A device and method for multi-duct engine inlet parameter testing

Abstract

The application belongs to the field of aero-engines, and provides a device and method for testing inlet parameters of a multi-duct engine. The device comprises a first measuring conduit and a second measuring conduit. The second measuring conduit is arranged at the end of the first measuring conduit along the airflow direction, and comprises an outer cylinder and an inner cylinder. The front end of the outer cylinder is connected with the first measuring conduit, and the rear end is connected with the outer casing of the twin-duct engine. The front end of the inner cylinder is embedded in the first measuring conduit, and the rear end is connected with the inner casing of the twin-duct engine. The first measuring conduit is provided with a first measuring device, and the second measuring conduit is provided with a second measuring device. Compared with the traditional measuring device, the above device overcomes the problem that the traditional single conduit cannot realize multi-duct measurement, can accurately measure the inlet flow of two ducts, and can realize the requirement of more accurately evaluating the working state of the equipment.

Description

Technical Field

[0001] This invention belongs to the field of aero-engines and designs engine testing technology, specifically involving a device and method for testing the inlet parameters of a multi-bypass engine. Background Technology

[0002] The research and experimentation of aero-engines, the monitoring of the engine's operating status by aircraft, and the health management of the engine itself all require the accurate acquisition of the engine's imported parameters. Moreover, with the continuous development of modern aviation technology, engines with multi-bypass configurations have gradually become the mainstream. In particular, the emergence of the concept of adaptive variable cycle engines has increased the number of bypass ducts in combat aircraft engines from the traditional two bypass ducts of turbofan engines to three or four bypass ducts, and even their core engines have two bypass ducts.

[0003] For engines with multi-duct configurations, especially variable-cycle engines, obtaining their inlet parameters becomes more complex. Traditional aero-engine inlet testing systems can only obtain the inlet flow rate of a single duct, making them unsuitable or unable to meet the testing requirements of multi-duct engines. For example, in variable-cycle engines, the inlet parameters of a single duct can only provide a portion of the engine's operating parameters; other parameters cannot be directly obtained and must be estimated or allocated based on experience, making it impossible to accurately assess the engine's operating status.

[0004] Furthermore, even if individual measurements are barely performed inside an aero-engine, the poor uniformity of the flow field and the limited number of measurement points mean that the measurements do not meet the conditions for flow measurement, resulting in a significant gap between the required accuracy and the actual accuracy.

[0005] Therefore, the accuracy of the engine inlet parameter data measured by traditional testing systems is low, which can bring unpredictable risks to flight safety. Summary of the Invention

[0006] To improve the accuracy of engine inlet parameter data measurement and reduce flight safety risks, this invention discloses an apparatus and method for testing inlet parameters of multi-bypass engines. The method and apparatus are particularly suitable for measuring inlet parameters such as flow rate, total temperature, and total pressure of engines, core engines, or components whose inlets are split into two or more bypass ducts. It can achieve comprehensive monitoring of inlet parameters of multi-bypass engine configurations, improve engine operating reliability and parameter measurement accuracy, and reduce flight safety risks.

[0007] The technical solution to achieve the purpose of the invention is as follows:

[0008] The first embodiment of the present invention discloses an apparatus for testing inlet parameters of a multi-bypass engine. The apparatus includes a first measuring guide tube and a second measuring guide tube. The second measuring guide tube is disposed at the end of the first measuring guide tube along the airflow direction and includes an outer cylinder and an inner cylinder. The front end of the outer cylinder is connected to the first measuring guide tube, and the rear end is connected to the outer casing of the multi-bypass engine. The front end of the inner cylinder is partially embedded in the first measuring guide tube, and the rear end is connected to the inner casing of the multi-bypass engine.

[0009] The first measuring conduit is equipped with a first measuring device, which is used to measure the inlet parameters of the dual-duct engine.

[0010] The second measuring conduit is equipped with a second measuring device, which is used to measure the inlet parameters of the inner duct of a dual-ducted engine.

[0011] Furthermore, a flow guide support plate is provided between the outer cylinder and the inner cylinder, and the second measuring device passes through the outer cylinder, the flow guide support plate, and the inner cylinder in sequence.

