Filling the lubricant tank of an aircraft turbine engine

Abstract

A twin-flow turbine engine (10) comprising: - at least one lubricant tank (40), the at least one lubricant tank being located in an annular space of a turbine engine body, - at least one hatch (46), the at least one hatch being arranged on an outer fairing (32) of a nacelle for filling the tank, the tank being configured to be filled by a removable tubular pipe (50) inserted from the hatch through the barrel into the tank, one of the barrels comprising a first interface (44), the pipe being configured to pass through the first interface, and the other of the barrels comprising a second interface (42) for connecting the pipe to the tank.

Description

Technical Field

[0001] The invention relates in particular to an aircraft turbine engine comprising a lubricant tank and to a method of filling the tank with lubricant. Background Art

[0002] In a conventional manner, a twin-flow turbine engine comprises a gas generator surrounded by a nacelle. A fan is located upstream of the gas generator and generates an airflow which is divided into a primary flow flowing inside the gas generator (through the compression stage, the combustion chamber and the turbine stage) and a secondary flow flowing between the gas generator and the nacelle.

[0003] The turbine engine is equipped with at least one lubricant tank for supplying lubricant, in particular oil, in particular to bearings of the turbine engine.

[0004] The lubricant tank is usually installed in a compartment of the nacelle, i.e. in a compartment defined externally by an external fairing of the nacelle. This compartment of the nacelle is defined internally by an external engine casing, formed, for example, by an assembly of a fan casing (also called a fan cowl) and an external intermediate casing shroud (also called VCI), which surrounds the gas generator and defines externally a duct for the flow of the secondary flow. The roughly annular space between the external fairing of the nacelle and the engine casing formed by the VCI and the fan casing is called the fan compartment and enables the storage of a plurality of equipment items of the turbine engine, such as the relatively large tanks described above. The positioning of the tank in this space facilitates access to the tank, since it is sufficient to provide a direct access hatch on the fairing or to dismantle a portion of the fairing in order to access the tank, for example for maintenance operations such as filling the tank.

[0005] In future architectures, the search for reducing the fuel consumption of the engine is moving in the direction of increasing the bypass ratio of the engine. This is the case with the preliminary design of an engine known as an ultra high bypass ratio (UHBR), in which the fan diameter of the engine is much larger than that of a conventional engine. The increase in fan diameter leads to an increase in the size of the nacelle, resulting in an increase in the aerodynamic losses caused by the nacelle (increased front surface and wetted surface). Therefore, the refinement of the lines of the nacelle is particularly important for this type of engine architecture. Reducing the height between the outer fairing of the nacelle and the engine case formed by the assembly of the VCI and the fan case (i.e., reducing the radial thickness of the fan compartment) requires shifting bulky equipment items from the compartment toward other locations on the turbine engine.

[0006] The study showed that there is a strong interest in arranging the lubricant tank in the engine compartment of the gas generator, i.e. in the venous compartment (or space) between the primary and secondary ducts of a twin-flow turbine engine, and in particular in the upstream region of this engine compartment (called the "booster" compartment), because this engine compartment is located substantially in line with the low-pressure compressor (booster) of the turbine engine. The first advantage is associated with the fact that the tank is located as close as possible to the lubrication unit of the turbine engine, and thus limits the length of the oil path between these elements. Another advantage is that the booster compartment is cooler and smaller than the rest of the engine compartment. Compared with the area downstream of the engine, especially the area near the turbine, the ambient temperature in the booster compartment is more conducive to the use of an electronic oil level sensor in the tank. Compared with the rest of the inter-duct space (also called the core area) in a twin-flow turbine engine, this thermal environment also contributes to a smaller and less expensive design of the tank and its supporting components.

[0007] The problem with this installation environment in the engine compartment is that the lubricant tank must be supplied from the outside ("under the wing") by a maintenance technician.

[0008] In the case of tanks known as "conventional", i.e. tanks equipped with a filling hole located on the tank itself, the filling operation is complicated because the tank, located in the engine compartment, is difficult to access. Indeed, due to its location inside the turbine engine, the tank and its filling hole are located inside several coaxial layers, such as the fan cover, the thrust reverser cover (possibly fixed to the UHBR architecture), the external shroud of the intermediate casing (also known as VCI) and the cowling of the engine package, the most central part of the environment.

[0009] Access to the filling hole in this case is problematic, since the filling operation must be completed in a very short time, and the openings of the fan cover and thrust reverser are not designed for this type of operation. The "number of layers" and the large diameter of the UHBR make it difficult to reach the tank from the outside. In addition, the filling operation must be able to be performed blindly, i.e. the operator may have to inject a predetermined amount of oil without having to obtain an indication of the filling level.

