Fluid flow regulating valve

Abstract

The invention relates to a system for regulating the flow rate of an inerting gas during a flight, the system comprising a fluid flow regulating valve (10) comprising: • - a body (11) having: • - a fluid intake opening (12), and • - a fluid discharge opening (13), • - a fluid flow rate adaptation device (15) able to modify, according to at least three different values, the surface area of a fluid passage orifice (16) positioned between the fluid intake opening (12) and the fluid discharge opening (13), • - a computer (48) configured to control an actuator associated with the valve so as to modify the surface area of the fluid passage orifice as a function of a difference between an inerting gas flow rate setpoint (Db) and an inerting flow rate measurement (Dmes) such that the valve makes it possible to ensure that the inerting setpoint (Db) is accurately tracked during the various phases of operation of an aircraft.

Description

DESCRIPTION TITLE: FLUID FLOW CONTROL VALVE

[0001] The present invention relates to a fluid flow regulating valve. The invention finds a particularly advantageous application in the field of aeronautics, with a system for inerting a fuel tank of an aircraft, such as an airplane, a helicopter or the like.

[0002] In the field of aeronautics, an inerting system makes it possible to generate an inerting gas, such as nitrogen, or any other neutral gas such as carbon dioxide for example, and to introduce said inerting gas into the fuel tanks for safety reasons in order to reduce the risk of explosion of said tanks.

[0003] A conventional inerting system generally comprises an on-board inert gas generator known as OBIGGS, "On Board Inert Gas Generating Systems" according to the English acronym, supplied with air, for example with compressed air diverted from at least one engine, from the so-called intermediate pressure stage and / or the so-called high pressure stage depending on the flight situation. It should be noted that the use of compressed air for air conditioning is advantageous because its pressure and temperature are relatively high, so that the air can be adjusted over a wide range of desired pressures and temperatures. The OBIGGS system is coupled to the aircraft's fuel tank, and separates the oxygen from the air.

[0004] The OBIGGS system comprises at least one air separation module containing, for example, permeable membranes, such as polymer membranes, through which an air flow passes. Due to the different permeabilities of the membrane to nitrogen and oxygen, the system divides the air flow in such a way that an air flow with a high nitrogen content and an air flow with a high oxygen content are obtained. The nitrogen-enriched air fraction, considered as the inerting gas, is fed into the fuel tanks in such a way that The mixture of air and kerosene vapor present in this location is displaced and vented outside the tanks.

[0005] The inerting flow rate of fuel tanks is conventionally managed by a flow control valve known as an FCV valve for "Flow Control Valve" in English terminology. Existing valves conventionally comprise two calibrated orifices made in a rotating mobile sphere so as to selectively obtain two inerting flow rates.

[0006] Figure 1 represents, as a function of time t, an inerting flow requirement Db and the inerting flow rates Dmin; Dmax which can be obtained using a conventional FCV valve during different operating phases of a P1-P5 aircraft.

[0007] Phase P1 corresponds to the aircraft's ground movement phase. Phase P2 corresponds to the aircraft's takeoff phase. Phase P3 corresponds to a stabilized flight phase. Phase P4 corresponds to the aircraft's landing phase. Phase P5 is another phase of aircraft ground movement.

[0008] It is observed that the conventional FCV valve provides an inert gas flow rate Dmax that is much higher than the required flow rate Db over a large part of the operating phases P1-P5. In other words, such an inerting system provides too much inert air into the tanks compared to the actual requirements. This leads to overconsumption by the engines or a compressor if the air is supplied by the latter.

[0009] In addition, the lack of a closed position in current devices requires the integration of an additional "all or nothing" valve, resulting in additional cost and weight for the assembly.

[0010] The invention aims to effectively remedy the aforementioned drawbacks by proposing a fluid flow regulating valve comprising: - a body having: - a fluid inlet opening, and - a fluid discharge opening, - said valve further comprising a fluid flow rate adaptation device capable of modifying, according to at least three different values, a surface area of ​​a fluid passage orifice arranged between the fluid inlet opening and the fluid discharge opening.

