Device for measuring parameters of an aerodynamic flow in a duct of a turbomachine

Abstract

The invention relates to a device (300) for measuring parameters of an aerodynamic flow in a duct of a turbomachine, the device comprising: - a guide housing (200) defining an inner cavity (230), - a comb (100) comprising a comb body (120) which extends between a comb head (110) and a lower end (123) of the comb (100), the comb head (110) being slidably mounted in the inner cavity (230), the comb body (120) extending outside the guide housing (200) through the opening present in the lower part (220) of the guide housing (200), at least one spring element (130) interposed between the comb head (110) and the upper part (210) of the guide housing (200), the comb head (110) being movable in the inner cavity (230) between a first position and a second position, the comb body further comprising means (121) for measuring parameters of an aerodynamic flow.

Description

Description Title of the invention: Device for measuring parameters of an aerodynamic flow in a duct of a turbomachine Technical Field

[0001] The present invention relates to the field of devices for measuring aerodynamic flow parameters. Previous technique

[0002] Climate change is a major concern for many legislative and regulatory bodies worldwide. Indeed, various restrictions on carbon emissions have been, are being, or will be adopted by different countries. In particular, an ambitious standard applies to both new types of aircraft and those already in operation, requiring the implementation of technological solutions to bring them into compliance with current regulations. Civil aviation has been actively contributing to the fight against climate change for several years now.

[0003] Technological research efforts have already led to very significant improvements in the environmental performance of aircraft. The Applicant takes into account the factors impacting all phases of design and development in order to obtain aeronautical components and products that are less energy-intensive, more environmentally friendly, and whose integration and use in civil aviation have moderate environmental impacts, with the aim of improving the energy efficiency of aircraft.

[0004] The Applicant works in research and development on new generations of engines, electric technologies to provide propulsion, and electric biofuels.

[0005] In this context, during the manufacture of the engines, the Applicant tests their performance in order to be able to certify their use.

[0006] During testing, numerous measurements of the aerodynamic airflow in terms of pressure and temperature are taken at predefined axial stations on the engine. These axial stations are generally known as "measurement planes".

[0007] Mapping the pressures and temperatures of the aerodynamic airflow is carried out using measurement devices known as "intrusive meters." These intrusive meters take pressure and temperature measurements directly within the aerodynamic flow.

[0008] At each axial station, the aerodynamic airflow passes between a first wall, called the "outer" wall, and a second wall, called the "inner" wall. As the air moves around the inner or outer wall, the velocity and pressure fields are perturbed by the wall. The fluid region adjacent to the wall, where accommodation occurs between the zero wall velocity and the local full velocity of the aerodynamic airflow, is known as the "boundary layer."

[0009] Some intrusive measuring devices are known as combs, and they have multiple nozzles for performing radial measurements. Combs are sometimes used to characterize the associated boundary layer. When possible, the comb is fixed to the wall where the boundary layer is present. This ensures that the comb's nozzles are positioned precisely and very close to the wall.

[0010] Integrating the combs onto the surface being measured is not always possible. This is particularly true when dealing with a hard-to-reach or cluttered area of ​​the motor. To overcome this problem, some solutions propose attaching the comb to a different location on the motor. However, such an alternative impacts the accuracy of the measurement.

[0011] Other solutions offer so-called "dual boundary layer combs." These types of meters are fixed to the outer wall and measure the boundary layer on both the outer and inner walls. A dual boundary layer comb has first nozzles on its upper end and second nozzles on its lower end.

[0012] However, this type of meter cannot guarantee the correct positioning of the nozzles, particularly on the wall opposite the one where the meter is mounted. Indeed, when the comb is fixed to the outer wall and measures the boundary layer associated with the inner wall, it is not possible to simultaneously align the first nozzles of the comb with the outer wall and the second set of nozzles with the inner wall.

[0013] Thus, there is a real need for a measuring device that allows the characterization of the boundary layer of the inner wall and the outer wall, and this without the aforementioned disadvantages. Description of the invention

[0014] To this end, the invention proposes a device for measuring parameters of an aerodynamic flow in a duct of a turbomachine, characterized in that the measuring device comprises: - a guide housing defining an internal cavity closed in its upper part and having an opening in its lower part, - a comb comprising a comb body extending between a comb head and a lower end of said comb, the comb head being slidably mounted in the internal cavity of the guide housing, the comb body extending outside the guide housing through the opening present in the lower part of said guide housing, at least one spring element interposed between the comb head and the upper part of the guide housing, the comb head being movable in the internal cavity of the guide housing between a first position corresponding to a start position of the comb stroke and a second position corresponding to an end position of the comb stroke, the comb body further comprising means for measuring parameters of an aerodynamic flow.

