Device for measuring parameters of an aerodynamic flow in an aircraft turbomachine

Abstract

A measuring device (1) for at least one parameter of the aerodynamic flow of an aircraft turbomachine (50), said device (1) being intended to traverse the aerodynamic flow of the turbomachine (50) and comprising: a body (2) elongated along an axis (Z), and data acquisition means (3) carried by the body (2) and configured to acquire information relating to the parameters of the aerodynamic flow of the turbomachine (50), characterized in that it further comprises: - at least one deformation sensor (30) of the body, - at least one actuator (32) for modifying the shape and / or position of the body (2), and - a control circuit (34) capable of controlling said at least one actuator (32) from signals emitted by said at least one sensor (30). Figure for the abstract: Figure 2

Description

Title of the invention: Device for measuring parameters of an aerodynamic flow IN AN AIRCRAFT TURBOMACHINE Technical field of the invention

[0001] The present invention relates to a device for measuring at least one parameter of an aerodynamic flow of a turbomachine, this device being intended to cross an aerodynamic flow of the aircraft turbomachine. Technical background

[0002] In the context of turbomachinery development, and in particular aircraft turbomachinery, these undergo a multitude of tests and trials to verify and validate, firstly, their proper functioning and, secondly, their ability to maintain their integrity and performance. Validation of these tests and trials leads to certification authorizing their entry into service. In particular, these tests and trials involve measurements of certain aerodynamic flow parameters, such as pressure, temperature, and / or acceleration, using a measuring device.

[0003] This measuring device is generally known as an intrusive flow meter or flow comb. Various types exist, each adapted to measure one or more flow parameters. These are typically installed in one or more specific areas of the turbomachine where the aerodynamic flow to be measured circulates, such as zones within an aerodynamic duct. These different zones are commonly referred to as the "measurement plane." Indeed, the aerodynamic flow circulating in a turbomachine duct exhibits different characteristics in various zones of the duct, for example, in its central zone, along the walls delimiting the duct, upstream of stator blades, etc. Therefore, several devices may be necessary for a complete mapping of the flow parameters within the duct.

[0004] A measuring device is generally fixed to a wall of the turbomachine and comprises an elongated body extending through the aerodynamic flow. The body is equipped with means for recording information relating to the flow parameters.

[0005] Such a device is known for example from documents FR-A1-1 753 977, FR-A1-2 952 713, FR-A1-3 052 863, FR-A1-3 106 660, and FR-A1-3 128 289.

[0006] It is known that measuring devices of this kind are subject to vibrational phenomena due to their intrusive nature in the aerodynamic flow. These vibrational phenomena originate from the perturbation of the flow due to integration of the measuring device in the flow upstream or downstream of a rotor disk following the flow circulation in the turbomachine.

[0007] The disturbance of the flow results in a malfunction of the turbomachine and also a risk of invalidating the measurements. Similarly, aeroelastic phenomena cause the measuring device to vibrate due to the cantilevered arrangement of the body in the aerodynamic flow and its low robustness.

[0008] Furthermore, the components of turbomachinery can never be perfectly balanced dynamically. Imbalances and aerodynamic disturbances generated by the turbomachine may correspond to one of the natural resonance frequencies of the measuring device.

[0009] In the worst case, the measuring device is likely to enter into resonance (the measuring device is unable to dissipate the energy received) which can cause cracks in it or even total breakage and consequently can induce significant damage to the turbomachine.

[0010] In the prior art, there are solutions for increasing the stiffness of the device, damping the amplitude of the device's vibrations, and / or modifying its fixing conditions.

[0011] The present invention proposes an alternative to known solutions to this problem, which is simple, effective and economical. Summary of the invention

[0012] The present invention proposes a device for measuring at least one parameter of an aerodynamic flow of an aircraft turbomachine, this device being intended to traverse an aerodynamic flow of the turbomachine and comprising: - a body with an elongated shape along a Z-axis, and - means of data collection which are carried by the body and which are configured to collect information relating to the parameters of the aerodynamic flow of the turbomachine,

[0013] characterized in that it further comprises:

[0014] - at least one body deformation sensor,

[0015] - at least one actuator for modifying the shape and / or position of the body, and

[0016] - a control circuit capable of controlling said at least one actuator from signals emitted by said at least one sensor.