[0011] The invention thus makes it possible, by adapting the surface area of ​​the fluid passage orifice, to precisely provide the flow rate of inerting gas necessary for inerting the tanks regardless of the aircraft's flight conditions. The invention thus makes it possible to reduce electrical consumption and / or fuel consumption linked to compressor operation. The invention also makes it possible to guarantee a sonic regime throughout the inerting request.

[0012] According to one embodiment of the invention, the fluid flow rate adaptation device is capable of assuming a closed state closing off a fluid passage inside the valve.

[0013] According to one embodiment of the invention, the fluid flow rate adaptation device comprises a diaphragm formed by a plurality of movable plates mounted movable relative to the body, each movable plate delimiting a portion of the fluid passage orifice, so that a movement of said movable plates relative to the body makes it possible to continuously vary a surface of the fluid passage orifice.

[0014] According to one embodiment of the invention, said valve comprises at least one actuator associated with a gear system capable of transforming a rotational movement of an actuator into a translational movement so as to move the movable plates relative to each other to modify a surface of the fluid passage orifice.

[0015] According to one embodiment of the invention, the gear system comprises a bevel gear capable of being driven in rotation by the actuator, said bevel gear meshing with a rotary driver, the rotary driver carrying axes mechanically linked to the movable plates, each axis being movable in translation. inside a corresponding light made in a guide fixed relative to the body.

[0016] According to one embodiment of the invention, each axis comprises a protuberance having locally a shape complementary to the corresponding lumen.

[0017] According to one embodiment of the invention, the fluid flow rate adaptation device comprises a barrel movable in rotation relative to the body, said barrel comprising a plurality of through-orifices of different diameters, so that a through-orifice of given diameter can selectively be arranged between the fluid inlet opening and the fluid discharge opening to constitute the fluid passage orifice.

[0018] According to one embodiment of the invention, the barrel comprises a plate in which the plurality of through-holes are made and a toothed crown arranged at an external periphery of the plate meshing with a bevel gear capable of being driven in rotation by an actuator.

[0019] According to one embodiment of the invention, said valve comprises an O-ring arranged in a groove made in a face of the body located opposite the barrel, said O-ring being intended to press against the barrel around the selected through-orifice.

[0020] The invention also relates to a system for regulating the flow rate of an inerting gas during a flight, comprising: - a fluid flow regulating valve as previously defined associated with an actuator, and - a computer configured to control the actuator so as to modify a surface area of ​​the fluid passage orifice as a function of a difference between an inerting gas flow rate setpoint and an inerting flow rate measurement.

[0021] The present invention will be better understood and other characteristics and advantages will become apparent upon reading the detailed description which follows, including embodiments given for illustrative purposes with reference to the attached figures, presented as non-limiting examples, which may serve to complete the understanding of the present invention and the description of its implementation and, where appropriate, contribute to its definition, in which:

[0022] [Fig. 1] Figure 1, already described, is a graphical representation, as a function of time, of an inerting flow rate requirement as well as the inerting flow rates that can be obtained by means of a valve according to the state of the art during different phases of operation of an aircraft;

[0023] [Fig. 2] Figure 2 is a perspective view of a first embodiment of a flow regulating valve according to the invention with a diaphragm;

[0024] [Fig. 3] Figure 3 is a perspective view of the diaphragm flow regulating valve according to the invention without the body;

[0025] [Fig. 4] Figure 4 is a perspective view illustrating a mechanical connection between axes linked to movable plates and a rotary driver of the diaphragm flow regulating valve according to the invention;

[0026] [Fig. 5] Figure 5 is a perspective view illustrating a mechanical connection between the axes linked to the movable plates and a guide fixed relative to the body of the diaphragm flow regulating valve according to the invention;

[0027] [Fig. 6] Figure 6 is a perspective view illustrating a fluid passage orifice delimited by the set of plates of the diaphragm flow regulating valve according to the invention;

