Aerodynamic measurement probe

Abstract

The present invention relates to an aerodynamic measurement probe (10) comprising a body (22) and means (40) for heating this body (22), the body (22) having a plurality of zones of interest. The heating means (40) comprise a thermodynamic circuit (42) configured to circulate a heat-transfer fluid. The thermodynamic circuit (42) comprises a heating channel (46) extending through the body (22) and at least one zone of interest of this body (22). The heating channel (46) is delimited by a tubular wall comprising at least one projection arranged in a portion of the heating channel (46) extending through at least one zone of interest.

Description

[0001] TITLE: Aerodynamic measuring probe

[0002] The present invention relates to an aerodynamic measuring probe.

[0003] In particular, the probe according to the invention makes it possible to measure at least one of the following quantities: total pressure, static pressure, incidence, temperature, speed, etc. Probes of this type are known as anemobaroclinometric probes.

[0004] The aerodynamic measuring probe can thus be used in any device exposed to an aerodynamic flow such as an aircraft or a wind turbine.

[0005] The technical problem addressed by the invention is the local accretion of frost on or in aerodynamic measuring probes.

[0006] Indeed, when this type of probe is exposed to icing conditions, frost accretions on the external or internal parts of it may appear.

[0007] This can then lead to a measurement error or the release of pieces of ice which can damage elements downstream of the measured flow.

[0008] To avoid these events, a heating power is emitted into the probe which increases the overall temperature of its body.

[0009] In the state of the art, numerous documents are already known which make it possible to implement means for heating aerodynamic measuring probes.

[0010] Thus, for example, we know the document FR 3 034 753 B1 which discloses a tubular two-phase thermodynamic circuit extending inside the body of the probe.

[0011] This circuit contains a heat transfer fluid which changes from gaseous to liquid state to heat the external part of the probe body.

[0012] This circuit can, for example, extend throughout the entire body of the probe, thus allowing it to be heated evenly.

[0013] However, the solution disclosed in the aforementioned document does not allow the energy density to be concentrated in the important areas of the probe while preserving a satisfactory footprint.

[0014] In fact, when it is necessary to concentrate heating in a given place, the external geometry of the thermodynamic circuit should be changed, which necessarily implies an increase in the overall size of the system.

[0015] The present invention aims to overcome these drawbacks and then propose an aerodynamic measuring probe making it possible to concentrate the energy density in predetermined areas of interest, while preserving a satisfactory size of the entire system.

[0016] To this end, the invention relates to an aerodynamic measuring probe comprising a body and means for heating this body, the body having a plurality of zones of interest; the heating means comprising a thermodynamic circuit configured to circulate a heat transfer fluid; the thermodynamic circuit comprising a heating channel extending through the body and at least one zone of interest of this body; the heating channel being delimited by a tubular wall comprising at least one projection arranged in a part of the heating channel extending through at least one zone of interest.

[0017] According to other advantageous aspects of the invention, the probe has one or more of the following characteristics, taken in isolation or in all technically possible combinations:

[0018] - the tubular wall forms an inner surface and an outer surface, the or each projection projecting relative to the inner surface;

[0019] - the or each projection is formed at least by one of the elements chosen from the group:

[0020] - a groove;

[0021] - a tapping;

[0022] - a plot;

[0023] - a bridge;

[0024] - a honeycomb;

[0025] - the tubular wall comprises a plurality of projections arranged in said portion of the heating channel extending through at least one area of ​​interest;

[0026] - the body includes a mast and a Pitot tube mounted on the mast;

[0027] - at least one area of ​​interest is formed in a junction between the mast and the Pitot tube;

[0028] - the Pitot tube extends between an open end and a closed end, at least one area of ​​interest is formed in at least one of the ends (24, 26) of the Pitot tube;

[0029] - the heating channel extends through the mast and the Pitot tube;

[0030] - the body defines an exterior surface, the or each area of ​​interest being adjacent to the exterior surface of the body; - the or each area of ​​interest has an area with an increased heating demand relative to other areas of the body.

[0031] The invention will appear more clearly on reading the description which follows, given solely by way of non-limiting example and made with reference to the drawings in which:

[0032] - [Fig.1] Figure 1 is a schematic perspective view in section of an aerodynamic measuring probe according to the invention;

[0033] - [Fig.2] Figure 2 is a schematic side view of a portion of the probe of Figure 1; and

[0034] - [Fig.3] Figure 3 is a schematic perspective view of part of the probe of Figure 1.