[0010] In document FR-A1-3 072 425, the Applicant proposes a solution that makes it possible to fill a tank located inside a turbine engine without opening the cover constituting the nacelle. The prior art also includes documents FR-A1-3 082 552 and FR-A1-3 079 873.

[0011] The present invention provides a simple, effective and economical alternative solution to the above problems. Summary of the invention

[0012] The present invention provides a dual-flow turbine engine, comprising:

[0013] - Gas generator,

[0014] - a nacelle surrounding the gas generator,

[0015] - an arm for connecting the gas generator to the nacelle,

[0016] an annular duct for the main flow, the duct being formed in the gas generator and being delimited externally by a first annular housing of the gas generator,

[0017] an annular duct for the flow of the secondary flow, the duct being formed between the gas generator and the nacelle and being delimited internally by a second annular housing of the gas generator and externally by a third annular housing surrounding the nacelle, the second housing and the third housing being connected together by at least some of the arms,

[0018] at least one lubricant tank, the at least one lubricant tank being located in an annular space extending between the first housing and the second housing,

[0019] - at least one hatch, at least one hatch provided on the outer fairing of the nacelle, for filling said tank,

[0020] Characterized in that the tank is constructed to be filled by a removable tubular pipe inserted into the tank from the hatch, the third shell includes a first interface constructed to be passed through by the pipe, and the second shell includes a second interface for connecting the pipe to the tank.

[0021] The invention thus proposes a simple solution for filling a lubricant tank located in the engine compartment. The filling is done through a pipe. The filling pipe has an elongated shape and is tubular. The filling pipe has a proximal end equipped with, for example, a funnel, into which the lubricant contained in a container is poured. The pipe also has a distal end, which is intended to be connected to the tank 40 so that the lubricant flows by gravity through the pipe and into the tank. The pipe passes through a number of layers as described above. On the one hand, the pipe passes through a hatch of the nacelle, which hatch can be of small dimensions considering the relatively small cross-section of the pipe. The pipe then passes through a first interface of a third housing to pass through a secondary duct, i.e. a duct of the secondary flow of a twin-flow turbine engine. This third housing can be a shroud of an intermediate housing. The pipe then reaches a second interface for connecting the pipe to the tank. The second interface is located on a second housing, which can be a panel of an engine kit of a turbine engine. The pipe is removable and is taken out after each filling.

[0022] One of the advantages of the invention is that after filling the tank and removing the tubing, the tubing for flowing the secondary flow is not affected. The first interface enables the tubing to be guided during insertion and the second interface ensures fluid connection with the tank without risk of leakage into the tubing.

[0023] The turbine engine according to the invention may include one or more of the following features, which may be taken independently of one another or in combination with one another:

[0024] - the first and second interfaces are located directly in the conduit for the flow of the secondary flow;

[0025] - said first interface comprises a telescopic guide system comprising a plurality of elements mounted coaxially and slidably inside each other, the system being suitable for being passed through by the pipe and being suitable for adopting a first retracted position in which the system has a minimum length or thickness and does not protrude into the conduit for the flow of the secondary flow, and a second extended position in which the system has a maximum length or thickness and protrudes into the conduit for the flow of the secondary flow towards the second interface;

[0026] - The second interface comprises a connection device, the connection device comprising:

[0027] an end piece configured to cooperate with a complementary end piece on the distal end of the pipe by male-female nesting, and

[0028] - an opening mechanism for opening the can when the nesting is effective;

[0029] - said opening mechanism comprises at least one part, at least one part being movable from a closed position of the can to an open position, the movable part being biased by an elastic member into the closed position of the movable part and being brought into the open position of the movable part by said male-female nesting;

[0030] - the second interface comprises a guiding and locking element configured to cooperate with an element complementary to the end piece on the pipe by a bayonet effect;

[0031] - the hatch is located upstream of the thrust reverser cover of the turbine engine;

[0032] - the tank has a generally curved shape and extends partially around the longitudinal axis of the turbine engine;

[0033] --The or each tank is substantially in line with the low pressure compressor of the gas generator.

[0034] The invention also relates to an assembly comprising a turbine engine as described above and a removable tubular duct for filling the tank, the duct being configured to pass through the first interface and to be connected to the tank through the second interface.

[0035] Advantageously, the pipe comprises a distal end provided with an end piece configured to cooperate with a complementary end piece of a second interface by male-female nesting, the end piece being provided with a gate device arranged to open the distal end of the pipe when the nesting is effective and to close the distal end when the end piece and the complementary end piece are disengaged from each other.

