Detection components and detection devices

Abstract

The present invention provides a detection assembly for use at an aircraft engine compressor outlet, wherein an arm has a rod bottom section and a rod top section respectively located at two ends, the arm is rotatably mounted on the aircraft engine around a rotation axis through the rod bottom section, the rod top section is located on the downstream side of a diffuser outlet, and a first side of the rod top section faces the diffuser outlet, a detection element is laterally protrudingly disposed on the first side of the rod top section for detecting airflow parameters, a guide vane is disposed on the second side of the rod top section, the rotation axis of the arm is within the extension plane of the guide vane, wherein the first side and the second side are opposite sides relative to the rotation axis of the arm, and a rotation limiting element is used to limit the rotation angle of the arm. The present invention also provides a detection device. The above-mentioned detection assembly and device can accurately measure the compressor outlet airflow parameters.

Description

Technical Field

[0001] The invention relates to a detection component for an outlet of an aircraft engine compressor and also relates to a detection device. Background Art

[0002] At present, in the performance test of aircraft engine complete machine, core machine and compressor parts, the total temperature and total pressure comb composite probe is used at the diffuser outlet of the compressor. Figure 1 The spatial position of the composite probe at the outlet of a high-pressure compressor is given, and a schematic diagram of the specific shape of the composite probe is given in Figure 2. The common practice in current experiments is to fix the angle of the measuring point in the direction of a circumferential deflection angle of 10°, such as Figure 3 As shown in the figure. Since the actual working conditions of the compressor are constantly changing during the test, the angle of the outlet airflow changes with the changes in the compressor working conditions, and the range of change is large, so the existing comb-shaped composite probe cannot ensure that each measuring point is facing the airflow direction under each working condition. Although there is an insensitive angle at the measuring point, when the incoming airflow angle is greater than the insensitive angle, the accuracy of the measured total temperature and total pressure will be relatively poor. Summary of the invention

[0003] The object of the present invention is to provide a detection component which can accurately measure the air flow parameters at the compressor outlet.

[0004] The present invention provides a detection assembly for an aircraft engine compressor outlet, wherein an arm has a rod bottom section and a rod top section respectively located at two ends, the arm is rotatably mounted on the aircraft engine around a rotation axis through the rod bottom section, the rod top section is located on the downstream side of a diffuser outlet, and a first side of the rod top section faces the diffuser outlet, a detection element is laterally protrudingly arranged on the first side of the rod top section for detecting airflow parameters, a guide vane is arranged on the second side of the rod top section, the rotation axis of the arm is within the extension plane of the guide vane, wherein the first side and the second side are opposite sides relative to the rotation axis of the arm, and a rotation limiting element is used to limit the rotation angle of the arm.

[0005] In one embodiment, the detection element is a cylindrical component having a central axis, and the central axis of the detection element is within the extension plane.

[0006] In one embodiment, the guide piece is a symmetrical shape having a symmetric plane, and the rotation axis of the arm is perpendicular to the symmetric plane of the guide piece and the central axis of the detection element.

[0007] In one embodiment, the casing of the aircraft engine provides a mounting hole extending in the radial direction, and the mounting hole includes a threaded hole located on the radial outside and a tapered hole located on the radial inside, and the cross-section of the tapered hole tapers radially inward; the bottom section and the top section of the arm are located on the radial outside and the radial inside, respectively, and the arm also has a shoulder section and a tapered section, the shoulder section is connected to the bottom section and protrudes outward relative to the bottom section, the tapered section is connected between the shoulder section and the top section, and is adapted in the tapered hole; the detection assembly also includes a pressure cap, which has a through hole for the bottom section to pass through, and also has an external thread, and the pressure cap is threadedly connected to the threaded hole through the external thread to press the shoulder section from the radial outside, thereby pressing the tapered section of the arm against the wall of the tapered hole.

[0008] In one embodiment, the detection assembly also includes a rotating bearing, which is sleeved on the bottom section of the rod and the radial inner end surface of the inner ring of the rotating bearing is pressed against the boss section, thereby fixing it to the arm rod; the pressure cap is pressed against the radial outer end surface of the outer ring of the rotating bearing, thereby pressing against the boss section from the radial outside.

