Module for an aircraft turbine engine, the module comprising a circuit for supplying oil to the lubrication chamber

Abstract

The invention relates to a module (30) for an aircraft turbine engine (10), this module (30) comprising: • - a lubrication chamber (38) for a bearing (44, 46), and • - a circuit (40) for supplying oil to the chamber (38), this circuit (40) comprising an oil distributor (48) and at least one oil line (50), the oil distributor (48) being rigidly connected to the casing (36) and comprising at least one oil inlet (48a) and at least one first oil outlet (48b), the distributor (48) comprising a member (60) that is movable from a first position in which it allows fluid communication between the inlet (48a) and the outlet (48b), and a second position in which it prevents fluid communication between the inlet (48a) and the outlet (48b). The distributor (48) is further configured so that the end (50a) of the line (50) bears on the member (60) and holds it in its first position in normal operation when the end (50a) of the line (50) is connected to the outlet (48a) of the distributor (48), and so that the member (60) assumes its second position when frangible bolts (42) have broken and when the end (50a) of the line (50) no longer bears on the member (60), the member (60) including a central bore (76) that extends over the entire length of the member (60) to ensure balanced pressure at both ends of the member (60).

Description

[0001] DESCRIPTION

[0002] MODULE FOR AN AIRCRAFT TURBOMACHINE WITH OIL SUPPLY CIRCUIT FOR THE LUBRICATION CABINET

[0003] Technical field of the invention

[0004] The present invention relates to a module for an aircraft turbomachine, as well as a turbomachine comprising such a module.

[0005] Technical background

[0006] The prior art includes in particular the document EP-B1-2 721 260, FR-A1- 2 824 127, FR-A1-2 831 624, EP-A1-1 662 636, US-A1-6,312,215 and EP-B1- 2 971 688.

[0007] An aircraft turbomachine includes a gas generator which classically 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.

[0008] In the case of a twin-spool turbofan engine, with low-pressure and high-pressure components respectively, the gas generator comprises, successively, a low-pressure compressor, a high-pressure compressor, the combustion chamber, a high-pressure turbine, and a low-pressure turbine. The gas generator defines a first annular flow path of gas, called the primary flow, which passes through the compressors, the combustion chamber, and the turbines.

[0009] The high-pressure compressor rotor is connected to the high-pressure turbine rotor by a high-pressure shaft. The low-pressure compressor rotor is connected to the low-pressure turbine rotor by a low-pressure shaft that passes through the high-pressure shaft and drives a propeller shaft, typically located upstream of the gas generator.

[0010] When this propeller is enclosed and therefore surrounded by an annular casing, this propeller is called a blower and generates an airflow, called secondary flow, which flows around the gas generator.

[0011] The propeller shaft and the low-pressure shaft are guided by bearings housed within a lubrication chamber. This chamber is surrounded by the first lubrication channel and is at least partially defined by bearing supports. A first rolling bearing located upstream is supported by a first bearing support, and a second rolling bearing located downstream is supported by a second bearing support. These bearing supports have radially oriented annular flanges that are axially pressed against each other and against an annular flange on a stator housing.

[0012] The lubrication chamber is designed to lubricate the bearings and maintain an oily atmosphere around them. Oil is supplied to the chamber via a supply circuit.

[0013] The propeller includes blades that are susceptible to breakage, although this is extremely rare. In such a case, a significant imbalance occurs on the propeller shaft, generating cyclic loads and vibrations that the upstream bearing transmits to the stator, with a considerable risk of damage.

[0014] To limit the forces transmitted to the stator in the presence of significant imbalance, a shear screw decoupling device is described in document FR-A1-2 831 624. In practice, the second bearing support is fixed to the stator housing by non-shear screws, and the first bearing support is fixed to the second bearing support by shear screws to form a connection that can be broken.

[0015] These so-called "fuse" screws, whose operation is fully described in the aforementioned document, have a reduced cross-section portion that is likely to break beyond a predetermined mechanical tensile force and thus achieve the decoupling of the bearing supports.

