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
  • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
  • B64D27/02—Aircraft characterised by the type or position of power plants
  • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
  • B64D27/18—Aircraft characterised by the type or position of power plants of jet type within, or attached to, wings
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
  • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
  • B64D27/40—Arrangements for mounting power plants in aircraft
  • B64D27/406—Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links
• • 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
  • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
• • 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
  • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
• • 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
  • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
  • F02K—JET-PROPULSION PLANTS
  • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
  • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
  • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
• • 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
  • F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
• • 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
  • F05D2220/70—Application in combination with
  • F05D2220/76—Application in combination with an electrical generator
• • 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
  • F05D2260/40—Transmission of power
  • F05D2260/403—Transmission of power through the shape of the drive components
  • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
• • 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
  • F05D2260/403—Transmission of power through the shape of the drive components
  • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
  • F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type

Definitions

• TITLE SUPPORT ASSEMBLY FOR AN AIRCRAFT TURBOMACHINE ACCESSORIES BOX
• the present invention relates to a support assembly for a main accessory box of an aircraft turbine engine.
• the technical background includes in particular documents US-A-4,068,470, US-A1-2019/218977 and US-A-5,687,561.
• An aircraft turbomachine comprises a gas generator which conventionally comprises, from upstream to downstream, with reference to the flow of gases in the turbomachine, at least one compressor, one annular combustion chamber and at least one turbine.
• the gas generator successively comprises a low pressure compressor, a high pressure compressor, the combustion chamber, the high pressure turbine and the low pressure turbine.
• the gas generator defines an annular stream of gas flow, called the primary flow, which crosses the compressors, the combustion chamber and the turbines.
• the high pressure compressor rotor is connected to the high pressure turbine rotor by a high pressure shaft.
• the rotor of the low pressure compressor is connected to the rotor of the low pressure turbine by a low pressure shaft which passes through the high pressure shaft and which rotates a propulsion propeller generally located upstream of the gas generator.
• this propeller is shrouded and therefore surrounded by an annular casing, called the fan casing, this propeller is called the fan and generates a flow of air which flows around the gas generator and is called the secondary flow.
• the propeller When the propeller is unducted, it also generates an airflow that flows around the gas generator.
• the turbomachine is attached to an element of the aircraft, such as a wing or the fuselage, by means of an attachment or attachment pylon also called a mast.
• This pylon generally has a generally elongated shape and comprises a beam which extends parallel to the longitudinal axis of the turbomachine.
• the pylon is located at 12 o'clock (12 o'clock) by analogy with the dial of a clock.
• the pylon comprises upstream members for fixing and suspending the turbomachine which are dedicated to one type of turbomachine and which cannot be used for another type of turbomachine.
• These fixing members are for example intended to be fixed on the fan casing of a turbomachine, which surrounds the fan propeller, and which therefore cannot be used for a turbomachine with an unducted propeller because this turbomachine does not comprise fan housing.
• the attachment pylon may include downstream members for attachment and suspension of the downstream end of a turbomachine.
• the gas generator ensures a transmission of forces between the upstream and downstream attachment points to the pylon, which result in deformations of the generator and of the gas and in modifications of the clearances between the rotors and the stators of the gas generator.
• the gas generator is thus subjected to a moment generated by the axial forces (offset thrust and thrust recovery).
• the turbomachine is also subjected to a moment generated by the asymmetry of axial forces on the blades of the fan propeller, and to forces originating from the capture of air (stick forces) by the turbomachine.
• turbomachine cantilever the turbomachine to the pylon. This would therefore amount to suspending a front or upstream part of the turbomachine from the pylon and leaving the rear or downstream part of the turbomachine free, such as its turbine casing for example.
• Another problem is linked to the hoisting of the turbomachine from a storage station placed on the ground to the pylon to which the turbomachine is intended to be fixed. The hoisting of a turbomachine may require movements in several directions until the turbomachine docks with the pylon and can be fixed to the pylon.
• AGB is the acronym for Accessory GearBox.
• the AGB is mounted around the fan casing, or is located in an inter-vein compartment, i.e. in a compartment located between the primary and secondary flow flow veins. Whenever possible, the AGB is fixed in this compartment on an external casing of the high pressure compressor.
• the AGB is located at 6 o'clock (6 o'clock) and suspended by connecting rods from this external casing. This is particularly the case in documents US-A-4,437,627 and US-A1 -6,260,351.