[0012] Further, the distance between the first measuring device and the inlet of the first measuring duct is defined as L1, the distance between the second measuring device and the apex of the intake cone of the dual-duct engine is defined as L4, the diameter of the first measuring duct is defined as D4, and the diameter of the inner duct of the engine is defined as D1, where L1 / D4 > 1.0, and 1.0 ≥ L4 / D1 ≥ 0.5.

[0013] Furthermore, the distance between the first measuring device and the inlet of the inner cylinder is defined as L2, the distance between the inlet of the inner cylinder and the second measuring device is defined as L3, and the diameter of the inner cylinder is defined as D3, where 1.0 ≥ L2 / D3 ≥ 0.5 and L3 / D3 > 1.0.

[0014] Furthermore, both the first measuring device and the second measuring device include a through-type total temperature and total pressure composite probe, a cantilever type total temperature and total pressure composite probe, and a wall static pressure measuring device;

[0015] Two cantilevered total temperature and total pressure composite probes are symmetrically arranged along the direction perpendicular to the through-type total temperature and total pressure composite probe;

[0016] The wall static pressure measuring device includes a plurality of wall static pressure measuring points uniformly arranged circumferentially on the inner wall of the first measuring conduit or the second measuring conduit.

[0017] Furthermore, the through-type total temperature and total pressure composite probe and the cantilever type total temperature and total pressure composite probe are provided with multiple total temperature and total pressure measuring points along the wall of the first measuring conduit to the center.

[0018] In an improved embodiment, the device further includes a transition section located between the second measuring conduit and the dual-duct engine, comprising an inner transition section and an outer transition section, wherein an outer duct of the transition section is formed between the inner and outer transition sections, and an inner duct of the transition section is formed on the inner wall surface of the inner transition section.

[0019] Furthermore, the inner transition section and the outer transition section are cylindrical surfaces or conical surfaces;

[0020] When the inner duct of the transition section is an expansion channel, the tangent of the angle between the conical generatrix of the transition section and the axis of the double-duct engine is ≤12.3% to satisfy the requirement that the diffuser flow does not separate.

[0021] When the inner duct of the transition section is a contraction channel, the tangent of the angle between the conical generatrix of the transition section and the axis of the double-ducted engine is ≤26.8% to ensure uniform flow field.

[0022] Furthermore, sealing rings are provided between the first measuring conduit and the outer cylinder, between the inner cylinder and the inner casing of the dual-ducted engine, and between the outer cylinder and the outer casing of the dual-ducted engine.

[0023] The second embodiment of the present invention discloses a method for testing the inlet parameters of a multi-bypass engine, which uses the apparatus described in the first embodiment to test the inlet parameters of the multi-bypass engine, and includes the following steps:

[0024] S1. Collect the inlet parameters of the dual-ducted engine and the inlet parameters of the inner duct. The inlet parameters of the dual-ducted engine include the first wall static pressure at multiple static pressure measuring points and the first total temperature and total pressure at multiple total temperature and total pressure measuring points. The inlet parameters of the inner duct include the second wall static pressure at multiple static pressure measuring points and the second total temperature and total pressure at multiple total temperature and total pressure measuring points.

[0025] S21. Calculate the average value of the first wall static pressure at multiple static pressure measuring points to obtain the inlet static pressure of the dual-ducted engine;

[0026] Based on the first total temperature and total pressure of each total temperature and total pressure measuring point, the position of each total temperature and total pressure measuring point in the first measuring duct, and the static pressure at the inlet of the dual-duct engine, the first air flow rate of each total temperature and total pressure measuring point in the first measuring duct is calculated.

[0027] S22. Calculate the average value of the static pressure on the second wall surface at multiple static pressure measuring points to obtain the static pressure at the inlet of the inner channel;

[0028] Based on the second total temperature and total pressure of each total temperature and total pressure measuring point, the position of each total temperature and total pressure measuring point in the second measuring conduit, and the static pressure at the inlet of the inner channel, calculate the second air flow rate of each total temperature and total pressure measuring point in the second measuring conduit;

[0029] S3. Calculate the total inlet flow of the dual-duct engine based on the first air flow rate at each total temperature and total pressure measuring point in the first measuring duct.