[0028] [Fig. 7a] [Fig. 7b] Figures 7a and 7b are front views illustrating a modulation of the amplitude of the fluid passage orifice of a diaphragm flow regulating valve according to the invention;

[0029] [Fig. 8] Figure 8 is a graphical representation illustrating a time monitoring of an inerting flow requirement that can be obtained by means of a diaphragm flow regulating valve according to the invention during different operating phases of an aircraft;

[0030] [Fig. 9] Figure 9 is a perspective view of a second embodiment of a flow regulating valve according to the invention with a barrel;

[0031] [Fig. 10] Figure 10 is a perspective view of the barrel flow regulating valve according to the invention without the body;

[0032] [Fig. 11] Figure 11 is a perspective view illustrating the positioning of a seal of the barrel flow regulating valve according to the invention;

[0033] [Fig. 12] Figure 12 is a front view of a barrel of a flow regulating valve according to the invention provided with a plurality of through-orifices;

[0034] [Fig. 13a] [Fig. 13b] Figures 13a and 13b are front views illustrating a selection of extreme diameters of the fluid passage orifice of a barrel flow control valve according to the invention;

[0035] [Fig. 14] Figure 14 is a graphical representation illustrating a time monitoring of an inerting flow requirement that can be obtained by means of a barrel flow regulating valve according to the invention during different operating phases of an aircraft;

[0036] [Fig. 15] Figure 15 is a schematic representation of a system for regulating the flow of an inerting gas during a flight.

[0037] It should be noted that the structural and / or functional elements common to the different embodiments may have the same references. Thus, unless otherwise stated, such elements have identical structural, dimensional and material properties.

[0038] Figures 2 to 7b and Figures 9 to 13b show a fluid flow regulating valve 10 having an axis X1. The valve 10 comprises a body 11 having a fluid inlet opening 12, and a fluid discharge opening 13. The openings 12 and 13 are coaxial with respect to the axis X1.

[0039] The valve 10 further comprises a fluid flow rate adaptation device 15 capable of modifying, according to at least three different values, a surface of a fluid passage orifice 16 disposed between the fluid inlet opening 12 and the fluid discharge opening 13.

[0040] In the embodiment of Figures 2 to 7b, the fluid flow rate adaptation device 15 comprises a diaphragm 19 visible in Figures 4, 5, 6, 7a and 7b formed by a plurality of movable plates 20 mounted movable relative to the body 11. Each movable plate 20 delimits a portion of the fluid passage orifice 16, so that a movement of said plates 20 relative to the body 11 makes it possible to continuously vary a surface of the fluid passage orifice 16. Such a configuration makes it possible to propose an infinite number of calibrated orifices (and therefore an infinite number of inerting flow rates).

[0041] As can be seen in Figures 4, 5, and 6, the movable plates 20 are arranged edge to edge with respect to each other. The movable plates 20 have a generally triangular shape. The two adjacent sides of the angle located on the side of the fluid passage orifice 16 are each in contact along their thickness against one side of a neighboring plate 20. In the example shown, the diaphragm 19 comprises six movable plates 20 delimiting a fluid passage orifice 16 having a quasi-circular hexagonal shape. Of course, the number of movable plates 20 used to form the diaphragm 19 may be greater or less than 6.

[0042] The valve 10 comprises at least one actuator 21 shown schematically in Figure 2 associated with a gear system 22 shown in Figures 3, 4, 5 and 6 capable of transforming a rotational movement of an actuator 21 in a translational movement so as to move the movable plates 20 relative to each other to modify a surface of the fluid passage orifice 16. The actuator 21 is preferably an electric actuator such as an electric motor. Alternatively, the actuator 21 is a pneumatic actuator or any other type of actuator suitable for the application.

[0043] The gear system 22 comprises a bevel gear 23 capable of being driven in rotation by the actuator 21 around an axis X2 having a radial orientation relative to the axis X1 of the valve 10. For this purpose, a shaft 25 carrying the bevel gear 23 comprises a connection interface 26 with the actuator 21. The connection interface 26 comprises, for example, a notch intended to cooperate with a complementary flat shape produced on the actuator 21. The notch is arranged at one end of the shaft 25.