[0015] Such a device allows for the measurement of aerodynamic flow parameters in a flow channel between an inner and outer wall. Indeed, the sliding comb head allows the comb body to assume different positions, enabling measurements to be taken at various heights within the flow channel.

[0016] Depending on a particular feature, a sealing gasket may be present between the comb head and a wall of the internal cavity of the guide housing.

[0017] Such a configuration ensures a seal between the guide housing and the comb.

[0018] According to a particular feature, the comb head may further include a groove which extends around the perimeter of the comb head, and the sealing gasket is present inside the groove.

[0019] Thus, it is possible to ensure a seal between an upper end of the comb head and a lower end of the comb head.

[0020] According to a particular feature, at least one deployment spring may be interposed between the comb head and the upper part of the guide housing, said at least spring exerting a displacement force against the comb head.

[0021] Thus, it is possible to attach the comb body to an internal surface of the turbomachine's inner wall regardless of the wall's position. This is particularly advantageous when measuring aerodynamic flow parameters at the inner wall of the flow stream.

[0022] According to a particular characteristic, the comb body comprises at least one flow sampling organ, said at least one organ being present at a determined position on the lower end of the comb.

[0023] The presence of such a device allows for the sampling of aerodynamic flow with greater precision.

[0024] According to another aspect, the invention proposes a turbomachine characterized in that it includes at least one device for measuring parameters of an aerodynamic flow according to the invention, the guide housing of the device for measuring parameters of an aerodynamic flow being fixed on a first wall of the turbomachine forming an external wall of a flow vein.

[0025] Thus, it is possible to obtain a turbomachine in which it is possible to control at any time and with greater precision its performance at the level of the external wall of the flow stream.

[0026] According to a particular feature, the lower end of the comb of the device for measuring parameters of an aerodynamic flow can be kept in contact with a second wall of the turbomachine delimiting an internal wall of the flow duct, the head of the comb being in a position between the first position and the second position or in the second position.

[0027] Thus, it is possible to obtain a turbomachine in which it is possible to control at any time and with greater precision its performance at the level of the internal wall of the flow stream.

[0028] According to yet another aspect, the invention proposes a method of mounting a device according to the invention in a turbomachine for measuring parameters of an aerodynamic flow in a duct of a turbomachine, the duct extending radially between a first wall and a second wall, the first wall comprising an opening, the method being characterized in that it includes a step of inserting the device into the opening of the first wall of the duct so as to align a first edge of the guide housing with an internal surface of the first wall of the duct.

[0029] Aligning the first edge of the guide housing with the inner surface of the first wall of the flow channel improves measurement accuracy. This allows for more precise measurement of aerodynamic flow parameters at the outer wall of the flow channel.

[0030] According to a particular feature, during the device insertion step the lower end of the comb can be positioned against an internal surface of the second wall of the vein.

[0031] This allows for a more precise measurement of aerodynamic flow parameters at the inner wall of the flow channel.

[0032] According to a particular feature, when the device is inserted into the opening of the first wall of the vein, a second edge of the guide housing is in contact with an external surface of the first wall, the second edge being opposite to the first edge of the guide housing.

[0033] This helps to ensure even better fixation of the measuring device when taking measurements. Brief description of the drawings

[0034] [Fig. 1] Figure 1 illustrates an example of a device for measuring parameters of an aerodynamic flow according to the invention,

[0035] [Fig. 2] Figure 2 illustrates the guide housing and the comb head of the measuring device of Figure 1,

[0036] [Fig. 3] Figure 3 illustrates the mounting of the measuring device of Figure 1 when the internal surface of the inner wall is located below the theoretical position of the internal surface of the inner wall,

[0037] [Fig. 4] Figure 4 illustrates the mounting of the measuring device of Figure 1 when the internal surface of the inner wall is positioned above the theoretical position of the internal surface of the inner wall, Description of the implementation methods

[0038] The invention applies generally to the measurement of parameters of an aerodynamic flow in a turbomachine. It implements a measuring device according to the invention.

