Aerodynamic measurement probe

Abstract

The present invention relates to an aerodynamic measurement probe (10) intended to be exposed to an air flow and comprising a body (12), the body (12) comprising a mast (14) and an acquisition tube (16) which is mounted on the mast (14) and defines an inlet (24) for the air flow, the mast (14) and the acquisition tube (16) together delimiting an internal part of the body (12). The aerodynamic measurement probe (10) further comprises guide means disposed in the internal part of the body (12) and configured to guide water droplets contained in the air flow towards a drainage hole provided in the body (12).

Description

[0001] TITLE: Aerodynamic Measurement 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, angle of incidence, temperature, speed, etc.

[0004] Probes of this type are known as anemobaroclinometric probes.

[0005] Such an aerodynamic measuring probe can therefore be used in any device exposed to an airflow such as an aircraft or a wind turbine.

[0006] The technical problem addressed by the present invention is the accumulation of water in the pressure circuit of aerodynamic measuring probes that are subjected to exposure to water.

[0007] Indeed, in the case of water ingestion in the pressure circuit, water (in all its forms) can alter the measurement value and can even in some cases damage the pressure sensor.

[0008] Several solutions already exist in the state of the art to overcome this problem.

[0009] Thus, some probes include devices called water traps which consist, for example, of partitions or labyrinths made in the acquisition tube of the probe.

[0010] These partitions or labyrinths then stop the water or water crystals which are then evacuated through at least one drainage hole made in a wall of the tube.

[0011] However, this solution is not completely satisfactory since water crystals can in some cases get stuck in the labyrinths or partitions forming a water trap, which causes the probe to become clogged.

[0012] The Applicant's document FR 3067 115 B1 proposes another solution in which the acquisition tube is free of any partition or labyrinth but includes a drainage hole made in a rear partition of this tube in the axis of symmetry of the latter.

[0013] This solution then makes it possible to solve the problem of the probe becoming clogged by water crystals, but in some cases does not allow for the total evacuation of the water.

[0014] The present invention aims to solve this prior art problem and to provide an aerodynamic measuring probe that efficiently removes water from the airflow while preventing the probe from becoming clogged with water crystals. To this end, the invention relates to an aerodynamic measuring probe designed to be exposed to an airflow and comprising a body. The body includes a mast and a data acquisition tube mounted on the mast, defining an airflow inlet. The mast and data acquisition tube together define an internal portion of the body.

[0015] The aerodynamic measuring probe further includes guidance means disposed in the internal part of the body and configured to guide water droplets contained in the airflow towards a drainage hole provided in the body.

[0016] 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:

[0017] - the guiding means have an aerodynamic shape according to the direction of airflow inside the acquisition tube;

[0018] - the guiding means include a first part forming at least a ramp configured to increase the kinetic energy of the airflow;

[0019] - the guidance means further include a second part delimiting an opening of a measurement channel extending through the mast;

[0020] - the guidance means are arranged in a junction zone of the mast and the acquisition tube;

[0021] - the drainage hole is provided in a rear wall of the acquisition tube, advantageously in the axis of symmetry of the latter;

[0022] - the measurement channel opens in a rear area of ​​the acquisition tube, the rear area being formed between the junction area and the rear wall;

[0023] - the measurement channel opens in the junction zone;

[0024] - the guidance systems are arranged in the mast;

[0025] - the drainage hole is made in a wall delimiting the mast.

[0026] The invention will become clearer upon reading the following description, given solely by way of non-limiting example, and made with reference to the drawings in which:

[0027] - [Fig. 1] Figure 1 is a schematic cross-sectional view of an aerodynamic measuring probe according to the invention, the probe comprising guiding means;

[0028] - [Fig. 2] Figure 2 is a detailed view of part II of Figure 1;

[0029] - [Fig. 3] [Fig. 4] [Fig. 5] [Fig. 6] [Fig. 7] [Fig. 8] Figures 3 to 8 are schematic views of guidance means according to other embodiments of the invention.

