EP3617518A1 - Pump of turbomachine - Google Patents

Abstract

The invention relates to a pump (50) for an aeronautical module (70), the pump (50) comprising a body (51) having at least one substantially planar external surface (511), remarkable in that it has an electrical connector (57), a hydraulic connector (52, 53) and a mechanical connector (59), for the electrical, hydraulic and mechanical connection of the pump (50) with the aeronautical module (70) and in that the connectors (52, 53, 57, 59) are all arranged on its flat surface (511). The invention also relates to a module capable of cooperating with such a pump, the module possibly being a subset of aircraft turbojet, such as a compressor or fuel cell.

Description

Technical area

The invention relates to a hydraulic pump for an aeronautical module such as a turbomachine compressor or a fuel cell. More particularly, the invention relates to the electrical, hydraulic and mechanical coupling between such a pump and such a module.

Prior art

In some aeronautical modules, a fluid circuit traverses the module to perform heat exchange, lubrication or other functions. In order to set this fluid in motion, a pump is arranged near the module and cooperates with the fluid circuit. The pump may be an electric pump or may require an electrical supply for control or detection functions in particular. Thus, the pump must be supplied with electricity and fluid. The module can sometimes have its own power supply which it can share with the pump. The pump is thus connected to the module by an electrical connector and a hydraulic connector. It can also be mechanically secured to the module.

The document JP-H-07109975 A ( JP19930258366 ) describes a refrigerator compressor comprising a body with a hydraulic port and an electric port. Thus, the hydraulic connection and the electrical connection are established between the compressor and the cooling circuit of the refrigerator.

This type of compressor is not suitable for aeronautical applications and leaves a room for improvement on the ease of mounting a pump on an aeronautical module.

Summary of the invention Technical problem

The invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to improve the ease of mounting and multifunction connection of a pump on a module aeronautics. The invention also aims to provide a simple, resistant, economical and reliable solution.

Technical solution

The invention relates to a pump for an aeronautical module, the pump comprising a body having at least one substantially planar external surface, characterized in that it has an electrical connector, a hydraulic connector and a connector mechanical, for the electrical, hydraulic and mechanical connection of the pump with the aeronautical module and in that the connectors are all arranged on its flat surface.

The module can be a sub-assembly of a turbojet engine such as a compressor or its casing, or a tank. The module can also be a fuel cell, a heat exchanger, an element of the water or air circuit of a cabin, etc.

• le connecteur électrique est composé de broches s'étendant perpendiculairement en saillie de la surface plane ;
• les broches sont supportées par des moyens élastiques ou amortissant, notamment des ressorts ;
• le connecteur hydraulique est composé d'au moins un port d'entrée de fluide et au moins un port de sortie de fluide ;
• le connecteur hydraulique comprend au moins un élément mâle en saillie de la surface plane ;
• l'élément mâle est un fuseau (aussi appelé « bobine »), qui peut être ou non supporté par des moyens élastiques ou amortissant, notamment des ressorts. Alternativement, l'élément mâle peut être venu de matière avec le corps de la pompe. Alternativement, l'élément mâle est du côté du module, soit venu de matière avec le corps du module, soit formé par une pièce additionnelle, la pompe et le module présentant des éléments femelles ;
• le connecteur hydraulique comprend au moins un élément femelle niché dans la surface plane ;
• la surface plane comprend des pattes munies d'orifices formant le connecteur mécanique. Alternativement, le contour de la surface plane définit une bride qui forme le connecteur mécanique, celle-ci étant apte à coopérer, par exemple au moyen d'un collier, avec une bride du module aéronautique. Un assemblage du type V-clamp peut être utilisé ;
• le corps de la pompe est de forme sensiblement cylindrique, la surface plane formant une des bases de la forme cylindrique ;
• le corps de la pompe est composé d'un carter en forme de cloche recouverte d'un couvercle, la surface externe plane étant la surface extérieure du couvercle. Ainsi, lorsque la pompe est fixée à son module, les connexions électriques et hydrauliques sont invisibles et sont donc protégées de tout endommagement, notamment en cas de feu ;
• la pompe est une pompe hydraulique à alimentation électrique. Les fluides transportés peuvent être un fluide de refroidissement, un fluide de lubrification, un fluide d'échangeur de chaleur, etc.