[0009] In one embodiment, the through hole of the pressure cap includes a first hole segment and a second hole segment that are connected to each other. Compared with the second hole segment, the first hole segment is closer to the boss segment and has a larger hole diameter; in the rotation limiting element, two stop pins are arranged at the bottom of the first hole segment and are spaced apart in the circumferential direction of the first hole segment, and the limit pin is laterally protrudingly arranged at the bottom segment of the rod, and is stopped by the two stop pins and limited between the two stop pins.

[0010] In one embodiment, in the rotation limiting element, the stopper includes two stop portions which are spaced apart in the rotation direction of the arm, the limiter is stopped by the two stop portions and is limited between the two stop portions in the rotation direction of the arm, and the limiter and the stopper are respectively arranged on one side and the other side of the arm and the aircraft engine.

[0011] In one embodiment, the rotation limiting element limits the arm so that a circumferential deflection angle of the arm is set to vary between -35° and 55°.

[0012] In one embodiment, the axis of rotation of the arm is in a meridian plane of the aircraft engine.

[0013] In one embodiment, the rotation axis of the arm is inclined 5-15° toward the downstream side from the radial outer side to the radial inner side.

[0014] The present invention also provides a detection device, wherein an arm has a bottom section and a top section respectively located at both ends, the arm is rotatably arranged around a rotation axis through the bottom section, a detection element is arranged on a first side of the top section for detecting fluid parameters, a guide plate is arranged on a second side of the top section, the rotation axis of the arm is within an extension plane of the guide plate, wherein the first side and the second side are opposite sides relative to the rotation axis of the arm, and a rotation limiting element is used to limit the rotation angle of the arm.

[0015] In the above-mentioned detection assembly and detection device, the guide plate can rotate the support arm as the incoming flow angle changes, so that the measuring point of the detection element is always aligned with the incoming flow, thereby accurately measuring the compressor outlet airflow parameters. Moreover, the rotation limiting element can limit the angle of the support arm's adaptive rotation to prevent unstable situations from occurring. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The above and other features, properties and advantages of the present invention will become more apparent through the following description in conjunction with the accompanying drawings and embodiments, in which:

[0017] Figure 1 It is a schematic diagram of a detection component fixedly installed at the outlet of an aircraft engine compressor.

[0018] Figure 2A is a schematic diagram of a fixed-set detection component.

[0019] Figure 2B yes Figure 2A Another schematic diagram of the detection component in FIG.

[0020] Figure 3 is a schematic diagram of an exemplary detection assembly of the present invention.

[0021] Figure 4 yes Figure 3 Schematic diagram of the rotation limiting element of an exemplary detection assembly in.

[0022] Figure 5 This is a schematic diagram of the installation location of the aircraft engine casing. DETAILED DESCRIPTION

[0023] The present invention is further described below in conjunction with specific implementation methods and accompanying drawings. More details are elaborated in the following description to facilitate a full understanding of the present invention. However, the present invention can obviously be implemented in a variety of other ways different from this description. Those skilled in the art can make similar generalizations and deductions based on actual application situations without violating the connotation of the present invention. Therefore, the scope of protection of the present invention should not be limited by the content of this specific implementation method.

[0024] For example, a first feature described later in the specification as being formed above or on a second feature may include an embodiment in which the first feature and the second feature are formed by direct connection, and may also include an embodiment in which an additional feature is formed between the first feature and the second feature, so that the first feature and the second feature may not be directly connected. Further, when a first element is described as being connected or combined with a second element, the description includes an embodiment in which the first element and the second element are directly connected or combined with each other, and also includes an embodiment in which one or more other intervening elements are added to indirectly connect or combine the first element and the second element.

[0025] like Figure 1 As shown, the detection assembly 10a is used at the compressor outlet A of the aircraft engine. Near the compressor outlet A, the aircraft engine 100 has a casing 20 and a diffuser 30 contained in the casing 20, and the detection element in the detection assembly 10a can be placed downstream of the diffuser outlet B. It should be understood that the drawings are only for example and are not drawn in proportion, and should not be used as a limitation on the actual protection scope of the present invention.

