ASSEMBLY COMPRISING A TURBOMACHINE AND A STRUCTURE FOR CONNECTING AND SUPPORTING THE TURBOMACHINE TO AN AIRCRAFT

Abstract

An assembly (6) comprising a turbomachine (8) and a structure (10) for connecting and supporting the turbomachine (8) to an aircraft, the structure (10) being of the cradle type and comprising a beam (12) extending along the axis (A), three hoops, respectively upstream (14), intermediate (16) and downstream (18), and connecting rods (20) for linking the hoops (14, 16, 18) to each other and / or from the beam (12) to the hoops (14, 16, 18), the hoops (14, 16, 18) being connected to the beam (12) and extending around the axis (A) and the gas generator (22) of the turbomachine, the downstream hoop (18) being fixed to a downstream casing, and the upstream hoop (14) being fixed to an upstream casing and being located downstream of a row of stator blades (30) with variable calibration. Figure for the abbreviation: Figure 6

Description

Title of the invention: ASSEMBLY COMPRISING A TURBOMACHINE AND A STRUCTURE FOR CONNECTING AND SUPPORTING THE TURBOMACHINE TO AN AIRCRAFT Technical field of the invention

[0001] The present invention relates to an assembly comprising a turbomachine and a linkage and support structure for the turbomachine to an aircraft. Technical background

[0002] The state of the art includes in particular documents FR-A1-2 892 706, FR-Al-2 969 700, FR-A1-2 987 347, FR-A1-2 987 401, FR-A1-3 015 434, FR-A1-3 058 127, and FR-A1-3 123 323.

[0003] An aircraft turbomachine includes a gas generator which conventionally comprises, from upstream to downstream, with reference to the gas flow in the turbomachine, at least one compressor, an annular combustion chamber, and at least one turbine. In the case of a twin-spool turbojet engine, with low-pressure and high-pressure cylinders respectively, the gas generator comprises successively 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 flow path for a gas stream, called the primary flow, which passes through the compressors, the combustion chamber, and the turbines.

[0004] The rotor of the high-pressure compressor is connected to the rotor of the high-pressure turbine 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 drives a propulsion propeller generally located upstream of the gas generator.

[0005] When this propeller is enclosed and thus surrounded by an annular casing, this propeller is called a blower and generates an airflow that flows around the gas generator and is called a secondary flow. When the propeller is not enclosed, it also generates an airflow that flows around the gas generator.

[0006] The turbomachine is attached to an aircraft component, such as a wing or the fuselage, by means of a connecting and support structure which generally includes a pylon, also called a mast. This pylon generally has an elongated shape and includes a beam extending parallel to the longitudinal axis of the turbomachine. When the turbomachine is attached under an aircraft wing, the pylon is located at the 12 o'clock position, by analogy with the face of a clock.

[0007] There are several types of linkage and support structure for a turbomachine to an aircraft and the present invention relates more particularly to the "cradle" type which is shown in figures 1 and 2.

[0008] The structure 10 comprises the beam 12, three hoops, respectively upstream 14, intermediate 16 and downstream 18, and connecting rods 20 linking the hoops 14, 16, 18 to each other and to the beam 12. The hoops 14, 16, 18 are connected to the beam 12 and extend around the gas generator 22 of the turbomachine. The hoops 14, 16, 18 are attached to external annular housings 24, 26 of the gas generator 22.

[0009] Figures 3 and 4 show a similar configuration with a turbomachine comprising an unfaired propulsion propeller 28 (of which only one blade is visible in [Fig. 3]) and an annular row of stator blades 30. The propulsion propeller 28 is located upstream of the gas generator 22 for its air supply. The row of stator blades 30 is located downstream of the propulsion propeller and is also unfaired.

[0010] It can be seen in figures 3 and 4 that the straightener blades 30 are located just downstream of the propulsion propeller 28 and at the level of the upstream arch 14.

[0011] Rectifier blades are stator blades, but it is advantageous to adjust their angular pitch and therefore to use variable pitch rectifier blades. In this case, variable pitch systems are connected to the roots of these blades and must be mounted around the gas generator.

