low pressure compressor which is connected to an intermediate pressure turbine.
• a free power turbine is mounted downstream of the intermediate pressure turbine and is connected to the propeller described below via a power transmission shaft to drive it in rotation.
• the fan 3 is here streamlined by a fan casing 19 which carries a nacelle 20.
• the fan 3 compresses an air flow which enters the turbomachine by dividing into a primary air flow F1 and a secondary air flow F2 at a separation spout 21 .
• the latter is carried by the inlet casing 18 centered on the longitudinal axis X.
• the inlet casing 18 is extended downstream by an external casing or inter-vein casing 22.
• the primary air flow F1 circulates in a primary stream 23 which crosses the gas generator 2 and escapes therefrom through a primary nozzle 24.
• the secondary air flow F2 circulates in a secondary stream 25 and escapes therefrom through a secondary nozzle 26.
• the primary stream 23 and the secondary vein 25 are separated by the inter-vein casing 22.
• the fan 3 comprises a series of fan blades 30 extending radially around a fan rotor 31 .
• the fan rotor 31 is crossed by a fan shaft 32, cylindrical, centered on the longitudinal axis X.
• the fan shaft 32 drives the fan rotor 31 in rotation around the longitudinal axis X.
• fan 32 is itself driven in rotation by a power transmission shaft with longitudinal axis X via a power transmission mechanism 33.
• the power transmission shaft is the low pressure shaft 9.
• Fan shaft 32 and low pressure shaft 9 are coaxial.
• the power shaft is a power turbine shaft supplied with gas by the gas generator 2.
• the power transmission mechanism 33 is a mechanical speed reducer 34 for reducing the rotational speed of the fan shaft 32 relative to the speed of the low pressure shaft 9.
• the speed reducer 34 allows the arrangement of a fan with a large diameter so as to have a high dilution rate.
• the reducer 34 is of the planetary gear train type. The latter is housed in a lubrication chamber 35 in which it is lubricated.
• the speed reducer 34 comprises an inner (or sun) sun gear 36, satellites 37, a planet carrier 38 and an outer ring gear 39 (outer sun gear).
• the inner sun gear 36 is centered on the longitudinal axis X and is coupled in rotation with the power shaft (here the low pressure shaft 9) along the longitudinal axis X.
• the latter comprises first elements intended to cooperate with second complementary coupling elements carried by the sun gear 36 inside.
• the satellites 37 are carried by the planet carrier 38 and each rotate around an axis substantially parallel to the longitudinal axis X.
• Each of the planets 37 meshes with the inner sun gear 36 and the outer crown 39.
• the planets 37 are arranged radially between the inner sun gear 36 and the crown exterior 39.
• three satellites 37 are provided.
• the speed reducer 34 may comprise a number of satellites greater than three.
• the outer ring 39 is coupled in rotation with the fan shaft 32.
• the ring 39 is centered on the longitudinal axis.
• the inner sun gear 36 forms the input of the speed reducer 34 while the outer crown 39 forms the output thereof.
• the planet carrier 38 is on the other hand fixed with respect to the crown 39.
• the planet carrier 38 is in particular fixed to a fixed structure of the turbomachine via a support ring 40.
• the latter is rigidly fixed to the inlet casing 18 of the turbomachine.
• the support ring 40 is also fixed to a first bearing support 41, fixed, integral with the inlet casing 18.
• the third bearing 15 is mounted downstream of the speed reducer 34 advantageously.
• Guide bearings, with bearings, are also arranged upstream of the speed reducer 34 to guide the fan shaft 32 in rotation. These bearings are also arranged in the lubrication enclosure 35. More precisely, we can see a fifth bearing 42 with bearings (with balls) just upstream of the reducer 34 and a sixth bearing 43 with bearings (with roller) upstream of the bearing. 42.
• the outer rings of these bearings are carried by a second bearing support 44, fixed, integral with the inlet casing 18.
