Aerodynamic measuring probe

Abstract

Aerodynamic Measurement Sound The present invention relates to an aerodynamic measurement probe (10) comprising a body (22) and heating means (40) for 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 disposed in a portion of the heating channel (46) extending through at least one zone of interest. Figure for the abstract: Figure 1

Description

Title of the invention: Aerodynamic measuring probe

[0001] The present invention relates to an aerodynamic measuring probe.

[0002] In particular, the probe according to the invention makes it possible to measure at least one of the following quantities: total pressure, static pressure, angle of incidence, temperature, velocity, etc. Probes of this type are known as anemobaroclinometric probes.

[0003] The aerodynamic measuring probe can thus be used in any device exposed to an aerodynamic flow such as an aircraft or a wind turbine.

[0004] The technical problem addressed by the invention is the local accretion of frost on or in aerodynamic measuring probes.

[0005] Indeed, when this type of probe is exposed to icing conditions, frost accretion may appear on its external or internal parts.

[0006] This can then lead to a measurement error or a release of pieces of ice which can damage elements downstream of the measured flow.

[0007] In order to avoid these events, a heating power is emitted in the probe which increases the overall temperature of its body.

[0008] In the prior art, many documents are already known which allow the implementation of means for heating aerodynamic measuring probes.

[0009] Thus, for example, we know of document FR 3 034 753 B1 which discloses a tubular two-phase thermodynamic circuit extending inside the body of the probe.

[0010] This circuit contains a heat transfer fluid which changes from a gaseous state to a liquid state to heat the outer part of the probe body.

[0011] This circuit can, for example, extend through the entire body of the probe, thus allowing for homogeneous heating of the probe.

[0012] However, the solution disclosed in the aforementioned document does not allow the energy density to be concentrated in important areas of the probe while maintaining a satisfactory size.

[0013] Indeed, when it is necessary to concentrate the 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.

[0014] The present invention aims to remedy these drawbacks and to propose an aerodynamic measuring probe that allows the energy density to be concentrated in predetermined areas of interest, while preserving a satisfactory size of the entire system.

[0015] To this end, the invention aims at an aerodynamic measuring probe comprising a body and means for heating this body, the body having a plurality of zones of interest;

[0016] heating means comprising a thermodynamic circuit configured to circulate a heat transfer fluid;

[0017] the thermodynamic circuit comprising a heating channel extending through the body and at least one area of ​​interest of this body;

[0018] the heating channel being delimited by a tubular wall comprising at least one projection disposed in a part of the heating channel extending through at least one area of ​​interest.

[0019] According to other advantageous aspects of the invention, the probe has one or more of the following characteristics, taken individually or in all technically possible combinations:

[0020] - the tubular wall forms an inner surface and an outer surface,

[0021] the or each projection protruding from the inner surface;

[0022] - the or each projection is formed by at least one of the elements chosen from the band :

[0023] - a groove;

[0024] - a tapping;

[0025] - a plot;

[0026] - a bridge;

[0027] - a honeycomb;

[0028] - the tubular wall comprises a plurality of projections arranged in said part of the heating duct extending through at least one area of ​​interest;

[0029] - the body includes a mast and a Pitot tube mounted on the mast;

[0030] - at least one area of ​​interest is formed in a junction between the mast and the tube of Pitot;

[0031] - the Pitot tube extends between an open end and a closed end, at less an area of ​​interest is formed in at least one of the ends (24, 26) of the Pitot tube;

[0032] - the heating channel extends through the mast and the Pitot tube;

[0033] - the body defines an exterior surface, the or each area of ​​interest being adjacent to the outer surface of the body;

[0034] - the or each area of ​​interest presents an area with a heating demand increased compared to other areas of the body.

[0035] The invention will become clearer upon reading the following description, given solely by way of non-limiting example and with reference to the drawings in which: - [Fig.1] [Fig.1] is a schematic perspective cutaway view of an aerodynamic measuring probe according to the invention; - [Fig.2] [Fig.2] is a schematic side view of part of the probe of the [Fig. 1]; and - [Fig. 3] [Fig. 3] is a schematic perspective view of part of the probe of the [Fig.l].