[0012] However, as can be seen in [Fig.5], there is no room to accommodate these systems 32 because the mounting environment for these systems is occupied here by the upstream hoop 14 and by the connecting rods 20 linked to this hoop.

[0013] The present invention offers a simple, effective and economical solution to this problem. Summary of the invention

[0014] The invention relates to an assembly comprising a turbomachine and a structure for connecting and supporting the turbomachine to an aircraft,

[0015] the turbomachine comprising a movable propulsion propeller rotating about an axis and an annular row of variable-pitch stator blades centered on the axis and located downstream of the propeller, the turbomachine further comprising a gas generator comprising from upstream to downstream a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine, the gas generator being surrounded by an annular casing formed by annular housings connected to each other along the axis, one of these housings being an upstream housing located axially upstream of the combustion chamber, and another of these housings being a downstream housing located axially downstream of the combustion chamber,

[0016] the structure being of the cradle type and comprising a beam extending along the axis, three hoops, respectively upstream, intermediate and downstream, and connecting rods of the hoops to each other and / or of the beam to the hoops, the hoops being connected to the beam and extending around the axis and the gas generator, the downstream hoop being fixed to the downstream casing, and the upstream hoop being located at the level or opposite the upstream casing and downstream of the row of stator blades.

[0017] The solution to the problem mentioned above therefore consists of shifting the upstream hoop downstream, so that it is then located around the inter-compressor housing. "Straight ahead or at the same level" here means that the upstream hoop is situated in a plane perpendicular to the axis, which passes through the inter-compressor housing. The rectifier blades are located upstream of the upstream hoop and, for example, at the level of a housing of the low-pressure compressor of the gas generator.

[0018] The invention may offer several advantages, including:

[0019] — the upstream casing is an inter-compressor casing located axially between the low pressure and high pressure compressors;

[0020] — the downstream casing is a turbine or exhaust casing;

[0021] — the downstream casing is a turbine casing located at the high-pressure turbine and / or the low-pressure turbine; - The invention allows the entire upstream part of the cradle to be offset, thus freeing up space for the blades and their variable-pitch system, as well as the associated servitudes, - the invention makes it possible to reduce the number of attachment points of the cradle to the turbomachine and therefore of the structure to the gas generator, - The aerodynamic torque of the blades can naturally compensate for some of the resulting moments; therefore, placing the fixing points downstream of the blade plane allows for absorbing less force than upstream of the blades. - the invention can make it possible to contain the center of gravity of the gas generator between two cradle mounting planes, which limits the upstream displacements of the turbomachine and thus the associated clearance consumption in the gas generator, - etc.

[0022] The assembly according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0023] — the propulsion propeller and the row of straightening blades are unfaired; - the row of rectifier blades is located around a low-pressure compressor housing; - the beam has an upstream end which is located axially at the level or directly above the upstream casing, and in particular the inter-compressor casing; - the assembly further includes a variable adjustment device for said blades, comprising variable adjustment systems which are distributed around the axis and which are connected respectively to the feet of said blades;

[0024] — said shimming systems are at an axial distance from the upstream end of the beam;

[0025] — the assembly further comprises a beam which extends along the axis in the axial extension of the beam and which includes an upstream end connected to a low pressure compressor housing, and a downstream end connected to the upstream end of the beam;

[0026] — the beam is detachably fixed to the beam;

[0027] — the beam supports one of said blades;

[0028] — the beam is at a circumferential distance from said blades and is covered by a fairing cover which has an elongated shape along the axis and extends downstream from an upstream end of the gas generator;

[0029] — the upstream hoop is fixed to the upstream casing, and in particular to the intermediate casing compressor;

[0030] — the upstream hoop is fixed to the upstream casing, and in particular to the intermediate casing compressor, by two fixing points which are located on two opposite sides of the gas generator, for example at 3 o'clock and 9 o'clock, or 2 o'clock and 8 o'clock; - the upstream hoop is connected to another hoop which is located upstream of the upstream hoop, at the right or at the level of a low pressure compressor housing, said other hoop being at an axial distance from the beam and extending around the axis and the gas generator;

[0031] — said other hoop is fixed to the low-pressure compressor housing by at least two fixing points;