• the inner rings are integral with the fan shaft 32.
• each fan blade 30 comprises a root 45 and a blade 46 extending radially outwards from the root 45.
• the root 45 of each blade 30 is typically in the form of a shaft or sleeve which is pivotally mounted along a wedging axis C in an internal housing 47 of a ring 48.
• the root 45 and the blade 46 are separated, the blade fitting into the root via a dovetail connection.
• the ring 48 is integral with the fan rotor 31, is centered on the longitudinal axis and comprises several housings 47 evenly distributed around the axis X.
• the wedge axis C is parallel to the radial axis.
• the foot shaft 45 is pivotally mounted by means of two guide bearings 49 mounted in each housing 47 and superimposed along the radial axis Z.
• These bearings 49 are preferably, but not limited to, rolling bearings.
• the rolling elements of these two bearings 49 here respectively comprise balls.
• the timing of the fan blades is achieved by means of a pitch change system 50 installed in the fan rotor 31 . This is arranged in particular upstream of the speed reducer 34.
• the pitch change system 50 comprises at least one link mechanism 51 connected to the fan blades 30 and a control means 52 acting on the link mechanism 51 .
• the control means 52 comprises a fixed body 53 and a movable body 54 with respect to the fixed body 53.
• the control means 52 is a linear actuator with an axis coaxial with the axis longitudinal X.
• the fixed body 53 is integral in rotation with the fan shaft 32.
• the movable body 54 moves in a translation along the longitudinal axis X with respect to the fixed body 53.
• the fixed body 53 is therefore rotating but not translating.
• the fixed body 53 is cylindrical, centered on the longitudinal axis X, and of circular section. Such a configuration makes it possible to limit the size of the control means 52 in the fan rotor both axially and radially.
• the fixed body 53 extends radially around the movable body 54.
• the fixed body 53 comprises a ferrule 55 which extends radially outwards from an outer surface 53a of the fixed body 53.
• the ferrule 55 comprises a first flange 56 which is fixed to a second flange 57 of a trunnion 58.
• This trunnion 58 is fixed to the external wall of the fan shaft 32 by means of suitable fixing elements.
• the ring 48 for holding the blades 30 is also fixed to a fan cone 59 which comprises a third radial flange 60.
• the third radial flange 60 is fixed to the second flange 57. In this way, the fan shaft 32 is connected to ring 48.
• Fan cone 59 transmits torque and radial loads.
• the three flanges 56, 57 and 60 are fixed together by fasteners (not shown) such as screws, nuts, bolts, studs or the like.
• control means 52 is a jack provided with a casing and a movable piston in a volume formed by the casing.
• the movable body 54 is in the form of an axial rod 61 which extends between a first end 61a and a second end 61b.
• Movable body 54 further includes an annular wall 62 which extends radially outward from an outer face and around stem 61 .
• the annular wall 62 is located at the level of the second end 61b of the rod. This annular wall 62 makes it possible to delimit two chambers 63a, 63b of variable volume in the fixed body 53 and which are axially opposed.
• the movable body 54 moves axially under the action of a command from the control means 52, and in particular of the pressure of a fluid circulating in each chamber 63a, 63b.
• the pitch change system 50 comprises power supply means ensuring the control thereof and described later in the description.
• the fluid received in the chambers 63a, 63b is for example hydraulic fluid under pressure, from a fluid supply system, so that the mobile body 54 occupies at least two positions. Of course, the mobile body 54 occupies several intermediate positions depending on the different flight phases of the aircraft. These two positions correspond respectively to the thrust reversal position known in English by the term “reverse” and to the feathering position of the variable-pitch blades.
• the displacement of the movable body 54 along the longitudinal axis X causes the movement of the link mechanism 51, in such a way that the latter causes the pivoting and the setting of the blades of the blades around the setting axis C.