[0030] Figure 1 illustrates an aerodynamic measuring probe 10 according to the invention. This probe can be used in any environment exposed to aerodynamic flows, particularly airflows. In particular, the probe 10 according to the invention allows the measurement of at least one physical value related to the environment, such as total pressure, static pressure, angle of attack, temperature, speed, etc.

[0031] More specifically, probe 10 is for example an anemobaroclinometric probe which can for example measure several of the aforementioned quantities at the same time.

[0032] The environment in which the probe is exposed is notably a freezing environment, that is to say an environment in which frost accretions are likely to form outside or inside the probe.

[0033] The probe 10 is advantageously mounted on an aircraft fuselage or on an external part of a wind turbine.

[0034] An aircraft is defined as any pilotable machine capable of moving through the air. Specifically, an aircraft can be an airplane, a helicopter, or a drone.

[0035] As illustrated in Figure 1, the probe 10 comprises a body 12 exposed to an airflow, for example fixed to the fuselage of the aircraft.

[0036] The body 12 includes a mast 14 fixed for example to the fuselage of the aircraft and an acquisition tube 16 mounted on the mast 14.

[0037] In some embodiments, the probe 10 may also include other elements, in particular an internal part which is for example disposed inside the fuselage as an extension of the mast 14. This internal part may include various elements, in particular electronic measuring elements which are known in themselves and will not be explained in detail thereafter.

[0038] The acquisition tube 16, also called the Pitot tube, is advantageously oriented according to the airflow F, for example, along the direction of flight of the aircraft. In other words, the acquisition tube 16 is advantageously parallel to the aircraft fuselage, while the mast 14 extends transversely to the fuselage and the acquisition tube 16. The mast 14 notably serves to keep the acquisition tube 16 away from the aircraft fuselage.

[0039] The acquisition tube 16 extends along a principal axis X presenting its axis of symmetry, between an open end 21 and a closed end 22.

[0040] The open end 21 then forms an inlet 24 of the airflow F and the closed end 22 forms a rear wall 26 of the acquisition tube 16.

[0041] The internal part of the acquisition tube 16 successively forms along the main axis X a front zone 31, a junction zone 32 and a rear zone 33.

[0042] The forward zone 31 extends for example over more than half the total length of the acquisition tube 16 and ensures the intake of the airflow from the inlet 24. In particular, in this forward zone 31, the airflow received via the inlet 24 flows substantially parallel to the main axis X.

[0043] The junction zone 32 ensures the connection between the acquisition tube 16 and the mast 14. Its precise shape can be varied according to different embodiments of the invention and will be explained in more detail later.

[0044] The rear zone 33 extends between the junction zone 32 and the rear wall 26 of the acquisition tube 16. In some embodiments, this rear zone 33 allows in particular the redirection of the airflow flowing in the front zone and the junction zone inside the mast 14 as will be explained in more detail later.

[0045] The rear wall 26, for example, has a rounded shape that allows the airflow to be redirected inside the mast 14.

[0046] The mast 14 delimits a measurement channel 38 extending in the embodiment of figure 1 along substantially the entire length of the mast 14.

[0047] The measurement channel 38 extends along a transverse axis Y.

[0048] In particular, the measurement channel 38 extends from the junction zone 32 of the acquisition tube 16 to substantially the fuselage of the aircraft.

[0049] This measurement channel 38 allows the airflow to be directed to a sensitive part allowing the pressure of this flow or any other value to be measured, for example, as explained above.

[0050] According to the invention, the body 12 of the probe 10 further includes guiding means 40 configured to guide water droplets contained in the airflow towards a drainage hole provided in the body 12.

[0051] According to the embodiment of Figure 1, these guiding means 40 are arranged in the junction zone 32.

[0052] These guidance means 40 will be explained in more detail with reference to figure 2 showing a detailed view of this junction zone 32.