[0026] Figure 2A and Figure 2B The structure of the detection assembly 10a is illustrated by taking the total temperature and total pressure comb-shaped composite probe as an example. The detection assembly 10a includes a support rod 11a, a rod seat 12a, a stagnation cover 21a and a pressure cap 3a. A sensor for detecting the total temperature and total pressure is arranged in the stagnation cover 21a, and the stagnation cover 21a can be provided with an orifice for the incoming flow to pass through and be detected by the sensor. The stagnation cover 21a together with the sensor arranged therein can together constitute a detection element 2a for detecting the total temperature and total pressure. The support rod 11a can be inserted into the rod seat 12a, forming a whole with the rod seat 12a, and together forming the arm 1a. The wire L1a can pass through the inside of the support rod 11a to transmit the data detected by the sensor arranged in the stagnation cover 21a to the outside for display, processing or analysis. The pressure cap 3a can install the detection assembly 10a to the compressor outlet A of the aircraft engine, specifically, to the casing 20, by pressing against the rod seat 12a. Figure 2B This is an example structure of the detection assembly 10a when viewed from the radial inner end outward along the rod length direction of the arm 1a. When the detection assembly 10a is arranged at the compressor outlet A of the aircraft engine, the circumferential deflection angle α0 of the arm 1a of the detection assembly 10a can be fixed at about 10°, for example. Figure 2B The meridian plane P0 of the aircraft engine 100 is deflected clockwise by about 10° relative to the meridian plane P0 of the aircraft engine 100. It can be understood that the meridian plane P0 of the aircraft engine 100 is also the plane defined by the radial and axial center lines of the aircraft engine 100, that is, Figure 1 The circumferential deflection angle α0 can be roughly understood as the angle between the central axis X2a of the detection element 2a in the detection assembly 10a and the meridian plane P0.

[0027] The inventors have discovered that during performance tests of aircraft engine complete machines, core machines and compressor components, when the operating state of the compressor changes, the outlet airflow angle varies greatly, and it is impossible to ensure that the measuring points of the outlet detection component 10a, such as the total temperature and total pressure comb-shaped composite probe, can be aligned with the airflow direction under each operating condition, which will result in large measurement errors.

[0028] Figure 3 The exemplary structure of the detection assembly 10 provided by the present invention is shown. Components in the detection assembly 10 similar to those in the detection assembly 10a are marked with similar reference numerals, and some corresponding descriptions may be omitted. The detection assembly 10 may be used in the compressor outlet A of an aircraft engine.

[0029] The detection assembly 10 includes an arm 1 , a detection element 2 , a guide piece 4 and a rotation limiting element 5 .

[0030] Combination Figure 1 and Figure 3 The arm 1 may have a bottom section 102 and a top section 101 located at both ends. The arm 1 may be rotatably mounted on the aircraft engine 100 around the rotation axis O1 through the bottom section 102. The mounting position of the arm 1 on the aircraft engine 100 is similar to Figure 1 The arm 1a of the detection assembly 10a is different from the arm 1 in that the arm 1 is rotatably mounted on the aircraft engine 100 instead of being fixedly mounted. For example, the aircraft engine 100 provides a circular hole, and the arm 1 fits into the circular hole with a small gap, thereby being rotatably mounted on the aircraft engine 100. The rotation axis O1 can be roughly the rod center axis of the arm 1.

[0031] The bottom section 102 of the arm 1 can be located at Figure 1 The first side S1 of the rod bottom section 102 faces the diffuser outlet B. In other words, the side of the rod bottom section 102 facing the diffuser outlet B is called the first side S1 of the rod bottom section 102, which can also be roughly called the front side or upstream side of the rod bottom section 102 relative to the air intake direction.

[0032] The detection element 2 can be laterally protrudingly arranged on the aforementioned first side S1 of the rod top section 101 of the arm 1 for detecting airflow parameters. That is, the detection element 2 is located on the side of the rod top section 101 facing the diffuser outlet B.

[0033] The guide blade 4 may be disposed on the second side S2 of the rod top section 101, wherein the first side S1 and the second side S2 are opposite sides relative to the rotation axis O1 of the arm 1. That is, the second side S2 is opposite to the first side S1 relative to the rotation axis O1 of the arm 1. The side of the rod bottom section 102 facing away from the diffuser outlet B is referred to as the second side S2 of the rod bottom section 102, and relative to the air intake direction, it may also be roughly referred to as the rear side or downstream side of the rod bottom section 102.

