Aircraft turbomachine assembly having an improved decoupling system in the event of a fan blade loss

Abstract

An assembly for a turbomachine includes a fan rotor drive shaft, a rolling element and a support of an exterior rolling-element bearing ring including an exterior annular element as well as an interior annular element coupled through a decoupling interface in the shape of a truncated sphere and configured to be retained by friction under normal operating conditions of the turbomachine, and to move with respect to one another in the event of a fan blade loss. The rolling-element bearing is designed so that each rolling element has four points of contact with the rings, and so that the interface between the ring and the support has a hollowed space for deformation routed around a central portion of the exterior ring.

Claims

1. An aircraft turbomachine assembly comprising: a fan rotor drive shaft; a rolling-element bearing comprising an exterior ring, an interior ring, and rolling elements arranged between the exterior and interior rings; means for connecting the interior rolling-element bearing ring to the drive shaft; a support for the exterior rolling-element bearing ring, said support being designed to be attached to a stator element of the turbomachine, and comprising an interior radial support surface in contact with an exterior radial surface of the exterior ring, the interior and exterior radial surfaces defining a junction interface between the exterior ring and the support, wherein said support includes an exterior annular element as well as an interior annular element coupled to the exterior annular element via a decoupling interface in the shape of a truncated sphere, the exterior and interior annular elements being configured to be retained with respect to one another by friction at their decoupling interface under normal operating conditions of the turbomachine, and to move with respect to one another in the event of a fan blade loss, under the influence of a decoupling moment originating in the drive shaft and transmitted by the rolling-element bearing which is designed so that each rolling element has two points of contact with the exterior ring and two points of contact with the interior ring, and so that said junction interface has, under normal operating conditions of the turbomachine, a hollowed space for deformation routed around a central portion of the exterior ring.

2. The assembly according to claim 1, wherein said means for connecting the interior rolling-element bearing ring to the drive shaft are made in a single part with the interior ring of the rolling-element bearing.

3. The assembly according to claim 1, wherein the exterior rolling-element bearing ring is split axially into two adjoining rings.

4. The assembly according to claim 1, wherein the exterior radial surface of the exterior ring comprises at a center of the exterior radial surface a notch having a half-section in the shape of a V radially open toward the exterior, delimiting a portion of said hollowed space.

5. The assembly according to claim 3, wherein the exterior radial surface of the exterior ring comprises at a center of the exterior radial surface a notch having a half-section in the shape of a V radially open toward the exterior, delimiting a portion of said hollowed space, the exterior radial surface of each of the two rings has a chamfer, and the two chamfers face one another so as to jointly form said notch.

6. The assembly according to claim 1, wherein said support is equipped with means of detecting the position of the interior annular element with respect to the exterior annular element.

7. The assembly according to claim 1, wherein the rolling elements are balls.

8. An aircraft turbomachine comprising at least one assembly according to claim 1.

9. The turbomachine according to claim 8, further comprising three rolling-element bearings for guiding the fan rotor drive shaft, wherein said rolling-element bearing of the assembly constitutes an intermediate rolling-element bearing situated between the two others.

10. The turbomachine according to claim 8, wherein the fan rotor drive shaft is a low-pressure shaft.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) This description will be made with reference to the appended drawings, among which;

(2) FIG. 1 shows a schematic view in longitudinal section of a portion of a turbojet, according to a design known from the prior art;

(3) FIG. 2 shows a view similar to that of FIG. 1, with the turbojet in a configuration as assumed after the mechanical decoupling of the front rolling-element bearing, after the loss of a fan blade;

(4) FIG. 3 shows a more detailed half-section view of a connection housing interposed between the fan drive shaft 8 and the intermediate rolling-element bearing of the turbojet shown in the preceding figures;

(5) FIG. 4 is a schematic view of a turbojet according to the invention;

(6) FIG. 5 is an enlarged half-section view of a portion of the turbojet shown in the preceding figure;

(7) FIG. 6 is an enlarge half-section view of the preceding figure, showing the intermediate rolling-element bearing and its surrounding elements;

(8) FIG. 7 is a half-section view substantially similar to the preceding figure, showing the intermediate rolling-element bearing in the case of a high radial load; and

(9) FIG. 8 is a half-section view similar to that of FIG. 5, after mechanical decoupling following the loss of a fan blade.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

(10) With reference to FIG. 4, an aircraft turbomachine 100 according to the invention is shown. This is a double flow two-spool turbojet. Nevertheless, it could be any other turbomachine with a fan disposed upstream or downstream of the gas generator, without departing from the scope of the invention.

