EP3617518B1 - Pump of turbomachine - Google Patents

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 technique

In some aeronautical modules, a fluid circuit runs through the module to perform heat exchange, lubrication or other functions. In order to set this fluid in motion, a pump is arranged close to the module and cooperates with the fluid circuit. The pump may be an electric pump or may require an electrical power supply for control or detection functions in particular. Thus, the pump must be supplied with electricity and fluid. The module may sometimes have its own power supply which it may 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 compressor for a refrigerator comprising a body with a hydraulic port and an electrical 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 vacant a margin of improvement on the ease of mounting a pump on an aeronautical module.

The document US 2012/0000556 A1 describes a pump intended to be submerged in a fuel tank for a motor vehicle. This is not suitable for aeronautics because an aircraft moves in all directions in space, and is not easy to assemble either.

Summary of the invention Technical problem

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

Technical solution

The invention relates to a pump according to claim 1.

The module can be a subassembly of a turbojet such as for example 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 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 embodiments of the invention, the pump may comprise one or more of the following characteristics, taken in isolation 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 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 be integral with the body of the pump. Alternatively, the male element is on the side of the module, either integral with the body of the module, or formed by an additional part, the pump and the module having female elements;
• the hydraulic connector comprises at least one female element nested in the flat surface;
• the flat surface includes lugs provided with orifices forming the mechanical connector. Alternatively, the outline of the flat surface defines a flange which forms the mechanical connector, the latter being capable of cooperating, for example by means of a collar, with a flange of the aeronautical module. A V-clamp type assembly can be used;
• the body of the pump is substantially cylindrical in shape, the flat surface forming one of the bases of the cylindrical shape;
• the body of the pump is composed of a bell-shaped casing covered with a cover, the flat outer surface being the outer surface of the cover. Thus, when the pump is attached to its module, the electrical and hydraulic connections are invisible and are therefore protected from any damage, particularly in the event of fire;
• the pump is an electrically powered hydraulic pump. The fluids transported can be coolant, lubricating fluid, heat exchanger fluid, etc.

The invention also relates to an aeronautical module comprising electrical, hydraulic and mechanical connection elements, arranged in such a way as to be able to cooperate with the respective connection elements of the pump according to one of the embodiments described 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 may include one or more of the following characteristics, taken in isolation 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 tank;
• 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 for mounting a pump according to one of the embodiments above on a module according to one of the embodiments described above, the method comprising a step of position of the pump against the module by translation in a direction perpendicular to the flat surface and a step of 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, unless the contrary is explicitly mentioned.

Benefits provided

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 assembly of the pump. Also, once the pump is mounted, the electrical and hydraulic connections are not subject to the particularly difficult external conditions (pressure, temperature and oxidation, fire, etc.) which may prevail in certain aeronautical environments. Thus, the system is made more reliable.

In addition, it is the only mechanical interlock of the one-module pump that provides electrical and hydraulic interlocking of the connections. There is therefore no need to lock the electrical and hydraulic connections independently.

Brief description of the drawings

• There figure 1 represents a system according to the invention;
• There figure 2 describes a sectional view of an electric pump of the state of the art;
• There picture 3 illustrates a sectional view of a pump according to the invention;
• There figure 4 shows an isometric view of the pump according to the invention and in particular seen from the flat surface of the pump;
• There 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 embodiments

In the following description, the terms “internal” and “external” refer to 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 refer to the main flow direction of the stream in the turbomachine. The term “integral” is understood as integral in rotation. There figure 1 schematically represents an axial turbomachine 2. This is a turbofan engine. The turbojet engine 2 comprises a first compression level, called low-pressure compressor 4, a second compression level, called 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 gradually compress the latter until it enters the combustion chamber 8.

An inlet fan commonly referred to 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 crossing the various aforementioned levels of the turbomachine, and a secondary flow 20 crossing 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 reduction gear 22, can reduce the speed of rotation of the fan and/or of the low-pressure compressor with respect 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 streams are coaxial annular streams fitted into one another. They are channeled through the casing of the turbomachine and/or the shrouds.

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

There figure 1 also very schematically shows a fuel cell 28. This enables the supply of electricity to certain engine components or to 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 ducts 32 for transporting the oil to the components of the turbojet 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 appropriate control system allow the oil to pass through one of the exchangers rather than the other, in order to maintain 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 regulated precisely.

The system also comprises a hydraulic circuit 40. This makes it possible to ensure proper operation of the fuel cell 28. Ducts 42 and a heat exchanger 44 make it possible to convey the oil to the fuel cell 28.

The two circuits 30, 40 can form only one common hydraulic circuit. Thus, the same oil can run 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 may be separate and each comprise (at least) a pump 50 and a reservoir 60 respectively.

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

The tank 60 can be fixed to the nacelle of the turbomachine 2, or to a compressor casing. It is optionally attached to an intermediate casing. Reservoir 60 can be placed between two annular walls guiding concentric flows; for example the secondary flow 20 and the flow surrounding the turbine engine 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 installation between two curved and close partitions.

There figure 2 schematically represents 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 by the inlet 52' and is discharged by the outlet 53'. A 54' impeller (paddle wheel) rotates to suck in 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 they are supplied with direct current greater than a nominal operating value, give off heat. This warms the cold oil and thins it.

The pump 50' can include all the appropriate means for its correct operation (sensors, pressure relief valves, purge valves, etc.).

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

Anchoring lugs 59' are placed 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 points of the pump. When mounting the pump 50' in the system, it is therefore necessary to carry out the operations relating to each of these types of connection independently. There picture 3 schematically represents 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 by the inlet 52 and is discharged by 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 both connectors 52, 53 can be of the female type. An impeller 54 (paddle wheel) rotates to draw in 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 appropriate means for its correct operation (sensors, pressure relief valves, purge valves, etc.).