• the pitch change system 50 comprises an annular part 70 (in a cross section at its axis of revolution) which has a general bell shape and which makes it possible to connect the link mechanism 51 to the control means 52
• general bell shape means that the shape is substantially flared or substantially tapered.
• the annular part 70 comprises a proximal portion 71 which is secured to the movable body 54 of the control means 52.
• Coupling means 79 are arranged between the movable body 54 and the annular part 70 so that these are integral in movement, and in particular in translation.
• Portion 71 is in the form of a disc centered on the longitudinal axis X.
• Portion 71 comprises a central hole 72 which passes through its wall on either side along the longitudinal axis X.
• the stem 61 of the body mobile 54 crosses at least partly the central hole 72 of the portion 71 which is fixed on the rod 61 .
• the first end 61a of the rod 61 extends upstream from the portion 71 and outside the annular piece 70.
• the coupling means 79 comprise first grooves 79a which are formed on a radially outer wall of the rod 61 and in the vicinity of the first end 61a. These first splines 79a engage with corresponding second splines 79b of portion 71 . These second grooves 79b are formed on a radially inner wall of the central hole 72.
• a tightening member 73 such as a nut is mounted on the outer wall of the rod 61 . The clamping member 73 makes it possible to axially lock the portion 71 on the rod 61 .
• the annular part 70 comprises a central portion 74 which has a first end connected to the proximal portion 71 and which extends downstream while widening.
• annular part 70 extends radially outside the fixed body 54.
• the central portion 74 has a substantially frustoconical axial section.
• Annular piece 70 includes a fourth flange 75 which extends radially outward from an outer surface of central portion 74. Flange 75 is arranged near a second end of central portion 74.
• the annular piece 70 comprises a distal cylindrical portion 76 which axially extends the central portion 74 at its second end.
• the cylindrical portion 76 has an internal diameter D3 (measured on the internal surface 77 of said portion 76) (visible in FIG. 7) which is greater than the external diameter D4 (defined by the free end of the flange 56) (and visible in Figure 7) of the fixed body 53.
• the flange 75 of the annular part 70 comprises an internal surface 78 which is defined in a plane perpendicular to the longitudinal axis X. This plane also passes substantially in the middle of the fixed body 53 (Along the axial length of the fixed body 53).
• the cylindrical portion 76 and the flange 75 have a substantially L-shaped axial shape.
• the pitch change system 50 comprises an annular interface ring 80 which is kinematically arranged between the annular part 70 and the link mechanism 51 .
• the annular shell 80 is an added piece. That is to say that the annular ferrule 80 is distinct from the annular part 70. This additional ferrule 80 allows simple assembly/disassembly of the control means 52 without the kinematics produced by the link mechanism 51 being impacted.
• the annular shell 80 is fixed in a removable manner to the annular part 70 and comprises attachment means 81, fixed, of the link mechanism 51.
• the annular shell 80 and the annular part 70 are fixed together by means of fixing members which are removable. This makes it possible to assemble and disassemble the control means of the link mechanism with great ease.
• the annular shell 80 has a U-shaped axial section with a first branch 82 and a second branch 83 which are connected by a bottom 84.
• first branch 82 and the second branch 83 each extend radially outwards.
• the bottom 84 extends along the longitudinal axis and is centered on the longitudinal axis X.
• the ferrule ring 80 is intended to be mounted at least partially radially outside the cylindrical portion 76.
• the ferrule 80 is intended to rest on the latter.
• the shroud 80 comprises a radially inner surface of complementary shape at least in part with a radially outer surface of the annular part 70.
• the first branch 82 comprises an outer surface 85 which has a shape complementary to the inner surface 78 of the flange 75. Outer surface 85 is defined in a plane parallel to the plane of inner surface 78. Inner and outer surfaces 78, 85 are planar in this example.
• the bottom 84 has a radially inner surface 86 of which at least part is complementary with a radially outer surface 87 of the cylindrical portion 76.
• the radially outer surface 87 of the cylindrical portion 76 forms a cylindrical bearing surface.