[0016] In this situation of shear screw failure, the first bearing support is no longer axially restrained. It moves axially upstream and therefore moves axially away from the second bearing support. This is especially true when the bearing supported by the first bearing support is a roller bearing, which does not provide axial restraint to the bearing support when it is separated from the second bearing support.

[0017] This phenomenon is problematic because the housing continues to be supplied with oil by the aforementioned circuit, and the oil accumulating within it is likely to pass through the annular passage formed between the bearing support flanges, which have moved axially apart. The oil then spills into the engine, generating contamination. This oil can reach the primary air intake, from which air is drawn to supply the aircraft equipped with the turbomachine. There is therefore a risk that the aircraft will be supplied with polluted air, or even with unpleasant fumes and odors. The invention relates to a technical solution aimed at eliminating the risk of oil leakage into the primary air intake after the bearing supports are decoupled from the lubrication housing.

[0018] Summary of the invention

[0019] The invention relates to a module for an aircraft turbomachine, this module comprising:

[0020] - a first annular bearing support extending around an axis and comprising a first annular fixing flange,

[0021] - a second annular bearing support extending around the axis and comprising a second annular fixing flange, the first and second flanges being suitable for axial application against each other and for being fixed together by shear screws,

[0022] - an annular housing that extends around the axis, the second bearing support being fixed to the housing,

[0023] - a lubrication enclosure which is at least partially delimited by the first bearing support, this lubrication enclosure containing a first bearing supported by the first bearing support and a second bearing supported by the second bearing support, and

[0024] - an oil supply circuit for the enclosure, this circuit comprising an oil distributor and at least one oil line, the oil distributor being integral with the crankcase and comprising at least one oil inlet and at least one first oil outlet, the oil line being integral with the first bearing support and comprising one end connected to the first oil outlet of the distributor for the purpose of circulating oil from said inlet to the line via said outlet, said end of the line being capable of being connected by male-female engagement in the axial direction with said outlet of the distributor and of being in fluidic communication with this outlet when the first and second flanges are applied axially against each other, the distributor comprising a body having an internal cavity which is connected to said inlet and to said first outlet,the distributor further comprising a member housed in said cavity and movable from a first position in which it permits fluid communication between the inlet and outlet, and a second position in which it prohibits fluid communication between the inlet and outlet, the distributor being further configured such that the end of the pipe bears against the member and maintains it in its first position in normal operation when the end of the pipe is connected to the outlet of the distributor, and that the member adopts its second position when the shear screws have broken, and the end of the pipe is no longer bearing against the member, the member comprising a central bore which extends over the entire length of the member to ensure pressure equalization at both ends of the member.

[0025] Under normal operation, shear bolts ensure the axial retention of the first bearing support relative to the second bearing support. If the shear bolts break, the bearing supports separate and move axially apart. This axial displacement of the first bearing support, away from the second bearing support, can cause the oil line to disconnect from the oil distributor. Consequently, the component within the distributor moves, as it is no longer held in its initial position by the end of the oil line. The component then moves from its initial position to its second position. The oil line and housing are then no longer supplied with oil, thus limiting the risk of oil accumulation at the bottom of the housing and contamination of the engine's first oil passage.

[0026] The module according to the invention may comprise one or more of the following features, taken individually or in combination with each other:

[0027] - said end of the pipe is capable of being disconnected from said outlet and of no longer being in fluidic communication with this outlet when the shear screws have broken and the first and second flanges are axially separated from each other,

[0028] - when the component adopts its second position, the end of the pipe is disconnected (totally or partially) or not from the distributor outlet;

[0029] - the organ is forced into its second position by a returning element such as a spring;

[0030] - the organ has a general shape of alternator;

[0031] - the organ includes an external annular groove which is in fluidic communication with said inlet of the distributor;

[0032] - said central bore ensures fluid communication between the groove and the first outlet of the distributor; - the distributor includes a second oil outlet which is connected to another line or to an oil jet;