• some turbomachines in particular those having a relatively high bypass ratio, have a high pressure compressor and an outer casing of relatively small diameter. This external casing is very sensitive to mechanical deformations which tend to ovalize it. This distortion is detrimental to the performance of the turbomachine and in particular to the high-pressure compressor because it impacts the clearances between the rotor and the stator of this compressor. It is therefore preferable not to mount heavy equipment and not to mechanically stress this external casing in operation.
• Attaching or suspending the AGB to the external housing of the high pressure compressor is therefore not always possible or desirable.
• the present invention proposes an improvement to current technologies, which makes it possible to solve at least some of the problems and drawbacks mentioned above.
• the invention relates to a support assembly for a main accessory box of an aircraft turbine engine, said accessory box comprising gears and carrying at least one piece of equipment driven by these gears, the support assembly being characterized in that it comprises a structure for connecting and supporting the turbomachine to a pylon of the aircraft, the structure comprising:
• an intermediate axial portion for attachment to the pylon comprising an upper end which defines a connection interface with the pylon, said intermediate portion carrying suspension rods which are intended to be connected to the turbomachine, - a front axial portion extending forward of said intermediate portion and comprising at least one suspension member which is intended to be connected to the turbine engine, and - A rear axial portion extending behind said intermediate portion and carrying the main accessory box.
• the connecting structure of the support assembly according to the invention has many advantages.
• a first advantage is that it makes it possible to suspend the turbomachine with front and rear suspensions which are close together and integrated within the structure, which makes it possible to have a unique suspension structure for the turbomachine.
• the structure is preferably connected to an upstream part of the turbomachine, such as an intermediate casing.
• the turbomachine is then intended to be mounted cantilevered on the pylon since it does not include a downstream part, such as a turbine casing, intended to be connected to the pylon.
• a second advantage of the invention is related to the hoisting of the turbomachine which is facilitated thanks to the connecting structure.
• This link structure includes a link interface with the pylon which defines a docking area for the pylon.
• a third advantage is linked to the attachment of the accessory box to this connecting structure.
• the accessory box is therefore not directly attached to the turbomachine, which avoids transmitting mechanical stresses to the turbomachine in operation and limits the aforementioned risk of ovalization of the outer casing of the high-pressure compressor of this turbomachine.
• the accessory box remains connected to the engine thanks to the connecting structure which connects them together. It is therefore not necessary to dismantle the AGB and to disconnect it from the turbomachine during the hoisting and fixing of the turbomachine to the pylon.
• the accessory box also retains its advantages in terms of accessibility and maintenance.
• the invention is applicable to all types of turbomachine (turbojet, turboprop, APU) installed under an aircraft wing, on a wing or behind the fuselage.
• turbomachine turbojet, turboprop, APU
• the support assembly according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
• connection interface with the pylon is substantially flat and extends over an upper end of the rear axial portion of the connection and support structure
• said at least one suspension member extends in a substantially vertical second plane, called the front plane, this front plane being at an axial distance from the intermediate plane;
• said accessory box is suspended from said rear portion by a support device which extends in a substantially vertical third plane, called the rear plane, this rear plane being at an axial distance from the intermediate plane;
• the connecting structure extends along a first axis of elongation contained in a median plane which is perpendicular to said connecting plane, and the accessory box extends on either side of the median plane;
• - Said accessory box comprises a front face crossed by a power input and possibly carrying at least one piece of equipment, and a rear face carrying at least one piece of equipment;
• - Said support device extends upwards from an upper face of the accessory box;
• said main accessory box is located at 12 o'clock (12 o'clock);
• said at least one suspension member is located at a free front end of the second portion; -- said at least one suspension member is a snout which comprises:
• a connecting rod for attachment to the turbomachine which extends in said front plane
• - A cylindrical body which is engaged in a housing of the free end of the second portion and which is able to pivot in this housing around an axis parallel to said first axis of elongation
• the intermediate axial portion carries three suspension rods in said rear plane, these three rods comprising:
• the intermediate axial portion has a length L1 measured along the first elongation axis, which is less than or equal to a length L2 of the front axial portion measured along this axis; alternatively, L1 is greater than or equal to L2;
• the forward axial portion comprises an upper platform for attaching at least one foot of a stator vane
• the or each stator vane is a fixed vane or a variable-pitch vane.