[0030] Based on the second air flow rate at each total temperature and total pressure measuring point in the second measuring conduit, calculate the inlet flow rate of each inner channel;

[0031] S4. Calculate the difference between the total inlet flow rate of the dual-bypass engine and the inlet flow rate of the inner duct to obtain the inlet flow rate of the outer duct of the dual-bypass engine.

[0032] Compared with existing technologies, the beneficial effects of this invention are as follows: The device for testing the inlet parameters of a multi-duct engine designed in this invention solves the problem of high-precision flow measurement of the two ducts in aerospace mechanical equipment with a dual-duct configuration and primarily using gas as the working medium. Compared with traditional measurement methods, it overcomes the problem that traditional single-duct methods cannot achieve multi-duct measurement, and can accurately measure the inlet flow of both ducts. Furthermore, the relevant algorithms in the method for testing the inlet parameters of a multi-duct engine designed in this invention have been programmed and have shown good results in practical applications. Attached Figure Description

[0033] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below.

[0034] Figure 1 This is a schematic diagram of the device used for testing the inlet parameters of a multi-bypass engine in Example 1;

[0035] Figure 2 This is a schematic diagram showing the key parameters of each component in the device for testing imported parameters in Example 1;

[0036] Figure 3 for Figure 2 A schematic diagram of the through-type total temperature and total pressure composite probe, the cantilever type total temperature and total pressure composite probe, and the wall static pressure measuring device shown in the cross section along the BB direction of the first measuring device;

[0037] Figure 4 This is a schematic diagram of the transition section in the device for testing inlet parameters in Example 1;

[0038] Among them, 1. First measuring conduit; 2. Second measuring conduit; 21. Outer cylinder; 22. Inner cylinder; 3. Flow guide support plate; 4. Adapter section; 10. First measuring device; 20. Second measuring device; 30. Through-type total temperature and total pressure composite probe; 40. Cantilever type total temperature and total pressure composite probe; 41. Inner adapter section; 42. Outer adapter section; 50. Wall static pressure measuring device. Detailed Implementation

[0039] The present invention will be further described below with reference to specific embodiments, and the advantages and features of the present invention will become clearer as a result. However, these embodiments are merely exemplary and do not constitute any limitation on the scope of the present invention. Those skilled in the art should understand that modifications or substitutions can be made to the details and form of the technical solutions of the present invention without departing from the spirit and scope of the present invention, but all such modifications and substitutions fall within the protection scope of the present invention.

[0040] Example 1:

[0041] This embodiment provides an apparatus for testing the inlet parameters of a multi-bypass engine. (See also...) Figure 1 As shown, the device for testing imported parameters includes a first measuring conduit 1 and a second measuring conduit 2. The second measuring conduit 2 is located at the end of the first measuring conduit 1 along the airflow direction and includes an outer cylinder 21 and an inner cylinder 22. The front end of the outer cylinder 21 is connected to the first measuring conduit 1 by bolts and flanges, and the rear end is connected to the outer casing of the dual-bypass engine by bolts and flanges. The front end of the inner cylinder 22 is embedded in the first measuring conduit 1, and the rear end is connected to the inner casing of the dual-bypass engine by bolts and flanges.

[0042] Among them, see Figure 1 As shown, the first measuring conduit 1 is equipped with a first measuring device 10, which is used to measure the inlet parameters of a dual-ducted engine. The second measuring conduit 2 is equipped with a second measuring device 20, which is used to measure the inlet parameters of the inner duct of the dual-ducted engine.

[0043] Preferably, the second measuring device 20 is located in the second measuring conduit 2 at the position where the flow guide support plate 3 is provided.

[0044] Further, see Figure 1 As shown, a flow guide support plate 3 is provided between the outer cylinder 21 and the inner cylinder 22, and the second measuring device 20 passes through the outer cylinder 21, the flow guide support plate 3, and the inner cylinder 22 in sequence.