(11) The turbojet 100 has a longitudinal axis 2 around which extend its different components. It comprises, from upstream to downstream along a principal direction 5 of gas flow through this turbojet, the fan rotor 4 bearing the fan blades 6, a low-pressure compressor 34, a high-pressure compressor 36, a combustion chamber 38, a high-pressure turbine 40 and a low-pressure turbine 42. These elements delimit a primary stream 44 through which a primary flow 44 passes, while a secondary stream 46 surrounds the primary stream, being partially delimited from it by a fan casing 48 with a secondary air flow 46 passing through it.

(12) In the description that follows, the terms front and rear are considered according to a direction 15 opposite to the principal direction 5 of gas flow within the turbojet, and parallel to the axis 2. In addition, the terms upstream and downstream are considered according to this same principal flow direction 5.

(13) The low-pressure compressor 34 and the low-pressure turbine 42 are connected by a low-pressure shaft 8, also corresponding to the fan rotor 4 drive shaft, while the high-pressure compressor 36 and the high-pressure turbine 40 are connected by a high-pressure shaft 8 coaxial with the low-pressure shaft 8. The invention is integrated into a front portion 60 of the turbojet, which will currently be described in reference to FIGS. 5 and 6.

(14) The front portion 60 includes here three rolling-element bearings for guiding the drive shaft 8. These are first of all the front rolling-element bearing 12a situated in proximity to a fan hub 62 arranged in proximity to the front end of the drive shaft 8 which drives it in rotation along the axis 2. Next is the intermediate rolling element bearing 12b situated facing radially a rear end of the low-pressure compressor 34, and finally the rear rolling-element bearing 12c situated between the low-pressure and high-pressure compressors. The front rolling-element bearing 12a is connected to a stator element 63 of the turbojet with by the rolling-element bearing support 14a which extends toward the rear and radially toward the exterior. The stator element 63 is the internal delimitation wall of the primary stream 44, which has a structural extension 64 on which is fixed the support 14a, via the calibrated screws 66. The screws 66 thus form the fusible connection 16a previously described. The intermediate rolling-element bearing 12b is connected to the same extension 64 by means of the support 14b, which has a flange 68 through which the calibrated screws 66 also pass.

(15) The intermediate rolling-element bearing 12b is an integral part here of an assembly 70 specific to the invention, which comprises furthermore the shaft 8, the support 14b and means 77 of connecting the interior ring of the rolling-element bearing to the shaft 8.

(16) Within this assembly 70, the rolling-element bearing 12b includes an exterior ring 72, an interior ring 74 as well as rolling elements 76 in the shape of balls. To facilitate manufacturing and assembly, the interior ring 74 and the connecting means 77 are made in a single part of which the upper end forms an interior rolling track for the balls 76, and of which the interior end is a bore cooperating with a portion of the shaft 8. Axial clamping means 80 allow the attachment of the single disk-shaped part to the drive shaft 8.

(17) Here, the support 14b has the characteristic of being made in two distinct portions, respectively constituted by an exterior annular element 82 and an interior annular element 84. The two elements 82, 84 are coupled to one another via a decoupling interface 86 in the shape of a truncated sphere. The center of this sphere is situated on the axis 2 of the assembly 70. The interior annular element 84 includes an interior radial support surface 88 receiving and being in contact with an exterior radial surface 90 of the exterior rolling-element bearing ring. These two surfaces 88, 90 together form a junction surface 89 between the exterior rolling-element bearing ring 72 and the support 14b. A clamping ring 92 makes it possible to ensure the axial clamping of the exterior ring 72 of the rolling-element bearing against a collar 94 of the interior annular element 84 of the support 14b.

(18) In this preferred embodiment, the exterior ring 72 is split into two axially adjoining rings. These two rings have the reference symbols 96 and 98. They are preferably joined together at a transverse plane passing substantially diametrically through the balls 76.