[0036] Preferably, the duct comprises at least one member movable between a retracted position along the duct and an extended position extending from the duct, the movable member being adapted to cooperate with the system to force the system to be retracted when the duct is removed from the turbine engine.

[0037] In one embodiment, the first interface is formed by an opening arranged in the third shell, the hatch includes a movable member for closing the hatch, the hatch is equipped with a gate, which is arranged to close the opening when the hatch is closed, and the pipeline is associated with a guide system, which is arranged to be installed at the position of the hatch once the hatch is opened and to be unloaded once the tank is filled.

[0038] The invention also relates to a method for filling a lubricant tank in an aircraft turbine engine by means of an assembly as described above, wherein the method comprises the following steps:

[0039] - Open the hatch of the engine room,

[0040] - Pass the pipe through the hatch and then insert it through the first interface,

[0041] - passing the pipe through the conduit for the flow of the secondary stream to a second interface for connecting the pipe to the tank, and

[0042] - The lubricant is caused to flow from the proximal end of the duct located outside the turbine engine to the distal end of the duct and to the tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] The invention will be better understood and other details, features and advantages of the invention will become more apparent in the following description made by way of non-limiting example and with reference to the accompanying drawings, in which:

[0044] [ Figure 1 ] Figure 1 is a very schematic front view of a turbine engine,

[0045] [ Figure 2 ] Figure 2is a very schematic axial cross-sectional view of a turbine engine,

[0046] [ Figure 3 ] Figure 3 is a schematic perspective view of the propulsion assembly,

[0047] [ Figure 4 ] Figure 4 Yes Figure 3 A partial schematic perspective view of a turbine engine of a propulsion assembly is shown,

[0048] [ Figure 5 ] Figure 5 is a very schematic cross-sectional view of the different layers that a filling pipe must pass through to reach a lubricant tank located in the engine compartment of a turbine engine,

[0049] [ Figure 6 ] Figure 6 is similar to Figure 5 and showing the steps of a method for filling a tank, the steps comprising inserting a pipe through the hatch and the first interface,

[0050] [ Figure 7 ] Figure 7 is similar to Figure 5 and showing a further step of the method for filling a tank, which step comprises connecting a pipe to a second interface and to the tank,

[0051] [ Figure 8 ] Figure 8 is a very schematic enlarged view of the connection between the pipe and the tank,

[0052] [ Figures 9 to 11 ] Figures 9 to 11 is similar to Figure 8 and showing the filling steps of the tank,

[0053] [ Fig.12 ] Fig.12 is similar to Figure 5 and showing an alternative embodiment of the filling conduit,

[0054] [ Figures 13 to 15 ] Figures 13 to 15 is similar to Fig.12 and showing the steps of removing the pipe and storing the first interface after filling the tank,

[0055] [ Fig.16 ] Fig.16 is similar to Figure 8 and showing a variant embodiment of a fluid connection between the pipeline and the second interface,

[0056] [ Fig.17 ] Fig.17 is a very schematic view of an optimized cross-sectional profile of a recess of a housing,

[0057] [ Fig.18 ] Fig.18 is similar to Figure 5 and showing an alternative embodiment of the present invention,

[0058] [ Fig.19 ] Fig.19 yes Fig.18 and showing the steps of a method for filling a tank, the steps comprising inserting a pipe through the hatch and the first interface, and

[0059] [ Fig. 20 ] Fig. 20 yes Fig.18 and shows a further step of the method for filling a tank, which step comprises connecting a pipe to a second interface and the tank. DETAILED DESCRIPTION

[0060] Figure 1 and Figure 2 An aircraft turbine engine 10 of the dual-flow type is schematically shown. The turbine engine 10 substantially comprises two parts, namely a gas generator 12 having a generally elongated shape along a longitudinal axis X and a nacelle 14 surrounding the gas generator 12 .

[0061] The gas generator 12 is not shown in detail. Typically, the gas generator includes two rotating bodies, namely a low pressure (BP) body and a high pressure (HP) body. Each body includes a compressor rotor and a turbine rotor. The gas generator includes a BP compressor, an HP compressor, a combustion chamber, an HP turbine and a BP turbine from upstream to downstream in the direction of gas flow. The rotor of the HP compressor and the rotor of the HP turbine are connected to each other through the HP shaft to form the HP body, and the rotor of the HP compressor and the rotor of the HP turbine are respectively located upstream and downstream of the combustion chamber. The rotor of the BP compressor and the rotor of the BP turbine are connected to each other through the BP shaft to form the BP body, and the rotor of the BP compressor and the rotor of the BP turbine are respectively located upstream of the HP compressor and downstream of the HP turbine. The BP shaft also drives the fan rotor 16 located on the upstream side of the gas generator directly or through a reducer.