According to advantageous modes of the invention, the pump can include one or more of the following characteristics, taken individually or according to all possible technical combinations:

• the electrical connector is composed of pins extending perpendicularly projecting from the flat surface;
• the pins are supported by elastic or damping means, in particular springs;
• the hydraulic connector is composed of at least one fluid inlet port and at least one fluid outlet port;
• the hydraulic connector comprises at least one male element projecting from the flat surface;
• the male element is a spindle (also called a “coil”), which may or may not be supported by elastic or damping means, in particular springs. Alternatively, the male element may have come integrally with the pump body. Alternatively, the male element is on the module side, either integrally with the module body, or formed by an additional part, the pump and the module having female elements;
• the hydraulic connector comprises at least one female element nestled in the flat surface;
• the flat surface includes tabs provided with orifices forming the mechanical connector. Alternatively, the contour of the flat surface defines a flange which forms the mechanical connector, the latter being able to cooperate, for example by means of a collar, with a flange of the aeronautical module. A V-clamp type assembly can be used;
• the pump body is of substantially cylindrical shape, the flat surface forming one of the bases of the cylindrical shape;
• the pump body is made up of a bell-shaped casing covered with a cover, the planar external surface being the external surface of the cover. Thus, when the pump is fixed to its module, the electrical and hydraulic connections are invisible and are therefore protected from any damage, especially in the event of fire;
• the pump is a hydraulic pump with electrical supply. The fluids transported can be a cooling fluid, a lubrication fluid, a heat exchanger fluid, etc.

The invention also relates to an aeronautical module comprising electrical, hydraulic and mechanical connection elements, arranged so as to be able to cooperate with the respective connection elements of the pump according to one of the embodiments set out above.

• le module se présente sous la forme d'un carter de turbomachine axiale, en particulier un carter de compresseur de turbomachine axiale ;
• le module est un réservoir ;
• le module se présente sous la forme d'une pile à combustible.

According to advantageous modes of the invention, the module can include one or more of the following characteristics, taken individually or according to all possible technical combinations:

• the module is in the form of an axial turbomachine casing, in particular an axial turbomachine compressor casing;
• the module is a reservoir;
• the module is in the form of a fuel cell.

The invention also relates to a system comprising a module according to one of the embodiments described above with a pump according to one of the embodiments described above, the pump being mounted in electrical, hydraulic and mechanical connection. with the module.

The invention also relates to a method of mounting a pump according to one of the above embodiments on a module according to one of the embodiments described above, the method comprising a step of setting position of the pump against the module by translation in a direction perpendicular to the flat surface and a step for locking the position, in particular by clamping means such as screws or a collar.

In general, the advantageous modes of each object of the invention are also applicable to the other objects of the invention. Each object of the invention can be combined with the other objects, and the objects of the invention can also be combined with the embodiments of the description, which in addition can be combined with one another, according to all possible technical combinations, unless the opposite is not explicitly mentioned.

Benefits

The fact of providing, on the same face, the connections of several types, in this case electrical, hydraulic and mechanical, makes it possible to greatly facilitate the mounting of the pump. Also, once the pump is mounted, the electrical and hydraulic connections are not subject to particularly difficult external conditions (pressure, temperature and oxidation, fire, etc.) which can prevail in certain aeronautical environments. Thus, the system is made more reliable.

In addition, it is the only mechanical locking of the pump to a module which ensures the electrical and hydraulic locking of the connections. There is therefore no need to lock the electrical and hydraulic connections independently.

Brief description of the drawings

• The figure 1 represents a system according to the invention;
• The figure 2 describes a sectional view of an electric pump of the state of the art;
• The figure 3 illustrates a sectional view of a pump according to the invention;
• The figure 4 shows an isometric view of the pump according to the invention and in particular seen from the flat surface of the pump;
• The figure 5 shows a cross section of an example of coupling between the pump of the invention and the module of the invention.

Description of the embodiments

In the following description, the terms "internal" and "external" refer to a positioning relative to the axis of rotation of an axial turbomachine. The axial direction corresponds to the direction along the axis of rotation of the turbomachine. The radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine. The term “solidarity” is understood to mean solidarity in rotation.

The figure 1 shows in a simplified manner an axial turbomachine 2. This is a double-flow turbojet engine. The turbojet engine 2 comprises a first level of compression, called a low-pressure compressor 4, a second level of compression, called a high-pressure compressor 6, a combustion chamber 8 and one or more levels of turbines 10. In operation, the mechanical power of the turbine 10 transmitted to the rotor 12 sets in motion the two compressors 4 and 6. The latter comprise several rows of rotor blades associated with rows of stator blades. The rotation of the rotor around its axis of rotation 14 thus makes it possible to generate an air flow and to compress it progressively until the inlet of the combustion chamber 8.