[0045] Further, see Figure 2The diagram shows the key parameter annotations for various components of the inlet parameter testing device, including the first measuring conduit 1, the second measuring conduit 2, the second measuring device 20, and the first measuring device 10, including axial key dimension annotations and radial key annotations. Specifically, the distance between the first measuring device 10 and the inlet of the first measuring conduit 1 is defined as L1; the distance between the second measuring device 20 and the apex of the dual-duct engine intake cone is defined as L4; the distance between the first measuring device 10 and the inlet of the inner cylinder 22 is defined as L2; ​​the distance between the inlet of the inner cylinder 22 and the second measuring device 20 is defined as L3; the diameter of the inner cylinder 22 is defined as D3; the diameter of the outer cylinder 21 is defined as D4; and the diameter of the engine inner duct is defined as D1.

[0046] Furthermore, the diameter of the first measuring catheter 1 is required to be D4, wherein L1 / D1>1.0, 1.0≥L4 / D1≥0.5; 1.0≥L2 / D3≥0.5, L3 / D3>1.0.

[0047] Further, see Figure 3 As shown, the first measuring device 10 includes a through-type total temperature and total pressure composite probe 30, a cantilever type total temperature and total pressure composite probe 40, and a wall static pressure measuring device 50. The structure of the second measuring device 20 is the same as that of the first measuring device 10. The difference between the two is that the first measuring device 10 passes through the wall of the first measuring conduit 1, and its sensor leads are made using a common method, while the second measuring device 20 passes through the outer cylinder 21, the flow guide support plate 3, and the inner cylinder 22 in sequence, and its sensor is led out and fixed after being connected to the flow guide support plate 3.

[0048] Two cantilevered total temperature and pressure composite probes 40 are symmetrically arranged in a direction perpendicular to the through-type total temperature and pressure composite probe 30. Multiple total temperature and pressure measuring points are provided on both the through-type and cantilevered total temperature and pressure composite probes 30 and 40 along the wall of the first measuring conduit 1 towards its center. Preferably, in this embodiment, both the through-type and cantilevered total temperature and pressure composite probes 30 and 40 have 14 total temperature and pressure measuring points, arranged in a non-uniform distribution. The first seven measuring points are located within the wall boundary layer, the thickness of which is related to the inlet conditions and the L1 / D4 ratio, typically approximately 0.2 times D4. The last seven measuring points are located in the core flow region and are arranged radially uniformly.

[0049] The wall static pressure measuring device 50 includes a plurality of wall static pressure measuring points uniformly arranged circumferentially on the inner wall of the first measuring conduit 1 or the second measuring conduit 2. It should be noted that, in actual arrangement, the plurality of wall static pressure measuring points need to avoid the circumferential positions of the cantilevered total temperature and total pressure composite probe 40 and the through-type total temperature and total pressure composite probe 30 to prevent interference from the cantilevered total temperature and total pressure composite probe 40 and the through-type total temperature and total pressure composite probe 30.

[0050] In an improved embodiment, since different multi-bypass engines have different dimensions, to ensure that the inlet parameter testing device is applicable to multi-bypass engines of different specifications, see [reference needed]. Figure 4 As shown, the device also includes a transition section 4, which is located between the second measuring conduit 2 and the dual-duct engine. The transition section 4 includes an inner transition section 41 and an outer transition section 42, and an outer duct of the transition section is formed between the inner transition section 41 and the outer transition section 42. An inner duct of the transition section is formed on the inner wall surface of the inner transition section 41.

[0051] Furthermore, the inner transition section 41 and the outer transition section 42 are cylindrical or conical surfaces. When the inner duct of the transition section is an expanding channel, the tangent of the angle between the conical generatrix of the transition section 4 and the axis of the dual-ducted engine is ≤12.3% to ensure that the diffuser flow does not separate; when the inner duct of the transition section is a contracting channel, the tangent of the angle between the conical generatrix of the transition section 4 and the axis of the dual-ducted engine is ≤26.8% to ensure that the flow field is uniform.

[0052] In an embodiment where no accompanying drawings are shown, sealing rings are provided between the first measuring conduit 1 and the outer cylinder 21, between the inner cylinder 22 and the inner casing of the dual-ducted engine, and between the outer cylinder 21 and the outer casing of the dual-ducted engine.

