TESTING DEVICE FOR AN AERONAUTICAL COMPONENT IN ICING CONDITIONS

Abstract

Device (10) for testing at least one aeronautical part (12), particularly in icing conditions, characterized in that it comprises: - a box (18) having an inlet port (20) for a gas flow and an outlet port (22) for this gas flow, the box (18) further having, between the inlet and outlet ports (20, 22), an opening (24) for accessing the inside of the box (18) which is closed by a removable partition (26), - a system (28) for holding said at least one part (12), this holding system (28) being configured to be mounted inside the box (18) through said opening (24), and - a member (30) for moving the system (28) and / or the part (12) in rotation about at least one axis (A), this member (30) being accessible from outside the box (18). Figure for the abbreviation: Figure 1

Description

Title of the invention: DEVICE FOR TESTING AN AERONAUTICAL PART IN ICING CONDITIONS Technical field of the invention

[0001] The present invention relates to the general field of testing aeronautical parts. It relates more particularly to a device for testing at least one aeronautical part, in particular in icing conditions. Technical background

[0002] In flight, an aircraft is subjected to extreme thermal conditions which are likely to affect the health of the parts and therefore their lifespan. It is therefore important to test aeronautical parts beforehand to anticipate their behavior in flight and to provide de-icing systems for these parts if necessary.

[0003] Icing tests on aeronautical parts are generally difficult to carry out due to the complex shape of the parts to be tested (parts with an aerodynamic profile, small section, etc.) and the difficulty of gripping associated with these different characteristics.

[0004] In the current technique, a test device is used in which the part to be tested is mounted and through which a flow of freezing gas passes. The part can be equipped with a defrosting system in order to evaluate its effectiveness.

[0005] Current technical solutions have many drawbacks: • it is difficult to hold a part firmly during a test, avoiding movements and vibrations, • it is difficult to adapt to all shapes and materials of the parts to be tested, • the tests are long and complex to implement, • the electrical cables connected to the defrosting system are bulky and tend to obstruct the flow of freezing gas around the room, • each test device is dedicated to a type or shape of part and it is not possible to use the same device to test different parts, which leads to having several device references and as many test device references as there are different parts to be tested, • it is not possible to adjust the position of the part being tested in the gas flow and it is therefore necessary to disassemble and reassemble the part in a new position to test its behavior in the freezing gas flow in this new position, etc.

[0006] The present invention aims to provide a solution to at least some of the problems of the prior art, which is simple, efficient and economical. Summary of the invention

[0007] The invention relates to a device for testing at least one aeronautical part, in particular in icing conditions, characterized in that it comprises:

[0008] - a box comprising an inlet port for a gas flow and an outlet port for this gas flow, the box further comprising, between the inlet and outlet ports, an access opening to the interior of the box which is closed by a removable wall,

[0009] - a system for holding said at least one part, this holding system being configured to be mounted inside the box through said opening, and

[0010] - a member for moving the system and / or the part in rotation around at least one axis at least one axis, this organ being accessible from outside the box.

[0011] The device according to the invention has many advantages. First of all, its box can accommodate several types of parts, which are different in their shapes, and / or their dimensions, and / or their materials. The removable wall of the box allows easy access to the inside of the box for mounting the part. The box can be easily connected to a freezing gas flow circuit, via its inlet and outlet ports. The holding system makes it possible to hold the part being tested fixedly and advantageously to avoid vibrations of the part. The holding system can be adapted to the part to be tested and it is then sufficient to replace the holding system with another, while keeping the box, to move from one part to a part of a different shape for example. The member also makes it possible to move the part being tested, or between two tests, without the need to dismantle the device and in particular the part.The invention therefore makes it possible to facilitate and accelerate tests, in particular icing tests, on aeronautical parts. Among the parts that can be tested, we can cite for example: a blade, a vane, or even a series of blades or vanes.