[0032] — the upstream hoop is connected to said other hoop by bars inclined with respect to planes passing through the axis and possibly intersecting to form a lattice between these arches; - the upstream hoop is connected by connecting rods to a low-pressure compressor housing;

[0033] — the connecting rods of said other hoop to the low-pressure compressor housing are distributed around the axis and spaced circumferentially from each other; - the upstream hoop is connected or integrated into an additional annular casing which surrounds the upstream casing, and in particular the inter-compressor casing;

[0034] — said shimming systems are housed in a defined annular space between the casing additional annular and upstream casing, and in particular the inter-compressor casing; - the upstream casing, and in particular the inter-compressor casing, is of the double annular skin type, respectively internal and external, and the upstream hoop is integrated into the external skin or fixed to this external skin; - the downstream hoop is connected to the downstream casing, and in particular to the turbine casing, by at least one fixing block which is interposed between the beam and the gas generator, and for example located at 12 o'clock;

[0035] — the downstream hoop is connected to the downstream casing, and in particular to the turbine casing, by two fixing pads which are inserted between the beam and the gas generator, and for example located respectively at 1 Ih and Ih;

[0036] — the assembly further comprises variable adjustment systems for said blades, which are distributed around the axis and connected respectively to the feet of said blades, these shimming systems being carried by the external or internal skin;

[0037] — the upstream and intermediate hoops are connected to each other by at least two connecting rods parallel to the axis and arranged on two opposite sides of the gas generator, and the intermediate and downstream hoops are connected to each other by at least two connecting rods parallel to the axis and arranged on two opposite sides of the gas generator;

[0038] — the upstream and intermediate hoops are connected to each other by two other connecting rods inclined relative to the axis and arranged on two opposite sides of the gas generator;

[0039] — the upstream hoop is connected to the beam by two connecting rods inclined with respect to the axis and arranged on two opposite sides of the gas generator;

[0040] — the beam has a downstream end which is located downstream of the gas generator and which is connected to the downstream hoop by at least two connecting rods arranged on two opposite sides of the gas generator;

[0041] — the beam is formed by several boxes arranged end to end or by a lattice structure;

[0042] — the upstream and intermediate arches, or even said other arch, each have a shape general C-shaped, a middle part of which can be connected to the beam, or have a general O-shaped shape and extend all around the gas generator;

[0043] — the downstream hoop has a general C-shape, a central part of which is connected to the beam, or has a general O shape and extends all around the gas generator;

[0044] — the assembly further includes connecting brackets for the beam to the aircraft, these screeds being located on the beam at the level of the downstream arch, or even also at the downstream end of the beam. Brief description of the figures

[0045] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0046] [Fig.1] [Fig.1] is a schematic side view of an assembly comprising a turbomachine and a linkage and support structure for the turbomachine to an aircraft;

[0047] [Fig.2] [Fig.2] is a schematic perspective view of the whole of [Fig.1];

[0048] [Fig.3] [Fig.3] is a schematic side view of another assembly comprising a turbomachine and a linkage and support structure for the turbomachine to an aircraft;

[0049] [Fig.4] [Fig.4] is a schematic perspective view of the whole of [Fig.3];

[0050] [Fig. 5] [Fig. 5] is a partial schematic side view of the entire [Fig.3], whose rectifier blades are of the variable pitch type;

[0051] [Fig.6] [Fig.6] is a partial schematic side view of an assembly according to one embodiment of the invention;

[0052] [Fig.7] [Fig.7] is a schematic side view of the whole of [Fig.6] and illustrates a first configuration;

[0053] [Fig.8] [Fig.8] is a schematic side view of the whole of [Fig.6] and illustrates a second configuration;

[0054] [Fig.9] [Fig.9] is another schematic side view of the whole of [Fig.6];

[0055] [Fig. 10] [Fig. 10] is a partial schematic side view of an assembly according to an alternative embodiment of the invention;

[0056] [Fig. 11] [Fig. 11] is a partial schematic side view of an assembly according to another embodiment of the invention;

[0057] [Fig. 12] [Fig. 12] is a partial schematic side view of an assembly according to another embodiment of the invention;

[0058] [Fig. 13] [Fig. 13] is a schematic side view of an assembly according to another embodiment of the invention.