[0044] The assembly between the actuator 21 and the body 11 of the valve 10 can be achieved by means of a clamping collar (not shown) intended to be arranged inside a groove 29. For this purpose, a connecting piece 24 comprises a central portion 24.1 of tubular shape mounted on the shaft 25 and two annular collars 24.2 of radial orientation relative to an axis of the shaft 25 (see figures 2, 3 and 9). Each collar 24.2 comes from one end of the central portion 24.1. The groove 29 extends between the two collars 24.2. The groove 29 has a U-shaped section. The connecting piece 24 is arranged at one end of the shaft 25 near the connection interface 26.

[0045] The bevel gear 23 meshes with a toothed crown of a rotary driver 30 movable in rotation around the axis X1 of the valve 10. The rotary driver 30 carries axes 31 visible in figures 4, 5 and 6 mechanically linked to the movable plates 20. Each axis 31 constituted by a rod is arranged inside a groove 32 made at a periphery of the rotary driver 30, as shown in figure 4. Each axis 31 is movable in translation inside a corresponding slot 33 made in a guide 36 fixed relative to the body 11 (see figure 5). The guide 36 comprises a tubular portion of axial orientation extended at one end by an annular portion of radial orientation in which the slots 33 are made.

[0046] Each axis 31 may comprise a protuberance 37 visible in figures 4 and 5 having locally a shape complementary to the light 33. Each light 33 has a direction D1 of longitudinal extension orthoradial with respect to the axis X1 of the valve 10. The orthoradial direction D1 is located in a plane perpendicular to the axis X1 of the valve 10 and is perpendicular to a radial direction with respect to the axis X1 of the valve 10.

[0047] An operation of the diaphragm valve 10 according to the invention is described below. A rotation of the actuator 21 in a first direction of rotation generates a rotation of the rotary driver 36 via the bevel gear 23. The rotary driver 36 moves the axes 31 inside the slots 33 of the guide 36 in a first direction, which causes a translational movement of the movable plates 20 so as to increase a surface area of ​​the fluid passage orifice 16.

[0048] The rotation of the actuator 21 in a second direction of rotation opposite to the first direction of rotation causes a rotation of the rotary driver 36 via the bevel gear 23. The rotary driver 36 moves the axes 31 inside the slots 33 of the guide 36 in a second direction (opposite to the first direction), which causes a translational movement of the movable plates 20 to reduce a surface area of ​​the fluid passage orifice 16.

[0049] Figures 7a and 7b are front views illustrating a modulation of the amplitude of the fluid passage orifice 16 between a minimized fluid passage area to ensure a low flow rate of inerting gas and a maximized fluid passage area to ensure a high flow rate of inerting gas. The fluid passage area can vary continuously between these two extreme positions. The fluid flow adaptation device 15 can also assume a state in which the movable plates 20 close a passage of the fluid inside the valve 10.

[0050] Figure 8 represents, as a function of time t, an inerting flow rate requirement Db (corresponding to an inerting flow rate setpoint) and the inerting flow rate Dv which can be obtained by means of the diaphragm valve 10 according to the invention during different operating phases of an aircraft P1-P5.

[0051] Phase P1 corresponds to the aircraft's ground movement phase. Phase P2 corresponds to the aircraft's takeoff phase. Phase P3 corresponds to a stabilized flight phase. Phase P4 corresponds to the aircraft's landing phase. Phase P5 is another phase of aircraft ground movement.

[0052] Figure 8 shows that the diaphragm-controlled valve 10 19 allows, by adapting the surface area of ​​the fluid passage orifice 16, to precisely and continuously supply the necessary inerting gas flow rates Db during the different operating phases P1-P5. Valve 10 therefore allows precise monitoring of an inerting flow rate setpoint corresponding to flow rate Db.