[0053] The aforementioned imported parameter test structure is simple and can be easily connected to the inner and outer casings of a multi-bypass engine. Through the first measuring device 10 and the second measuring device 20, the total temperature, total pressure and wall static pressure at different locations of different multi-bypass engines can be measured, thereby accurately calculating the flow rate of the inner and outer bypass ducts in the multi-bypass engine.

[0054] Example 2:

[0055] This embodiment provides a method for testing the inlet parameters of a multi-bypass engine. The method uses the inlet parameter testing device described in Embodiment 1 to test the inlet parameters of the multi-bypass engine, and includes the following steps:

[0056] S1. Collect the inlet parameters of the dual-ducted engine and the inlet parameters of the inner duct. The inlet parameters of the dual-ducted engine include the first wall static pressure at multiple static pressure measuring points and the first total temperature and total pressure at multiple total temperature and total pressure measuring points. The inlet parameters of the inner duct include the second wall static pressure at multiple static pressure measuring points and the second total temperature and total pressure at multiple total temperature and total pressure measuring points.

[0057] S21. Calculate the average value of the first wall static pressure at multiple static pressure measuring points to obtain the inlet static pressure of the dual-ducted engine;

[0058] Based on the first total temperature and total pressure of each total temperature and total pressure measuring point, the position of each total temperature and total pressure measuring point in the first measuring duct, and the static pressure at the inlet of the dual-duct engine, the first air flow rate of each total temperature and total pressure measuring point in the first measuring duct is calculated.

[0059] S22. Calculate the average value of the static pressure on the second wall surface at multiple static pressure measuring points to obtain the static pressure at the inlet of the inner channel;

[0060] Based on the second total temperature and total pressure of each total temperature and total pressure measuring point, the position of each total temperature and total pressure measuring point in the second measuring conduit, and the static pressure at the inlet of the inner channel, calculate the second air flow rate of each total temperature and total pressure measuring point in the second measuring conduit;

[0061] S3. Calculate the total inlet flow of the dual-duct engine based on the first air flow rate at each total temperature and total pressure measuring point in the first measuring duct.

[0062] Based on the second air flow rate at each total temperature and total pressure measuring point in the second measuring conduit, calculate the inlet flow rate of each inner channel;

[0063] S4. Calculate the difference between the total inlet flow rate of the dual-bypass engine and the inlet flow rate of the inner duct to obtain the inlet flow rate of the outer duct of the dual-bypass engine.

[0064] The above method allows for the calculation of the airflow W1 in the first measuring duct 1, which is the total flow rate entering the multi-duct engine inlet, using the total temperature and pressure data and wall static pressure data collected by the first measuring device 10; and the calculation of the airflow W2 in the second measuring duct 2, which is the flow rate entering the inner duct of the multi-duct engine, using the total temperature and pressure data and wall static pressure data collected by the second measuring device 20; and the calculation of the difference between W1 and W2 yields the airflow rate entering the outer duct.

[0065] It should be noted again that when a dual-duct engine operates in single-duct mode, where airflow occurs through the inner duct but not the outer duct, the above method still applies, i.e., W1 = W2. Here, it should be pointed out that when there is a significant difference between W1 and W2, and excluding any malfunctions in the measuring device, the engine flow rate should be calculated using the value of W2. Furthermore, a W1 - W2 > 0 can be considered a sign of air leakage. Additionally, W1 and W2 can be used as mutual verification in this case. Based on testing personnel's experience, when a large deviation occurs between W1 and W2, relevant troubleshooting actions should be taken.

[0066] This embodiment uses 14 total temperature and total pressure measuring points on the through-type total temperature and total pressure composite probe 30 and the cantilever type total temperature and total pressure composite probe 40, and 6 static pressure measuring points on the wall static pressure measuring device 50 to illustrate the above method:

[0067] First, the parameters measured at the six static pressure measuring points of the wall static pressure measuring device 50 are expressed as ps. k (k represents the static pressure measuring point, numbered 1 to 6), according to the formula The static pressure ps can be calculated by averaging the parameters at the six measuring points, including the static pressure at the inlet of the dual-duct engine and the static pressure at the inlet of the inner duct.