[0035] Figure 1 illustrates an aerodynamic measuring probe 10 according to the invention. This probe can be used in any environment exposed to aerodynamic flows.

[0036] In particular, the probe 10 according to the invention makes it possible to measure at least one of the physical values ​​relating to the medium, such as the total pressure, the static pressure, the incidence, the temperature, the speed, etc.

[0037] More particularly, the probe 10 is an anemobaroclinometric probe which can, for example, measure several of the aforementioned quantities.

[0038] The environment in which the probe 10 is exposed is in particular an icing environment, that is to say an environment in which ice accretions are likely to form outside or inside the probe.

[0039] The probe 10 is advantageously mounted on a fuselage of an aircraft or on an external part of a wind turbine.

[0040] An aircraft is any pilotable device capable of moving through the air. In particular, an aircraft can be an airplane, a helicopter, or a drone.

[0041] As illustrated in Figure 1, the probe 10 comprises an internal part 12, a base 14, a mast 16 and a Pitot tube 18.

[0042] The base 14 makes it possible to fix the probe 10 on an external surface which is exposed to aerodynamic flows.

[0043] In particular, the base 14 can be fixed to a surface of the fuselage of the aircraft or to an external surface of the wind turbine such as a blade.

[0044] This surface is designated by the reference 20 in figure 1.

[0045] Mast 16 extends from base 14 and supports the Pitot tube

[0046] 18 at a distance from the surface 20. In particular, the length of the mast 16 is determined by the application given to the probe 10 and makes it possible in particular to avoid surface flows in the vicinity of the surface 20.

[0047] The inner portion 12 also extends from the base 14 but in the opposite direction to that of the mast 16.

[0048] In particular, the internal part 12 is intended to be received in a cavity formed in the surface 20.

[0049] The Pitot tube 18 is mounted at the end of the mast 16 as will be explained in more detail later.

[0050] In the remainder of the description, it will be considered that the base 14, the mast 16 and the Pitot tube 18 form a body 22 of the probe 10.

[0051] In particular, the body 22 is intended to be exposed to the exterior of the object on which the probe 10 is mounted. In other words, the body 22 is exposed to aerodynamic flows while the internal part 12 remains protected from them.

[0052] In the example of Figure 1, the body 22 is static. According to other embodiments, the body 22 or at least certain parts of it can be made mobile. For example, the Pitot tube 18 can be mounted on a wind vane making it possible to orient this tube 18, for example, according to the aerodynamic flows.

[0053] In the example of Figure 1, the Pitot tube 18 extends substantially along, for example, a longitudinal axis of the object on which the probe 10 is mounted, for example along the longitudinal axis of the aircraft. In other words, in this example, the Pitot tube 18 is parallel at least locally to the surface 20.

[0054] Along this axis, the Pitot tube 18 extends between an open end 24 and a closed end 26.

[0055] The open end 24 allows air to enter the probe 10. The closed end 26 allows the Pitot tube 18 to be mounted at the end of the mast 16 and comprises, for example, a sensitive part allowing at least one physical quantity to be measured as is known per se.

[0056] Further, the body 22 of the probe 10 defines an outer surface 28 and an inner surface 30.

[0057] The inner surface 30 defines a conduit 32 extending from the open end 24 of the Pitot tube 18 to substantially the inner portion 12 through the Pitot tube 18, the mast 16 and possibly partially the base 14.

[0058] This conduit 32 makes it possible to conduct air from the external flow to one or more sensitive parts arranged in the different parts of the probe 10, as is known per se. The body 22 and the internal part 12 delimit different components of the probe 10 making it possible to implement its operation.

[0059] In particular, these components comprise heating means 40 for heating the body 22 and thus preventing icing on these different parts, as will be explained in more detail later. The other components of the probe 10 (such as sensors, different electrical circuits, etc.) are known per se and will not be explained later.

[0060] The heating means 40 comprise in particular a thermodynamic circuit 42 and an evaporator 44.

[0061] As can be seen in Figure 1, the evaporator 44 is arranged for example in the internal part 12 of the probe 10 and makes it possible to heat a heat transfer fluid circulating in the thermodynamic circuit 42.

[0062] In particular, the evaporator 44 comprises at least one heating element, for example a resistive heating element, which is powered by an external energy source to heat and advantageously evaporate the heat transfer fluid circulating in the thermodynamic circuit. The evaporator 44 has a shape suitable for heating and evaporating the heat transfer fluid inside the thermodynamic circuit 42 efficiently, as is known per se.