[0053] In the embodiment of Figures 9 to 13b, the fluid flow rate adapting device 15 comprises a barrel 40 movable in rotation relative to the body 11. The barrel 40 visible in Figure 10 comprises a plurality of through-orifices 41 of different diameters, so that a through-orifice 41 of given diameter can selectively be arranged between the fluid inlet opening 12 and the fluid discharge opening 13 to constitute the fluid passage orifice 16. An axis of rotation X3 of the barrel 40 is parallel to the axis X1 of the valve 10.

[0054] The barrel 40 comprises a disc-shaped plate 42 in which the plurality of through-orifices 41 are made and a toothed crown 43 arranged at an external periphery of the plate 42 meshing with a bevel gear 23. The through-orifices 41 are advantageously arranged along the same circumference of the barrel 40.

[0055] In this case, as illustrated in Figure 12, the barrel 40 has 8 through-holes 41. Alternatively, the barrel 40 has a number less than or greater than 8 through-holes. Preferably, the number of through-holes 41 is at least equal to 5. The greater the number of through-holes 41, the greater the precision of the regulating valve 10, but the greater its size due to the increase in the diameter of the barrel 40.

[0056] In order to rotate the barrel 40 and modify the diameter of the fluid passage orifice 16, the bevel gear 23 is capable of being rotated by the actuator 21 along an axis X2 having a radial orientation relative to the axis X1 of the valve 10 (see FIG. 9). For this purpose, the shaft 25 carrying the bevel gear 23 comprises a connection interface 26 with the actuator 21. The connection interface 26 comprises, for example, a notch intended to cooperate with a complementary flat shape produced on the actuator 21. The assembly between the actuator 21 and the body 11 of the valve 10 can be achieved by means of a clamping collar (not shown) intended to be arranged inside a groove 29 provided for this purpose.

[0057] The operation of the actuator 21 then causes a rotation of the bevel gear 23 which moves the barrel 40 in rotation around the axis X3 to select the through orifice 41 constituting the desired fluid passage orifice 16.

[0058] As shown in Figure 11, the seal is ensured by means of an O-ring 45 arranged in a groove 46 made in a face of the body 11 located opposite the barrel 40. The through-orifices 41 come selectively between the fluid inlet opening 12 and the fluid discharge opening 13, so that the O-ring 45 is pressed against the barrel 40 around the selected through-orifice 41 to ensure the seal around said through-orifice 41.

[0059] Figures 13a and 13b respectively show the selection of a small diameter fluid passage orifice 16 to ensure a low inerting gas flow rate and a large diameter fluid passage orifice 16 to ensure a high inerting gas flow rate.

[0060] By placing a solid portion 44 of the barrel 40 between the fluid inlet opening 12 and the fluid discharge opening 13, the fluid passage is closed so as to obtain a closed state of the valve 10. The solid portion 44 of the barrel 40 is for example provided between two consecutive through-orifices (see figure 12).

[0061] Figure 14 represents, as a function of time t, an inerting flow rate requirement Db (corresponding to an inerting flow rate setpoint) and the inerting flow rate Dv which can be obtained by means of the barrel valve 10 according to the invention during different operating phases of an aircraft P1-P5.

[0062] Phase P1 corresponds to the aircraft's ground movement phase. Phase P2 corresponds to the aircraft's takeoff phase. Phase P3 corresponds to a stabilized flight phase. Phase P4 corresponds to the aircraft's landing phase. Phase P5 is another phase of aircraft ground movement.

[0063] Figure 8 shows that with 5 different equivalent diameters: Diam=2.5mm, 4mm, 7.5mm, 8.5mm and 9mm, the barrel-controlled valve 10 ensures precise monitoring of the inerting flow rate setpoint Db during the different operating phases P1-P5 of the aircraft.

[0064] Figure 15 shows a system for regulating the flow rate of an inerting gas during a flight comprising a fluid flow rate regulating valve 10 associated with an actuator 21, and a computer 48 configured to control the actuator 21 so as to modify a surface area of ​​the fluid passage orifice 16 as a function of a difference between an inerting gas flow rate setpoint Db and an inerting flow rate measurement Dmes. The inerting gas flow rate setpoint Db varies as a function of the operating phase P1-P5 of the aircraft.