[0039] Figure 1 illustrates an example of a device for measuring parameters of an aerodynamic flow according to the invention. The measuring device 300 comprises a comb 100 and a guide housing 200.

[0040] The guide box 200 has an upper part 210 and a lower part 220. The upper part 210 of the guide box 200 is closed and the lower part 220 of the guide box 200 has an opening 231. The guide box 200 extends in length along a longitudinal axis Y and in width along a transverse axis X which is orthogonal to the longitudinal axis Y.

[0041] The upper part 210 of the guide housing 200 is closed by a cover 240. The cover 240 includes a cavity 241 as illustrated in Figure 2.

[0042] The guide housing 200 further comprises an internal cavity 230 formed between the upper part 210, the lower part 220 and lateral walls 232a and 232b extending between the upper part 210 and the lower part 220. As shown in Figure 2, the guide housing 200 comprises a first edge 221 on the lower part 220 and a second edge 211 on the upper part 210.

[0043] The comb 100 comprises a comb body 120 and a comb head 110. The comb body 120 extends along the longitudinal axis Y between the comb head 110 and a lower end 123 (distal end) of the comb 100, as illustrated in Figure 1.

[0044] The comb body 120 has, along the longitudinal axis Y, a length greater than the length of the comb head 110. The comb head 110 has a width, along the transverse axis X, greater than the width of the comb body 120.

[0045] According to another variant, the comb head 110 and the comb body 120 can have the same width.

[0046] The comb body 120 extends outside the guide housing 200 and passes through the opening 231 present in the lower part 220 of the guide housing 200.

[0047] The comb head 110 further includes a groove 112 which extends around the perimeter of the comb head 110, as illustrated in Figure 1.

[0048] The measuring device 300 further includes a sealing gasket 111 which is present between the comb head 110 and a wall 232a, 232b delimiting the internal cavity 230 of the guide housing 200. The sealing gasket 111 is housed inside the groove 112, as illustrated in Figure 1.

[0049] The presence of the groove 112 is not limiting to the invention. According to one embodiment, the comb head may be without a groove.

[0050] The measuring device 300 is intended to be housed within a duct of an aircraft turbomachine. The turbomachine includes, in particular, a first wall 400 and a second wall 500, shown in Figures 3 and 4. The first wall 400 of the turbomachine has an external surface 410 and an internal surface 420. The second wall 500 of the turbomachine has an external surface 510 and an internal surface 520r. The duct extends radially between the first wall 400 of the turbomachine and the second wall 500 of the turbomachine. More precisely, the duct extends between the internal surface 420 of the first wall 400 of the turbomachine and the internal surface 520r of the second wall 500 of the turbomachine, as illustrated in Figures 3 and 4.

[0051] The flow comprises a region called the "inner boundary layer" and a region called the "outer boundary layer". The inner boundary layer corresponds to the region of the flow that is close to the second wall 500 of the turbomachine. The outer boundary layer corresponds to the region of the flow that is close to the first wall 400 of the turbomachine.

[0052] The first wall 400 of the turbomachine is also called the outer wall and the second wall 500 of the turbomachine is also called the inner wall.

[0053] The comb body 120 of the measuring device 300 further includes a spring element 130 and a plurality of means 121 for measuring aerodynamic flow parameters.

[0054] The number of measuring means 121 is not limiting to the invention. According to one embodiment, the measuring device 300 may comprise a single measuring means 121 for aerodynamic flow parameters.

[0055] The spring element 130 is interposed between the comb head 110 and the upper part 210 of the guide housing 200. In other words, the spring element 130 separates the comb head 110 from the cover 240 of the guide housing 200.

[0056] The number of spring elements is not a limitation of the invention. According to one embodiment, the comb body comprises a plurality of spring elements.

[0057] The spring element 130 can be a deployment spring, as illustrated in figures 1, 3 and 4. The deployment spring exerts a displacement force against the comb head 110. Thus it is possible to facilitate the optimal positioning of the lower end 123 of the comb 100 on the internal surface 520r of the second wall 500 of the turbomachine.

[0058] The aerodynamic flow parameter measurement means 121 extend in length between a first end 1210a and a second end 1210b. The second end 1210b extends parallel to the transverse axis X. The first end 1210a extends parallel to the longitudinal axis Y.