[0034] The rotation axis O1 of the arm 1 is within the extension plane of the guide piece 4. The guide piece 4 refers to a flat sheet or thin sheet, such as a straight thin sheet with a thickness of 0.5 to 3 mm. The extension plane of the guide piece 4, that is, the plane where the guide piece 4 extends, can be defined as the center plane of the guide piece 4 in the thickness direction, or a plane defined by any surface of the guide piece 4 in the thickness direction. Since the guide piece 4 is a thin sheet with a thickness of the mm level, the difference between the different defined planes is only in the mm level, which is within the allowable tolerance range. The guide piece 4 with an extension plane can be made of metal, for example, and can be welded to the second side S2 of the rod top section 101 through a connecting rod 41. The guide piece 4 can be Figure 3 The arrow tail shape shown can also be other shapes such as rectangle, triangle, etc. The connecting rod 41 can be, for example, a short cylindrical metal, with two ends welded to the downstream side of the arm 1 and the upstream side of the guide piece 4 respectively.

[0035] The rotation limiting element 5 can limit the rotation angle of the arm 1. In one embodiment, the rotation limiting element 5 can be a wire rope connecting the arm 1 and the aircraft engine 100. When the arm 1 rotates beyond a predetermined angle, the wire rope is straightened and tightened, thereby preventing the arm 1 from continuing to rotate, thereby limiting the rotation angle of the arm 1. In the illustrated embodiment, the rotation limiting element 5 may include a stopper 51 and a limiting member 52. The stopper 51 may include two stoppers 511 and 512 spaced apart in the rotation direction C1 of the arm 1. The limiting member 52 may be stopped by the two stoppers 511 and 512 and limited between the stopper 51 and the limiting member 52 in the rotation direction C1 of the arm 1. The limiting member 52 and the stopper 51 may be respectively provided on one and the other of the arm 1 and the aircraft engine 100. In other words, the limit member 52 and the stop member 51 can be respectively arranged on the arm 1 and the aircraft engine 100, or they can be interchangeably arranged on the aircraft engine 100 and the arm 1, respectively. The rotation limiting element 5 of the above-mentioned structure has high reliability in limiting the rotation angle of the arm 1 and is not easy to be damaged. In one embodiment, the stop member 51 can be, for example, an arc-shaped waist hole, and the two side walls of the arc-shaped waist hole constitute the two stop parts of the stop member 51, and the limit member 52 can be a movable pin that can be movably adapted in the arc-shaped waist hole. In the illustrated embodiment, as mentioned above, the rotation axis O1 of the arm 1 is roughly the central axis of the arm 1 along the length direction of the rod, and the aforementioned rotation direction C1 of the arm 1 is also roughly the circumferential direction of the arm 1.

[0036] In the above detection assembly 10, the arm 1 can rotate freely, and a guide vane 4 is provided in the opposite direction of the measuring point of the detection element 2. When the compressor of the aircraft engine 100 is running, if the incoming flow direction forms an angle with the guide vane 4, the incoming flow will generate pressure on the guide vane 4, and this force can be decomposed into two forces parallel and perpendicular to the guide vane 4. Since the wind receiving area of ​​the measuring point of the detection element 2 can be smaller and the wind receiving area of ​​the guide vane 4 can be larger, the wind pressures felt are not equal, and the wind pressure perpendicular to the guide vane 4 generates a wind pressure torque, which causes the arm 1 to rotate until the measuring point of the detection element 2 is just aligned with the incoming flow direction. At this time, the forces on both sides of the guide vane 4 are balanced, and the detection element 2 is stabilized in the direction aligned with the incoming flow, and the rotation limiting element 5 can prevent the arm 1 from excessive rotation and instability.

[0037] The present invention also provides a detection device. The detection device may include an arm 1, a detection element 2, a guide piece 4 and a rotation-limiting element 5. The arm 1 may have a rod bottom section 102 and a rod top section 101 respectively located at both ends. The arm 1 may be rotatably arranged around a rotation axis O1 through the rod bottom section 102. The detection element 2 may be arranged on a first side of the rod top section 101 for detecting fluid parameters. The guide piece 4 may be arranged on a second side S2 of the rod top section 101, wherein the first side S1 and the second side S2 are opposite sides relative to the rotation axis O1 of the arm 1. The rotation axis O1 of the arm 1 is within the extension plane of the guide piece 4. The rotation-limiting element 5 may be used to limit the rotation angle of the arm 1.