[0033] - when the organ is in its first position, it allows fluidic communication between the inlet and each of the first and second outlets, and when the organ is in its second position, it prohibits fluidic communication between the inlet and each of the first and second outlets;

[0034] - when the organ is in its first position, the throat is in fluidic communication with each of the outlets, and when the organ is in its second position, the throat is no longer in fluidic communication with each of the outlets;

[0035] - said pipe passes through an axial passage of the second bearing support;

[0036] - the flange of the second bearing support is axially interposed between the flange of the first bearing support and another flange of the housing;

[0037] - the flange of the second bearing support is fixed to the flange of the casing by non-shear screws;

[0038] -- the distributor is of the hydraulic type;

[0039] -- the first outlet of the distributor is oriented in an axial direction, in particular towards the first bearing support, and preferably upstream.

[0040] The present invention also relates to an aircraft turbomachine, comprising at least one module as described above.

[0041] Brief description of the figures

[0042] 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 attached drawings in which:

[0043] [Fig.1] Figure 1 is a schematic half-view in axial cross-section of part of an aircraft turbomachine,

[0044] [Fig. 2] Figure 2 is a partial schematic axial cross-sectional view of a bearing lubrication chamber,

[0045] [Fig. 3] Figure 3 is a larger-scale view of a portion of Figure 2 and shows a decoupling device comprising fusible screws, here unbroken; [Fig. 4] Figure 4 is a view similar to that of Figure 3 and shows the decoupling device with fusible screws, here broken; [Fig. 5] Figure 5 is a highly schematic axial cross-sectional view of an oil distributor comprising a movable element located in a first position, and illustrates an embodiment of the invention.

[0046] [Fig.6] Figure 6 is a view similar to that of Figure 5 and shows the oil distributor with the moving part located in a second position.

[0047] Detailed description of the invention

[0048] Figure 1 shows a turbomachine 10 for an aircraft, this turbomachine 10 being here a twin-spool turbojet.

[0049] Axis A designates the longitudinal axis of the turbomachine.

[0050] The turbomachine 10 comprises a gas generator 12 which includes, from upstream to downstream with reference to the gas flow along axis A, a low-pressure (LP) compressor 14, a high-pressure (HP) compressor, an annular combustion chamber, a high-pressure (HP) turbine, and a low-pressure (LP) turbine. The turbomachine 10 is partially shown, and only the LP compressor 14 is depicted in the drawing.

[0051] Although not visible in Figure 1, the HP compressor rotor is connected to the HP turbine rotor by a high-pressure shaft, and the LP compressor rotor 14 is connected to the LP turbine rotor by a low-pressure shaft which passes through the high-pressure shaft and drives a propulsion propeller, called a blower 16, located upstream of the gas generator 12 and surrounded by an annular casing called a blower casing 18.

[0052] The blower housing 18 is connected to the gas generator 12 by an intermediate housing 20 which includes a central hub 22 and a series of radial arms 24 connecting the hub 22 to the blower housing 18.

[0053] The gas generator 12 defines a main annular flow channel V1 for a first air flow, called the primary flow F1. The gas generator 12 is surrounded by a secondary annular flow channel V2 for a second air flow, called the secondary flow F2.

[0054] The airflow F entering the blower 16 splits into two parts: one forming the primary flow F1, and the other the secondary flow F2, which is then mixed with fuel and burned in the combustion chamber. The combustion gases from the primary flow are subsequently expanded in the HP and BP turbines and finally exit through an exhaust nozzle. The remaining portion of the airflow entering the blower 16 forms the secondary flow F2 and is intended to be mixed with the primary flow F1 downstream of the nozzle.

[0055] Figure 1 further shows a module 30 of the turbomachine, this module 30 comprising annular bearing supports 32, 34, an annular housing 36, a lubrication chamber 38 and an oil supply circuit 40 for the chamber 38.

[0056] A first annular bearing support 32 extends around the axis A and includes a first annular fixing flange 32a, more clearly visible in figure 2.