[0059] [Fig. 14] [Fig. 14] is a partial schematic perspective view of an assembly according to another embodiment of the invention;

[0060] [Fig. 15] [Fig. 15] is a partial schematic perspective view of an assembly according to another embodiment of the invention;

[0061] [Fig. 16] the [Fig. 16] is a partial schematic perspective view of an assembly according to another variant of the invention;

[0062] [Fig. 17] [Fig. 17] is a partial schematic perspective view of an assembly according to another embodiment of the invention. Detailed description of the invention

[0063] Figures 1 to 5 have been described above.

[0064] Reference is first made to Figures 6 to 9, which illustrate a first embodiment according to the invention.

[0065] The invention relates to an assembly 6 comprising a turbomachine 8 and a structure 10 for linking and supporting the turbomachine 8 to an aircraft (not shown).

[0066] Axis A designates the longitudinal axis of the turbomachine 8.

[0067] The turbomachine 8 includes a propulsion propeller 28 partially represented, which is movable in rotation about the axis A.

[0068] The turbomachine 8 further comprises an annular row of variable pitch stator blades 30 which is centered on axis A and located downstream of propeller 28.

[0069] The propulsion propeller 28 and the row of blades 30 are unfaired.

[0070] The turbomachine 8 further comprises a gas generator 22 which includes from upstream to downstream a low pressure compressor 22a, a high pressure compressor 22b, a combustion chamber 22c, a high pressure turbine 22d and a low pressure turbine 22e.

[0071] The gas generator 22 is surrounded by an annular casing 34 formed by annular housings connected to each other along the axis A, for example by clamping.

[0072] Among these housings, we may note a low-pressure compressor housing 36 extending around the low-pressure compressor 22a, an inter-compressor housing 38 extending axially between the low-pressure and high-pressure compressors 22a, 22b, a chamber housing 40 extending around the combustion chamber 22c, a high-pressure turbine housing 42 extending around the high-pressure turbine 22d, an inter-turbine housing 44 extending axially between the turbines 22d, 22e, and a low-pressure turbine housing 46 extending around the low-pressure turbine 22e. The casing 34 may further include an exhaust housing 48 downstream of the turbine housings 42, 44, 46.

[0073] The structure 10 is of the cradle type and comprises a beam 12 extending along the axis A, three arches, respectively upstream 14, intermediate 16 and downstream 18, and connecting rods 20 of the arches 14, 16, 18 to each other and / or of the beam 12 to the arches 14, 16, 18.

[0074] The hoops 14, 16, 18 are connected to the beam 12 and extend around the axis A and the gas generator 22.

[0075] The downstream hoop 18 is fixed to a downstream casing (of the combustion chamber 22c) and in particular to one of the turbine casings 42, 44, 46 or even to the exhaust casing 48.

[0076] The intermediate hoop 16 is not necessarily fixed to the casing 34 of the gas generator 22. The hoop 16 can extend around the chamber casing 40 for example.

[0077] The upstream hoop 14 has the particularity of being located at the level or opposite an upstream casing (of the combustion chamber 22c) and in particular of the inter-compressor casing 38, that is to say that it is located in a plane perpendicular to the axis A and passing through the inter-compressor casing 38.

[0078] The upstream hoop 14 is also located downstream of the row of stator blades 30 so as to leave room for the mounting of a variable pitch device upstream of the hoop 14, as can be seen in Figures 6 and 9. The device includes variable pitch systems 32 and there are as many systems 32 as there are blades 30.

[0079] The row of blades 30 can be located around the housing 36 of the low-pressure compressor 22a.

[0080] The beam 12 has an upstream end 12a and a downstream end 12b.

[0081] The downstream end 12b can be located well downstream of the gas generator 22.

[0082] The upstream end 12a can be located axially at the level of the inter-compressor housing 38.

[0083] The variable shimming systems 32 are distributed around the axis A and are connected respectively to feet (not shown) of the blades 30. These systems 32 can be axial distance from the upstream end 12a of the beam 12.

[0084] The assembly 6 may further include a beam 50 which extends along the axis A in the axial extension of the beam 12 and which includes an upstream end 50a and a downstream end 50b.