[0053] Thus, as shown in Figure 2, the guiding means 40 comprise a first part 41 and a second part 42.

[0054] The first part 41 is positioned facing the airflow circulating in the front area 31 of the acquisition tube 16 and forms a ramp configured to increase the kinetic energy of this airflow.

[0055] In particular, in the example of Figure 2, the first part 41 has a spoiler extending transversely into the acquisition tube 16 so as to restrict the cross-sectional area of ​​the acquisition tube 16.

[0056] This first part 41 extends for example along an axis perpendicular to the main axis X of the acquisition tube between two opposite walls of this acquisition tube 16. In addition, this first part 41 extends transversely to the extension of the measurement channel 38 thus partially forming its closure along the transverse axis Y which is perpendicular to the main axis X.

[0057] The first part 41 advantageously has a rounded shape allowing the incoming airflow to be directed aerodynamically towards the rear area 33 of the acquisition tube.

[0058] In some examples, the first part 41 may have a substantially spherical shape, thus forming at least one rounded shape along the principal X axis and one rounded shape along an axis perpendicular to the X and Y axes (i.e., an axis perpendicular to the plane of figures 1 and 2).

[0059] The second part 42 allows for the delimitation of an opening 45 of the measurement channel 38.

[0060] The dimensions of this opening and its exact position are determined, for example, by the nature of the value measured by the measuring channel 38.

[0061] In the example in Figure 2, the second part 42 extends transversely from a junction point between the acquisition tube 16 and the mast 14. This second part 42 forms an angle of approximately 45° with each of the X and Y axes.

[0062] Just like the first part 41, the second part 42 extends for example transversely between two opposite walls of the main tube 16 or of the mast 14.

[0063] The opening 45 of the measuring channel 38 is thus formed in the example of this figure between the first part 41 and the second part 42 of the guiding means 40.

[0064] Furthermore, in this example, the measurement channel 38 opens in the rear area 33 of the acquisition tube 16. In other words, in this example, the opening 45 is oriented towards the rear area 33 of this acquisition tube 16.

[0065] In the first embodiment, a drainage hole 50 is provided in the rear wall 26 of the acquisition tube 16 in the axis of symmetry of this tube 16, the axis of symmetry then being parallel to or coinciding with the principal axis X.

[0066] Thus, this drainage hole 50 is positioned opposite the first part 41 of the guiding means 40.

[0067] During the operation of the probe 10, the incoming airflow is first directed by the front area 31 of the acquisition tube 16 in a manner substantially parallel to the main axis X.

[0068] Then, when this airflow encounters the guiding means 40 in the junction zone 32 of this tube 16, it slightly deflects its direction by the ramp formed by the first part 41 of the guiding means 40. This increases the speed of this airflow and consequently its kinetic energy. Then, upon entering the rear zone 33 of the acquisition tube 16, the water droplets, having a greater mass than the other particles in the airflow, are projected towards the drainage hole 50 due to their greater kinetic energy compared to the other particles in the airflow.

[0069] As for the latter, they are directed by the rear area 33 towards the opening 45 and then by the measurement channel 38 towards the sensitive part.

[0070] Thus, the water droplets are separated from the rest of the airflow and are efficiently drained through the drainage hole 50.

[0071] Figure 3 illustrates another embodiment of the guidance means 40.

[0072] According to this embodiment, the guiding means 40 also include a first part 41 similar to that described with reference to figures 1 and 2.

[0073] According to this embodiment of Figure 3, the guiding means 40 also include a second part 42 which, just as in the previous embodiment, extends from a junction point between the acquisition tube 16 and the mast 14, delimiting the opening 45.

[0074] However, according to this embodiment, the second part 42 of the guiding means 40 constitutes an extension of the first part 41. Thus, in this example, the second part 42 extends substantially along the Y axis of the measuring channel 38 and the opening 45 is formed in the spherical shape formed by these two parts 41 and 42.