[0012] The device according to the invention may also have one or more of the following characteristics, taken alone or in combination with each other: • the box has a generally parallelepiped shape, the inlet and outlet ports being arranged on two opposite sides or ends of the box; • the removable wall is an upper wall of the box which has, for example, a generally rectangular shape; • the movement member passes through a light in the box and in particular in the wall, this light opening into the inside of the box; • the light has a generally curved shape and has an angle which corresponds to a possible angular travel of movement of the system and / or the part around said axis; • the system comprises two pivots aligned on said axis; • one of the pivots is guided in an orifice of the removable wall, and the other of the pivots is guided in an orifice of a wall of the box, which is opposite the removable wall; • the system further comprises two circular plates configured to be inserted respectively between the pivots and the part, or to be mounted around these pivots, at least one of these plates comprising at least one hole for the passage of electrical connection wires; • the system comprises two pairs of jaws, a first pair of jaws being configured to grip one end of the workpiece, and a second pair of jaws being configured to grip an opposite end of the workpiece; • a first of the jaws of the first pair of jaws is secured to a first of the pivots, a second jaw of this first pair of jaws being configured to be fixed to the first jaw of this pair; • a second of the jaws of the second pair of jaws is secured to a second of the pivots, a second jaw of this second pair of jaws being configured to be fixed to the first jaw of this pair; and • the box, and in particular the removable wall, comprises a first visual marker configured to inform an operator of the angular position of the part around said axis, and / or a second visual marker configured to inform an operator of the direction of flow of the gas flow in the box.

[0013] The present invention also relates to an installation for testing at least one aeronautical part in icing conditions, this installation comprising a device as described above and a circuit for generating a flow of icing gas, for example at a temperature between -5°C and -30°C, and at a speed between 50 and 200m / s with an LWC between 0.1 and 1g / m3.

[0014] The present invention also relates to a method of mounting an aeronautical part, such as a blade, in a device as described above, comprising the following steps:

[0015] a) disassemble and remove the removable wall of the box,

[0016] b) mount the part with its holding system in the box so that the axis of displacement is oriented vertically, and

[0017] c) close the opening of the box with the removable wall.

[0018] The method according to the invention may also have one or more of the following characteristics or steps, taken alone or in combination with each other: • the method comprises, after step b), a step w) of adjusting the angular position of the part around said axis, using the displacement member; • the method comprises, between steps a) and b), the following steps:

[0019] i) providing a mounting bracket,

[0020] ii) positioning the first jaws with the pivots on the mounting support, the pivots being housed in arrangements of the mounting support and the first jaws being supported on receiving surfaces of the mounting support,

[0021] iii) position the part on the first jaws,

[0022] iv) positioning the second jaws on the part and fixing them respectively to the first jaws, and

[0023] v) separating the assembly formed by the part and the holding system from the mounting support. Brief description of the figures

[0024] Other characteristics and advantages of the invention will appear during the reading of the detailed description which follows for the understanding of which reference will be made to the appended drawings in which:

[0025] [Fig-1] [Fig.l] is a schematic perspective view of a device according to the trial invention of an aeronautical part,

[0026] [Fig.2] [Fig.2] is a schematic sectional view along line II-II of [Fig.l],

[0027] [Fig.3] [Fig.3] is a schematic sectional view of the holding system of the device, according to line III-III of [Fig.l] or according to line III-III of [Fig.2],

[0028] [Fig.4] [Fig.4] is a schematic perspective view of a mounting bracket of the holding system,

[0029] [Fig.5a-5b] Figures 5a and 5b are schematic perspective views of the jaws of a first pair of jaws of the holding system,

[0030] [Fig.6a-6b] Figures 6a and 6b are schematic perspective views of the jaws of a second pair of jaws of the holding system,

[0031] [Fig.7a-7b] Figures 7a and 7b illustrate steps of an assembly method according to the invention, and show in particular the mounting of jaws on the mounting support of [Fig.4],

[0032] [Fig.8] [Fig.8] illustrates another step of the mounting method according to the invention, and shows in particular the mounting of the part on the mounting support,

[0033] [Fig.9] [Fig.9] is a schematic detail view of the mounting bracket and the holding system, and shows a plate of this holding system,