[0017] The proposed technical solution thus consists of equipping the device with one or more sensors and one or more actuators, preferably with very short reaction times, capable of modifying the profile and / or position of the body. Modifying the profile and / or position of the body will change the body's lift and therefore its behavior in the face of the flow around it. A modification of the shape or profile is understood as a modification of the external shape of the body, and a change in position is understood as a movement of all or part of the body such as a rotation of the body for example.

[0018] The device according to the invention may comprise one or more of the following features, taken individually or in combination with each other: - the body is tubular and includes an internal cavity extending along the Z axis, said at least one sensor and said at least one actuator being housed in this cavity;

[0019] — said circuit is configured to control said at least one actuator to deformations of the body with a phase shift so as to oppose or dampen these deformations; the actuator or each actuator can thus be directly controlled to the deformations of the body with a phase shift so as to oppose or dampen these deformations; the control is ensured by the circuit which induces a phase shift according to a law depending on the frequency for example, circuit and law being chosen so that the effect of the lifts induced by the actuators reduce the oscillations due to the aero-elastic couplings between the vein flow and the body; - said circuit is capable of receiving one or more input parameters chosen from among a temperature, in particular of the body, a flow velocity, a flow pressure, and a flow temperature; the circuit can thus be controlled according to an input signal taking into account physical parameters of the flow (pressure, temperature, velocity, etc...) or of the body (temperature...) to adjust the phase shift and the amplitude of the lift generated and take into account aero-elastic couplings; - said sensor is chosen by a strain gauge, an accelerometer, a force gauge, and a distance sensor; - said actuator is a piezoelectric actuator; - the body comprises a fixed part and a movable or deformable part connected to the fixed part by said at least one actuator; - the moving part is mobile in rotation around an axis of rotation parallel to said Z axis or coinciding with said Z axis; - the fixed part is inside the moving part which defines the external profile of the body; the actuator can thus act on the overall orientation of the body in the flow, inducing an angle between its neutral lift orientation in the flow and a position resulting in slight lift; - the fixed part defines a leading edge of the body, and the moving part defines a trailing edge of the body; the actuator can thus control a flap on the trailing edge of the body; - the fixed part defines a first axial section of the body extending along the Z axis, and the moving part defines a second axial section of the body extending along the Z axis, the first and second sections being arranged one after the other; the actuator can thus control a pivoting terminal section on the Z axis of the body; - the fixed part includes the leading and trailing edges of the body, and the moving part includes at least one of the lateral walls of the body which extend between the leading and trailing edges; the actuator can thus control a section of the intrados and / or the extrados; - the body has a streamlined cross-section with a curved leading edge and a thinned trailing edge; - the streamlined shape of the body has a median plane of symmetry passing through the middle of the body and extending between the leading edge and the trailing edge; - in its free state without deformation, the body has zero or neutral lift.

[0020] The present invention also relates to a turbomachine, in particular an aircraft turbomachine, comprising at least one device as described above which passes through an aerodynamic flow of the turbomachine.

[0021] The invention further relates to a method of controlling a device as described above, the control being carried out by the control circuit which is configured to control said at least one actuator to the deformations of the body with a phase shift so as to oppose these deformations or to dampen them. Brief description of the figures

[0022] The invention will be better understood and other details, features and advantages of the invention will become apparent upon reading the following description, given by way of non-limiting example with reference to the accompanying drawings, in which:

[0023] [Fig-1] [Fig.1] schematically represents, in axial and partial section, a example of a turbomachine to which the invention applies;

[0024] [Fig.2] Fig.2 illustrates in perspective a device for measuring at least one parameter of an aerodynamic flow in a turbomachine;