• the present invention also relates to an aircraft turbine engine, comprising a support assembly for a main accessory box as described above, the turbine engine being configured to be mounted cantilevered on a pylon thanks to the connecting structure of the support assembly.
• the turbomachine according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
• the turbomachine comprises a gas generator which has a longitudinal axis and drives an unducted propeller, the gas generator comprising from upstream to downstream, in the direction of gas flow, at least one compressor, an annular combustion chamber and at least one turbine, the gas generator defining a main annular flow path for a first air flow and being intended to be surrounded by a secondary annular flow path for a second air flow, the connecting structure being attached to the gas generator such that an elongation axis of the connecting structure is located at a radius measured with respect to the longitudinal axis, which is between the minimum radius and the maximum radius of the helix;
• the gas generator comprises two compressors, respectively low pressure and high pressure, and an intermediate casing interposed axially between these two compressors, said box of accessories being located just downstream of this intermediate casing;
• said intermediate casing comprises a central hub connected by radial arms to an annular ferrule extending around the central hub, this annular ferrule being connected to said suspension rods of said intermediate portion;
• the accessory box is connected to said annular shell by at least two connecting rods;
• a power input of the accessory box is connected to an intermediate gearbox which is itself connected by another substantially radial shaft to power tapping gears on a shaft of the gas generator;
• turbomachine further comprises a secondary accessories box which comprises: - at least one shaft connected to a starter,
• this electric generator or this hydraulic pump being connected to an electric motor or to a hydraulic turbine mounted on the main accessory box, for the electrical supply or hydraulics of this electric motor or this hydraulic turbine;
• Said secondary accessory box is fixed to said hub of the intermediate casing;
• Said starter is an electric starter/generator, a hydraulic pump or an air starter;
• said structure has a generally elongated shape
• turbomachine is of the shrouded or non-shrouded type, -- said secondary stream is shrouded or unshrouded;
• - Said propeller is located upstream of the main and secondary streams; alternatively, the helix is located downstream of these veins;
• the connecting structure is fixed to the gas generator downstream of the propeller; alternatively, the connecting structure is fixed to the gas generator upstream of the propeller;
• the turbomachine comprises an annular row of stator vanes which is located downstream of the propeller in the secondary stream, the second portion of the structure being located between two adjacent vanes of this row of vanes or carrying one blades of this row of blades; -- the stator vanes are fixed vanes or variable-pitch vanes;
• stator vanes are located downstream of the propeller in the secondary stream
• said front plane is located upstream or in line with the leading edges of the blades of the row of blades, and/or said rear plane is located downstream of the trailing edges of the blades of the row of blades;
• the assembly further comprises a pylon having a second axis of elongation and comprising a front end for attachment to the first portion of the structure; -- the assembly further comprises thrust take-up bars or connecting rods, these connecting rods having front ends fixed to the gas generator and rear ends connected to a spreader fixed to the pylon, behind the structure.
• Figure 1 is a very schematic view of an assembly comprising an aircraft turbine engine and its attachment pylon, according to the technique prior to the invention
• FIG.2 Figure 2 is a very schematic view of an aircraft turbomachine and shows points of attachment and suspension to an attachment pylon, according to the technique prior to the invention
• FIG.3 is a very schematic view of another aircraft turbine engine and shows points of attachment and suspension to an attachment pylon, according to the technique prior to the invention;
• Figure 4 is a schematic perspective view of an assembly comprising an aircraft turbine engine, an attachment pylon, and a structure for connecting the turbine engine to the pylon;
• Figure 5 is a schematic side view of the tower and the connecting structure of Figure 4;
• Figure 6 is a schematic perspective view of a front suspension member of the connecting structure of Figure 4;
• Figure 7 is another schematic perspective view of the front suspension member of the connecting structure of Figure 4.
• FIG.8 is a schematic perspective view of the rear suspension rods of the connecting structure of Figure 4.
• Figure 9 is a schematic side view of the connecting structure of Figure 4 during a hoisting step towards the pylon; and
• Figure 10 is a schematic perspective and front view of the connection structure and the pylon of Figure 4, and illustrates the moments which apply in operation to the connection points of the structure to the turbomachinery.