[0068] Secondly, the numbers of the through-type total temperature and total pressure composite probe 30 are set to 2 and 3 respectively, and the numbers of the cantilever type total temperature and total pressure composite probe 40 are set to 1 and 4 respectively. Each total temperature and total pressure measuring point measures 3 parameters, and the radius of each total temperature and total pressure measuring point is r. The measured total temperature is Tt, and the measured total pressure is Pt. That is, the parameters obtained by the j-th total temperature and total pressure measuring point of the i-th probe are r(i,j), Tt(i,j), and Pt(i,j); i represents the probe number; j represents the total temperature and total pressure measuring point number on the probe.

[0069] Then, the average value of the same parameters on the through-type total temperature and total pressure composite probe 30 and the cantilever type total temperature and total pressure composite probe 40 on the first measuring catheter 1 and the second measuring catheter 2 are calculated respectively to obtain the average radius. and average radius place and

[0070] Secondly, based on the average radius According to the formula Calculate the average radius torus area

[0071] Based on average radius place and and torus area According to the formula Calculate the airflow W at the torus where the j-th total temperature and pressure measuring point is located. j This includes the airflow at the j-th total temperature and total pressure measuring point on the first measuring conduit 1 and the second measuring conduit 2, where... The average total pressure on the defined wall surface is equal to the static pressure because the airflow velocity is 0 due to the viscous force at the wall surface. T0 is the average total temperature on the defined wall surface; T0 is the total temperature of the environment in which the measuring device is located.

[0072] According to the formula Calculate the total flow rate at 14 total temperature and total pressure measurement points, including the total flow rate at the inlet of the dual-duct engine and the inlet flow rate at the inner duct.

[0073] Finally, the difference between the total inlet flow rate of the dual-duct engine and the inlet flow rate of the inner duct is used to obtain the inlet flow rate of the outer duct.

[0074] The device for testing the inlet parameters of a multi-duct engine designed in this invention solves the problem of high-precision flow measurement of the two ducts in aerospace mechanical equipment with a dual-duct configuration and primarily using gas as the working medium. Compared with traditional measurement methods, it overcomes the limitation of traditional single-duct measurement, which cannot achieve multi-duct measurement. It can accurately measure the inlet flow of both ducts, enabling a more accurate assessment of the equipment's operating status. Furthermore, the relevant algorithms in the multi-duct engine inlet parameter testing method designed in this invention have been programmed and have shown good results in practical application.

[0075] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention. Specifically, the apparatus and method for testing inlet parameters of the present invention are also applicable to the measurement of inlet flow rates of ducted engines with three or more ducts; and see also... Figure 4 As shown, the apparatus and method for testing inlet parameters of the present invention are also applicable to the measurement of inlet flow of fans or other front-end components or devices that only have multi-duct systems.

[0076] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An apparatus for multi-draught engine inlet parameter testing, characterized by, The device comprises a first measuring conduit (1), a second measuring conduit (2) arranged at the end of the first measuring conduit (1) along the airflow direction, an outer cylinder (21), and an inner cylinder (22), wherein the front end of the outer cylinder (21) is connected with the first measuring conduit (1), and the rear end is connected with the outer casing of the dual-channel engine; the front end of the inner cylinder (22) is embedded in the first measuring conduit (1), and the rear end is connected with the inner casing of the dual-channel engine; The first measuring conduit (1) is provided with a first measuring device (10) for measuring the inlet parameters of the dual-channel engine; The second measuring conduit (2) is provided with a second measuring device (20) for measuring the inlet parameters of the inner channel of the dual-channel engine; Wherein, the distance between the first measuring device (10) and the inlet of the first measuring conduit (1) is defined as L1, the distance between the second measuring device (20) and the vertex of the inlet cone of the dual-channel engine is defined as L4, the diameter of the first measuring conduit (1) is defined as D4, and the diameter of the inner channel of the engine is defined as D1, wherein L1 / D4>1.0, 1.0≥L4 / D1≥0.5; The distance between the first measuring device (10) and the inlet of the inner cylinder (22) is defined as L2, the distance between the inlet of the inner cylinder (22) and the second measuring device (20) is defined as L3, and the diameter of the inner cylinder (22) is defined as D3, wherein 1.0≥L2 / D3≥0.5, L3 / D3>1.0; The first measuring device (10) and the second measuring device (20) each comprise a through-type total temperature and total pressure compound probe (30), a cantilever-type total temperature and total pressure compound probe (40), and a wall static pressure measuring device (50); the cantilever-type total temperature and total pressure compound probe (40) is symmetrically provided with two branches along a direction perpendicular to the through-type total temperature and total pressure compound probe (30); the wall static pressure measuring device (50) comprises a plurality of wall static pressure measuring points uniformly arranged on the inner wall of the first measuring conduit (1) or the second measuring conduit (2) in the circumferential direction. A plurality of total temperature and total pressure measuring points are arranged on the through-type total temperature and total pressure compound probe (30) and the cantilever-type total temperature and total pressure compound probe (40) along the direction from the wall of the first measuring conduit (1) to the center.