[0025] [Fig.3] The [Fig.3] is an axial cross-sectional view of a turbomachine duct with the measuring device of the [Fig.2] mounted in its wall guiding an aerodynamic flow;

[0026] [Fig.4] [Fig.4] is a schematic cross-sectional view of a measuring device according to a first embodiment of the invention,

[0027] [Fig.5] [Fig.5] is a schematic cross-sectional view of a measuring device according to a second embodiment of the invention,

[0028] [Fig. 6] [Fig. 6] is a schematic cross-sectional view of a device measurement according to a third embodiment of the invention,

[0029] [Fig.7] [Fig.7] is a schematic side view of the measuring device [Fig.6]

[0030] [Fig.8] [Fig.8] is a schematic cross-sectional view of a measuring device according to a fourth embodiment of the invention. Detailed description of the invention

[0031] Figure 1 shows a partial axial cross-sectional view of a turbomachine with longitudinal axis X, in particular a twin-flow turbomachine 50 according to the invention. Of course, the invention is not limited to this type of turbomachine.

[0032] This twin-flow turbomachine 50 generally comprises a gas compressor 51 upstream of which a fan 52 is mounted. In the present invention, and generally, the terms "upstream" and "downstream" are defined with respect to the gas flow in the turbomachine, and here along the longitudinal axis X. Similarly, the terms "radial," "internal," and "external" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X. The turbomachine 50 also comprises, downstream of the compressor assembly 51, a combustion chamber 53 followed by a turbine assembly 54. The turbomachine 50 comprises a first annular stream, called the primary stream 55, in which a primary aerodynamic flow, or hot stream, circulates, and a second annular stream, called the secondary stream 56, in which a secondary aerodynamic flow, or cold stream, circulates around the primary stream 55.The primary flow passes through the compressor assembly 51, the combustion chamber 53, and the turbine assembly 54. The secondary flow circulates around an inter-flow casing 57 that encloses the compressor assembly 51 (which may include a high-pressure compressor and a low-pressure compressor), the combustion chamber 53, and the turbine assembly 54 (which may include a low-pressure turbine and a high-pressure turbine). The primary and secondary flows 55, 56 are coaxial. In particular, the primary flow 55 is radially delimited by an annular inner casing 58 and the annular inter-flow casing 57. The secondary flow 56 is radially delimited by the inter-flow casing 57 and an annular outer casing 59 to which a blower casing 60 is attached.The turbomachine further comprises an annular ejection nozzle 61, located downstream of the turbine assembly 54, through which the primary and secondary flows are ejected outside the turbomachine, and in particular into the atmosphere.

[0033] The turbomachine 50 includes at least one device for measuring parameters of an aerodynamic flow which is intended to measure one or more parameters of the flow circulating in the turbomachine so as to establish a map of the Pressures, temperatures, accelerations, and / or the composition of the flow in the vicinity of the measuring device are measured. These parameters are necessary to obtain certification of the turbomachine before its commercialization, for example, or to verify the turbomachine's condition. The measurement is considered intrusive because it is performed directly within the flow. The measuring device 1 is designed to be installed substantially radially in one of the primary and secondary channels 55, 56 of the turbomachine. Each channel 55, 56 is radially delimited by a radially external wall 62 and a radially internal wall 63 with respect to the radial axis Z. The radially external and internal walls 62, 63 are annular and coaxial.

[0034] With reference to Figures 2 and 3, the measuring device 1 comprises a body 2 and information-gathering means 3 configured to gather information relating to at least one parameter of the flow in the turbomachine.

