AIRCRAFT PROPULSION ASSEMBLY WITH A FILTERED CRADLE

Abstract

The invention provides an aircraft propulsion assembly comprising a gas generator coupled by a coupling mechanism to a thrust generator having a structural torque transmission gearbox, and a rigid cradle rigidly supporting firstly the thrust generator in a first suspension plane and secondly the gas generator in distinct second and third suspension planes, the cradle being for securing to a structural element of the aircraft via a vibration-filtering flexible connection.

Claims

1. An aircraft propulsion assembly comprising a gas generator coupled by a coupling mechanism to a thrust generator having a structural torque transmission gearbox, and a rigid cradle rigidly supporting firstly the thrust generator in a first suspension plane and secondly the gas generator in distinct second and third suspension planes, the cradle being for securing to a structural element of the aircraft via a vibration-filtering flexible connection.

2. The propulsion assembly according to claim 1, wherein the cradle supports the thrust generator in rigid manner via the torque transmission gearbox.

3. The propulsion assembly according to claim 2, wherein the cradle comprises: a main beam that extends parallel to a longitudinal axis of the gas generator, that is rigidly secured at one end to the torque transmission gearbox of the thrust generator in order to form the first suspension plane, and that is for securing at an opposite end via the vibration-filtering flexible connection to the structural element of the aircraft; and two transverse frames that are axially spaced apart from each other and secured rigidly to the gas generator in order to form the second and third suspension planes.

4. The propulsion assembly according to claim 3, wherein the main beam is secured to the torque transmission gearbox via a set of connecting rods.

5. The propulsion assembly according to claim 1, wherein the cradle has two flexible suspensions for forming the vibration-filtering flexible connection with the structural element of the aircraft.

6. The propulsion assembly according to claim 1, consisting in an airplane turboprop in which the thrust generator comprises a propeller that is coupled to the gas generator via a gearbox.

7. The propulsion assembly according to claim 1, consisting in an airplane turbojet in which the thrust generator comprises two contrarotating propellers that are coupled to the gas generator via a gearbox.

8. The propulsion assembly according to claim 1, consisting in an airplane turbojet in which the thrust generator comprises a ducted fan that is coupled to the gas generator via reduction gearing.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other characteristics and advantages of the present invention appear from the following description given with reference to the accompanying drawings, which shows embodiments having no limiting character. In the figures:

[0022] FIG. 1 is a diagrammatic side view of a propulsion assembly in a first embodiment (application of the invention to a turboprop having one propeller);

[0023] FIG. 2 is a diagrammatic side view of a propulsion assembly in a second embodiment (application of the invention to a turboprop having two unducted contrarotating propellers); and

[0024] FIG. 3 is a diagrammatic side view of a propulsion assembly in a third embodiment (application of the invention to a turbojet jet having a ducted fan).

DETAILED DESCRIPTION OF THE INVENTION

[0025] The invention applies to any aircraft propulsion assembly that comprises a gas generator coupled by a transmission shaft to a thrust generator and having a structural torque-transmitting gearbox, such as an airplane turboprop of the kind shown in FIG. 1.

[0026] In known manner, the turboprop 2 comprises a gas generator 4 driving rotation of a thrust generator 6, which itself comprises a propeller 8 and a gearbox 10 for transmitting torque to the propeller.

[0027] More precisely, the gas generator 4 comprises a low pressure turbine shaft 12 coupled to the gearbox 10 of the thrust generator via a coupling mechanism 13 so as to provide structural decoupling between the gas generator and the thrust generator.

[0028] The turboprop 2 is for securing to a wing box 14 of the airplane via a suspension structure referred to as a “cradle” 16.

[0029] The cradle 16 is in the form of a rigid structure comprising a main beam (or main bar) 18 that extends substantially parallel to a longitudinal axis X-X of the gas generator 4 and that has a front end secured in rigid manner to the gearbox 10 of the thrust generator 6 in order to form a first suspension plane P1 (referred to as the “front” suspension plane).

[0030] The cradle 16 also has two transverse frames 20 and 22 that are spaced apart axially from each other and connected to the main beam 18. At their free ends, each of these transverse frames is respectively secured in rigid manner to the gas generator 4 in order to form respectively a second suspension plane P2 (referred to as the “intermediate” suspension plane) and a third suspension plane P3 (referred to as the “rear” suspension plane).

[0031] The intermediate suspension plane of the cradle corresponding to the transverse frame 20 is of the conventional boomerang type having low weight. Specifically, no engine torque is taken up via this suspension plane, this torque take-up being offset to the rear suspension plane corresponding to the transverse frame 22.

[0032] The rear end of the main beam 18 of the cradle (remote from its front end secured to the gearbox 10) is secured to the wing box 14 of the airplane via a vibration-filtering connection.

[0033] In this example, the vibration-filtering connection is implemented using two flexible suspensions 24. For this purpose, various flexible suspensions can be used: laminated elastomer ball joints, stays filtered by elastomers, or metal cushions, etc. Reference may be made to Document FR 2 917 711, which describes an embodiment of such flexible suspensions.

[0034] The invention also applies to an airplane turbojet with contrarotating propellers (also known as “open rotors”), as shown in FIG. 2.

[0035] This turbojet 2′ comprises a gas generator 4′ driving rotation of a thrust generator 6′, itself having two contrarotating propellers 8′a and 8′b together with a gearbox 10′ for transmitting torque to the two propellers 8′a and 8′b.