[0062] The gas generator 12 includes a duct for flowing the main flow or hot flow through the compressor, combustion chamber and turbine. The duct, which is called the main duct, is usually defined by an annular casing 18 inside and an annular casing 20 outside, in particular, the blades of the compressor and turbine extend between the annular casings 18 and 20. The annular casing 20 that defines the duct outside is itself surrounded by an annular casing 22 at a distance, and the annular casing 22 defines the secondary duct of the dual-flow turbine engine 10 inside. The annular casing 22 can be composed of a cover and / or a panel. The casings 20 and 22 are radially spaced from each other, and an annular space 24 is defined between the casings 20 and 22, which is called the inter-duct space or engine compartment. The casings 20 and 22 can form an assembly at the BP and HP compressors, which is usually called the intermediate casing hub.

[0063] The gas generator 12 is surrounded by an annular fan housing 26 which extends around the fan rotor 16 and is rigidly connected to the gas generator at the housing 22 by an annular row of generally radial tubular arms 28. These arms may be what are commonly referred to as Outlet Guide Vanes (OGVs).

[0064] exist Figure 2 In the embodiment, for simplicity, the annular housing 26 is designated as also including the VCI, ie, the outer intermediate housing shroud. As used herein, the housing 26 also refers to the combination of the fan housing and the VCI.

[0065] The assembly comprising the gas generator 12, the fan rotor 16, the casing 26 and the arm 28 forms the engine part of the turbine engine. The casing 26 supports the nacelle, which comprises annular covers 29, 30 extending upstream and downstream of the casing 26 as an extension of the casing, and an outer annular fairing 32 extending around the casing 26, 29, 30. The fairing 32 extends from the casing 26, 29, 30 at a radial distance and delimits with the casing an annular space called the nacelle compartment 34.

[0066] In the present technology, a tank of lubricant, in particular oil, for example for lubricating the bearings of the turbine engine 10 is installed in the nacelle compartment 34. Thus, the tank can be accessed inside the nacelle compartment, for example by disassembling a panel of the fairing 32, in order to fill it and to know its oil level.

[0067] The present invention proposes positioning the lubricant tank 40 within the engine compartment 24, such as Figure 1 and Figure 2 In the example shown, the lubricant tank is located between the housings 20, 22, substantially in line with the compressor (eg BP) and / or in line with the arm 28. In the particular embodiment shown (see Figure 2), the lubricant tank is located in a transverse plane that passes substantially through the radially outer end of the arm 28, the radially outer end of the arm extending radially outward from upstream to downstream. The tank 40 has a generally curved shape (see Figure 1 ), and therefore roughly matches the shape of the engine compartment 24 available in this plane.

[0068] Figure 3 and Figure 4 The tank 40 is filled by means of a removable tubular conduit 50 which is inserted through the hatch 46 and the first interface 44 until it reaches the second interface 42 for fluid connection to the tank 40 .

[0069] The hatch 46 is located on the outer fairing 32 of the nacelle 14, preferably just upstream of the thrust reverser cover. The hatch 46 comprises, for example, a flap 46a hingedly mounted on a panel of the fairing 32 and movable between a position for closing the hatch opening and a position for freely accessing the opening.

[0070] The flaps 46a of the hatch 46 can be equipped with a spring-type connection for returning the flaps to their closed position. The flaps of the hatch can be opened, for example, by simply pressing the pipe 50 and closed again when the pipe is removed.

[0071] The interface 42 is located on the housing 22 and communicates directly with the filling opening of the tank 40 .

[0072] The interface 44 is located on the housing 26 .

[0073] The pipe 50 has an elongated shape and is tubular and comprises a proximal end equipped with, for example, a funnel into which the lubricant contained in, for example, a container is poured. The pipe also has a distal end intended to be connected to the tank 40 so that the lubricant flows by gravity through the pipe and into the tank.

[0074] Thus, the pipe 50 is inserted and positioned in the turbine engine 10 so that oil can flow by gravity from the proximal end of the pipe to the distal end of the pipe and the tank 40 .