An inlet fan commonly designated as a fan or blower 16 is coupled to the rotor 12 and generates an air flow which is divided into a primary flow 18 passing through the various aforementioned levels of the turbomachine, and into a secondary flow 20 passing through an annular duct. (partially shown) along the machine to then join the primary flow at the turbine outlet.

Reduction means, such as a planetary gear reducer 22, can reduce the speed of rotation of the fan and / or the low-pressure compressor relative to the associated turbine. The secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft. The primary 18 and secondary 20 flows are annular coaxial flows and fitted one inside the other. They are channeled through the casing of the turbomachine and / or of the ferrules.

The rotor 12 comprises a transmission shaft 24 mounted on the casing by means of two bearings 26.

The figure 1 also very schematically shows a fuel cell 28. This allows the supply of electricity to certain engine components or auxiliary equipment of the aircraft.

In order to lubricate the rotating elements of the turbojet engine 2, a lubrication circuit 30 is provided. This circuit 30 comprises conduits 32 for transporting the oil to the organs of the turbojet engine requiring it, such as in particular the gearbox 22 and the bearings 26. A heat exchanger 34 can be provided to regulate the temperature of the oil in the circuit 30. The exchanger 34 can be positioned in the secondary flow 20 to cool the oil. Alternatively, or in addition, an exchanger 34 can also be provided downstream of the bleed valves, to heat the oil. When both types of exchanger (cold and hot) are provided, valves and an adequate control system allow oil to pass more through one of the exchangers than the other, in order to keep the oil at a temperature wanted. By adapting the flow rate or the passage time in one and / or the other of the exchangers, the temperature can be precisely regulated.

The system also includes a hydraulic circuit 40. This ensures correct operation of the fuel cell 28. Conduits 42 and a heat exchanger 44 allow oil to be conveyed to the fuel cell 28.

The two circuits 30, 40 can form only one common hydraulic circuit. Thus, the same oil can travel through both circuits. A reservoir 60 common to the two circuits and at least one pump 50 ensure an oil flow in the two circuits.

Alternatively, the two circuits 30, 40 can be separate and each comprise (at least) a pump 50 and a respective reservoir 60.

It is understood that the circuits include all the organs making it possible to control the temperature, the pressure and the flow rate in order to obtain optimal operation of the fuel cell 28 and of the turbojet engine 2 (sensors, valves, blower, flow reducer, etc.) .

The reservoir 60 can be fixed to the nacelle of the turbomachine 2, or to a compressor casing. It is optionally attached to an intermediate casing. The reservoir 60 can be placed between two annular walls guiding concentric flows; for example the secondary flow 20 and the flow surrounding the turbomachine 2, or between the primary flow 18 and the secondary flow 20. In order to increase its useful volume, the tank 60 is essentially elongated while following a general shape curve. This curvature allows implantation between two curved and closely spaced partitions.

The figure 2 shows schematically a sectional view of a known electric pump 50 '. The pump comprises a body 51 ′ whose walls describe a generally cylindrical shape. The oil is sucked in through the inlet 52 'and is discharged through the outlet 53'. A 54 'impeller (impeller) rotates to draw the oil. The impeller is integral with a rotor 55 'driven in rotation by the electromagnetic field created by a stator 56'.

The oil can come into contact with the turns of the stator 56 'which, when supplied with direct current above a nominal operating value, give off heat. This warms up the cold oil and makes it more fluid.

The pump 50 ′ may include all the means suitable for its proper functioning (sensors, pressure relief valves, purge valves, etc.).

An electrical connector 57 'as well as a cable 58' make it possible to supply the stator 56 'with current.

Anchoring tabs 59 'are arranged on the body 51' to mechanically connect the pump to the rest of the system with which it interacts.

In this example of a pump, the electrical (57 '), hydraulic (52', 53 ') and mechanical (59') connections are arranged at different locations on the pump. When mounting the pump 50 'in the system, it is therefore necessary to carry out independently the operations relating to each of these types of connection.