[0085] The downstream end 50b is preferably connected to the upstream end 12a of the beam 12.

[0086] The upstream end 50a can be connected to the housing 36 of the low-pressure compressor 20a. It is therefore understood that the fixing point of the beam 50 to the gas generator 22 is located upstream of the upstream hoop 14, and possibly of the fixing point(s) of the upstream hoop 14 to the gas generator 22.

[0087] The beam 50 is preferably fixed in a detachable manner to the beam 12.

[0088] In the configuration of [Fig.7], the beam 50 is part of the El environment of the turbomachine 8. In the configuration of [Fig.8], the beam 50 is part of the environment E2 of the structure 10.

[0089] In [Fig.6], it can be seen that the beam 50 can support one of the blades 30. In this case, even if the other blades in the row have variable pitch, this blade may not be and therefore may not be associated with a system 32.

[0090] In the alternative of [Fig.9], the beam 50 is at a circumferential distance from the blades 30 and is covered by a fairing hood 60 which has an elongated shape along the axis A and extends downstream from an upstream end of the gas generator 22.

[0091] The upstream hoop 14 can be connected or fixed to the inter-compressor housing 38 by two fixing studs 70 which are located on two opposite sides of the gas generator 22, for example at 3 o'clock and 9 o'clock, or 2 o'clock and 8 o'clock (by analogy with the face of a clock).

[0092] The downstream hoop 18 can be connected or fixed to the turbine housing 42, 44, 46 by a fixing block 72. This fixing block 72 can be fixed either to the downstream hoop 18 or under the beam 12. The fixing block 72 is interposed between the beam 12 and the gas generator 22, and is for example located at 12 o'clock.

[0093] Alternatively, the downstream hoop 18 could be connected or fixed to the turbine housing 42, 44, 46 by two fixing studs 72 which would be interposed between the beam 12 and the gas generator 22, and for example located respectively at 1 Ih and Ih.

[0094] Finally, the upstream end 50a of the beam 50 can be connected to the casing 36 by another fixing block 74, for example located at 12 o'clock.

[0095] The upstream hoops 14 and intermediate hoops 16 can be connected to each other by at least two connecting rods 20a parallel to the axis A and arranged on two opposite sides of the gas generator 22.

[0096] The upstream hoops 14 and intermediate hoops 16 can be connected to each other by two other connecting rods 20b inclined with respect to the axis A and arranged on two opposite sides of the gas generator 22.

[0097] Alternatively, the upstream hoop 14 could be connected to the beam 12, for example upstream of the intermediate hoop 16, by similar connecting rods inclined with respect to the axis and arranged on two opposite sides of the gas generator 22.

[0098] The intermediate hoops 16 and downstream hoops 18 can be connected to each other by at least two connecting rods 20c parallel to the axis A and arranged on two opposite sides of the gas generator 22.

[0099] The downstream end 12a of the beam 12 can be connected to the downstream hoop 18 by at least two connecting rods 20d arranged on two opposite sides of the gas generator 22.

[0100] The beam 12 can be formed by several boxes arranged end to end or by a truss structure.

[0101] The upstream arches 14 and intermediate arches 16 can each have a general C shape, a middle part of which is connected to the beam 12.

[0102] The downstream hoop 18 may have a general C-shape, a middle portion of which is connected to the beam. Alternatively, the downstream hoop 18 could have a general O-shape and extend all around the gas generator 22 ([Fig.4]).

[0103] Furthermore, the assembly 6 may include connecting cleats 80 of the beam 12 to the aircraft, these cleats 80 being located on the beam 12 at the level of the downstream hoop 18 or also at the downstream end 12a of the beam 12.

[0104] This variant makes it possible, in particular, to limit the impact of a rotor disc bursting on one of the compressors or turbines. The upstream attachment point at 12 o'clock formed by the stud 74 allows, in the event of loss of the two other attachment points formed by the studs 70, for an upstream attachment point to be maintained on the turbomachine. Furthermore, the stud 72 and the downstream clevises 80 can be defined outside the discharge cones of the low-pressure turbine 22e.

[0105] The variant embodiment of [Fig. 10] differs from the previous embodiment essentially in that it does not include a beam 50.