[0075] During filling, the angle of the duct 50 relative to the longitudinal axis X of the turbine engine depends on the one hand on the inclination necessary to make the oil flow during filling (for example, approximately 4°) and on the other hand on the roll angle of the aircraft equipped with the turbine engine (for example, approximately 6°). In this example, the total angle between the duct 50 and the axis X is, for example, 10°. Due to this relatively large angle, the duct cannot pass through one of the arms 28, since the dimensions of the duct would have to be too large.

[0076] The solution is therefore to have the pipe 50 pass through the interfaces 42, 44 which are directly located in or open into the conduit for the flow of the secondary flow.

[0077] Figure 5 is a cross-sectional view of the cover 32 and the housings 22 , 26 and interfaces 42 , 44 .

[0078] In the example shown, the interface 44 is intended to be passed through by a pipe 50 and comprises a telescopic guide system 52 comprising a plurality of elements 52a, 52b, ..., 52i, which are coaxially and slidably mounted in each other. Element 52a is the smallest element located at the center of the system 52, and element 52i is the largest element located at the periphery of the system 52.

[0079] Alternatively, the system 52 may be integrated into the hatch 46 .

[0080] System 52 is suitable for use with Figure 5 A first retracted position is shown in which the system has a minimum length or thickness measured in a radial direction relative to the axis X and does not protrude into the duct for the flow of the secondary flow. This thickness may be similar to the thickness of the shell 26. In the event that the thickness of the system is greater than the thickness of the shell 26, the radially inner end of the system will be aligned with the inner surface of the shell 26 and the radially outer end of the system will be located in the cabin compartment.

[0081] System 52 is suitable for use with Figure 6 A second extended position is visible in which the system has a maximum length or thickness and projects into a conduit for the secondary flow to another interface 42. The number of elements 52a, 52b, ..., 52i of the system 52 is, for example, between three and ten.

[0082] like Figure 8 As shown, the interface 42 includes a connection device, which includes:

[0083] an end piece 54 configured to cooperate with a complementary end piece 50a at the distal end of the pipe 50 by male-female nesting, and

[0084] An opening mechanism 56 for opening the tank 40 when the nesting is effective.

[0085] It will be appreciated that the interface 42 at the casing 22 and the filling orifice of the tank 40 are common, which has the advantage of facilitating the guidance of the duct 50 and limiting the mass and overall dimensions of this interface.

[0086] In the example shown, the conduit 50 includes a male end member 50a that engages with a female end member 54 of the interface 42. Fig.16As shown, the end pieces may be generally cylindrical in shape, or they may include free ends having complementary frustoconical surfaces 58 to facilitate centering of the end pieces and guiding the end pieces into each other. Fig.16 For simplification, the opening mechanism 56 of the tank 40 and the gate device 62 of the pipeline 50 are not shown in this figure.

[0087] When the duct 50 is removed, a slight groove may remain in the interface 42 due to the grooves in the interface, which creates some disturbance in the flow of the airflow along the housing 22 . Fig.17 The optimized shape of the groove is shown in FIG.

[0088] For end parts, e.g. Fig.16 As shown, a turbine engine configuration is conceivable in which the first interface 44 does not include a telescopic guidance system 52 for the pipe, since the end pieces may be slightly off-center relative to each other when approaching. Therefore, the accuracy of the guidance system of the pipe 50 may be lower than that obtained by the telescopic guidance, since the centering defects are compensated during the nesting due to the shape of the two end pieces, which facilitates the centering and guidance of one end piece in the other.

[0089] For example, a guiding system may be provided which is associated on the one hand with holes for passing the pipe 50 in the interface 44 intended to be passed by the pipe and on the other hand with holes for passing the pipe in the nacelle arranged below the hatch 46 .

[0090] It is also possible to provide a guide system which is independent of the interface 44 and uses a device fitted to the nacelle. Such a guide system can be installed before arranging the duct 50 for filling at a location cleared by the opening of the hatch 46 and is therefore intended to be removed after the duct is removed. Figures 18 to 20 An example of such an embodiment is described below.

[0091] The opening mechanism 56 of the can 40 includes at least one portion 56a, at least one portion can be opened from Figure 8 The visible closed position moves to Fig. 9 The open position of the can 40 can be seen in FIG. The movable part 56a is biased into its closed position by a resilient member 60, such as one or more springs, and is brought into its open position by the nesting of the end pieces.

[0092] As in the example shown, the distal end of the duct 50 may also comprise a shutter device 62 in the form of an opening mechanism similar to the tank opening mechanism 56. Advantageously, this shutter device 62 and the mechanism 56 are intended to operate simultaneously.