The figure 3 shows schematically a sectional view of an electric pump 50 according to the invention. The pump comprises a body 51 whose walls describe a generally cylindrical shape. The oil is sucked in through the inlet 52 and is discharged through the outlet 53. In this example, the inlet and the outlet are represented by male connectors, projecting from the body 51 of the pump 50. Alternatively, the one, the other or the two connectors 52, 53 may be of the female type. An impeller 54 (impeller) rotates to suck up the oil. The impeller 54 is integral with a rotor 55 driven in rotation by the electromagnetic field created by a stator 56.

The pump 50 can include all the means suitable for its proper functioning (sensors, pressure relief valves, purge valves, etc.).

An electrical connector 57 and a cable 58 make it possible to supply the stator 56 with current. The cable 58 runs in the pump body in an appropriate housing until it reaches, or until it forms, a turn of the stator 56. On an enlarged part of the figure 3 , below, it is noted that the connector 57 may comprise a pin 571 made of a conductive material and mounted in an insulating slide 572, itself received in a cavity 573 of the body 51 of the pump 50. Alternatively, each of the pins 571 can be mounted independently and supported by a spring. A spring 574 and a ring 575 maintain the connector 57 in the body 51 of the pump 50 with a certain cushioning. This makes it possible to overcome the positioning uncertainties and to guard against damage which could occur during the mounting of the pump 50 on the aeronautical module. The spring 574 is sufficiently stiff for an electrical contact to be maintained with the electrical outlet with which the pin 571 must cooperate, whatever the operating conditions (vibration, expansion, etc.). The spring can alternatively be on the module side, either to support male pins or female housings.

Anchoring tabs 59 in the form of a single flange or of several tabs angularly spaced at the periphery of the pump body 51 make it possible to mechanically connect the pump 50 to the system with which it cooperates. The tabs include, for example, an orifice for receiving a screw element.

In this example of a pump according to the invention, the electrical connections 57, hydraulic 52, 53 and mechanical 59 are arranged on the same side of the pump body 51 and in particular on the same surface, substantially planar, 511.

When mounting the pump 50 in a system, it is therefore possible to carry out the connection operations relating to each of these types of connection simultaneously. It is moreover the locking of the mechanical connection which simultaneously locks the other types of connection.

On a partial enlarged view of the figure 3 , above, an example of a male hydraulic port 53 is described. In this example, the port 53 comprises a spindle 531 held in an orifice 514 of the body 51. The spindle 531 can be mounted clamped in the hole 514 and / or may be provided with a seal 532. A shoulder 515 can serve as an axial stop for the spindle. In the light of the electrical connector 57, the spindle 531 can be supported by springs, for example placed between the shoulder 515 and the spindle 531. When coupling the pump 50 with a module with which the pump 50 cooperates , time zone 531 will enter an appropriate hole in the module.

It should be noted that the figure 3 is very schematic and that the skilled person could adapt the teaching of figure 2 to different types or forms of pump.

The figure 4 shows an external isometric view of the pump 50. It shows the flat surface 511 provided with the various elements for the electrical connection 57, hydraulic 52, 53 and mechanical 59.

The pump body 51 can be made in the form of a bell 512 and a cover 513, the bell 512 containing all of the functional elements of the pump 50 and the cover 513 covering the bell 512 and comprising the surface plane 511. Thus, once mounted on the module (see figure 5 ), no part of the pump is accessible, visible or in contact with the environment.

The figure 5 describes a sectional view of the pump 50 and of a module 70 to which the pump 50 is assembled. This is a schematic representation. The module 70 can be a module directly using the fluid from the pump. Alternatively and as shown in the figure 5 , the module can be an adapter designed to distribute the fluid to another element. By way of illustration, the module 70 can be connected on the one hand to an oil tank and on the other hand to a turbomachine compressor.

The pump 50 and the module 70 are assembled so that the surface 511 of the pump 50 is brought into contact with a surface 711 of the module 70.

The pump 50 includes legs 59, only two of which are visible on the figure 5 . These tabs include orifices making it possible to receive screws (not shown) which cooperate with a thread (not shown) in the module 70. The thread forms an example of a mechanical connection element of the module. A centering shoulder (not shown) or chamfers can be provided to ensure correct positioning of the pump during assembly.

The fluid inlet 52 and outlet 53 ports in the pump 50 are set look of corresponding pipes 72, 73 in module 70. A time zone 531 (see also figure 3 above) can be provided at the interface between the ports 52, 53 and the respective pipes 72, 73. Seals 532 can be arranged on the pump side 50 and / or on the module side 70 in order to ensure a seal.