[0035] The body 2 carries the means 3 for collecting information through the flow. For this purpose, the body 2 extends along the radial axis Z (in an installed state of the measuring device in the turbomachine). In particular, the body 2 has a free cantilevered length L determined between a radially internal end 4 and a radially external end 5 which are opposite along the radial axis Z. As can also be seen in [Fig. 2], the body 2 has a leading edge 6 and a trailing edge 7 opposite along the longitudinal axis X. The leading edge 6 and the trailing edge 7 connect, respectively upstream and downstream, two opposite lateral faces 9 along a transverse axis T. The transverse axis T is perpendicular to the longitudinal axis X and the radial axis Z. The term "transverse" is therefore defined with respect to this transverse axis T.More precisely, the body 2 has a significantly decreasing thickness from the leading edge 6 to the trailing edge 7 (so as to present, for example, a NACA-type profile, the initials of which stand for "National Advisory Committee for Aeronautics"). The opposing lateral faces 9 thus meet at a ridge at the trailing edge 7. Such a streamlined shape of the body 2 makes it possible to reduce the aerodynamic losses introduced into the flow when the measuring device 1 is installed in one of the ducts 55, 56 of the turbomachine 50.

[0036] In an installed state of the measuring device 1, the leading edge 6 is upstream of the trailing edge 7 with respect to the direction of the aerodynamic flow. Of course, the body 2 may have a different cross-section that is aerodynamic and does not disturb the flow, or only very slightly, such as an oblong cross-section.

[0037] The measuring device 1 includes a base 10 for fixing the measuring device 1 in the turbomachine 50 and for supporting the body 2 which extends through the aerodynamic flow. More specifically, the base 10 includes a wall extending along a plane substantially perpendicular to the radial axis Z. The Body 2 extends radially from the base 10. In the installation configuration shown in [Fig. 3], the base is intended to rest on a radially external surface 62a of the radially external wall 62 of the vein 55, 56, or, for example, on a radially external edge of a boss (not shown). To secure the base 10, the base includes through-holes 11 passing through its wall on either side along the radial axis Z. The through-holes 11 receive fasteners 12 designed to secure the base 10 to the radially external wall 62 of the vein 55, 56, thus creating a fixed connection. The radially external wall 62 (or boss) also includes blind holes (not shown) which are aligned, once the base 10 is installed, with the through holes 11. The fasteners 12 are also engaged in the blind holes.The fastening elements 12 include screws, bolts or other similar elements enabling the measuring device 1 to be easily mounted and dismounted. The base 10 has a substantially parallelepiped, circular or rectangular shape.

[0038] Fig. 3 illustrates the measuring device 1 which is fixed to the radially external wall 62 of the turbomachine duct. The radially external wall 62 is traversed radially by the body 2 of the measuring device 1. For this purpose, the radially external wall 62 includes a through-opening 64 that passes through its thickness on both sides along the radial axis Z. The through-opening 64 opens into the vein 55, 56. This through-opening 64 allows the passage of the body 2. The base 10 rests outside the vein 55, 56, while the body 2 (with the data acquisition means 3) extends into the vein 55, 56. The through-opening 64 allows for precise positioning of the measuring device 1 within the radially external wall 62. For this purpose, the through-opening 64 has a cross-section substantially corresponding to that of the body 2 of the measuring device 1.The through-hole 64 may have a different shape than the body 2, provided that the latter can cooperate with or fit tightly into the through-hole 64. Advantageously, but not exclusively, the measuring device 1 includes a base 13 designed to be arranged within the thickness of the radially external wall 62 so as to allow precise positioning of the measuring device 1 within the radially external wall 62 and to hold the body 2 through the flow. The base 13 is arranged radially between the foot 10 and the rest of the body 2, which is cantilevered in the aerodynamic flow. In the present example, the base 13 has an oblong cross-section. This shape may, of course, be rectangular, circular, or otherwise.