An electrical connector 57 and a cable 58 supply the stator 56 with current. The cable 58 runs through the body of the pump in a suitable housing until it reaches, or until it forms, a turn of the stator 56. On an enlarged part of the picture 3 , at the bottom, it is noted that the connector 57 may comprise a pin 571 made of a conductive material and mounted in an insulating slider 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 compensate for positioning uncertainties and to guard against damage that could occur during the mounting of the pump 50 on the aeronautical module. The spring 574 is stiff enough so that electrical contact is 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 lugs 59 in the form of a single flange or several lugs spaced angularly at the periphery of the body 51 of the pump 50 make it possible to mechanically connect the pump 50 to the system with which it cooperates. The lugs comprise for example an orifice to receive a fastener element.

In this example of a pump according to the invention, the electrical 57, hydraulic 52, 53 and mechanical 59 connections are arranged on the same side of the body 51 of the pump 50 and in particular on the same substantially flat surface 511.

When mounting the pump 50 in a system, it is therefore possible to perform 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 an enlarged partial view of the picture 3 , top, an example of a male hydraulic port 53 is depicted. In this example, port 53 includes a spindle 531 held in a hole 514 of body 51. Spindle 531 can be mounted clamped in the orifice 514 and/or may be provided with a seal 532. A shoulder 515 can serve as an axial stop for the spindle. In terms 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 , spindle 531 will enter an appropriate hole in the module.

It should be noted that the picture 3 is very schematic and that a person skilled in the art would be able to adapt the teaching of the picture 2 to different types or shapes of pump.

There 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 57, hydraulic 52, 53 and mechanical 59 connection.

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 coming to cover 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. There figure 5 depicts a sectional view of pump 50 and a module 70 to which 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 aimed at distributing 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, of which only two are visible on the figure 5 . These lugs include holes for receiving 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 may be provided to ensure correct positioning of the pump during assembly.

The fluid inlet 52 and outlet 53 ports in the pump 50 are placed in look of corresponding pipes 72, 73 in the module 70. A spindle 531 (see also picture 3 top) may be provided at the interface between the ports 52, 53 and the respective pipes 72, 73. Gaskets 532 can be arranged on the pump 50 side and/or on the module 70 side in order to ensure sealing.

Optionally, a flat gasket can be inserted between surface 511 and surface 711 over the entire contact zone between pump 50 and 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 only illustrate possible embodiments of the invention. Other embodiments of the invention are possible.

For example, the lugs 59 can be replaced by elastic L-shaped tabs, which cooperate with notches arranged on the module 70. Any device of the quick fastening 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 inlets and/or several outlets. The position of the connectors on the face 511 is only given 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 the manufacturing constraints, to the standards in force, to the nature of the fluid transported, to the type of module with which the pump interacts, etc.

The present invention relates mainly to the electrical, hydraulic and mechanical interface between a pump and a module. The operation of the pump is irrelevant 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 (14)

1. Pump (50) for an aeronautical module (70), the pump (50) comprising a body (51) having at least one substantially flat outer surface (511), the pump including an electrical connector (57), a hydraulic connector (52, 53) and a mechanical connector (59) for electrical, hydraulic and mechanical connection of the pump (50) to the aeronautical module (70),
   wherein the connectors (52, 53, 57, 59) are all arranged on its flat surface (511), and wherein the hydraulic connector (52, 53) is comprised of at least one fluid inlet port (52) for the entry of fluid into the body (51) and at least one fluid outlet port (53) for the exit of fluid from the body (51).
2. Pump (50) according to claim 1, wherein the electrical connector (57) is composed of pins (571) extending perpendicularly from the flat surface (511).
3. Pump (50) according to claim 1 or 2, wherein the pins (571) are supported by elastic means (574) or damping means, in particular springs.
4. Pump (50) according to any one of claims 1 to 3, wherein the hydraulic connector (52, 53) comprises at least one male element (52, 53) protruding from the flat surface (511).
5. Pump (50) according to claim 4, wherein the male element (52, 53) is a spindle (531), preferably supported by elastic or damping means, in particular springs.
6. Pump (50) according to any one of claims 1 to 5, wherein the hydraulic connector (52, 53) comprises at least one female element embedded in the flat surface (511).
7. Pump (50) according to any one of claims 1 to 6, wherein the flat surface (511) includes lugs (59) provided with holes (591) forming the mechanical connector (59).
8. Pump (50) according to any one of claims 1 to 7, wherein the contour of the flat surface (511) defines a flange that forms the mechanical connector (59), the latter being adapted to cooperate, for example by means of a collar, with a flange of the aeronautical module.
9. Pump (50) according to any one of claims 1 to 8, wherein the body (51) of the pump (50) is substantially cylindrical in shape, the flat surface (511) forming one of the bases of the cylindrical shape.
10. Pump (50) according to any one of claims 1 to 9, wherein the body (51) of the pump (50) is composed of a bell (512) covered with a lid (513), the flat outer surface (511) being the outer surface of the lid (513).
11. Pump (50) according to any one of claims 1 to 10, the pump being an electric powered hydraulic pump (50).
12. An 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 any of claims 1 to 11, the module being optionally constructed in the form of a compressor housing (4, 6) of an axial turbomachine (2) or in the form of a fuel cell (28).
13. System comprising a module (70) according to claim 12 and a pump (50) according to any of claims 1 to 11 mounted in electrical, hydraulic and mechanical connection with said module (70).
14. Method for mounting a pump (50) according to any of claims 1 to 11 on a module (70) according to claim 12, the method comprising:

    positioning the pump (50) against the module (70) by translation in a direction (A) perpendicular to the flat surface (511) and

    securing in the desired position, in particular by clamping means such as screws.

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