[0075] In other words, in this embodiment, the second part 42 is curved to form an extension of the shape of the first part 41. In the previous embodiment, this second part 42 is, on the contrary, for example, substantially flat in shape.

[0076] Figure 4 illustrates another embodiment of the guidance means 40.

[0077] According to this embodiment, the first part 41 of these guiding means comprises a leading edge 61 arranged to meet the airflow before any other element of the guiding means 40 and two ramps 62 extending from this leading edge 61. As can be seen in the section DD of figure 4, the leading edge 61 extends substantially along the transverse axis Y and each of the ramps 62 forms an angle (for example substantially equal to 45°) with the principal axis X.

[0078] Thus, the first part 41 of the guiding means 40 allows the incoming airflow to be guided on either side of these ramps 62 to the rear area 33 of the acquisition tube 16.

[0079] In this example, the opening 45 of the measuring channel 38 extends substantially perpendicularly to the main axis X and is thus positioned opposite the drainage hole 50, as can be seen in particular on section CC of figure 4. Thus, in this embodiment, the second part 42 of the guiding means simply forms an extension of a wall of the measuring channel 38 to delimit the opening 45.

[0080] Finally, according to this embodiment, the ramps 62 extend only partially through the acquisition tube 16 along the transverse axis Y. Thus, a gap 65 is formed between a wall of the acquisition tube 16 and the first part 41 of the guiding means 40.

[0081] The guiding means illustrated in Figure 5 are substantially similar to those in Figure 4 and form in particular a leading edge 61 and two ramps 62 in the first part 41 of these means 40.

[0082] Unlike the previous embodiment, the ramps 62 of this embodiment extend substantially entirely through the acquisition tube 16, along the transverse axis Y. Thus, unlike the previous embodiment, no gap is formed between the corresponding wall of the acquisition tube and these ramps. Consequently, the entire airflow flows on both sides of the ramps 62, as illustrated in the lower part of Figure 5 showing section DD.

[0083] In the embodiment of figure 6, the guiding means 40 also include a first part 41 and a second part 42.

[0084] According to this previous embodiment, the first part 41 is separated from the second part 42 along the main axis X.

[0085] In particular, in this embodiment, the first part 41 forms a leading edge 61 and two ramps 62 extending from this leading edge 61, as can be seen in section DD of Figure 6. The first part 41 is arranged entirely upstream of the second part 42 along the principal axis X.

[0086] In addition, the second part 42 completely delimits the opening 45 of the measurement channel 38.

[0087] Furthermore, this opening 45 is arranged between the first part 41 and the second part 42 so that the measurement channel 38 opens in a region formed between the first part 41 and the second part 42 of the guiding means 40. In other words, in this embodiment, the measurement channel 38 opens in the junction zone 32 of the acquisition tube 16.

[0088] Furthermore, the second part 42 forms a play with each of the lateral walls of the acquisition tube 16 in order to conduct the water drops into the rear area 33 of the acquisition tube 16 and evacuate them through the drainage hole 50 formed also as in the previous embodiments in the axis of symmetry of this acquisition tube. In addition, unlike the previous embodiments, in this embodiment the rear area 33 can form a funnel shape converging then towards the drainage hole 50.

[0089] In all the preceding embodiments, the guiding means 40 are formed in the junction zone 32 of the acquisition tube 16 and the drainage hole 50 is formed in the rear wall 26 of this acquisition tube 16.

[0090] However, it is possible to place these guiding means 40 in any other location of the internal part of the body 12 formed by the internal part of the acquisition tube 16 and the measurement channel 38 of the mast 14.

[0091] Thus, in the following embodiments explained with reference to figures 7 and 8, the guiding means 40 are arranged in the mast 14 and in particular in the measuring channel 38.

[0092] Thus, in the example of these figures, the internal part of the acquisition tube 16 is free of any obstruction.

[0093] The guiding means 40, as in previous embodiments, comprise a first part 41 and a second part 42.

[0094] The second part 42 always delimits the opening 45 of the measurement channel 38.