[0034] [Fig. 10] [Fig. 10] illustrates another step of the mounting method according to the invention, and shows in particular the mounting of jaws on the mounting support,

[0035] [Fig. 1 la-11b] Figures 1 la and 11b illustrate steps of a mounting method according to the invention, and show in particular the mounting of the part with its holding system in a box of the device,

[0036] [Fig. 1 lc-1 Id] Figures 1 le and 1 Id illustrate steps of an assembly method according to the invention, and show in particular the closing of the box of the device, by a removable wall, and

[0037] [Fig. 12] [Fig. 12] is a schematic detail view of the closing wall of the box and shows visual markers on this wall as well as a displacement member. Detailed description of the invention

[0038] Figures 1 to 12 illustrate an embodiment of a testing device 10 according to the invention of at least one aeronautical part 12, in particular in icing conditions.

[0039] In the example shown, the part 12 is a blade or vane although this aspect is not limiting. Furthermore, although only one part 12 is illustrated in the drawings and being tested, several parts could be tested simultaneously in a single device 10.

[0040] The device 10 is visible as a whole in [Fig.l], the other figures illustrating details or parts of this device as well as steps of a method of mounting the part 12 in this device 10.

[0041] [Fig.l] also shows an installation 14 for testing the part 12 in icing conditions, this installation 14 comprising the device 10 and a circuit 16 for generating a flow of icing gas which circulates according to the arrows.

[0042] The flow of freezing gas is for example an air flow.

[0043] The flow of freezing gas may have a temperature between -5°C and -30°C.

[0044] The flow of freezing gas can have a speed of between 50 and 200m / s, and by example of 80 m / s, and an LWC between 0.1 and lg / m3, and for example 0.3g / m3. LWC is the acronym for Liquid Water Content, that is to say the quantity of water present in the air to cause the gas flow to freeze.

[0045] The device 10 essentially comprises three parts:

[0046] - a box 20 comprising a gas flow inlet port 20 and an outlet port 22 of the gas flow, the box 20 further comprising, between the inlet and outlet ports 20, 22, an opening 24 for access to the interior of the box 20 which is closed by a removable wall 26,

[0047] - a system 28 for holding the part(s) 12, this holding system 28 being configured to be mounted inside the box 20 through said opening 24, and

[0048] - a member 30 for moving the system 28 and / or the part 12 in rotation around of at least one axis A, this member 30 being accessible from outside the box 20.

[0049] The box 20 preferably has the function of reconstituting a flow vein of a gas flow from an aircraft engine, such as a turbojet or turboprop for example.

[0050] The box 20 has for example a general parallelepiped shape, the inlet and outlet ports 20, 22 being arranged on two opposite sides or ends of the box 20.

[0051] The box 20 may have an elongated shape along an axis B, the inlet and outlet ports 20, 22 being arranged at the opposite axial ends of the box 20.

[0052] The input and output ports 20, 22 are preferably configured to be connected, for example by fitting onto complementary ends of the circuit 16. The input and output ports 20, 22 are for example of the female type and engaged by fitting onto male ends of the circuit 16.

[0053] The opening 24 is for example located in the middle of the box 20. The opening 24 is here located on the top of the box 20. The removable wall 26 is thus an upper wall of the box 20.

[0054] The opening 24 and the wall 26 have a generally rectangular shape in the example shown.

[0055] The dimensions of the opening 24 are advantageously designed to allow the passage and mounting of the part 12 with the holding system 28 inside the box 20.

[0056] In the example shown, the movement member 30 comprises a handle 32 which is accessible at the level of the removable wall 26. The handle 32 is connected to a finger 34 which passes through a slot 36 of the removable wall 26 and which is engaged in an orifice of the holding system 28 ([Fig.2]).

[0057] The axis A of movement of the part 12 is a vertical axis in the example shown. This axis A passes through the box 20 and passes through the closing wall 26.