[0039] The information-gathering means 3 are arranged at the leading edge 6 of the body 2. These are also arranged and distributed regularly along the leading edge, i.e., along the radial axis Z. The information-gathering means 3 can measure information relating to pressure, temperature, and / or flow acceleration. The data acquisition means 3 are connected to means for conveying (not shown) the data acquired by the data acquisition means 3. These conveying means are also connected to an information processing system 66 of the turbomachine 50 as schematically illustrated in [Fig. 1]. In this example, the data acquisition means 3 comprise cylindrical channels, each extending along the longitudinal axis X in the body wall. Each channel opens on one side onto an external surface of the leading edge 6 via an inlet orifice 15, which is exposed to the aerodynamic flow to collect a sample. We can see on [Fig.2] six inlet orifices 15 on the leading edge 6. On the other hand, each channel opens into a longitudinal cavity (not shown) formed inside the body 2.The longitudinal cavity extends along the body 2 and opens outside the measuring device 1 through a slot 16 defined in a radially external surface 17 of the base 10. The routing means run partly within the body 2 and extend outwards from the measuring device 1. Each channel is connected to a cable of the routing means. The cables are retained within the longitudinal cavity. For example, thermocouples and / or Kiehl's probes can be installed in the channels or at the inlet ports 15.

[0040] The body 2 of the measuring device 1 of [Fig. 2] is formed from a single piece. Alternatively, the body of the measuring device could be modular and formed by assembling at least two pieces.

[0041] The invention proposes an improvement to the measuring device 1 of figures 2 and 3, embodiments of which are illustrated in figures 4 and following.

[0042] As mentioned above, the measuring device 1 comprises: - a body 2 with an elongated shape along the Z-axis, and - information gathering means 3 which are carried by the body 2 and which are configured to gather information relating to the parameters of the aerodynamic flow of the turbomachine 50.

[0043] According to the invention, the measuring device 1 further comprises:

[0044] - at least one body deformation sensor 30 2,

[0045] - at least one actuator 32 for modifying the shape and / or position of the body 2, and

[0046] - a control circuit 34 capable of controlling said at least one actuator 32 from of signals emitted by said at least one actuator 32.

[0047] The body 2 is tubular and includes an internal cavity 20 extending along the Z axis. The sensor(s) 30 and the actuator(s) 32 are preferably housed in this cavity 20.

[0048] The body 2 has in section a streamlined shape comprising a curved leading edge 6 and a thinned trailing edge 7.

[0049] The streamlined shape of the body 2 has a median plane P of symmetry passing through the middle of the body 2 and extending between the leading edge 6 and the trailing edge 7.

[0050] The sensor or each of the 30 is preferably chosen by a strain gauge, an accelerometer, a force gauge, and a distance sensor.

[0051] The actuator or each actuator 32 is preferably a piezoelectric actuator.

[0052] The circuit 34 is advantageously configured to control the actuator(s) 32 to the deformations of the body 2 with a phase shift so as to oppose these deformations or to dampen them.

[0053] The circuit 34 is preferably capable of receiving one or more input parameters chosen from a temperature, in particular of the body, a flow velocity, a flow pressure, and a flow temperature.

[0054] Advantageously, the body 2 comprises a fixed part 36 and a movable or deformable part 38 connected to the fixed part 36 by the actuator(s) 32.

[0055] In the embodiment of [Fig.4], the movable part 38 is free to rotate about an axis of rotation A parallel to the Z axis or coinciding with the Z axis. The fixed part 36 is inside the movable part 38 which defines the external profile of the body 2.

[0056] In the embodiment of [Fig.5], the fixed part 36 defines the leading edge 6 of the body 2, and the movable part 38 defines the trailing edge 7 of the body 2. The assembly formed by the reference marks 30, 32 and 34 is designated by the reference 37.

[0057] In the embodiment shown in Figures 6 and 7, the fixed part 36 defines a first axial section 2a of the body 2 extending along the Z-axis, and the movable part 38 defines a second axial section 2b of the body 2 extending along the Z-axis. The first and second sections 2a, 2b are arranged one after the other. In the example shown, the first section 2a is in the upper part and is connected to the aforementioned base 10. The assembly formed by the reference numerals 30, 32, and 34 is designated by reference numeral 37.