[0059] Each aerodynamic flow parameter measurement means 121 comprises a flow sampling element 122. Each flow sampling element 122 is located at the second end 1210b of the aerodynamic flow parameter measurement means 121, as illustrated in Figures 1, 3, and 4.

[0060] The number of flow sampling organs 122 included in each aerodynamic flow parameter measurement means 121 is not limiting of the invention.

[0061] According to one variant, each means of measuring 121 of aerodynamic flow parameters comprises a plurality of flow sampling organs 122.

[0062] The comb head 110 slides within the internal cavity 230 of the guide housing 200. In other words, the comb head 110 is movable within the internal cavity 230 of the guide housing 200 between a first position and a second position. The first position corresponds to the starting position of the comb 100's stroke, and the second position to the end position of the comb 100's stroke.

[0063] When the sliding motion of the comb head 110 is at its maximum, the first position corresponds to the position in which an upper edge of the comb head 110 is in contact with a lower edge of the cover 240. In this case, the spring element 130 is fully compressed. The second position corresponds to the position in which a lower edge of the comb head 110 is in contact with the lower part 220 of the guide housing 200. In this case, the spring element 130 is fully extended.

[0064] The lower end 123 of the comb 100 includes a contact element 125 which is positioned in contact with an internal surface 520r of the second wall 500 of the turbomachine. This is most advantageous when it is desired to measure the parameters of the aerodynamic flow at the level of the internal wall of the flow channel.

[0065] In one variant, the contact element incorporates a friction-limiting material such as Teflon.

[0066] The presence of the contact element 125 is not limiting to the invention. According to one embodiment, the lower end 123 of the comb 100 is devoid of the contact element 125. In this case, the lower end 123 of the comb 100 comes directly into contact with the internal surface 520r of the second wall 500 of the turbomachine.

[0067] The measuring device 300 further includes an instrumentation channel 140, as illustrated in Figures 1 and 2. The instrumentation channel 140 comprises an upper portion 1400a and a lower portion 1400b, as illustrated in Figure 2. The lower portion 1400b of the instrumentation channel 140 is surrounded by the spring element 130. The lower portion 1400b of the instrumentation channel 140 is fixed to an upper edge of the comb head 110. The upper portion 1400a of the instrumentation channel 140 passes through the cavity 241 of the cover 240.

[0068] A region of the upper portion 1400a of the instrumentation chimney 140 protrudes from the cover 240, as illustrated in figures 1, 3 and 4.

[0069] Now we will describe the assembly process of the measuring device according to the invention.

[0070] During the installation of the measuring device 300 in the turbomachine, the device is inserted through an opening in the first wall 400 of the turbomachine, as illustrated in Figures 1, 3, and 4. During insertion, the first edge 221 of the guide housing 200 is aligned with the inner surface 420 of the first wall 400 of the turbomachine. This ensures the accuracy of the aerodynamic flow parameter measurements near the first wall 400 of the turbomachine. In other words, it guarantees the accuracy of the aerodynamic flow parameter measurements in the outer boundary layer of the flow path. This alignment ensures that the parameter measuring means 121 are positioned perpendicular to the inner surface 420 of the first wall 400 of the turbomachine.

[0071] When the measuring device 300 is inserted, the lower end 123 of the comb 100 can be positioned against the inner surface 520r of the second wall 500 of the turbomachine. In the examples shown in Figures 3 and 4, the contact element 125 of the lower end 123 of the comb 100 is in contact with the inner surface 520r of the second wall 500 of the turbomachine. This is most advantageous when it is desired to measure the aerodynamic flow parameters near the second wall 500 of the turbomachine, or in other words, within the inner boundary layer of the turbomachine's flow path.

[0072] The positioning of the lower end 123 of the comb 100 against the inner surface 520r of the second wall 500 of the turbomachine is not a limiting feature of the invention. In one embodiment, the assembly method omits this step. This is particularly relevant when it is desired to measure only the aerodynamic flow parameters near the first wall, or in other words, in the outer boundary layer of the flow stream.

[0073] During insertion, the theoretical position 520t of the internal surface of the second wall 500 of the turbomachine can be predetermined.