(19) The rolling-element bearing 12b is configured so that under normal operating conditions of the turbojet, each ball 76 has two points of contact 101, 102 with the interior ring 74, as well as two points of contact 103, 104 with respectively the two rings 96, 98 forming the exterior ring 72. The presence of these four contact points allows reinforcement of the angular stiffness of the rolling-element bearing 12b, by an embedding effect. It is the shape of the rolling tracks defined by the rings which leads to obtaining these four points of contact with the balls 76.

(20) Another characteristic of the invention resides in the presence of a hollowed space 106 which is routed continuously around a central portion 73 of the exterior ring of the rolling-element bearing. This hollowed space 106, which can be observed at the junction interface 89 at least under normal operating conditions of the turbojet, is made so as to form a deformation zone of the exterior ring 72, as will be explained hereafter. In the preferred embodiment shown, the exterior radial surface 90 of the ring 72 has at its center a half-section shaped like a V radially open toward the exterior. It is this notch which forms all or a part of the hollowed space 106. It is accomplished using two axially facing chamfers 108, 110, respectively provided on the exterior radial surface 90 of the two rings 96, 98.

(21) Under normal operating conditions of the turbojet, the assembly 70 assumes a configuration shown in FIG. 6, in which four contact points 101, 102, 103, 104 are observed between the rings and the balls. In this configuration, the imbalance is low or nonexistent, so that the shaft is only slightly loaded in bending. Only a slight moment is applied to the shaft 8, which is then transmitted by the rolling-element bearing 12b to the interior annular element 84. However, despite the absence of fusible shear pins at the decoupling interface 86, the interior annular element 84 remains static with respect to the exterior annular element 82 due to high-intensity friction between the surfaces in contact.

(22) In this regard, it is indicated that the assembly 70 could be equipped with means 114 of detecting the relative position between the two elements 82, 84. These means 114, easily installed at the decoupling interface 86, would allow in particular ensuring the absence of relative movement between the two elements 82, 84 apart from extreme situations such as the loss of a fan blade.

(23) On the other hand, in the event of an exceptional problem leading to the loss of one or more fan blades, the calibrated screws 66 are designed to break due to the observed imbalance. This implies that the front rolling-element bearing 12a is not correctly guided by the support 14a. During this decoupling of the front rolling-element bearing 12a, bending is created in the drive shaft 8, and hence a decoupling moment which is transmitted by this shaft to the rolling-element bearing 12b, which then undergoes not only the decoupling moment but also considerable radial loads. As illustrated in FIG. 7, the radial loads allow deformation of the exterior ring, the two rings of which, 96, 98 have a tendency to undergo movement comparable to pivoting with respect to the central portion 73, thus causing a kind of closure or squeezing of the exterior ring 72. This deformation, shown schematically by the arrows 116 and made possible by the hollowed space 106 which fills as the deformation progresses, has as its consequence a separation of the two contact points 103, 104 between the balls 76 and the two rings 96, 98. Thanks to this separation of two points of contact 103, 104, the angular stiffness of the rolling-element bearing 12b is increased. The rolling-element bearing 12b becomes capable, in an extremely short period following the fan blade loss, of having a sufficiently high angular stiffness to withstand and transmit the decoupling moment to the interior annular element 84. This causes the movement of the latter with respect to the exterior annular element 82. This desired mechanical decoupling is observed when the decoupling moment Md becomes greater than the moment of the frictional resistance at the decoupling interface 86. At this state, as shown in FIG. 8, the interior annular element 84 has therefore been pivoted with respect to the exterior annular element 82. The dissipated energy resulting from the relative displacement between the two elements 82, 84 guarantees the absence of the transmission of possibly destructive forces within the structure of the turbojet.

(24) It is noted that in this embodiment, decoupling at the two rolling element bearings 12a, 12b occurs extremely rapidly and substantially simultaneously. However, a slight temporal offset can be observed between these two decouplings, in particular when the support 14b of the intermediate rolling-element bearing 12b is not attached to the stator by calibrated fusible screws 66 serving to attach the other support 14a of the front rolling-element bearing 12a.

(25) Of course, various modifications can be applied by a person skilled in the art to the invention which has just been described, solely by way of non-limiting examples.