[0095] In the embodiments of figures 7 and 8, this opening 45 is formed in a side wall of the acquisition tube 16 in the junction area 32.

[0096] The first part 41 of the guiding means 40 forms in these embodiments several ramps to guide the water droplets contained in the airflow towards a drainage hole 50. In these embodiments, this drainage hole 50 is then provided in a wall of the mast 14.

[0097] In the embodiment of Figure 7, the first part 41 of the guiding means 40 has two substantially flat ramps extending from the opposite walls of the measuring channel 38. The first ramp, arranged upstream, is then oriented towards the second ramp while leaving a hole for the passage of the airflow into the interior of the measuring channel 38. In this example, the drainage hole 50 is provided, for example, in the point of junction between the second ramp and the corresponding wall of the measuring channel 38.

[0098] In the embodiment shown in Figure 8, the first ramp of the first part 41 is substantially similar to that described previously. In particular, it has a substantially flat shape.

[0099] In contrast, the second ramp is formed by a hook extending from the corresponding wall of the measuring channel 38. Just as in the previous case, a passage hole is formed between these two ramps to allow the airflow to pass inside the measuring channel 38 and the drainage hole 50 is formed in the junction point between the second ramp forming a hook and the corresponding wall of the measuring channel 38.

[0100] Of course, many other implementation methods are also possible.

[0101] It is therefore understandable that the present invention offers a number of advantages.

[0102] Firstly, the guidance means as described above with reference to the different embodiments make it possible to increase the kinetic energy of the airflow circulating inside the probe and to partially guide this flow towards a drainage hole.

[0103] Thus, the heaviest particles contained in this airflow, i.e. the water droplets, are projected towards the drainage hole and evacuated outside the probe via it, while the other particles of the flow continue to circulate inside the probe to ensure the required measurement.

[0104] This allows the water droplets to be separated from the airflow efficiently.

[0105] It should also be noted that guidance systems with aerodynamic shapes do not create areas of airflow stagnation. This prevents the probe from becoming clogged by crystal formation in such areas.

Claims

DEMANDS 1. Aerodynamic measuring probe (10) intended to be exposed to an airflow and comprising a body (12), the body (12) comprising a mast (14) and an acquisition tube (16) mounted on the mast (14) and defining an inlet (24) of the airflow, the mast (14) and the acquisition tube (16) together delimiting an internal part of the body (12); the aerodynamic measuring probe (10) further comprising guiding means (40) disposed in the internal part of the body (12) and configured to guide water droplets contained in the airflow towards a drainage hole (50) provided in the body (12); the guiding means (40) comprising a first part (41) forming at least one ramp configured to increase the kinetic energy of the airflow.

2. Probe (10) according to claim 1, wherein the guiding means (40) have an aerodynamic shape along the direction of flow of the airflow inside the acquisition tube (16).

3. Probe (10) according to claim 1 or 2, wherein the guiding means (40) further comprise a second part (42) defining an opening (45) of a measuring channel (38) extending through the mast (14).

4. Probe (10) according to any one of the preceding claims, wherein the guiding means (40) are arranged in a junction zone (32) of the mast (14) and the acquisition tube (16).

5. Probe (10) according to claim 4, wherein the drainage hole (50) is provided in a rear wall (26) of the acquisition tube (16), advantageously in the axis of symmetry thereof.

6. Probe (10) according to claim 5 taken in combination with claim 3, wherein the measurement channel (38) opens in a rear area (33) of the acquisition tube (16), the rear area (33) being formed between the junction area (32) and the rear wall (26).

7. Probe (10) according to claim 5 taken in combination with claim 3, wherein the measuring channel (38) opens in the junction zone (32).

8. Probe (10) according to any one of claims 1 to 3, wherein the guiding means (40) are arranged in the mast (14).

9. Probe (10) according to claim 8, wherein the drainage hole (50) is provided in a wall delimiting the mast (14).

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