[0106] In this case, the structure 10 may not be fixed to the gas generator 22 by a fixing point at 12 o'clock. It is then preferable to move the fixing points of the upstream hoop 14 to the sides towards 12 o'clock. In the example shown, the fixing studs 70 of the upstream hoop 14 to the inter-compressor housing 38 are located at approximately 2 o'clock and 8 o'clock, or approximately 3 o'clock and 9 o'clock, respectively.

[0107] This variant allows the entire upstream part of the cradle to be offset, thus freeing up space for the blades 30 and their variable pitching systems 32. The aerodynamic torque of the blades 30 naturally compensates for some of the moment forces. Placing the cradle's supports 70 downstream of the blades 30 therefore allows them to absorb less force than upstream of the blades 30.

[0108] This variant may be preferred if the specified stiffness of the cradle to be supported is less critical. It may also be preferred if no need is identified for cradle attachments upstream and downstream of the engine's center of gravity.

[0109] The embodiment variants of figures 11 to 13 differ from the previous embodiment essentially in that the inter-compressor housing 38 is of the annular double-skin type, respectively internal 38a and external 38b.

[0110] In the case of [Fig. 11], the upstream arch 14 is integrated into the outer skin 38b.

[0111] In the case of figures 12 and 13, the upstream hoop 14 is fixed to the external skin 38b.

[0112] In these cases, the structure 10 can be fixed to the gas generator 22 by a fixing point at 12h. This fixing point can then be provided directly at the upstream end 12a of the beam 12. In the examples shown, a fixing block 70' of the end 12a is seen on the outer skin 38b.

[0113] In Figures 12 and 13, it can also be seen that the variable support systems 32 are supported by the outer skin 38b. A fixing point of the structure 10 to the gas generator 22 is provided at 12 o'clock. This fixing point can be formed by the mounting stud 70' of the hoop 14 to the outer skin 38b.

[0114] Alternatively, the variable support systems 32 could be carried by the inner skin 38 a.

[0115] The variants in Figures 12 and 13 have the same advantages as those of the previous variant.

[0116] These variants may be preferred in the event of a less important specification of the stiffness of the cradle to be held, or if there is no identified need for cradle attachments upstream and downstream of the engine center of gravity, or in the event of a low passage of servicing at the level of the low pressure compressor 36.

[0117] Figures 14 and 15 show variants in which the upstream hoop 14 surrounds the inter-compressor housing 38 but is not fixed to the latter.

[0118] The upstream hoop 14 is here connected to another hoop 14' which is located upstream of the upstream hoop 14, at the same level as or on the housing 36 of the low-pressure compressor 22a, that is to say that this other arch 14' is located in a plane perpendicular to the axis A which passes through the casing 36.

[0119] In the example shown, this other arch 14' is at an axial distance from the beam 12 and extending around the axis A and the gas generator 22. It has, for example, a general C-shaped form.

[0120] The other hoop 14' can be fixed to the housing 36 by at least two fixing studs 70'. In the example shown, the number of studs 70' is four. There are two diametrically opposed studs 70' located on each side of the gas generator (at 3 o'clock and 9 o'clock for example), at the circumferential ends of the hoop 14'. And there are two other studs 70' spaced circumferentially from each other and from the other two studs and therefore located approximately at 1 Ih and Ih.

[0121] The upstream hoop 14 can be connected to the other hoop 14' by bars 90.

[0122] In [Fig.15], the bars 90 are inclined with respect to planes passing through axis A.

[0123] In [Fig.14], in addition to being inclined, the bars 90 are interlaced to form a lattice between the hoops 14, 14'.

[0124] Fig. 16 shows another variant in which the upstream hoop 14 is connected or integrated into an additional annular housing 92 which surrounds the inter-compressor housing 38. The housings 92, 38 define between them an annular space 94 in which the shim systems 32 are housed.

[0125] The housing 92 can be stiffened by reinforcements 92' such as stiffening ribs which extend along the X axis in the space 94.

[0126] The housing 92 can be rigidly fixed to the casing 34, for example at the level of the housing 36 of the low pressure compressor 22a.