• Figure 11 is a schematic perspective view of an assembly comprising an aircraft turbine engine, an attachment pylon, and a connecting structure of the turbine engine to the pylon, according to an embodiment of the present invention
• Figure 12 is another schematic perspective view of the assembly of Figure 11;
• Figure 13 is another schematic perspective view of the assembly of Figure 11, years the attachment pylon;
• Figure 14 is a view similar to that of Figure 11; and [Fig.15] Figure 15 is a view similar to those of Figures 8 and 10 and shows the connecting rods of the accessory box.
• FIG. 1 shows a turbomachine 10 for an aircraft, this turbomachine 10 here being a turbofan and twin-body turbojet.
• Axis A designates the longitudinal axis of the turbomachine.
• the orthonormal reference XYZ is represented in certain figures including FIG. 1.
• the direction X is parallel to the axis X and oriented towards the upstream or the front of the turbomachine 10, the axis Y is oriented upwards, and the Z axis is oriented to one side.
• the turbomachine 10 comprises a gas generator 12 which comprises, upstream to downstream with reference to the flow of gases along the axis A, a LP 14 or low pressure compressor, an HP 16 or high pressure compressor, a chamber annular combustion 18, an HP 20 or high pressure turbine and a LP 22 or low pressure turbine.
• a gas generator 12 which comprises, upstream to downstream with reference to the flow of gases along the axis A, a LP 14 or low pressure compressor, an HP 16 or high pressure compressor, a chamber annular combustion 18, an HP 20 or high pressure turbine and a LP 22 or low pressure turbine.
• the HP compressor rotor 16 is connected to the HP turbine rotor 20 by a high pressure shaft
• the LP compressor rotor 14 is connected to the LP turbine rotor 22 by a low pressure shaft which passes through the high pressure shaft and which drives in rotation a propulsion propeller located upstream of the gas generator 12 and which is surrounded by an annular casing called the fan casing 24.
• the fan casing 24 is connected to the gas generator 12 by an intermediate casing 26 which comprises a central hub 28 and a series of radial arms connecting the hub 28 to the fan casing 24.
• the gas generator 12 defines a main annular vein for the flow of a first air flow, called the primary flow.
• the gas generator 12 is surrounded by a secondary annular vein for the flow of a second air flow, called secondary flow.
• the air flow entering the fan is divided into a part forming the primary flow.
• the air from this primary flow is compressed in the LP compressors 14 and HP 16, then mixed with fuel and burned in the combustion chamber 18.
• the combustion gases from the primary flow are then expanded in the HP 20 and LP 22 turbines and finally flow into an exhaust nozzle 30.
• the other part of the air flow entering the fan forms the secondary flow which flows around the gas generator 12 and which is intended to be mixed with the primary flow downstream of the nozzle 30.
• the turbomachine 10 is fixed to an element of the aircraft via a pylon 32 which has a generally elongated shape along the axis A and therefore comprises an axis of elongation B parallel to the axis A.
• the pylon 32 comprises members 34, 38 for fixing and suspending the turbomachine 10.
• FIGS 1 to 3 illustrate the state of the art prior to the present invention.
• FIGS. 1 and 2 there are three points or fixing zones of the pylon 32 to the turbomachine 10. Two of the points are located in an upstream or front plane P1 perpendicular to the axis A and the last point is located in a downstream or rear plane P2 perpendicular to the axis A.
• a first fixing member 34 ensures the connection of the pylon 32 to the fan casing 24.
• the fixing member 38 ensures the fixing of the pylon 32 to a turbine casing or exhaust 40.
• This fixing member 38 is also connected by thrust take-up bars or connecting rods 36 to the hub 28 of the intermediate casing 26. These bars 36 ensure the transmission of the thrust from the turbomachine 10 to the pylon 32 and therefore to the 'aircraft.
• FIG. 4 illustrates a cantilevered connecting and fixing structure 50 of an aircraft turbine engine 10 to a pylon 32.
• the turbine engine 10 is partially illustrated in FIG. 4 and the preceding description in relation to FIG. 1 can be applied to the turbine engine 10 of FIG. 4 except as regards the attachment of the turbine engine 10 to the pylon 32.
• the fan casing 24 is not shown because this technology applies to a propeller 52 which is faired by such a casing 24 to form a fan, or which on the contrary is not faired.
• the propeller 52 comprises blades which extend radially with respect to the axis A of the turbine engine 10.