[0038] The arm 1 in the above detection device can be guided by the guide plate 4 so that the arm 1 can be rotated so that the detection element 2 is exactly aligned with the incoming flow, and the rotation limiting element 5 can prevent the arm 1 from excessive rotation, so that the fluid parameters can always be stably, reliably and accurately detected.

[0039] It is understood that specific words are used herein to describe embodiments of the present invention, such as "one embodiment", "another embodiment", and / or "some embodiments" to refer to a certain feature, structure or characteristic associated with at least one embodiment of the present invention. Therefore, it should be emphasized and noted that "one embodiment" or "another embodiment" mentioned twice or more in different locations in this specification does not necessarily refer to the same embodiment. In addition, certain features, structures or characteristics in one or more embodiments of the present invention may be appropriately combined. In addition, the use of words such as "first" and "second" to define features is only for the convenience of distinguishing the corresponding features. If not otherwise stated, the above words have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0040] In the illustrated embodiment, the detection element 2 may be a cylindrical component having a central axis X2. For example, the detection element 2 may be a cylindrical stagnation cover containing a sensor, and the central axis X2 is also the center line of the stagnation cover. The central axis X2 of the detection element 2 may be within the aforementioned extension plane of the guide piece 4. That is, the central axis X2 of the detection element 2 and the rotation axis O1 of the arm 1 are located in the same plane, or it can be said that the extension plane where the guide piece 4 is located is a plane formed or defined by the central axis X2 of the detection element 2 and the rotation axis O1 of the arm 1. In this way, the guide piece 4 is more likely to affect the alignment position of the detection element 2.

[0041] In the illustrated embodiment, the guide piece 4 may be a symmetrical shape having a symmetry plane P4. The rotation axis O1 of the arm 1 is perpendicular to the symmetry plane P4 of the guide piece 4 and the central axis X2 of the detection element 2. In this way, the guiding effect of the guide piece 4 can be better. It can be understood that the expressions "perpendicular" and "parallel" used in the text allow a certain tolerance, such as an angle deviation of ±5° compared to the strict mathematical requirement.

[0042] In the illustrated embodiment, the detection assembly 10 may include a plurality of detection elements 2 uniformly arranged along the length direction of the arm 1. In this way, a plurality of measuring points may be provided to form a comb-shaped probe to measure parameter distribution. The plurality of detection elements 2 may be symmetrically arranged relative to the symmetry plane P4 of the guide piece 4. In this way, the guiding effect of the guide piece 4 may be better. The aforementioned connecting rod 41 may be a short cylindrical member having a central axis, and the central axis thereof may be located within the symmetry plane P4. By connecting the guide piece 4 to the arm 1 through the short connecting rod 41, the guide piece 4 may avoid the turbulence immediately following the tail of the arm 1, so as to enable better guidance.

[0043] In the illustrated embodiment, the arm 1 may be a hollow shaft with an axial hole 109. The axial hole 109 may allow a wire L1 to pass through to transmit data detected by the detection element 2, such as to a converter, a display, etc., for observation, processing, and analysis by test personnel. The hollow shaft of the arm 1 may provide a hole H2 on the peripheral wall for the detection element 2 to pass through and contact the incoming flow, so that the detection element 2 can detect relevant parameters of the incoming flow, such as total temperature and total pressure. For example, Figure 3 In the embodiment, the wire L1 passes through the arm 1 and can be connected to the air pipe, the thermocouple L2, etc.

[0044] See also Figure 5 , the casing 20 of the aircraft engine 100 provides a mounting hole 201 extending in the radial direction R0. The mounting hole 201 may include a threaded hole 202 located on the radial outside and a tapered hole 203 located on the radial inside. The cross section of the tapered hole 203 may taper inward in the radial direction R0. Unless otherwise stated, the extension in a specific direction herein does not require strict compliance with the definition in a mathematical sense, but requires that the extension direction must have a component in the specific direction. Preferably, the angle between the extension direction and the specific direction is less than 45°. For example, in the illustrated embodiment, the mounting hole 201 defined as extending in the radial direction R0 may substantially extend strictly along the hole depth direction D1, and the hole depth direction D1 may have a component in the radial direction R0.