[0063] The thermodynamic circuit 42 makes it possible to circulate the heat transfer fluid through the body 22 of the probe 10.

[0064] Advantageously, in certain embodiments, the thermodynamic circuit 42 comprises actuation means for setting the heat transfer fluid in motion. According to an exemplary embodiment, these actuation means have active means comprising, for example, a pump. According to another exemplary embodiment, these actuation means are passive means, such as a localized capillary system (also called porous). Such an element then forms the capillary pump of the system. Locating this element in a restricted area makes it possible to use very small pore radii (of the order of 1 μm), which makes it possible to release a significant capillary force.

[0065] The thermodynamic circuit 42 has a closed circuit in which the heat transfer fluid circulates in gaseous form and / or in liquid form. Advantageously, the heat transfer fluid has the gaseous form at the outlet of the evaporator 44 and the liquid form at the inlet of the evaporator 44.

[0066] The thermodynamic circuit 42 has one or more heating channels 46 for circulating the heat transfer fluid. In the example of FIG. 1, only one heating channel 46 is shown. In other examples, several heating channels 46 can be switched off, for example in parallel to each other.

[0067] This heating channel 46 extends from the evaporator 44 then passes through the mast 16 then passes through the Pitot tube 18 and makes a turn in this Pitot tube 18 to then return to the evaporator 44 via the mast 16.

[0068] In particular, in the mast 16, the heating channel 46 may extend on either side of the air duct 32 described above. More particularly and as illustrated in FIG. 2, the heating channel 46 extends in the mast 16 between the outer surface 28 and the inner surface 30 on both sides of the air duct 32.

[0069] Similarly, in the Pitot tube 18, the heating channel 46 may extend on either side of the air duct 32 between the outer surface 28 and the inner surface 30 of the body 22.

[0070] Additionally, in the Pitot tube 18, the heating channel 46 may include circumferential sections to form a loop. In FIG. 1, several at least partially circumferential sections are shown.

[0071] Advantageously, according to the invention, the heating channel 46 extends through at least one area of ​​interest of the body 22.

[0072] In the remainder of the description, by zone of interest is meant an area of ​​the body 22 with an increased heating demand compared to other areas of the body 22.

[0073] In particular, in each area of ​​interest, the body 22 presents an increased probability of icing accretion or corresponds to a sensitive part of this body affecting the quality of measurement by the probe 10.

[0074] Each area of ​​interest may be adjacent to the outer surface 28 of the body 22 or to the inner surface 30 of this body 22.

[0075] In the example of Figure 2, four areas of interest 50 are represented.

[0076] Among these areas of interest, two areas of interest 50 are arranged at the open end 24 of the Pitot tube 18, on either side of the air duct 32. Another area of ​​interest 50 is arranged at the closed end 26 of the Pitot tube 18 and yet another area of ​​interest 50 is arranged at the junction between the Pitot tube 18 and the mast 16. Of course, other locations of the body 22 may also have areas of interest.

[0077] The areas of interest 50 described above are advantageously adjacent to the outer surface 28 of the body 22. However, it is also possible for at least one area of ​​interest to be adjacent to the inner surface 30 of the body 22 or, for example, to both the outer surface 28 and the inner surface 30 of the body 22. The heating channel 46 advantageously has a tubular shape. In other words, the heating channel 46 is delimited by a tubular wall. This tubular wall is made, for example, of a thermally conductive material, for example a metal or ceramic. The tubular wall may, for example, have a substantially circular or rectangular transverse shape.

[0078] This tubular wall forms an inner surface 58 which is in contact with the heat transfer fluid and an outer surface 60 which is opposite the inner surface 58.

[0079] The inner surface 58 of the tubular wall advantageously has a substantially smooth surface except for the parts of the heating channel 46 passing through the areas of interest 50, as will be explained in more detail below.

[0080] By a substantially smooth shape of a surface, we mean that the surface is derivable at least twice in each of its points in each of the directions.

[0081] In the parts of the heating channel 46 passing through the areas of interest 50, the inner surface 58 of the tubular wall has a plurality of projections 65 visible in FIG. 3 for example. These projections 65 advantageously have roughnesses in the inner surface 58 of the tubular wall which increase the contact surface with the heat transfer fluid compared to the case of a smooth tubular portion of this surface.