• the blades of the propeller 52 extend between a minimum radius Rmin measured at the level of the blade roots from the axis A, and a maximum radius Rmax measured from the tips of the blades from the axis A.
• primary F2 which flows in the gas generator 12, and in a secondary flow F3 which flows around the gas generator 12.
• the turbomachine 10 Downstream of the propeller 52, the turbomachine 10 comprises fixed stator vanes 54, commonly called OGV (acronym for Outer Guide Vanes). These vanes 54 extend radially with respect to the axis A from a ferrule of the intermediate casing 26.
• OGV an outer guide Vane
• the pylon 32 has its axis of elongation B parallel to the axis A and its upstream or front end is located downstream of the trailing edges 54b of the blades 54.
• the pylon 32 has its front end 32a which is located at or at above the intermediate casing 26.
• a specificity of the assembly is linked to the position of the pylon 32 with respect to the secondary flow F3.
• the pylon 32 of Figure 4 extends closer to the gas generator 12.
• the axis of elongation B is thus located at a radius of the axis A, which is between Rmin and Rmax.
• the turbomachine 10 which is fixed cantilevered to the pylon 32 is connected to the latter by thrust take-up bars 36.
• the connecting rods 36 are arranged symmetrically with respect to a vertical median plane passing through the axis A. They each have front ends 36a fixed to the gas generator 12, for example at the level of the intermediate casing 26 , and rear ends 36b connected to a beam 56 fixed to the pylon 32, at a distance from its axial end 32a.
• the ends 36a, 36b of the connecting rods 36 are preferably articulated by ball joints, respectively to yokes integral with the intermediate casing 26, and yokes integral with the spreader bar 56.
• the turbomachine 10 is fixed and suspended from the pylon 32 by means of a single connecting structure 50 which defines two planes, respectively front P1 and rear P2, of suspension of the turbomachine from the pylon.
• the connecting structure 50 is located at the front end 32a of the pylon 32, so that the rear suspension plane of the turbine engine 10 is closer to the front and the front plane P1, which allows the cantilever assembly of the turbine engine 10.
• Figures 5 to 8 allow a better view of the characteristics of the connecting structure 50.
• the connecting structure 50 has a generally elongated shape and has an axis of elongation C parallel to the axes A, B.
• the structure 50 essentially comprises two axial portions, namely:
• FIG. 5 shows that the intermediate portion 50a has a length L1 measured along the axis C, which is less than or equal to the length L2 of the front portion 50b measured along this axis .
• the intermediate portion 50a has an upper end 60 which defines a substantially horizontal interface plane P3 with the pylon 32.
• This intermediate portion 50a further comprises a lower end carrying suspension rods 62, 64 which are intended to be connected to the turbine engine 10 and which extend in the rear plane P2.
• the front portion 50b comprises at least one suspension member 66 which is intended to be connected to the turbine engine 10 and which extends in the front plane, P1.
• the connecting structure 50 can be formed from a single piece or from several assembled pieces.
• it comprises a main beam 68 which forms the intermediate portion 50a and an upper part of the front portion 50b.
• the lower part of the front portion 50b is then formed by a structural part 70 added and fixed under the beam 68, as shown in FIG. 7, but which can be integrated into this beam 68.
• the interface plane P4 between the beam 68 and the piece 70 can be substantially horizontal.
• the suspension member 66 is located at a free front end of the front portion 50b and is here formed by a snout which comprises:
• the connecting structure 50 is connected to the turbomachine 10 by a sliding pivot connection allowing rotational movements around the axis D.
• the member 66 can be configured to leave a degree of freedom to the turbomachine 10 along the axis X. In other words, the member 66 may not be configured to take up the forces of the turbomachine 10 and transmit them to the pylon 32 in the X direction. The member 66 is therefore advantageously configured to take up the forces in the Y and Z directions.
• the connecting structure 50 comprises three suspension rods 62, 64 in the rear plane P2, among which:
• the connecting rods 62, 64 have their ends which are articulated by ball joints respectively to yokes 78 integral with the gas generator (in particular at the level of the intermediate casing), and to the portion 50a.
• the connecting rods 62, 64 are configured to take up and transmit the forces applied to the turbomachine in the Y and Z directions and the moments along the X direction.
• FIG. 10 shows that the forces in the Y and Z directions are taken up by the connecting rods 62 (arrows F6), and that the connecting rod 64 picks up the moments in the direction X (arrow F7).