[0045] See also Figure 3The rod bottom section 102 and the rod top section 101 of the arm 1 can be located radially outward and radially inward, respectively, and the arm 1 can also have a shoulder section 103 and a tapered section 104. The shoulder section 103 can be connected to the rod bottom section 102 and protrude relative to the rod bottom section 102. The tapered section 104 can be connected between the shoulder section 103 and the rod top section 101. The tapered section 104 can be fitted into the tapered hole 203 of the mounting hole 201 of the casing 20. For example, the arm 1 can include a support rod 11 and a rod seat 12, the cylindrical rod seat 12 is sleeved outside the cylindrical support rod 11 and is fixed to the support rod 11 as a whole, one end of the rod seat 12 can constitute the shoulder section 103, and the cylindrical hole of the cylindrical support rod 11 constitutes the aforementioned shaft hole 109.

[0046] The detection assembly 10 may further include a pressing cap 3. The pressing cap 3 may have a through hole 31 for the rod top section 101 to pass through, and may also have an external thread 32. The pressing cap 3 may be threadedly connected to the threaded hole 202 of the mounting hole 201 of the casing 20 through the external thread 32 to press against the shoulder section 103 of the arm 1 from the radial outside, thereby pressing against the hole wall of the tapered hole 203 to press against the tapered section 104 of the arm 1.

[0047] In the illustrated embodiment, the detection assembly 10 may further include a rotary bearing 6. The rotary bearing 6 may be fitted over the rod top section 101 and the radial inner end face 611 of the inner ring 61 of the rotary bearing 6 may be pressed against the shoulder section 103 of the arm 1, thereby being fixedly connected to the arm 1. The pressing cap 3 may be pressed against the radial outer end face 622 of the outer ring 62 of the rotary bearing 6, thereby pressing against the shoulder section 103 of the arm 1 from the radial outer side. In other words, the two ends of the rotary bearing 6 are respectively firmly installed by pressing the pressing cap 3 against the outer ring 62 and the shoulder section 103 against the inner ring 61.

[0048] The above structure can facilitate and securely mount the arm 1 to the casing 20 of the aircraft engine 100 .

[0049] In the illustrated embodiment, the through hole 31 of the pressure cap 3 includes a first hole section 311 and a second hole section 312 that are connected to each other. Compared with the second hole section 312, the first hole section 311 is closer to the shoulder section 103 of the arm 1 and has a larger hole diameter. That is, the hole diameter of the first hole section 311 on the radial inner side is larger than that of the second hole section 312 on the radial outer side.

[0050] The aforementioned rotation limiting element 5 may include two stop pins and a limit pin. The two stop pins may be arranged at the bottom 311a of the first hole section 311 and spaced apart in the circumferential direction of the first hole section 311. In other words, the two stop pins may serve as the aforementioned two stop portions 511 and 512, respectively. The limit pin may be arranged at the rod bottom section 102 in a laterally protruding manner, and may be stopped by the aforementioned two stop pins and limited between the aforementioned two stop pins. In other words, the limit pin may serve as the aforementioned limit member 52. The aforementioned rotation limiting element may prevent the arm 1 from excessively rotating due to the airflow during the operation of the compressor, thereby causing unstable situations such as 360-degree rotation.

[0051] In the illustrated embodiment, the rotation limiting element 5 can limit the arm 1 to: the circumferential deflection angle α0 of the arm 1 is set to vary between α1 and α2. After experimental verification, the circumferential deflection angle α0 of the arm 1 is set to vary between -35 and 55 degrees, which can effectively align the incoming flow and prevent the arm 1 from excessive rotation.

[0052] In the illustrated embodiment, the rotation axis O1 of the arm 1 may be within the meridian plane P0 of the aircraft engine 100. Preferably, the rotation axis O1 of the arm 1 may be inclined 5 to 15 degrees from the radial outer side to the radial inner side toward the downstream side (or toward the rear side). Figure 5 The angle between the hole depth direction D1 and the radial direction R0 of the mounting hole 201 is about 10°, for example, 5 to 15°. This can adapt to the airflow distribution at the diffuser outlet B. The range values ​​represented by "~" in the text include both end point values.