[0036] Figure 1 illustrates an aerodynamic measuring probe 10 according to the invention. This probe can be used in any medium exposed to aerodynamic flows.

[0037] 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 total pressure, static pressure, incidence, temperature, speed, etc.

[0038] More specifically, probe 10 is an anemobaroclinometric probe which can, for example, measure several of the aforementioned quantities.

[0039] The medium in which the probe 10 is exposed is in particular a freezing medium, that is to say a medium in which frost accretions are likely to form outside or inside the probe.

[0040] The probe 10 is advantageously mounted on the fuselage of an aircraft or on an external part of a wind turbine.

[0041] Aircraft means any pilotable machine capable of moving through the air. In particular, an aircraft may refer to an airplane, a helicopter, or a drone.

[0042] As illustrated in [Fig.1], the probe 10 comprises an internal part 12, a base 14, a mast 16 and a Pitot tube 18.

[0043] The base 14 allows the probe 10 to be fixed on an external surface which is exposed to aerodynamic flows.

[0044] In particular, the base 14 can be fixed to a surface of the aircraft fuselage or to an external surface of the wind turbine such as a blade.

[0045] This surface is designated under reference 20 on [Fig.1].

[0046] The mast 16 extends from the base 14 and supports the Pitot tube 18 at a distance from the surface 20.

[0047] 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 fluxes in the vicinity of the surface 20.

[0048] The internal part 12 also extends from the base 14 but in the opposite direction to that of the mast 16.

[0049] In particular, the internal part 12 is intended to be received in a cavity formed in the surface 20.

[0050] The Pitot tube 18 is mounted at the end of the mast 16 as will be explained in more detail later.

[0051] In the rest 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.

[0052] In particular, the body 22 is intended to be exposed to the outside 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 sheltered from them.

[0053] In the example of [Fig. 1], the body 22 is static. According to other embodiments, the body 22, or at least certain parts thereof, can be made movable. For example, the Pitot tube 18 can be mounted on a wind vane, allowing the tube 18 to be oriented, for example, according to the aerodynamic flows.

[0054] In the example of [Fig. 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.

[0055] Along this axis, the Pitot tube 18 extends between an open end 24 and a closed end 26.

[0056] The open end 24 allows air to enter the probe 10. The closed end 26 allows the Pitot tube 18 to be mounted on the end of the mast 16 and includes, for example, a sensitive part allowing the measurement of at least one physical quantity as is known per se.

[0057] In addition, the body 22 of the probe 10 defines an outer surface 28 and an inner surface 30.

[0058] The inner surface 30 delimits a conduit 32 extending from the open end 24 of the Pitot tube 18 to substantially the inner part 12 through the Pitot tube 18, the mast 16 and possibly partially the base 14.

[0059] This conduit 32 allows air from the outside flow to be conducted to one or more sensitive parts arranged in the different parts of the probe 10, as is known per se.

[0060] The body 22 and the internal part 12 delimit different components of the probe 10 enabling its operation to be implemented.

[0061] In particular, these components include heating means 40 for heating the body 22 and thus preventing icing on its various parts, as will be explained in more detail later. The other components of the probe 10 (such as sensors, various electrical circuits, etc.) are known per se and will not be explained further.

[0062] The heating means 40 include in particular a thermodynamic circuit 42 and an evaporator 44.

[0063] As can be seen in [Fig. 1], the evaporator 44 is arranged for example in the internal part 12 of the probe 10 and allows heating of a heat transfer fluid circulating in the thermodynamic circuit 42.

[0064] 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 adapted to efficiently heat and evaporate the heat transfer fluid inside the thermodynamic circuit 42, as is known per se.

[0065] The thermodynamic circuit 42 allows the heat transfer fluid to circulate through the body 22 of the probe 10.

[0066] The thermodynamic circuit 42 has a closed circuit in which the heat transfer fluid circulates in gaseous and / or liquid form. Advantageously, the heat transfer fluid is in gaseous form at the outlet of the evaporator 44 and in liquid form at the inlet of the evaporator 44.