[0065] The actuator 21 can be controlled in real time by PID (Proportional, Integral, Derivative) or other type regulation depending on a flow measurement recorded by a flow sensor integrated or external to the valve 10. As a variant, it can be envisaged to effectively ensure the control of the valve 10 according to recorded flight profiles, in particular via the use of suitable mapping.

[0066] The invention also relates to an aircraft comprising at least one fuel tank, an OBIGGS type inerting system coupled to the fuel tank, as well as the air flow regulation system of figure 15.

[0067] Of course, the various features, variations and / or embodiments of the present invention may be combined with each other in various combinations to the extent that they are not incompatible or mutually exclusive.

[0068] Furthermore, the invention is not limited to the embodiments described above and provided solely by way of example. It encompasses various modifications, alternative forms and other variations that may be envisaged by those skilled in the art within the scope of the present invention and in particular all combinations of the different operating modes described above, which can be taken separately or in association.

Claims

CLAIMS 1. System for regulating the flow of an inerting gas during a flight, characterized in that it comprises: - a fluid flow regulating valve (10) comprising: - a body (11) having: a fluid inlet opening (12), and a fluid discharge opening (13), said valve (10) further comprising a fluid flow rate adaptation device (15) capable of modifying, according to at least three different values, a surface area of ​​a fluid passage orifice (16) arranged between the fluid inlet opening (12) and the fluid discharge opening (13), - a computer (48) configured to control the actuator (21) so as to modify a surface area of ​​the fluid passage orifice (16) as a function of a difference between an inerting gas flow rate setpoint (Db) and an inerting flow rate measurement (Dmes) so that the valve (10) makes it possible to ensure precise monitoring of the inerting flow rate setpoint (Db) during different operating phases of an aircraft.

2. System according to claim 1, characterized in that the fluid flow adaptation device (15) is capable of taking a closed state closing a fluid passage inside the valve (10).

3. System according to claim 1 or 2, characterized in that the fluid flow rate adaptation device (15) comprises a diaphragm (19) formed by a plurality of movable plates (20) mounted movable relative to the body (11), each movable plate (20) delimiting a portion of the fluid passage orifice (16), so that a movement of said movable plates (20) relative to the body (11) makes it possible to continuously vary a surface of the fluid passage orifice (16).

4. System according to claim 3, characterized in that it comprises at least one actuator (21) associated with a gear system (22) capable of transforming a rotational movement of an actuator (21) into a translational movement so as to move the movable plates (20) relative to each other to modify a surface of the fluid passage orifice (16).

5. System according to claim 4, characterized in that the gear system (22) comprises a bevel gear (23) capable of being driven in rotation by the actuator (21), said bevel gear (23) meshing with a rotary driver (30), the rotary driver (30) carrying axes (31) mechanically linked to the movable plates (20), each axis (31) being movable in translation inside a corresponding slot (33) made in a guide (36) fixed relative to the body (11).

6. System according to claim 5, characterized in that each axis (31) comprises a protuberance (37) having locally a shape complementary to the corresponding light (33).

7. System according to claim 1 or 2, characterized in that the fluid flow rate adaptation device (15) comprises a barrel (40) movable in rotation relative to the body (11), said barrel (40) comprising a plurality of through-orifices (41) of different diameters, so that a through-orifice (41) of given diameter can selectively be arranged between the fluid inlet opening (12) and the fluid discharge opening (13) to constitute the fluid passage orifice (16).

8. System according to claim 7, characterized in that the barrel (40) comprises a plate (42) in which the plurality of through-orifices (41) are made and a toothed crown (43) arranged at an external periphery of the plate (42) meshing with a bevel gear (23) capable of being driven in rotation by an actuator (21).

9. System according to claim 7 or 8, characterized in that it comprises an O-ring (45) arranged in a groove (46) made in a face of the body (11) located opposite the barrel (40), said O-ring (45) being intended to come and press against the barrel (40) around the selected through-orifice (41).