[0057] A second annular bearing support 34 extends around the axis A and includes a second annular fixing flange 34a. The flanges 32a, 34a extend radially outwards and are suitable for being applied axially against each other and fixed together by screws 42 which are shear-off and more clearly visible in figures 2 to 4.

[0058] An annular housing 36 extends around axis A, and the second bearing support 34 is fixed to this housing 36 by screws that are not shear bolts and are not shown in the drawings. The shear bolts 42 and the non-shear bolts may be located on the same circumference centered on axis A. The housing 36 may be the intermediate housing 20 of Figure 1 or another housing fixed to or integral with this intermediate housing 20.

[0059] The housing 36 includes a flange 36a onto which the flange 34a is applied and secured by the aforementioned non-sheathable screws. The flange 34a of the second bearing support 34 is axially interposed between the flange 32a of the first bearing support 32 and the flange 36a of the housing 36, as illustrated in Figures 2 to 4.

[0060] The lubrication enclosure 38 is at least partly delimited by the first bearing support 32 and contains a first bearing 44, or upstream bearing, carried by the first bearing support 32, and a second bearing 46, or downstream bearing, carried by the second bearing support 34.

[0061] In the example shown, the upstream bearing 44 is a roller bearing and the downstream bearing 46 is a ball bearing.

[0062] Furthermore, in the example shown, the first bearing support 32 has a generally annular shape and is elongated along axis A. It comprises an upstream end carrying the rolling bearing 44 and a downstream end connected to the flange 32a. The second bearing support 34 has a generally annular and radial shape and comprises a radially internal end carrying the downstream bearing 46 and a radially external end connected to the flange 34a. The oil supply circuit 40 for the housing 38 is more clearly visible in Figure 2 and includes an oil distributor 48 and at least one oil line 50. The oil distributor 48 is integral with the housing 36 and includes at least one oil inlet 48a and at least one first oil outlet 48b.

[0063] The oil inlet 48a is suitable for connection to an oil reservoir not shown.

[0064] The oil line 50 is integral with the first bearing support 32 and has an end 40a, here downstream, connected to the first oil outlet 48b of the distributor 48 for the purpose of circulating oil from said inlet 48a to said at least one outlet 48b.

[0065] In the example shown, the distributor 48 comprises two oil outlets 48b and 48c: the first oil outlet 48b mentioned above and a second oil outlet 48c. The second oil outlet 48c can be connected to another line or to an oil nozzle 52, as illustrated in the drawing. The nozzle 52 sprays oil onto the downstream bearing 46, while the line 50 connected to the first outlet 48b of the distributor 48 supplies oil to the upstream bearing 44 for lubrication.

[0066] Preferably, the first outlet 48b is oriented axially, specifically towards the first bearing support 32, i.e., upstream in this case. The second outlet 48c can be oriented radially inwards.

[0067] Figures 2 to 4 further show that the conduit 50 includes a part which extends axially and which passes through an axial orifice 54 of the second bearing support 34. The conduit 50 is radially interposed between the downstream bearing 46 and the flanges 32a, 34a of the bearing supports 32, 34.

[0068] Figure 3 shows the default and normal operating case in which the flanges 32a of the bearing supports 32 are applied axially to each other and fixed together by the shear screws 42.

[0069] As mentioned above, in the event of imbalance and vibrations, the shear screws 42 are liable to break as illustrated in figure 4. The flange 32a of the first bearing support 32, and in particular the first bearing support 32 as a whole, is then no longer axially retained and moves axially away from the second bearing support 32. The first bearing support 32 then moves upstream which creates an annular passage 56 between the flanges 32a, 34a of the bearing supports 32, 34.

[0070] The oil supplied by distributor 48 continues to flow into the enclosure and accumulates there. This oil is then likely to flow by gravity through passage 56 and can reach the primary vein V1, which is problematic as mentioned above.

[0071] The present invention offers a simple, effective and economical solution to this problem.