• the cylindrical portion 76 allows for short centering.
• the radially outer surface 87 is radially opposed to the inner surface 77.
• the annular shroud 80 may comprise ribs (not shown) extending between the first branch and the bottom so as to stiffen the latter.
• the flange 75 and the first branch 82 are fastened together via removable fasteners (not shown).
• the flange 75 comprises a plurality of first orifices 88 which pass through the wall of the flange 75 on either side in a direction parallel to the longitudinal axis X. These first orifices 88 are regularly distributed around the longitudinal axis.
• the first branch 82 also comprises second orifices 89 which pass through its wall on either side in a direction parallel to the longitudinal axis. In the installation situation, the first and second orifices 88, 89 are each facing each other and coaxial.
• the fasteners may include screws, studs, nuts for mounting and dismounting these elements easily and quickly.
• the fixing members are axial.
• the members can be different and can be adapted to the configuration of the interface between the annular part and the annular shroud.
• the ferrule 80 is mounted on the annular piece 70 according to a sliding fit at the level of the cylindrical surface 76 of the annular piece 70 to facilitate the dismantling of the annular piece 70 with respect to the annular ferrule 80.
• the internal diameter D2 of the annular shell 80 (measured at the radially internal surface 86 of the bottom 84) is greater than the external diameter D1 (measured at the radially outer surface 87) of the cylindrical portion 76.
• the inner diameter of the ferrule 80 is also greater than the outer diameter of the flange 56 (measured at the edge 90 thereof).
• the annular ferrule is shrunk onto the annular part.
• extraction holes are made in the flange 75 and for example between, circumferentially, the first orifices 88.
• the extraction holes have axes parallel to those of the first orifices 88 and cross on both sides. the other flange 75 along the longitudinal axis X.
• the extraction holes are advantageously, but not exclusively threaded.
• a screw-type extraction element is screwed into at least one extraction hole so that the screw is in abutment and presses on the outer surface 85 of the first branch 82 of the ferrule 80 so as to separate the annular part 70 relative to the annular ferrule 80 once the fasteners have been removed.
• the annular part 70 is perforated so as to lighten the mass thereof.
• through slots, and having an elongated shape, are made in the central portion 74 of the annular part 70.
• the link mechanism 51 comprises several links 91 .
• One of the links 91 is shown for example in Figure 3.
• Each link 91 comprises a first end 92a and a second end 92b opposite in the direction of elongation of the link 91.
• the direction of elongation is here substantially parallel to the longitudinal axis (in the installation situation).
• the first end 92a is connected to the attachment means 81 integral with the annular shell 80.
• the attachment means 81 here comprise yokes each formed of two lugs 93a, 93b.
• the two lugs 93a, 93b of each yoke are traversed by a hinge pin 94 substantially parallel to the radial axis and around which a rod 91 pivots.
• each link 91 (shown in Figure 2) is hinged to a fork 95a provided at the free end of an arm 95 (see Figure 2) connected to the foot 45 of a fan blade.
• the arm 95 forms an eccentric for each blade.
• the links 91 are made of a metallic material.
• each link 91 is each adjustable in length.
• each link 91 includes a threaded intermediate pin (not shown) extending between a first end and a second end.
• the first end of the intermediate shaft is screwed into a threaded hole in a first link portion (provided with one of the ends of the link).
• the second end of the axis intermediate is also screwed into a tapped hole of a second link portion (with the other end of the link).
• This configuration makes it possible to adjust the pitch of the blades with respect to each other.
• the timings are thus finely adjusted despite manufacturing, tolerance and aging defects that may affect the various parts constituting the fan and the pitch change system.
• the annular ring 80 makes it possible to maintain the setting despite the dismantling of the control means 52 (actuator).
• the turbomachine 1 comprises a fluid supply system 100 making it possible to distribute a lubricating fluid to the various organs and/or equipment which need it, such as the means 52, bearings, etc.