[0093] In this case, the opening mechanism 56 comprises a fixed portion 56b, relative to which the portion 56a can move. During male-female nesting, the fixed portion 56b cooperates with the movable portion 62a of the shutter device 62 of the pipe 50 via a bearing to move the movable portion from Figure 8 The closed position shown is shifted to Fig. 9 50. The closed position is a static position because a resilient member 64 (e.g., one or more springs) biases the movable portion 62a of the conduit to this position. The member 64 extends between the movable portion 62a of the conduit 50 and the fixed support 62b1. During male-female nesting, the fixed portion 62b of the gate device 62 of the conduit 50 abuts against the movable portion 56a of the opening mechanism 56 and pushes the movable portion to its open position.

[0094] from Figure 8 As can be seen, the fixed part 56b of the opening mechanism 56 comprises a shutter 56b1 of a central hole 56a1 of the movable part 56a. The shutter 56b1 is rigidly connected to a fixed support 56b3 of the part 56b by means of a rod 56b2.

[0095] One or more elastic members 60 extend between the support 56b3 and the movable part 56a to bias the latter into a rest position in which the shutter 56b1 abuts against a shoulder 56a2 of the hole 56a1 forming a seat for the shutter to abut and thus ensuring tight closure of the interface 42. Preferably, the interface 42 comprises a guide and locking element 64 configured to cooperate with an element 66 complementary to the end piece 50a of the pipe 50 by a bayonet effect.

[0096] exist Figures 5 to 15 In the example shown, the end piece 54 of the interface 42 comprises a lug 65 for engagement and sliding fit with an L-shaped groove or slit 66 in the end piece 50a of the pipe 50. The nesting of the end piece is achieved along the axis A, and the lug 65 extends radially inwards from the end piece 54, that is, towards the axis A. It can therefore be understood that the slit 66 is located at the periphery of the end piece 50a. The slit 66 comprises a longitudinal section 66a that opens onto the free end of the end piece 50a and a transverse section 66b oriented circumferentially relative to the axis A.

[0097] When the end pieces 50a, 54 are nested together, the lug 65 engages in the longitudinal section 66a of the slit and slides in the longitudinal section 66a of the slit until it reaches the transverse section of the slit (arrow F1- Fig. 9). The pressure along the axis A exerted by the pipe 50 on the interface 42 enables the mechanism 56, 62 to be opened. The length of the section 66a can be determined so that the mechanism opens only at the end of the travel of the lug 65 in this section 66a. In this position, as Fig. 9 As shown, the two mechanisms are thus opened and the rotation of the pipe 50 and its end piece 50a in the end piece 54 of the interface 42 causes the lug 65 to slide in the transverse section 66b of the slot 66 (arrow F2- Fig.10 ). Then, with the mechanism 56, 62 open, the end piece is locked in the nested position and oil can be injected into the tank 40 through the pipe 50 for refilling. The elastic members 60, 64 are kept compressed by the mechanical lock.

[0098] The oil can then flow through the pipe 50 to the tank 40 (arrow F3- Fig.10 ). After filling the tank 40, the end pieces are disengaged from each other by repeating the above displacement in reverse order. The pipe 50 and its end piece 50a are rotationally displaced about the axis A so that the lug 65 slides into the transverse section 66b and reaches the longitudinal section 66a of the slit 66. The connection is then unlocked and the elastic members 60, 64 ensure the return to the rest position of the movable part of the mechanism. The pipe 50 is then removed by axial translation and sliding of the lug 65 in the longitudinal section 66a of the slit, so that the shutter 56b1 comes to rest on the shoulder 56a2 of the movable part 56a ( Fig.11 ). If residual oil leaks into the pipeline, it is retained by the tight seal of the mechanism of the end piece of the pipeline.

[0099] exist Fig.16 In the embodiment shown, the lug 65 is carried by the end piece 50 a of the pipe 50 , and the slot 66 is then formed in the end piece of the interface 42 .

[0100] The invention therefore relates to a method for filling a lubricant tank 40 in an aircraft turbine engine, comprising a number of steps:

[0101] - a step of opening the hatch 46 of the nacelle 14;

[0102] -like Figure 6 4 , the steps of inserting the pipe 50 through the hatch 46 and then through the second interface 42; the pipe is then guided by the system of the second interface 42, which telescopes along the pipe 50 and is as close as possible to the first interface 44; the element 52a can be equipped with flaps 53, which include at least one pivoting flap, each of which is equipped with a spring-type connection for returning to the closed position and will open under simple pressure of the pipe 50, closing again when the pipe is removed;

[0103] - a step of passing the pipe 50 through the conduit for the flow of the secondary stream to the first interface 44 in order to connect the pipe 50 to the tank 40;

[0104] A step of causing the lubricant to flow from the proximal end of the duct situated outside the turbine engine to the distal end of the duct and towards the tank 40 .