[0053] In general, the above-mentioned detection component 10 is achieved by simply modifying the detection component 10a so that the detection element at the compressor outlet, such as the comb-shaped composite probe, has the freedom of rotation and can automatically align with the incoming flow direction when the compressor is running. It has good dynamic characteristics and can quickly and accurately follow the changes in the compressor outlet airflow angle, so that each measuring point is always within the angular range of high measurement accuracy, which can improve the validity and accuracy of the test results.

[0054] Although the present invention is disclosed as above with preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, any modification, equivalent change and modification made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope defined by the claims of the present invention.

Claims

1. A detection assembly for an aircraft engine compressor outlet, characterized in that: include: An arm having a rod bottom section and a rod top section respectively located at two ends, wherein the arm is rotatably mounted on the aircraft engine around a rotation axis through the rod bottom section, the rod top section is located at a downstream side of a diffuser outlet, and a first side of the rod top section faces the diffuser outlet; A detection element, disposed on the first side of the rod top section in a laterally protruding manner, for detecting airflow parameters; a guide piece, arranged on a second side of the rod top section, the rotation axis of the arm rod being within an extension plane of the guide piece, wherein the first side and the second side are opposite sides relative to the rotation axis of the arm rod; and A rotation limiting element, used to limit the rotation angle of the arm; The casing of the aircraft engine provides a mounting hole extending in the radial direction, wherein the mounting hole comprises a threaded hole located on the radial outer side and a tapered hole located on the radial inner side, and the cross section of the tapered hole tapers inwardly in the radial direction; The rod bottom section and the rod top section of the arm rod are located at the radial outer side and the radial inner side respectively, and the arm rod further comprises a convex shoulder section and a conical section, wherein the convex shoulder section is connected to the rod bottom section and protrudes outward relative to the rod bottom section, and the conical section is connected between the convex shoulder section and the rod top section and is adapted in the conical hole; The detection assembly also includes a pressure cap, which has a through hole for the bottom section of the rod to pass through and an external thread. The pressure cap is threadedly connected to the threaded hole through the external thread to press the boss section from the radial outside, thereby pressing against the wall of the tapered hole to press the tapered section of the arm.

2. The detection assembly according to claim 1, characterized in that The detection element is a cylindrical component having a central axis, and the central axis of the detection element is within the extension plane.

3. The detection assembly according to claim 2, characterized in that: The guide piece is in a symmetrical shape with a symmetrical plane, and the rotation axis of the arm is perpendicular to the symmetrical plane of the guide piece and the central axis of the detection element.

4. The detection assembly according to claim 1, characterized in that: The detection assembly further comprises a rotary bearing, the rotary bearing being sleeved on the rod bottom section and the radial inner end surface of the inner ring of the rotary bearing being pressed against the shoulder section, thereby being fixedly connected with the arm; The pressing cap presses against the radial outer end surface of the outer ring of the rotary bearing, thereby pressing against the shoulder section from the radial outer side.

5. The detection assembly according to claim 1, characterized in that: The through hole of the pressure cap comprises a first hole segment and a second hole segment which are connected to each other. Compared with the second hole segment, the first hole segment is closer to the shoulder segment and has a larger hole diameter. The rotation limiting element comprises: two stop pins, arranged at the bottom of the first hole segment and spaced apart in the circumferential direction of the first hole segment; and The limiting pin is arranged on the bottom section of the rod in a sideways protruding manner, and is stopped by the two stop pins and limited between the two stop pins.

6. The detection assembly according to claim 1, characterized in that The rotation limiting element comprises: a stopper including two stopper portions spaced apart in a rotation direction of the arm; and The limiting member is stopped by the two stop parts and is limited between the two stop parts in the rotation direction of the arm. The limiting member and the stop member are respectively arranged on one side and the other side of the arm and the aircraft engine.

7. The detection assembly according to claim 1, characterized in that The rotation limiting element limits the arm so that the circumferential deflection angle of the arm is set to vary between -35° and 55°.

8. The detection assembly according to claim 1, characterized in that The axis of rotation of the arm is in the meridian plane of the aircraft engine.

9. The detection assembly according to claim 8, characterized in that The rotation axis of the arm is inclined toward the downstream side by 5 to 15 degrees from the radial outer side to the radial inner side.

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