• the fluid is advantageously pressurized oil.
• the supply system 100 comprises a supply source 101 (or a reservoir) (cf. FIG. 1) and a pump making it possible to circulate the oil to the organs and/or equipment.
• the power source 101 is arranged in a fixed frame of the turbine engine and generally in the nacelle 20 as illustrated in Figure 1 or in the inter-vein housing 22.
• the turbomachine comprises a fluid transfer device 103 (cf. FIG. 2) or oil transfer bearing.
• This transfer device 103 is known by the acronym "OTB” for "Oil Transfer Bearing” and as its name suggests allows the transfer of oil from the fixed marker to the rotating marker.
• the oil transfer device 103 is arranged upstream of the speed reducer 34 according to FIG. 2. The location of the oil transfer device is advantageous because it facilitates its disassembly/assembly without intervening on the reducer. of speed.
• the supply system 100 also comprises several supply channels 104 for conveying the oil to the organs and/or equipment and which are shown in dotted lines in FIG. 1 and in FIG. 4. Some of these channels 104 cross the door -38 satellites which is fixed.
• the transfer device 103 extends inside the fan shaft 32 (which is hollow) so as to reduce the axial and radial bulk. In particular, the size is advantageously reduced upstream where the control means 52 is located.
• the control means 52 is generally mounted upstream of the fan shaft 32 along the longitudinal axis.
• the device 103 comprises a stator part 105 which is centered on the longitudinal axis X.
• the stator part 105 is mounted integral with a fixed structure of the turbomachine. In this example, the stator part 105 is attached to the planet carrier 38 via a tubular element 106.
• the stator part 105 comprises a seventh radial flange 108 which extends radially outward from the outer surface of the stator part 105.
• the flange 108 is fixed to an eighth radial flange 109 of the tubular element 106 via fasteners (here screws and nuts or other other similar elements).
• the stator part 105 comprises an internal cylindrical surface 110 into which first pipes 111 open.
• the device 103 also comprises a rotor part 112 which is engaged inside the stator part 105.
• the rotor part 112 has a cylindrical shape and extends along the longitudinal axis X.
• the rotor part 112 is rotatable at inside the stator part 105 along the longitudinal axis.
• the rotor part 112 is integral in rotation with the control means 52, and here more particularly with the fixed body 53 thereof.
• the rotor part 112 comprises an outer cylindrical surface 113 which faces the inner cylindrical surface 110 of the stator part 105.
• the rotor part 112 further comprises second pipes 114 which each open into the outer cylindrical surface 113 via orifices 117.
• the second pipes 114 are in fluid communication with the first pipes 111 of the stator part.
• these second pipes 114 are fluidly connected with the supply means of the control means 52.
• the second ducts 114 comprise an external duct 114a which extends in the thickness of the wall of the rotor part 112.
• the orifice 117 of the external duct 114a is opposite one of the first ducts 111 (here the first upstream pipeline).
• the second pipes 114 also include a central pipe 114b which extends for the most part along the central axis of the rotor part 112.
• the orifice 117 of the central pipe 114b is opposite the other of the first pipes 111 (here the first pipeline downstream).
• the external pipe 114a is coupled to a first pipe 115 which extends in the wall thickness of the fixed body 53.
• the first pipe 115 comprises a substantially radial portion 115a which is arranged downstream of the chambers 63a and 63b and an axial portion 115b which extends along the chambers 63a, 63b of the fixed body.
• the axial portion 115b opens into the chamber 63a.
• the central pipe 114b is coupled to a second pipe 116 of the fixed body 53.
• the central pipe 114b and the second pipe 116 are coaxial.
• the second pipe 116 opens into the chamber 63b. In this way, the fluid, the oil, can circulate from the power source 101 to the control means 52 passing on the one hand through the speed reducer 34, and on the other hand through the transfer device 103 of fluid.
• the rotor part 112 is rotatably mounted relative to the stator part 105 by means of bearings.