[0082] The projections 65 may for example be made of the same material as the tubular wall. Advantageously, an additive manufacturing technique such as 3D printing is used to form the projections 65 and / or the tubular wall.

[0083] At least some of the projections 65 may form a single part with the tubular wall. Advantageously, each projection 65 is integral with the tubular wall.

[0084] Advantageously, the outer surface 60 of the tubular wall always has a smooth surface which does not show projections or cavities due to the projections 65.

[0085] In other words, the projections 65 have excess thicknesses in the tubular wall of the heating channel 46.

[0086] In other words, the projections 65 have a greater concentration of material in the corresponding area of ​​interest 50 than the surface of the heating channel 46 outside any area of ​​interest.

[0087] In the example of Figure 3, each projection 65 is formed by a stud having for example a substantially cylindrical shape which projects from the interior surface 58 of the tubular wall.

[0088] In other embodiments, each projection 65 may represent any other suitable shape such as a polygonal groove, a thread, a bridge or a honeycomb. More generally, each projection 65 has a greater concentration of material than that outside any area of ​​interest, thus making it possible to concentrate the heat carried by the heat transfer fluid in this location.

[0089] The present invention has a number of advantages. First of all, it is clear that the probe according to the invention makes it possible to adapt the heating system in order to heat more areas of interest.

[0090] Thus, it is possible to have concentrated heating in these areas of interest.

[0091] Areas of interest can represent any area where additional heating is required to prevent or minimize the risk of icing. This can be achieved by creating extra thicknesses in the thermodynamic circuit but without changing its shape, particularly its external shape. Thus, this thermodynamic circuit does not create more space than a known thermodynamic circuit used for homogeneous heating of the body.

[0092] Finally, the use of actuating means to set the heat transfer fluid in motion makes it possible to compensate for any pressure losses due to the presence of the projections.

Claims

CLAIMS 1. Aerodynamic measuring probe (10) comprising a body (22) and heating means (40) for this body (22), the body (22) having a plurality of zones of interest (50); the heating means (40) comprising a thermodynamic circuit (42) configured to circulate a heat transfer fluid; the thermodynamic circuit (42) comprising a heating channel (46) extending through the body (22) and at least one zone of interest (50) of this body (22); the heating channel (46) being delimited by a tubular wall comprising at least one projection (65) arranged in a portion of the heating channel (46) extending through at least one zone of interest (50); the or each projection (65) having a greater concentration of material in the corresponding area of ​​interest (50) than the surface of the heating channel (46) outside any area of ​​interest (50).

2. Aerodynamic measuring probe (10) according to claim 1, wherein the tubular wall forms an inner surface (58) and an outer surface (60); the or each projection (65) protruding relative to the inner surface (58).

3. Aerodynamic measuring probe (10) according to claim 1 or 2, wherein the or each projection (65) is formed at least by one of the elements chosen from the group: - a groove; - a tapping; - a plot; - a bridge; - a honeycomb.

4. An aerodynamic measuring probe (10) according to any preceding claim, wherein the tubular wall comprises a plurality of projections (65) disposed in said portion of the heating channel extending through at least one area of ​​interest (50).

5. An aerodynamic measuring probe (10) according to any preceding claim, wherein the body (22) comprises a mast (16) and a Pitot tube (18) mounted on the mast (16).

6. Aerodynamic measuring probe (10) according to claim 5, wherein at least one area of ​​interest (50) is formed in a junction between the mast (16) and the Pitot tube (18).

7. Aerodynamic measuring probe (10) according to claim 5 or 6, wherein the Pitot tube (18) extends between an open end (24) and a closed end (26); at least one area of ​​interest (50) is formed in at least one of the ends (24, 26) of the Pitot tube (18).

8. An aerodynamic measuring probe (10) according to any one of claims 5 to 7, wherein the heating channel (46) extends through the mast (16) and the Pitot tube (18).

9. An aerodynamic measuring probe (10) according to any preceding claim, wherein the body (22) defines an outer surface (28), the or each area of ​​interest (50) being adjacent to the outer surface (28) of the body (22).

10. An aerodynamic measuring probe (10) according to any preceding claim, wherein the or each area of ​​interest (50) has an area with an increased heating demand relative to other areas of the body (22).

11. Aerodynamic measuring probe (10) according to any one of the preceding claims, in which the thermodynamic circuit (42) comprises actuating means configured to set the heat transfer fluid in motion.

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