[0036] The gas generator 4′ includes a low pressure turbine shaft 12′ that is coupled to the gearbox 10′ of the thrust generator via a coupling mechanism 13′ so as to provide structural decoupling between the gas generator and the thrust generator.

[0037] In the example shown in FIG. 2, the propellers 8′a and 8′b are located upstream from the gas generator 4′ (in a “puller” version), however they could equally well be placed downstream therefrom (in a “pusher” version).

[0038] In this example, the turbojet 2′ is for securing to a wing box or to a pylon 14′ of the airplane that it propels by means of a cradle 16′. The cradle is substantially identical to that described with reference to FIG. 1, i.e. it is in the form of a rigid structure comprising a main beam 18′ that extends substantially parallel to a longitudinal axis X-X of the gas generator 4′, having a front end secured to the gearbox 10′ of the thrust generator 6′ in order to form a first suspension plane P1 (referred to as the “front” suspension plane). This first suspension plane is defined as being a plane perpendicular to the longitudinal axis X-X of the gas generator and containing the attachment points between the cradle 16′ and the gearbox 10′. In the event of the attachment points being axially offset relative to one another, consideration is given to the furthest forward attachment point(s).

[0039] The front end of the main beam 18′ may be secured to the gearbox 10′ via a set of connecting rods 19, which in this example are considered as forming part of the cradle 16′. The gearbox 10′ is structural, e.g. having a structural casing. The casings of the coupling mechanism 13′ and of the low pressure turbine shaft 12′ may also be structural so that the gas generator 4′ contributes to supporting the assembly constituted by the thrust generator 6′ and the gearbox 10′.

[0040] Alternatively, the cradle 16′ may be made without using connecting rods 19. For example, the front end of the main beam 18′ could extend forwards as far as the first suspension plane P1 and could be connected to the gearbox 10′ by a transverse frame. Nevertheless, this solution is less advantageous in terms of the weight of the cradle 16′ and of the cantilevered-out weight of the assembly.

[0041] The cradle 16′ also has two transverse frames 20′ and 22′ that are axially spaced apart from each other and connected to the main beam 18′. At their free ends, each of these transverse frames is respectively secured in rigid manner to the gas generator 4′ so as to form respectively a second suspension plane (referred to as the “intermediate” suspension plane) and a third suspension plane (referred to as the “rear” suspension plane).

[0042] The rear end of the main beam 18′ of the cradle (remote from its front end secured to the gearbox 10′), is secured to the wing box or to the pylon 14′ of the airplane via a vibration-filtering connection, constituted in this example by two flexible suspensions 24′.

[0043] The invention also applies to an airplane ducted fan turbojet, as shown in FIG. 3.

[0044] The turbojet 2″ comprises a gas generator 4″ driving rotation of a thrust generator 6″, itself comprising a ducted fan 8″ and reduction gearing 10″ for transmitting torque to the fan 8″.

[0045] The gas generator 4″ includes a low pressure turbine shaft 12″ that is coupled to the gearing 10″ of the thrust generator via a coupling 13″ so as to provide structural decoupling between the gas generator and the thrust generator. By way of example, the gearing 10″ is an epicyclic geartrain having its inlet via its sun gear, it then being possible for the low pressure turbine shaft 12″ optionally to be in alignment with the axis of the gearing that corresponds to the axis of its sun gear.

[0046] In such an aligned configuration, the coupling 13″ could consist in a removable connection arranged axially between the low pressure turbine shaft 12″ and the sun gear of the gearing 10″ in order to connect them together. The term “removable connection” is used to mean a connection that can be removed while the thrust generator 6″ and possibly also the gas generator 4″ remain in place in the cradle 16″. As in the embodiments described with reference to FIGS. 1 and 2, this provision enables the gas generator to be removed without it being necessary to remove the thrust generator. This removable connection may for example comprise a shaft with curved fluting to provide a universal joint type transmission in order to compensate for small misalignments that may occur in operation, in particular because of vibration that can induce relative movements between the gearing and the low pressure turbine shaft.

[0047] In the configuration in which the low pressure turbine shaft 12″ is not in alignment with the axis of the gearing 10″, the coupling 13″ may make use of a removable connection as mentioned above together with a transfer box for connecting a shaft of this connection to the sun gear of the gearing 10″. The transfer box (not shown in FIG. 3) may be integrated in the same assembly as the gearing 10″.

[0048] The turbojet 2″ is for securing to a wing box or a pylon 14″ of the airplane it propels via a cradle 16″. This cradle is substantially identical to those described above with reference to FIGS. 1 and 2, i.e. it is in the form of a rigid structure comprising a main beam 18″ that extends parallel to a longitudinal axis X-X of the gas generator 4″ and that has a front end secured rigidly to the gearing 10″ of the thrust generator 6″ in order to form a first suspension plane (referred to as the “front” suspension plane).

[0049] The cradle 16″ also has two transverse frames 20″ and 22″ that are axially spaced apart from each other and connected to the main beam 18″. At their free ends, each of these transverse frames is respectively secured in rigid manner to the gas generator 4″ in order to form respectively a second suspension plane (referred to as the “intermediate” suspension plane) and a third suspension plane (referred to as the “rear” suspension plane).

[0050] The rear end of the main beam 18″ of the cradle (remote from its front end secured to the gearing 10″) is secured to the wing box or to the pylon 14″ of the airplane via a vibration-filtering connection constituted in this example by two flexible suspensions 24″.