Optionally, a flat seal can be inserted between the surface 511 and the surface 711 over the entire contact area between the pump 50 and the module 70.

A female electrical socket 757 and a cable 758 are provided in the module 70 in order to ensure the electrical connection with the connector 57 of the pump 50. The cable 758 can be supplied with current by a battery or a current generator, possibly via other intermediate parts (not shown) which also include cables or conductors.

The figures illustrate only possible examples of embodiment of the invention. Other embodiments of the invention are possible.

For example, the legs 59 can be replaced by elastic L-shaped tongues which cooperate with notches arranged on the module 70. Any device of the quick fixing type (“snap-fit”, bayonet) can be used. Also, permanent or semi-permanent assembly means such as gluing or welding can be used.

The pump can be provided with several inputs and / or several outputs. The position of the connectors on the face 511 is given only by way of example in the figures. A person skilled in the art would be able to adapt the position, type and number of connectors to his needs, to manufacturing constraints, to standards in force, to the nature of the fluid transported, to the type of module with which the pump interacts, etc.

The present invention mainly relates to the electrical, hydraulic and mechanical interface between a pump and a module. The operation of the pump is indifferent and those skilled in the art would recognize that several types of pump can be used without departing from the scope of protection conferred by the appended claims.

Claims (15)

Pump (50) for an aeronautical module (70), the pump (50) comprising a body (51) having at least one substantially planar external surface (511), characterized in that it has an electrical connector (57) , a hydraulic connector (52, 53) and a mechanical connector (59), for the electrical, hydraulic and mechanical connection of the pump (50) with the aeronautical module (70) and in that the connectors (52 , 53, 57, 59) are all arranged on its flat surface (511). Pump (50) according to claim 1, characterized in that the electrical connector (57) is composed of pins (571) extending perpendicularly projecting from the planar surface (511). Pump (50) according to one of claims 1 or 2, characterized in that the pins (571) are supported by elastic means (574) or damping, in particular springs. Pump (50) according to one of claims 1 to 3, characterized in that the hydraulic connector (52, 53) is composed of at least one fluid inlet port (52) and at least one outlet port ( 53) of fluid. Pump (50) according to one of claims 1 to 4, characterized in that the hydraulic connector (52, 53) comprises at least one male element (52, 53) projecting from the planar surface (511). Pump (50) according to claim 5, characterized in that the male element (52, 53) is a spindle (531), preferably supported by elastic or damping means, in particular springs. Pump (50) according to one of claims 1 to 6, characterized in that the hydraulic connector (52, 53) comprises at least one female element nestled in the flat surface (511). Pump (50) according to one of claims 1 to 7, characterized in that the planar surface (511) comprises tabs (59) provided with orifices (591) forming the mechanical connector (59). Pump (50) according to one of claims 1 to 8, characterized in that the contour of the flat surface (511) defines a flange which forms the mechanical connector (59), the latter being able to cooperate, for example at by means of a collar, with a flange of the aeronautical module. Pump (50) according to one of claims 1 to 9, characterized in that the body (51) of the pump (50) is of substantially cylindrical shape, the flat surface (511) forming one of the bases of the cylindrical shape. Pump (50) according to one of claims 1 to 10, characterized in that the body (51) of the pump (50) is composed of a bell (512) covered with a cover (513), the external surface plane (511) being the outer surface of the cover (513). Pump (50) according to one of Claims 1 to 11, characterized in that it is a hydraulic pump (50) with electrical supply. Aeronautical module (70) comprising electrical (757), hydraulic (72, 73) and mechanical connection elements, arranged so as to be able to cooperate with the respective connection elements (52, 53, 57, 59) of the pump ( 50) according to one of claims 1 to 12, the module being optionally in the form of a compressor casing (4, 6) of an axial turbomachine (2) or in the form of a fuel cell (28) . System comprising a module (70) according to claim 13 and a pump (50) according to one of claims 1 to 12 mounted in electrical, hydraulic and mechanical connection with said module (70). Method for mounting a pump (50) according to one of claims 1 to 12 on a module (70) according to claim 13, the method comprising a step of positioning the pump (50) against the module (70 ) by translation in a direction (A) perpendicular to the flat surface (511) and a step of locking the position, in particular by clamping means such as screws.

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