[0072] The invention first proposes a particular distributor 48, one embodiment of which is illustrated in figures 5 and 6.

[0073] The oil distributor 48 has its first outlet 48b which is suitable to be connected to the end 50a of the line 50 by male-female engagement in the axial direction or any equivalent solution permitting mutual clearance to disconnection between said first outlet 48b and said end 50a of the line 50.

[0074] When the end 50a of the pipe 50 is engaged in the outlet 48b of the distributor 48, or vice versa, the outlet 48b and the inlet 48a of the distributor 50 are in fluidic communication with each other (Figure 5). This scenario corresponds to the default configuration and normal operation in which the flanges 32a, 34a of the bearing supports 32, 34a are axially pressed against each other and secured together by the shear screws 42.

[0075] When the end 50a of the pipe 50 is disengaged, totally or partially, from the outlet 48b of the distributor 48, each outlet 48b, 48c and the inlet 48a of the distributor 48 are no longer in fluidic communication with each other (Figure 6). This scenario corresponds to the situation in which the shear screws 42 have broken and the flanges 32a, 34a of the bearing supports 32, 34 are axially separated from each other.

[0076] Fluid communication between the inlet 48a and the outlets 48b, 48c of the distributor 48 is allowed or prohibited by means of a movable element 60 in the distributor 48 so as to constitute a distributor spool.

[0077] The distributor 48 comprises a body 62 having an internal cavity 64 which is connected to the inlet 48a and the outlets 48b, 48c. The member 60 is housed in the cavity 64 and is movable in this cavity 64 from a first position in which it allows fluidic communication between the inlet 48a and the outlets 48b, 48c (figure 5), and a second position in which it prohibits fluidic communication between the inlet 48a and the outlets 48b, 48c (figure 6).

[0078] The distributor 48 is further configured so that the member 60 adopts its first position in normal operation when the end 50a of the pipe 50 is connected to the outlet 48b of the distributor 48 and that this end 50a is in contact with the member 60 to hold it in its first position (figure 5).

[0079] The component 60 assumes its second position when the shear screws 42 have broken and the end 50a of the pipe no longer presses against and holds the component 60 in its first position. The end 50a of the pipe 50 can then be disconnected from the outlet 48b of the distributor 48. The component 60 then moves into its second position (Figure 6).

[0080] In other words, the operation of the distributor 48 is mechanical. In normal operation (the line 50 is engaged in the outlet 48b - figure 5), the element 60 is mechanically held in its first position by the line 50. In the event of breakage of the shear screws 42 (the line 50 disengages totally or partially from the outlet 48b - figure 6), the element 60 is no longer mechanically held by the line 50 and moves in the distributor 48 from its first to its second position.

[0081] Figures 5 and 6 show that the component 60 is forced into its second position by a return element 70, such as a spring. In practice, the component 60 can be mounted freely between the return element 70 on one side and the pipe 50 on the other. It is therefore clear that, when assembling the module 30, inserting the end 50a of the pipe 50 into the outlet 48b of the distributor is sufficient to move the component 60 into its first operating position. This insertion will compress the return element 70.

[0082] The component 60 may have a general shape resembling a dumbbell, as illustrated in the drawings, and may include an internal annular groove 74 substantially in its middle. The inlet 48a of the distributor 48 preferably opens into this groove 74.

[0083] The second outlet 48c can open into the groove 74 when the organ 60 is in its first position (figure 5), and may not open into the groove 74 when the organ 60 is in its second position (figure 6).

[0084] The first outlet 48b can be connected to the inlet 48a by a central bore 76 of the member 60 which ensures fluidic communication between the groove 74 and the first outlet 48b of the distributor 48. The central bore 76 also ensures communication between the two cavities 64 in order to axially cancel the pressure forces.

[0085] It is therefore understood that the invention makes it possible to stop the oil supply to the enclosure 38 when a breakage of the fusible screws 42 occurs.