• the push rods 36 take up the forces in the direction X.
• the connecting structure 50 extends forward in the extension of the pylon 32 and is fixed to the gas generator 12, downstream of the propeller 52, so that its axis of elongation C is located at a radius measured with respect to the axis A, which is between the radius Rmin and Rmax.
• the front portion 50b of the structure 50 is located at the level of the fixed vanes 54 and two configurations are then possible.
• the front portion 50b of the structure 50 carries one of the blades 54.
• the front portion 50b comprises an upper platform 79 configured to be connected or secured to a blade 54, in particular to that located at 12 o'clock.
• this upper platform 79 can carry a root blank 80 configured to be fixed to the root of a blade 54.
• the front portion 50b of the structure 50 is located between two adjacent blades 54.
• the vanes 54 are of the variable-pitch type and are therefore each able to be positioned angularly around a radial axis with a precise angle.
• the structure 50 can comprise a mechanism for guiding the root of the blade 54, such as a bearing, or an actuation system comprising for example connecting rods, a gear, an actuator, etc.
• the structure 50 could support two blades 54 or even more.
• Figure 5 shows that, in the example shown, the front plane P1 is located upstream or to the right of the leading edges 54a of the blades 54, and the rear plane P2 is located downstream of the trailing edges 54b of the blades 54 and is intended to pass at the level of the intermediate casing of the turbomachine.
• FIG. 9 illustrates a step and a method for hoisting a turbomachine 10 equipped with the connecting structure 50 up to the pylon 32.
• the turbomachine is not represented in this drawing, it should be understood that the structure 50 is previously fixed to the turbomachine, that is to say that the flange 72 of its member 66 is fixed to a complementary flange of the gas generator 12, upstream or in line with the leading edges 54a of the blades 54, as mentioned in the above, and the connecting rods 62, 64 are attached to the gas generator as well.
• the structure 50 therefore has the advantage of being able to be fixed on the turbomachine in the assembly line of the latter. Thrust take-up connecting rods 36 can also be attached to turbomachine 10.
• the turbomachine can be moved on the ground using a trolley or suspended and moved using one or more hoists.
• the turbomachine is positioned under the pylon 32 so that the axes B and C are parallel and the portion 50a of the structure 50 is located just below the pylon 32, as illustrated in FIG. 9.
• the turbomachine is then hoisted towards the pylon 32, by a single movement in vertical translation from the bottom upwards (arrows F5), until the portion 50a and the pylon are supported in the interface plane P3.
• the structure 50 can then be fixed to the pylon 32, for example by means of the screw-nut type or the like.
• the spreader bar 56 attached to the connecting rods 36 can also be attached to the pylon behind the structure 50, as shown in Figure 5.
• FIGS. 11 to 15 illustrate a preferred embodiment of the present invention which uses a connecting structure 50 as described in the foregoing, and which relates to a support assembly for a main accessory box 82 of a turbomachine. , said assembly comprising this connecting structure 50.
• the turbomachine 10 is of the same type as that represented in FIG. 4 and described above. However, the invention is not limited to this type of turbomachine (with a non-ducted fan) and could be applied to another type of turbomachine, such as a turbomachine with a ducted fan of the bypass turbojet type for example.
• the connecting structure 50 differs from that described above in that it further comprises a third axial portion, namely a rear axial portion 50c which extends behind the intermediate portion 50a and intended to extend under the pylon 32.
• This rear axial portion 50c can be formed in one piece with the intermediate portion 50a.
• this rear portion 50c carries a main accessory box 82, also called AGB as mentioned above.
• This accessory box 82 comprising at least one power input 88 and gears (not visible) coupled to at least one output shaft (not visible) intended for driving at least one piece of equipment 86.
• this equipment 86 there may for example be an electric motor, an electric generator, a hydraulic pump, etc., as will be described in more detail below.
• the accessory box 82 is located at 12 o'clock (12 o'clock) and just downstream of the intermediate casing 26.
• the accessory box 82 comprises a front face 82a oriented upstream, a rear face 82b oriented downstream, and upper 82c and lower 82d faces which interconnect the faces 82a, 82b .
• the accessory box 82 may have a generally curved shape around the turbine engine 10.
• the upper face 82c then has a convex curved shape and the lower face 82d has a concave curved shape.