[0058] In the embodiment of [Fig.8], the fixed part 36 comprises leading and trailing edges 6, 7 of the body 2, and the movable part 38 comprises at least one of the side walls 40 of the body 2 which extend between the leading and trailing edges 6, 7. The assembly formed by the reference numerals 30, 32 and 34 is designated by the reference numeral 37.

[0059] The invention makes it possible, in particular, to reduce the amplitude of the device's vibration modes, both in motion and under stress, which allows, under identical operating conditions, the design of slimmer devices with an acceptable lifespan. Consequently, the invention makes it possible to reduce, compared to the prior art, the disturbance of vein flow caused by intrusive measurements.

[0060] The invention also allows for an improvement in the representativeness of the measurements.

Claims

Demands

1. A measuring device (1) for at least one parameter of an aerodynamic flow of an aircraft turbomachine (50), said device (1) being intended to traverse an aerodynamic flow of the turbomachine (50) and comprising: - a body (2) of elongated shape along an axis (Z), and - information-gathering means (3) which are carried by the body (2) and which are configured to gather information relating to the parameters of the aerodynamic flow of the turbomachine (50), characterized in that it further comprises: - at least one deformation sensor (30) of the body, - at least one actuator (32) for modifying the shape and / or position of the body (2), and - a control circuit (34) capable of controlling said at least one actuator (32) from signals emitted by said at least one sensor (30).

2. Device (1) according to claim 1, wherein the body (2) is tubular and comprises an internal cavity (20) extending along the axis (Z), said at least one sensor (30) and said at least one actuator (32) being housed in this cavity (20).

3. Device (1) according to claim 1 or 2, wherein said circuit (34) is capable of receiving one or more input parameters selected from a temperature, in particular of the body, a flow velocity, a flow pressure, and a flow temperature.

4. Device (1) according to any one of the preceding claims, wherein said sensor (30) is selected by a strain gauge, an accelerometer, a force gauge, and a distance sensor.

5. Device (1) according to any one of the preceding claims, wherein said actuator (32) is a piezoelectric actuator.

6. Device (1) according to any one of the preceding claims, wherein the body (2) comprises a fixed part (36) and a movable or deformable part (38) connected to the fixed part (36) by said at least one actuator (32).

7. Device (1) according to claim 6, wherein the movable part (38) is movable in rotation about an axis of rotation (A) parallel to said axis (Z) or coincident with said axis (Z).

8. Device (1) according to claim 6 or 7, wherein the fixed part (36) is inside the movable part (38) which defines the external profile of the body (2).

9. Device (1) according to claim 6 or 7, wherein the fixed part (36) defines a leading edge (6) of the body (2), and the movable part (38) defines a trailing edge (7) of the body (2).

10. Device (1) according to claim 6 or 7, wherein the fixed part (36) defines a first axial section (2a) of the body extending along the axis (Z), and the movable part (38) defines a second axial section (2b) of the body (2) extending along the axis (Z), the first and second sections (2a, 2b) being arranged one after the other.

11. Device (1) according to claim 6, wherein the fixed part (36) comprises trailing leading edges (6, 7) of the body (2), and the movable part (38) comprises at least one of the side walls (40) of the body (2) which extend between the leading and trailing edges (6, 7).

12. Device (1) according to any one of the preceding claims, wherein the body (2) has in section a streamlined shape comprising a curved leading edge (6) and a thinned trailing edge (7).

13. Device (1) according to the preceding claim, wherein the streamlined shape of the body (2) has a median plane (P) of symmetry passing through the middle of the body (2) and extending between the leading edge (6) and the trailing edge (7).

14. Aircraft turbomachine (50), comprising at least one device (1) according to any one of the preceding claims which passes through an aerodynamic flow of the turbomachine.

15. Method of controlling a device (1) according to any one of claims 1 to 13, the control being carried out by the control circuit (34) which is configured to control said at least one actuator (32) to the deformations of the body (2) with a phase shift so as to oppose these deformations or to dampen them.

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