2. The device for multi-duct engine inlet parameter testing according to claim 1, characterized in that, A flow guide support plate (3) is arranged between the outer cylinder (21) and the inner cylinder (22), and the second measuring device (20) sequentially passes through the outer cylinder (21), the flow guide support plate (3), and the inner cylinder (22).

3. A device for multi-duct engine inlet parameter testing according to claim 1 or 2, characterized in that, The device further comprises an adapter section (4) located between the second measuring conduit (2) and the dual-channel engine, which comprises an inner adapter section (41) and an outer adapter section (42), and an adapter section outer channel is formed between the inner adapter section (41) and the outer adapter section (42), and the inner wall of the inner adapter section (41) forms an adapter section inner channel.

4. The device for multi-duct engine inlet parameter testing according to claim 3, characterized in that, The inner adapter section (41) and the outer adapter section (42) are cylindrical curved surfaces or conical curved surfaces. When the inner duct of the adapter section is an expansion passage, the tangent value of the included angle between the conical generatrix of the adapter section (4) and the axis of the dual-duct engine is ≤12.3% to meet the non-separation of the diffuser flow; When the inner duct of the adapter section is a contraction passage, the tangent value of the included angle between the conical generatrix of the adapter section (4) and the axis of the dual-duct engine is ≤26.8% to meet the uniformity of the flow field.

5. The device for multi-duct engine inlet parameter testing according to claim 1, characterized in that, Sealing rings are arranged between the first measuring conduit (1) and the outer barrel (21), between the inner barrel (22) and the inner casing of the dual-duct engine, and between the outer barrel (21) and the outer casing of the dual-duct engine.

6. A method for multi-draught engine inlet parameter testing, characterized in that, The device of any one of claims 1-5 is used to test the inlet parameters of a multi-duct engine, including the following steps: S1, collecting the dual-duct engine inlet parameters and the inner duct inlet parameters, wherein the dual-duct engine inlet parameters include the first wall static pressure of a plurality of static pressure measuring points and the first total temperature and total pressure of a plurality of total temperature and total pressure measuring points; the inner duct inlet parameters include the second wall static pressure of a plurality of static pressure measuring points and the second total temperature and total pressure of a plurality of total temperature and total pressure measuring points; S21, calculating the average value of the first wall static pressure of a plurality of static pressure measuring points to obtain the dual-duct engine inlet static pressure; According to the first total temperature and total pressure of each total temperature and total pressure measuring point, the position of each total temperature and total pressure measuring point in the first measuring conduit (1), and the dual-duct engine inlet static pressure, the first air flow of each total temperature and total pressure measuring point in the first measuring conduit (1) is calculated; S22, calculating the average value of the second wall static pressure of a plurality of static pressure measuring points to obtain the inner duct inlet static pressure; According to the second total temperature and total pressure of each total temperature and total pressure measuring point, the position of each total temperature and total pressure measuring point in the second measuring conduit (2), and the inner duct inlet static pressure, the second air flow of each total temperature and total pressure measuring point in the second measuring conduit (2) is calculated; S3, calculating the total flow of the dual-duct engine inlet according to the first air flow of each total temperature and total pressure measuring point in the first measuring conduit (1); calculating the inner duct inlet flow according to the second air flow of each total temperature and total pressure measuring point in the second measuring conduit (2); S4, calculating the difference between the total flow of the dual-duct engine inlet and the inner duct inlet flow to obtain the outer duct inlet flow of the dual-duct engine.

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