[0105] Figures 12 to 15 The subsequent step of removing the pipe 50 after the tank 40 has been filled is shown.

[0106] Advantageously, when the pipe 50 is removed at the interface 44 , the system 52 collapses automatically by translation of the pipe.

[0107] To this end, the conduit 50 may include at least one or more members 68 that can be in a retracted position ( Fig.12 ) and the extension position from the pipe ( Figure 13-Figure 15 ) between. These movable members can cooperate with the system 50 to force the system to retract when the pipe 50 is removed. For example, the member 68 is a fin.

[0108] When the pipe 50 moves upwards through the system, the member comes to bear against each of the elements 52a, 52b, . . . , 52i which fold into the upper element (arrow F4). The displacement of the member 68 is ensured by control means located at the distal end of the pipe 50.

[0109] The interface 44 on the housing 26 then returns to its original state ( Figure 5 ).

[0110] Now refer to Figures 18 to 20 , Figures 18 to 20 An alternative embodiment of a turbine engine according to the invention is shown. The elements of the turbine engine already described above are described below and Figures 18 to 20 The same reference numerals are used in the drawings.

[0111] In this alternative embodiment, the first interface 44 is a simple opening 70 provided in the housing 26 .

[0112] In the example shown, the hatch 46 comprises a movable member 46b for closing the hatch, the hatch being equipped with a gate 46c, which is arranged to close the opening 70 when the hatch is closed. The movable member 46b is in the form of a wall for closing the opening of the hatch 46 and is fixed to the gate 46c, which is in the form of an elongated finger extending substantially perpendicularly from the inner surface of the movable member 46b. The finger comprises a free end opposite the movable member 46b, which is configured to engage in the opening 70. The free end of the finger thus has a shape complementary to the shape of the opening 70. The member 46b is movable and in particular removable, since it can be disassembled and removed from the turbine engine, as Fig.19 shown.

[0113] The pipe 50 is similar to the pipe described above and is here associated with a guide system 72 which is arranged to be installed at the location of the hatch 46 once the hatch 46 is opened and to be unloaded once the tank 40 is filled. The system 72 is in the form of a box 74 comprising two parallel walls 76 which comprise aligned holes 78 for the passage of the pipe 50. After removing the member 46b, the box 74 is installed in the opening of the hatch 46 and the pipe 50 is then slid through the hole 78 which may be equipped with a friction reducing ring 80 or the like ( Fig.19 and Fig. 20 ).

[0114] Figures 18 to 20 An additional advantageous feature is shown which may also be equipped to the turbine engine described with reference to the preceding figures. This is a line 82 for placing the interior of the tank 40 in fluid communication with the external environment of the turbine engine, and in particular for exhausting air from the tank to the outside when the tank is filled. This allows the oil to flow continuously through the duct without the need for air exhausted from the tank as a result of filling with oil to flow back through the duct, so that the filling flow is not affected. This line 82 extends from the tank 40 to the casing 26 and comprises an end 84 which opens into the cabin compartment 34 at the opening of the hatch 46, so that this end 84 is ventilated at least when the hatch 46 is removed ( Fig.19 ). The diameter of this pipe 82 can be very small (for example, a few millimeters) and can pass through an OGV arm or an auxiliary channel between the shells 22, 26. In the example shown, in particular in order to be able to pressurize the tank 40 when the turbine engine is running, that is, so that the pressure inside the tank can be higher than the pressure of the environment outside the turbine engine, the end 84 of the pipe 82 is arranged to be closed when the hatch 46 is closed. For this purpose, the movable member 46b of the hatch 46 can be provided to carry a plug 86 ( Fig.18 ).

Claims

1. A twin-flow turbine engine (10), include: - a gas generator (12), - a nacelle (14) surrounding said gas generator, - an arm (28) for connecting the gas generator to the nacelle, - a first annular duct for the main flow, which is formed in the gas generator and is delimited externally by a first annular casing (20) of the gas generator, a second annular duct for the flow of the secondary flow, the second annular duct being formed between the gas generator and the nacelle and being delimited internally by a second annular casing (22) of the gas generator and externally by a third annular casing (26) surrounding the nacelle, the second and third annular casings being connected together by at least some of the arms, at least one lubricant tank (40) located in an annular space extending between the first annular housing and the second annular housing, at least one hatch (46) provided on the outer fairing (32) of the nacelle for filling the lubricant tank, Characterized in that the lubricant tank is configured to be filled by a removable tubular pipe (50) inserted from the hatch into the lubricant tank, the third annular shell (26) includes a first interface (44) configured to be passed through by the tubular pipe, and the second annular shell includes a second interface (42) for connecting the tubular pipe to the lubricant tank.