• a first bearing 120 is mounted upstream of the orifices 117 formed in the external cylindrical surface 113 and through which the pipes 114 open.
• the first bearing 120 is on bearings.
• This comprises an inner ring 121 which is carried by the outer cylindrical surface and an outer ring 122 which is carried by the inner cylindrical surface of the stator part 105.
• the outer ring 122 is axially blocked on the one hand, by a bearing surface cylindrical, and on the other hand, by a nut or a hoop 123.
• the inner ring is carried by the outer cylindrical surface of the rotor part.
• the inner ring 121 is blocked axially on the one hand, by a cylindrical seat, and on the other hand, by a cylindrical sleeve 124.
• the cylindrical sleeve 124 is blocked upstream by a hoop or a nut 125.
• the rolling elements are marbles.
• Sleeve 124 includes a radial flange 126 which extends radially outward.
• the flange 126 is attached to a flange 127 which extends radially outward from a proximal portion 128 of the fixed body 53.
• annular seal 129 which is defined in a plane perpendicular to the longitudinal axis X.
• the annular seal 126 comprises an inner edge fixed between the flanges via fasteners such as screws and nuts and an outer edge in contact with a cylindrical inner wall 130 of the fan shaft 32.
• a second bearing 131 is also mounted between the rotor part 112 and the stator part 105.
• the second bearing 131 is also a rolling bearing.
• the rolling elements of this bearing 131 are rollers.
• This bearing 131 is mounted downstream of the first bearing 120 and in particular downstream of the orifices 117 formed in the outer cylindrical surface 113.
• the second bearing 131 comprises an inner ring 132 and an outer ring 133.
• the outer ring 133 is carried by the surface inner cylindrical 110.
• the outer ring 133 is blocked axially upstream by a cylindrical seat and downstream by a hoop or a nut 134.
• the inner ring 132 is carried by the outer cylindrical surface 113. This is blocked upstream by a cylindrical bearing and downstream by a hoop one or a nut 135.
• FIGS. 5 to 8 illustrate a method 200 for dismantling the turbomachine module as described previously.
• the dismantling process makes it possible to intervene on the control means 52 and possibly on the oil transfer device 103 without intervening on the connecting rods 91, the adjustment of which must be precise for all the blades and is tedious.
• the method includes a step 220 of extracting the annular part 70 from the fan rotor as shown in Figure 6. During this step 220, the fasteners on the annular shroud 80 and on the rod 61 of the moving , withdrawn. The annular shell 80 remains fixed to the connecting rods 91 .
• the method includes a step 230 of extracting the control means 52 as illustrated in FIG. 7.
• step 230 the attachments between the fixed body and the fan shaft 32 are removed.
• the control means 52 is moved upstream without obstacle because the diameter of the flange 56 is smaller than the diameter of the annular shroud 80.
• the control means 52 passes through the annular shroud 80.
• the oil transfer device 103 can also be extracted. For this, the fasteners between the flanges 108 and 109 are removed.
• the method Prior to step 220, the method includes a step of extracting the nose 210 which is fixed to the fan rotor 31 so as to be able to access the annular part 70.
• the reassembly of these elements is carried out by reversing the steps of the dismantling process set out above.

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• Engineering & Computer Science (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Aviation & Aerospace Engineering (AREA)
• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)
• Structures Of Non-Positive Displacement Pumps (AREA)

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• 2021
  • 2021-12-20 FR FR2113951A patent/FR3130894B1/fr active Active
• 2022
  • 2022-12-13 EP EP22840795.3A patent/EP4453399A1/de active Pending
  • 2022-12-13 CN CN202280083746.6A patent/CN118434961A/zh active Pending
  • 2022-12-13 WO PCT/FR2022/052320 patent/WO2023118686A1/fr not_active Ceased
  • 2022-12-13 US US18/721,298 patent/US12480427B2/en active Active

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