[0058] Figures 1 and 12 show that the light 36 has a generally curved shape and has an angle which corresponds to a possible angular travel of movement of the system and the part around the axis A. This angular travel can be represented on an upper surface of the wall 26 by a first visual reference 38, as can be seen in [Fig.12],

[0059] The displacement member 30 may also comprise a plate 40 crossed by the handle 32 or the finger 34 and affixed to the upper surface of the closing wall 26. This plate 40 carries a movable indexing pin 42 which is movable in a direction parallel to the axis A, from a first position in which the displacement member 30 can move freely in the slot 36 to a second position in which it is engaged in a hole 44 of the wall 26 and locks the displacement member 30 in a given angular position around the axis A. As seen in [Fig. 12], the wall 26 comprises a series of holes 44 which can accommodate the pin 42 and which are distributed over the predetermined angular travel, preferably at regular intervals.

[0060] For example, the angular travel of movement of the member 30, and therefore the angular extent of the light 36, is 30°, and the holes are distributed every 5° along this travel.

[0061] The plate 40 can carry another movable pin 46 which is movable like the pin 42, in a direction parallel to the axis A, from a first position in which the displacement member 30 can move freely in the slot 36 to a second position in which it is engaged in a single hole 48 of the wall 26 and secures the locking of the displacement member 30 in a given angular position around the axis A (figures 1 and 2).

[0062] [Fig. 12] also shows that the removable wall 26 comprises a second visual marker 50 which informs the operator of the direction of flow of the gas flow in the box 20.

[0063] The holding system 28 is shown in detail in Figures 2, 3 and 5a to 6b.

[0064] In the example shown, the system 24 is capable of rotating the part 12 around of the axis A and for this purpose comprises two pivots 52 aligned on this axis A. Each of the pivots 52, 54 has a generally cylindrical shape in the example shown.

[0065] One of the pivots 52 is guided in an orifice 56 of the removable wall 26, and the other of the pivots 54 is guided in an orifice 58 of a wall of the box 20, which is opposite the removable wall 26.

[0066] The system 24 further comprises two circular plates 60, 62 configured to be interposed respectively between the pivots 52, 54 and the part 12, or else mounted around the pivots 52, 54.

[0067] In the drawings, and in particular [Fig. 8], it can be seen that each of these plates 60, 62 advantageously comprises a hole 64 for the passage of electrical connection wires or cables (not shown) in particular to a defrosting unit (not shown) of the part 10. Each of the plates 60, 62 may comprise two holes 64 of this type, diametrically opposite with respect to the axis A. Each of the holes 64 may have a general oval or elliptical shape for example. Here they are located at a distance from the center and the periphery of the plates 60, 62.

[0068] The system further comprises two pairs of jaws 66, 68 for securely holding the part 12.

[0069] A first pair of jaws 66 is configured to grip one end of the part 12 and is visible in FIGS. 5a and 5b. This first pair of jaws 66 can be equipped with counterforms 67 capable of matching the shape of the part to be gripped. It is therefore understood that only the counterforms 67 could be changed to grip with the first pair of jaws 66 the end of a part of different shape for example.

[0070] A second pair of jaws 68 is configured to grip an opposite end of the part and is visible in Figures 6a and 6b. This second pair of jaws can be equipped with counterforms 69 capable of matching the shape of the part to be gripped. It is therefore understood that only the counterforms 69 could be changed to grip with the second pair of jaws 68 the other end of the aforementioned part of different shape.

[0071] A first of the jaws 66b of the first pair of jaws 66 is secured to the pivot 52 which passes through the removable wall 26, as well as to the plate 60 associated with this pivot 52. In practice, as in the example shown, the orifice 58 of the wall 26 can be designed to accommodate the plate 60 and guide the pivot 52 via this plate 60.

[0072] A second jaw 66a of this first pair of jaws 66 is configured to be fixed to the first jaw 66b of this pair. The end of the part 12 is intended to be inserted between the jaws 66a, 66b.

[0073] A first of the jaws 68b of the second pair of jaws 68 is secured to the pivot 54 which passes through the wall of the box 20 opposite the removable wall 26, as well as to the plate 62 associated with this pivot 54. In practice, as in the example shown, the orifice of this wall can be designed to accommodate the plate 62 and guide the pivot 54 by means of this plate 62.