[0067] The thermodynamic circuit 42 has one or more heating channels 46 allowing the heat transfer fluid to circulate.

[0068] In the example in [Fig. 1], only one heating channel 46 is shown. In other examples, several heating channels 46 can be switched off, for example, in parallel with each other.

[0069] 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.

[0070] In particular, in the mast 16, the heating channel 46 can extend on either side of the air duct 32 described above. More specifically, 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.

[0071] Similarly, in the Pitot tube 18, the heating channel 46 can extend on either side of the air duct 32 between the outer surface 28 and the inner surface 30 of the body 22.

[0072] Furthermore, 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.

[0073] Advantageously, according to the invention, the heating channel 46 extends through at least one area of ​​interest of the body 22.

[0074] In the following description, by area of ​​interest, we mean an area of ​​body 22 with an increased heating demand compared to other areas of body 22.

[0075] In particular, in each area of ​​interest, the body 22 has an increased probability of icing accretion or corresponds to a sensitive part of this body affecting the measurement quality by the probe 10.

[0076] 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.

[0077] In the example of [Fig.2], four areas of interest 50 are represented.

[0078] Among these areas of interest, two areas of interest 50 are located at the open end 24 of the Pitot tube 18, on either side of the air duct 32. Another area of ​​interest 50 is located at the closed end 26 of the Pitot tube 18 and yet another area of ​​interest 50 is located at the junction between the Pitot tube 18 and the mast 16. Of course, other locations on the body 22 may also have areas of interest.

[0079] The areas of interest 50 described above are advantageously adjacent to the outer surface 28 of the body 22. However, it is also possible that at least one area of ​​interest is 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.

[0080] 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, such as a metal or a ceramic. The tubular wall may, for example, have a substantially circular or rectangular cross-sectional shape.

[0081] 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.

[0082] 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 later.

[0083] By a substantially smooth shape of a surface, it is understood that the surface is differentiable at least twice in each of its points along each of the directions.

[0084] In the portions of the heating channel 46 passing through the areas of interest 50, the inner surface 58 of the tube wall has a plurality of projections 65 visible in [Fig. 3], for example. These projections 65 advantageously present roughness in the inner surface 58 of the tube wall, which increases the contact area with the heat transfer fluid compared to the case of a smooth tubular portion of this surface.

[0085] The projections 65 can, for example, be made of the same material as the tube wall. Advantageously, an additive manufacturing technique such as 3D printing is used to form the projections 65 and / or the tube wall.

[0086] At least some of the projections 65 can form a single piece with the tubular wall. Advantageously, each projection 65 is formed from the material of the tubular wall.

[0087] Advantageously, the outer surface 60 of the tubular wall always has a smooth surface which does not show any protrusions or cavities due to the protrusions 65.

[0088] In other words, the projections 65 have overthicknesses in the tubular wall of the heating channel 46.

[0089] In other words, the projections 65 have a higher concentration of material in the corresponding area of ​​interest 50 than the surface of the heating channel 46 outside of any area of ​​interest.

[0090] In the example of [Fig.3], each projection 65 is formed by a stud having, for example, a substantially cylindrical shape which projects from the inner surface 58 of the tubular wall.

[0091] In other embodiments, each projection 65 can represent any other suitable shape such as a polygonal groove, a tapped hole, a bridge or a honeycomb.

[0092] More generally, each projection 65 has a higher concentration of material than outside any area of ​​interest, thus allowing the heat carried by the heat transfer fluid to be concentrated in that area.

[0093] The present invention has a number of advantages.

[0094] 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.

[0095] Thus, it is possible to have concentrated heating in these areas of interest.

[0096] Areas of interest may represent any area where more heating is needed to prevent frost formation or to minimize the risk of frost formation.

[0097] This can be done by creating additional thicknesses in the thermodynamic circuit but without altering its shape, particularly its external shape. Thus, this thermodynamic circuit does not create any more bulk compared to a known thermodynamic circuit used for homogeneous heating of the body.

Claims

Demands

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) disposed in a portion of the heating channel (46) extending through at least one zone of interest (50); the or each projection (65) presenting a higher 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) projecting out from the inner surface (58).

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

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

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

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