Claims

DEMANDS 1. Module (30) for an aircraft turbomachine (10), this module (30) comprising: - a first annular bearing support (32) which extends around an axis (A) and which includes a first annular fixing flange (32a), - a second annular bearing support (34) which extends around the axis (A) and which includes a second annular fixing flange (34a), the first and second flanges (32a, 34a) being applied axially against each other and fixed to each other by shear screws (42), - an annular housing (36) which extends around the axis (A), the second bearing support (34) being fixed to the housing (36), - a lubrication chamber (38) which is at least partially delimited by the first bearing support (32), this lubrication chamber (38) containing a first bearing (44) carried by the first bearing support (32) and a second bearing (46) carried by the second bearing support (34), and - an oil supply circuit (40) for the enclosure (38), this circuit (40) comprising an oil distributor (48) and at least one oil line (50), the oil distributor (48) being integral with the housing (36) and comprising at least one oil inlet (48a) and at least one first oil outlet (48b), the oil line (50) being integral with the first bearing support (32) and comprising an end (50a) connected to the first oil outlet (48b) of the distributor (48) for the circulation of oil from said inlet (48a) to the line (50) via said outlet (48b), said end (50a) of the line (50) being connected by male-female engagement in the axial direction with said outlet (48b) of the distributor (48) and in fluidic communication with this outlet (48b) when the first and second flanges (32a, 34a) are applied axially against each other,the distributor (48) comprising a body (62) having an internal cavity (64) which is connected to said inlet (48a) and to said first outlet (48b), the distributor (48) further comprising a member (60) housed in said cavity (64) and movable from a first position in which it permits fluidic communication between the inlet (48a) and the outlet (48b), and a second position in which it prohibits fluidic communication between the inlet (48a) and the outlet (48b), the distributor (48) being further configured so that the end (50a) of the line (50) bears against the member (60) and maintains it in its first position in normal operation when the end (50a) of the line (50) is connected to the outlet (48a) of the distributor (48), and that the member (60) adopts its second position when the shear screws (42) have broken, and that the end (50a) of the line (50) is no longer bearing against the member (60), the member (60) comprising a central bore (76) which extends over the entire length of the member (60) to ensure pressure balancing at both ends of the member (60).

2. Module (30) according to claim 1, wherein the member (60) is forced into its second position by a return element (70) such as a spring.

3. Module (30) according to claim 1 or 2, wherein the component (60) has a general shape of alternator.

4. Module (30) according to any one of the preceding claims, wherein the member (60) comprises an external annular groove (74) which is in fluidic communication with said inlet (48a) of the distributor (48).

5. Module (30) according to the preceding claim, wherein said central bore (76) ensures fluidic communication between the groove (74) and the first outlet (48b) of the distributor (48).

6. Module (30) according to any one of the preceding claims, wherein the distributor (48) includes a second oil outlet (48b) which is connected to another line (50) or to an oil nozzle (52).

7. Module (30) according to the preceding claim, wherein, when the member (60) is in its first position, it permits fluidic communication between the inlet (48a) and each of the first and second outlets (48b, 48c), and when the member (60) is in its second position, it prohibits fluidic communication between the inlet (48a) and each of the first and second outlets (48b, 48c).

8. Module (30) according to the preceding claim depending on claim 4 or 5, wherein, when the member (60) is in its first position, the groove (74) is in fluidic communication with each of the outlets (48b, 48c), and when the member is in its second position, the groove (74) is no longer in fluidic communication with each of the outlets (48b, 48c).

9. Module (30) according to any one of the preceding claims, wherein said conduit (50) passes through an axial passage (54) of the second bearing support (34).

10. Module (30) according to any one of the preceding claims, wherein the flange (34a) of the second bearing support (34) is axially interposed between the flange (32a) of the first bearing support (32) and another flange (36a) of the housing (36).

11. Module (30) according to any one of the preceding claims, wherein the flange (34a) of the second bearing support (34) is fixed to a flange (36a) of the housing (36) by non-fusible screws.

12. Turbomachine for an aircraft, comprising at least one module (30) according to one of the preceding claims.

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