2. The twin-flow turbine engine (10) according to claim 1, in, The first port (44) and the second port (42) are located directly in the second annular duct for flowing the secondary flow.

3. The twin-flow turbine engine (10) according to claim 2, in, The first interface (44) comprises a telescopic guide system (52), the telescopic guide system comprising a plurality of elements (52a, 52b, ..., 52i), the plurality of elements being coaxially mounted and slidably mounted within each other, the telescopic guide system being adapted to be passed through by the tubular conduit (50) and being adapted to adopt a first retracted position and a second extended position, in the first retracted position, the telescopic guide system having a minimum length or thickness and not extending into the second annular conduit for the secondary flow to flow, and in the second extended position, the telescopic guide system having a maximum length or thickness and extending into the second annular conduit for the secondary flow to flow toward the second interface (42).

4. A twin-flow turbine engine (10) according to any one of claims 1 to 3, in, The second interface (42) comprises a connecting device, the connecting device comprising: - a first end piece (54) configured to cooperate with a complementary second end piece (50a) on the distal end of the tubular pipe (50) by male-female nesting, and - an opening mechanism (56) for opening the lubricant tank when the male-female nesting is effective.

5. The twin-flow turbine engine (10) according to claim 4, in, The opening mechanism (56) includes at least one movable part (56a), which can be moved from a closed position of the lubricant tank (40) to an open position, and the movable part is biased to the closed position of the movable part by an elastic member (60) and is brought to the open position of the movable part by the male-female nesting.

6. The twin-flow turbine engine (10) according to claim 4, in, The second interface (42) comprises a guiding and locking element (64) configured to cooperate with a complementary element (66) of the second end piece (50a) on the tubular pipe (50) by a bayonet effect.

7. A twin-flow turbine engine (10) according to any one of claims 1 to 3, in, The hatch (46) is located upstream of the thrust reverser cover of the twin-flow turbine engine.

8. An assembly comprising a twin-flow turbine engine (10) according to any one of claims 1 to 7 and a removable tubular duct (50) for filling the lubricant tank (40), the tubular duct being configured to pass through the first interface (44) and to be connected to the lubricant tank (40) via the second interface (42).

9. The assembly according to claim 8, in, The tubular pipe (50) includes a distal end, which is equipped with a second end component (50a), and the second end component is constructed to cooperate with the complementary first end component (54) of the second interface (42) through male-female nesting. The second end component (50a) is equipped with a gate device (62), which is configured to open the distal end of the tubular pipe (50) when the male-female nesting is effective, and to close the distal end when the second end component (50a) and the complementary first end component (54) are disengaged from each other.

10. The assembly according to claim 8 or 9, the twin-flow turbine engine (10) being as defined in claim 3, in, The tubular duct (50) includes at least one movable member (68) movable between a retracted position along the tubular duct and an extended position extending from the tubular duct, the movable member being adapted to cooperate with the telescopic guide system (52) to force the telescopic guide system to retract when the tubular duct is removed from the dual-flow turbine engine.

11. The assembly according to claim 8 or 9, the twin-flow turbine engine (10) being as defined in claim 1 or 2, in, The first interface (44) is formed by an opening (70) provided in the third annular shell (26), the hatch (46) comprising a movable member (46b) for closing the hatch, the hatch being provided with a gate (46c) arranged to close the opening when the hatch is closed, the tubular duct (50) being associated with a guide system (72) arranged to be installed at the position of the hatch (46) once the hatch is opened and to be unloaded once the lubricant tank (40) is filled.

12. A method for filling a lubricant tank (40) in a twin-flow turbine engine by means of an assembly according to any one of claims 8 to 11, in, The method comprises the following steps: - opening the hatch (46) of the nacelle (14), - inserting the tubular conduit (50) through the hatch (46) and then through the first port (44), - passing the tubular duct (50) through the second annular conduit for the flow of the secondary flow to the second interface (42) for connecting the tubular duct (50) to the lubricant tank (40), and - causing the lubricant to flow from the proximal end of the tubular duct (50) located outside the twin-flow turbine engine (10) to the distal end of the tubular duct and to the lubricant tank (40).

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