[0127] The hoop 14 is therefore not necessarily fixed itself to the inter-compressor housing 38.

[0128] Fig. 17 shows another variant in which the upstream hoop 14 surrounds the inter-compressor housing 38.

[0129] The upstream hoop 14 is here connected by connecting rods 96 to the housing 36 of the low-pressure compressor 22a. The connecting rods 96 are preferably distributed around the axis A and spaced circumferentially from each other, as illustrated.

[0130] The hoop 14 is therefore not necessarily fixed itself to the inter-compressor housing 38.

[0131] In the preceding description, the pads 70, 70', 72, 74 can be rigid pads or, on the contrary, flexible pads, that is to say, pads conferring at least one degree of freedom between the elements connected to each other.

Claims

Demands

1. An assembly (6) comprising a turbomachine (8) and a structure (10) for connecting and supporting the turbomachine (8) to an aircraft, the turbomachine (8) comprising a propulsion propeller (28) rotatable about an axis (A) and an annular array of variable-pitch stator blades (30) centered on the axis (A) and located downstream of the propeller (28), the turbomachine (8) further comprising a gas generator (22) comprising, from upstream to downstream, a low-pressure compressor (22a), a high-pressure compressor (22b), a combustion chamber (22c), a high-pressure turbine (22d) and a low-pressure turbine (22e), the gas generator (22) being surrounded by an annular casing (34) formed by annular housings connected to each other along the axis (A), one of these housings being an upstream housing located axially upstream of the combustion chamber (22c),and another of these casings being a downstream casing located axially downstream of the combustion chamber (22c), the structure (10) being of the cradle type and comprising a beam (12) extending along the axis (A), three hoops, respectively upstream (14), intermediate (16) and downstream (18), and connecting rods (20) of the hoops (14, 16, 18) to each other and / or of the beam (12) to the hoops (14, 16, 18), the hoops (14, 16, 18) being connected to the beam (12) and extending around the axis (A) and the gas generator (22), the downstream hoop (18) being fixed to the downstream casing, and the upstream hoop (14) being located at or opposite the upstream casing and being located downstream of the row of stator blades (30).

2. Assembly (6) according to claim 1, wherein the row of straightener blades (30) is located around a housing (36) of the low-pressure compressor (22a).

3. Assembly (6) according to claim 1 or 2, wherein the beam (12) has an upstream end (12a) which is located axially at the level or opposite the upstream casing.

4. Assembly (6) according to any one of the preceding claims, wherein it further comprises a variable shimming device for said blades (30), comprising variable shimming systems (32) which are distributed around the axis (A) and which are connected respectively to feet of said blades (30).

5. Assembly (6) according to any one of claims 1 to 4, wherein the upstream hoop (14) is connected to another hoop (14') which is located upstream of the upstream hoop (14), at the right or at the level of a housing (36) of the low pressure compressor (22a), said other hoop (14') being at an axial distance from the beam (12) and extending around the axis (A) and the gas generator (22).

6. Assembly (6) according to any one of claims 1 to 4, wherein the upstream hoop (14) is connected by connecting rods (96) to a housing (36) of the low-pressure compressor (22a).

7. Assembly (6) according to any one of claims 1 to 4, wherein the upstream hoop (14) is connected or integrated into an additional annular housing (92) which surrounds the upstream housing.

8. Assembly (6) according to any one of claims 1 to 4, wherein the upstream casing is of the annular double-skin type, respectively inner and outer, and the upstream hoop (14) is integrated into the outer skin (38b) or fixed to this outer skin (38b).

9. Assembly (6) according to any one of the preceding claims, wherein the downstream hoop (18) is connected to the downstream casing by at least one fixing stud (72) which is interposed between the beam (12) and the gas generator (22), and for example located at 12 o'clock.

10. Assembly (6) according to any one of the preceding claims, wherein the upstream hoops (14) and intermediate hoops (16) are connected to each other by at least two connecting rods (20a) parallel to the axis (A) and arranged on two opposite sides of the gas generator (22), and the intermediate hoops (16) and downstream hoops (18) are connected to each other by at least two connecting rods (20c) parallel to the axis (A) and arranged on two opposite sides of the gas generator (22).

Images