[0074] A second jaw 68a of this second pair of jaws 68 is configured to be fixed to the first jaw 68b of this pair. The end of the part 12 is intended to be inserted between the jaws 68a, 68b.

[0075] The present invention also relates to a method of mounting the part 12 in the device 10.

[0076] This method comprises the following steps:

[0077] a) disassemble and remove the removable wall 26 from the box 20,

[0078] b) mounting the part 12 with its holding system 28 in the box 20 so that the axis A of movement is preferably oriented vertically, and

[0079] c) closing the opening 24 of the box 20 with the removable wall 26.

[0080] These steps are shown schematically in Figures 11a to 11d.

[0081] The method may comprise, after step b), a step w) of adjusting the position angular position of the part 12 around the axis A, thanks to the displacement member 30. In the example shown, in particular in [Fig. 12], the two angular positions of the part 12 in the box 20 are separated from each other by 30° and the part can adopt any angular position between these extreme positions, by increments of 5°. The position of the part can be locked by inserting the pin 42 into the corresponding hole 44 of the wall 26, or even secured by inserting the pin 46 into the hole 48 of this wall 26.

[0082] To facilitate the mounting of the part 12, in particular in its holding support 28, the method may comprise the following steps:

[0083] i) providing a mounting bracket 70, an example of which is illustrated in [Fig.4],

[0084] ii) position the first jaws 66b, 68b with the pivots 52, 54 on the support of mounting 70, the pivots 52, 54 being housed in arrangements 72 of the mounting support 70 and the first jaws 66b, 68b being supported on receiving surfaces 74 of the mounting support 70 (figures 7a-7b),

[0085] iii) position the part 12 on the first jaws 66a, 68a ([Fig.8]),

[0086] iv) position the second jaws 66a, 68a on the part 12 and fix them respectively to the first bits 66b, 68b ([Fig. 10]), and

[0087] v) separate the assembly formed by the part 12 and the holding system 28 from the mounting support 70 (figures 1 la-11b).

[0088] The mounting bracket 70 is particularly useful for facilitating the mounting of the holding system 70 on the part 12, and especially for ensuring the mutual alignment of the pivots 52, 54.

[0089] The method may also comprise, between steps iv) and v), a step of passing electrical wires or cables through the holes 64 of the plates 60, 62, for the electrical connection of the defrosting unit mentioned above.

[0090] The invention provides several advantages, including: • the invention makes it possible to avoid having to carry out the test on the engine or to develop a specific machine, the development of which would be very long and very costly, • the invention allows direct and immediate visualization of the results in terms of ice accretion and defrosting of specimens, • the invention makes it possible to immobilize a part 12 in a given position regardless of the complexity of its geometry, • the holding system 28 with counterforms 67, 69 allows you to quickly and easily move from one part 12 to another, • the mounting support 70 makes it possible to prepare a part 12 to be tested in masked time while another part is being tested, which therefore does not create unnecessary immobilization of the test device, • the holes 64 on the plates 60, 62 of the holding system 28 allow the passage of the power connectors to the defrosting unit, and also allow the passage of a large number of wires, etc. • these holes 64 present at both ends of the part allow the choice of wire evacuation (from the top or from the bottom) so that they do not impact the aerodynamic flow in the test zone, • the displacement member forms an angular setting system for the part, which allows the angle of incidence (from 0° to 30° in 5° increments) of the gas flow on the part in the vein to be easily and precisely adjusted and this position to be locked using the indexing pin, etc.

Claims

Claims

1. Device (10) for testing at least one aeronautical part (12), in particular in icing conditions, characterized in that it comprises: - a box (18) comprising an inlet port (20) for a gas flow and an outlet port (22) for this gas flow, the box (18) further comprising, between the inlet and outlet ports (20, 22), an opening (24) for access to the interior of the box (18) which is closed by a removable wall (26), - a system (28) for holding said at least one part (12), this holding system (28) being configured to be mounted inside the box (18) through said opening (24), and - a member (30) for moving the system (28) and / or the part (12) in rotation about at least one axis (A), this member (30) being accessible from outside the box (18).