• the faces 82a, 82b can have a radial or perpendicular orientation to the axis A of the turbomachine 10.
• the equipment 86 is generally located on the front face 82a and/or the rear face 82b of the accessory box 82.
• the accessory box 82 is suspended from the rear portion 50c of the connecting structure 50 by at least one support device 84 which may include at least one connecting rod.
• this support device 84 extends in a substantially vertical third plane, called the rear plane P5.
• This rear plane P5 is at an axial distance from the intermediate plane P2 described above.
• the axis of elongation C of the connecting structure 50 is contained in a median plane P6 which is perpendicular to the connecting plane P3 and which passes substantially through this support device 84 in the example illustrated in FIG. 13.
• This device 84 may include at least one connecting rod which extends to the structure from the upper face 82c of the accessory box 82.
• the support device 84 comprises two connecting rods which respectively extend from the connecting structure 50 to the opposite ends of the accessory box 82.
• the rear axial portion 50c and the ends connecting rods may include clevises 85 for articulation to the connecting rods.
• These connecting rods are thus located on either side of the aforementioned plane P6.
• Figures 11 to 13 show that the accessory box 82 is connected to the first ends of at least two connecting rods 87 whose opposite second ends are connected to the turbine engine 10, and more particularly to a ferrule 27 of the intermediate casing 26. This ferrule 27 is connected to hub 28 of intermediate casing 26 by radial arms which are not shown in the drawings for greater clarity.
• the median plane P6 passes substantially between the connecting rods 87 and for example at an equal distance from these connecting rods 87, as illustrated in FIG. 13. These connecting rods 87 extend upstream and as far as the ferrule 27 from the front face 82a from the accessory box 82.
• the support device 84 and the connecting rods 87 are preferably positioned and configured to ensure isostatic mounting of the accessory box 82.
• the connecting rods 87 are moreover preferably configured to allow (micro) displacements in the three directions with respect to to the intermediate casing 26.
• the aforementioned median plane P6 also passes substantially through the power input 88 of the accessory box 82.
• This power input 88 can be a power transmission shaft, an electrical or hydraulic power passage conduit or cable, pneumatic, etc
• this power input 88 is formed by a shaft 90 which crosses the front face 82a of the accessory box 82.
• Shaft 90 extends substantially parallel to axis C and is connected to an intermediate gearbox 92 (also called TGB, acronym for Transfer GearBox).
• This TGB is itself connected by another substantially radial shaft 94 to an internal gear box 96 (also called IGB, acronym for Inlet GearBox).
• the TGB is for example fixed on the ferrule 27 of the intermediate casing 26.
• the IGB is mounted in the gas generator and makes it possible to draw power from an engine shaft.
• the shaft 90 is preferably connected to the AGB and to the TGB by flexibility devices (conventionally coupling devices with domed splines or cardan type) which allow movement in the three directions.
• Figure 11 shows that the assembly according to the invention may further comprise a secondary accessory box 98 which is preferably fixed to the hub 28 of the intermediate casing 26 and which comprises:
• a secondary accessory box 98 can for example be connected to the hub of the intermediate casing and take mechanical power from a shaft of the gas generator in a manner known per se, as carried out for the accessory box described in application FR- A1-3017660.
• the electric generator 102 is preferably connected to an electric motor 104 mounted on the main accessory box 82, with a view to supplying electric power to this electric motor 104.
• This type of architecture is called distributed electric architecture.
• this pump is connected to a motor or to a hydraulic turbine mounted on the main accessory box 82, for the hydraulic supply of this pump. It is the hydraulic transposition of the distributed electrical architecture.
• Starter 100 can be an electric starter/generator, hydraulic pump, air starter, etc.
• the engine 104 forms one of the equipment items 86 of the accessory box 82.
• Another of these pieces of equipment 86 can be an air power turbine (for example to drive the gears and therefore the equipment). This turbine can be powered by air taken from the high pressure compressor.

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

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• 2021
  • 2021-05-27 FR FR2105532A patent/FR3123377B1/fr active Active
• 2022
  • 2022-05-20 CN CN202280037086.8A patent/CN117355670A/zh active Pending
  • 2022-05-20 EP EP22732287.2A patent/EP4348020A1/de active Pending
  • 2022-05-20 WO PCT/FR2022/050965 patent/WO2022248795A1/fr active Application Filing
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