[0074] When the inner surface 520r of the second wall 500 of the turbomachine is located below the theoretical position 520t of the inner surface of the second wall 500 of the turbomachine (i.e., at a greater radial distance from the first wall 400), the spring element 130 relaxes and causes the comb head 110 to move towards the lower part 220 of the guide housing 200 and the comb head 110 to move from a first position to a second position, as illustrated in Figure 3. Thus, the lower end 123 of the comb 100 can reach the actual position of the inner surface 520r of the second wall 500 of the turbomachine. Consequently, the contact element 125 of the lower end 123 of the comb 100 can bear against the inner surface 520r of the second wall, as illustrated in Figure 3.

[0075] When the inner surface 520r of the second wall 500 of the turbomachine is located above the theoretical position 520t of the inner surface of the second wall 500 of the turbomachine (i.e., at a smaller radial distance from the first wall 400), the spring element 130 is compressed and causes the comb head 120 to move towards the upper part 210 of the guide housing 200 and the comb head 110 to move from a first position to a second position, as illustrated in Figure 4. Thus, the contact element 125 of the lower end 123 of the comb 100 can be positioned in contact with the inner surface 520r of the second wall, as illustrated in Figure 4.

[0076] When inserting the measuring device 300, the second edge 211 of the guide housing 200 can rest on the external surface 410 of the first wall 400 of the turbomachine, as illustrated in Figures 3 and 4. This allows for better fixing of the measuring device 300.

[0077] The positioning of the second edge 211 of the guide housing 200 in support on the internal surface of the first wall is not limiting of the invention.

Claims

Demands

1. A device (300) for measuring parameters of an aerodynamic flow in a duct of a turbomachine, characterized in that the measuring device (300) comprises: - a guide housing (200) defining an internal cavity (230) closed in an upper part (210) and having an opening in a lower part (220), - a comb (100) comprising a comb body (120) extending between a comb head (110) and a lower end (123) of said comb, the comb head (110) being slidably mounted in the internal cavity (230) of the guide housing, the comb body (120) extending outside the guide housing (200) through the opening in the lower part (220) of said guide housing (200), at least one spring element (130) interposed between the comb head (110) and the upper part (210) of the guide housing (200), the comb head (110) being movable within the internal cavity (230) of the guide housing (200) between a first position corresponding to a starting position of the comb's stroke and a second position corresponding to an ending position of the comb's stroke, the comb body further comprising means (121) for measuring parameters of a flow aerodynamics.

2. Device according to claim 1, wherein a sealing gasket (111) is present between the comb head (110) and a wall (232a, 232b) of the internal cavity (230) of the guide housing (200).

3. Device according to claim 2, wherein the comb head (110) further comprises a groove (112) which extends around the periphery of the comb head (110), and wherein the sealing gasket (111) is present inside the groove (112).

4. A device according to any one of claims 1 to 3, wherein at least one deployment spring is interposed between the comb head (110) and the upper part (210) of the guide housing (200), said at least one spring exerting a displacement force against the comb head (110).

5. A device according to any one of claims 1 to 4, wherein the comb body (120) comprises at least one flow sampling element (122), said at least one sampling element (122) being present at a determined position on the lower end (123) of the comb (100).

6. Turbomachine characterized in that it comprises at least one device for measuring parameters of an aerodynamic flow according to any one of claims 1 to 5, the guide housing (200) of the device for measuring parameters of an aerodynamic flow being fixed on a first wall (400) of the turbomachine forming an external wall of a flow duct.

7. Turbomachine according to claim 6, wherein the lower end (123) of the comb (100) of the device for measuring parameters of an aerodynamic flow is kept in contact with a second wall (500) of the turbomachine delimiting an internal wall of the flow duct, the comb head (110) being in a position between the first position and the second position or in the second position.

8. Method of mounting a device (300) according to any one of claims 1 to 5 in a turbomachine for measuring parameters of an aerodynamic flow in a duct of a turbomachine, the duct extending radially between a first wall (400) and a second wall (500), the first wall (400) comprising an opening, the method being characterized in that it comprises a step of inserting the device into the opening of the first wall (400) of the duct so as to align a first edge (221) of the guide housing (200) with an internal surface (420) of the first wall (400) of the duct.

9. Method according to claim 8, wherein during the insertion step of the device (300), the lower end (123) of the comb (100) is positioned against an internal surface (520) of the second wall (500) of the vein.

10. A method according to any one of claims 8 or 9, wherein when the device (300) is inserted into the opening of the first wall (400) of the vein, a second edge (211) of the guide housing (200) is in contact with an external surface (410) of the first wall (400), the second edge (211) being opposite the first edge (221) of the guide housing (200).

Images