2. A device (10) according to claim 1, wherein the box (18) has a generally parallelepiped shape, the inlet and outlet ports (20, 22) being arranged on two opposite sides or ends of the box (18).

3. Device (10) according to claim 1 or 2, in which the removable wall (26) is an upper wall of the box (18) which has for example a generally rectangular shape.

4. Device (10) according to one of the preceding claims, in which the displacement member (30) passes through a light (36) of the box (18) and in particular of the wall (26), this light (36) opening into the interior of the box (18).

5. Device (10) according to claim 4, wherein the light (36) has a generally curved shape and has an angle which corresponds to a possible angular travel of movement of the system (28) and / or the part (12) around said axis (A).

6. Device (10) according to one of the preceding claims, in which the system (28) comprises two pivots (52, 54) aligned on said axis (A).

7. Device (10) according to claim 6, wherein one of the pivots (52) is guided in an orifice (56) of the removable wall (26), and the other of the pivots (54) is guided in an orifice (58) of a wall of the box (18), which is opposite the removable wall (26).

8. Device (10) according to claim 6 or 7, wherein the system (28) further comprises two circular plates (60, 62) configured to be interposed respectively between the pivots (52, 54) and the part (12), or to be mounted around these pivots (52, 54), at least one of these plates (60, 62) comprising at least one hole (64) for the passage of electrical connection wires.

9. Device (10) according to one of the preceding claims, wherein the system (28) comprises two pairs of jaws (66, 68), a first pair of jaws (66) being configured to grip one end of the workpiece (12), and a second pair of jaws (68) being configured to grip an opposite end of the workpiece (12).

10. Device (10) according to claim 8, dependent on claim 6 or 7, in which: - a first of the jaws (66b) of the first pair of jaws (66) is secured to a first of the pivots (52), a second jaw (66a) of this first pair of jaws (66) being configured to be fixed to the first jaw (66b) of this pair, and - a second of the jaws (68b) of the second pair of jaws (68) is secured to a second of the pivots (54), a second jaw (68a) of this second pair of jaws (68) being configured to be fixed to the first jaw (68b) of this pair.

11. Device (10) according to one of the preceding claims, in which the box (18), and in particular the removable wall (26), comprises a first visual marker (38) configured to inform an operator of the angular position of the part (12) around said axis (A), and / or a second visual marker (50) configured to inform an operator of the direction of flow of the gas flow in the box (18).

12. Test installation (14) of at least one aeronautical part (12) in icing conditions, this installation comprising a device (10) according to one of the preceding claims and a circuit (16) for generating a flow of icing gas, for example at a temperature between -5°C and -30°C, and at a speed between 50 and 200m / s with an LWC between 0.1 and 1g / m3.

13. Method for mounting an aeronautical part, such as a blade, in a device (10) according to one of claims 1 to 11, comprising the following steps: a) dismantling and removing the removable wall (26) from the box (18), b) mounting the part (24) with its holding system (28) in the box (18) so that the axis of movement (A) is oriented vertically, and c) closing the opening (24) of the box (18) with the removable wall (26).

14. Method according to claim 13, in which it comprises, after step b), a step w) of adjusting the angular position of the part (12) around said axis (A), thanks to the displacement member (30).

15. A method according to claim 13 or 14, the device (10) being as defined in claim 10, wherein it comprises, between steps a) and b), the following steps: (i) providing a mounting bracket (70), ii) positioning the first jaws (66b, 68b) with the pivots (52, 54) on the mounting support (70), the pivots (52, 54) being housed in arrangements (72) of the mounting support (70) and the first jaws (66b, 68b) being supported on receiving surfaces (74) of the mounting support (70), iii) position the part (12) on the first jaws (66b, 68b), iv) positioning the second jaws (66a, 68a) on the part (12) and fixing them respectively to the first jaws (66b, 68b), and v) separating the assembly formed by the part (12) and the holding system (28) from the mounting support (70).

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