Air inlet channel anti-icing test piece

Abstract

The invention discloses an air inlet channel anti-icing test piece, and belongs to the field of aero-engines. The air inlet channel anti-icing test piece comprises a skin with an arc-shaped structure and a plurality of replaceable side plate pairs, the side plate pairs provide mounting interfaces for flute-shaped pipes, different side plate pairs have mounting interfaces at different positions, the flute-shaped pipes are rigidly and fixedly connected to the mounting interfaces, an anti-icing test cavity is defined by the skin and the side plate pairs, and the flute-shaped pipes are arranged in the anti-icing test cavity. When different side plate pairs are adopted, the jet flow holes of the flute-shaped pipe and the skin have different relative position relations. The air inlet duct anti-icing test piece can provide a plurality of different flute-shaped pipe mounting positions, and provides stable and accurate positioning for the flute-shaped pipe under different test conditions, thereby improving the accuracy of an air inlet duct anti-icing test.

Description

Technical Field

[0001] This invention belongs to the field of aero-engines, and specifically relates to an air intake anti-icing test piece. Background Technology

[0002] When an aircraft flies in icing conditions, ice can form on the engine's air intake, intake components, and power unit, significantly impacting the engine. Icing in the intake system reduces airflow area, decreases the amount of air drawn into the compressor, reduces engine thrust, and can even cause compressor surge. If ice breaks off from the intake, it can damage the high-speed rotating fan or compressor blades, leading to more serious safety incidents. Therefore, air intake anti-icing tests are crucial for improving the safety performance of aero engines.

[0003] Patent CN103076150B discloses an airfoil test piece. A flute-shaped tube test piece is movably mounted within an airfoil shell via a position adjustment assembly and has multiple slots. This allows for adjustment of the flute-shaped tube's spatial position by engaging it in different slots during inlet anti-icing tests. The handle attached to the flute-shaped tube test piece facilitates further adjustment. However, the numerous slots, handles, nuts, and other components on the cover plate compromise its structural integrity and detachability, affecting the cover plate's rigidity during testing. Under significant temperature variations, thermal deformation can negatively impact the positioning accuracy of the flute-shaped tube test piece, hindering improved test precision. Therefore, providing a more reliable inlet anti-icing test piece is crucial for improving the accuracy of inlet anti-icing tests for aero-engines. Summary of the Invention

[0004] The purpose of this invention is to provide an intake anti-icing test piece to improve the test accuracy of intake anti-icing tests.

[0005] According to one embodiment of the present invention, an air intake anti-icing component is provided, comprising:

[0006] The skin is configured as a curved surface structure;

[0007] Multiple sets of side panel pairs, each side panel pair providing an installation interface, with different installation interfaces for different side panel pairs;

[0008] A flute-shaped tube with a jet hole, the flute-shaped tube being rigidly fixed to the mounting interface;

[0009] The skin can be spliced ​​with each of the side plate pairs to define an anti-icing test chamber. When the flute tube is installed at the mounting interface of different side plate pairs, the jet hole and the skin have different relative positional relationships.

[0010] The test parameters of the flute tube can be changed by replacing the side plate pair. The flute tube and the side plate pair are rigidly fixedly connected, which can effectively improve the installation accuracy of the flute tube and the geometric stability during the test, thereby improving the test accuracy.

[0011] Furthermore, in some embodiments, the mounting interface is configured as multiple threaded holes, and the flute tube is fixedly connected to the threaded holes by bolts.

[0012] Furthermore, in some embodiments, the plurality of threaded holes provide a plurality of mounting positions, and when the flute tube is mounted in different mounting positions, the jet hole faces different circumferential positions.

[0013] Furthermore, in some embodiments, the mounting interface is provided with a positioning groove, which provides radial restraint for the flute-shaped tube.

[0014] Furthermore, in some embodiments, the test piece also includes a sealing gasket disposed between the mounting interface and the flute tube.

[0015] Furthermore, in some embodiments, the test piece also includes a partition frame, and the edge of the skin between the side panel pairs is fixed to the partition frame.

[0016] Furthermore, in some embodiments, mounting holes are provided at the connection positions of the partition frame and the side panel pair, and the frame is fixedly connected to the skin by bolts provided in the mounting holes.

[0017] Furthermore, in some embodiments, the skin is provided with raised ribs, and the ribs are provided with screw holes that match the mounting holes, so as to allow the bolts to be fixed in the screw holes.

[0018] Furthermore, in some embodiments, the diameter of the flute-shaped tube is 10mm-50mm, the distance between the surface of the flute-shaped tube and the skin is 10mm-50mm, and the distance between the axial projection of the jet hole of the flute-shaped tube to the skin and the leading edge of the skin is 50mm-200mm.

[0019] The intake anti-icing test piece provided by the embodiments of the present invention can accurately position the flute tube in the anti-icing cavity by installing an interface on the side plate, and can adjust the position of the flute tube in the anti-icing test cavity by replacing the side plate, which facilitates the selection and optimization test of intake flute tube anti-icing system parameters and obtains the structural parameters corresponding to the best performance of the anti-icing system. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of the intake anti-icing test specimen in one embodiment;

[0021] Figure 2 This is a schematic cross-sectional view of an air intake anti-icing test specimen in one embodiment;

[0022] Figure 3 This is a schematic diagram of the installation position of the air intake anti-icing test piece in one embodiment;

[0023] Figure 4 This is a schematic diagram of the cross-sectional structure of the air intake anti-icing test piece in another embodiment;

[0024] Figure 5 This is a schematic cross-sectional view of the air intake anti-icing test piece in another embodiment.

[0025] Meaning of the reference numerals in the attached figures:

[0026] 101 - First side plate;

[0027] 102 - Second side plate;

[0028] 103 - Frame;

[0029] 104 - Flange;

[0030] 105-Skin;

[0031] 106-ribs;

[0032] 107 - Positioning groove;

[0033] 108-Flute tube;

[0034] 109 - Gasket;

[0035] 110-ribs;

[0036] 201-Fronting Edge Point;

[0037] 202 - Projection point.

[0038] The purpose of the above-described drawings is to provide a detailed description of the present invention so that those skilled in the art can understand the technical concept of the invention, and is not intended to limit the invention. For the sake of brevity, the above-described drawings only schematically depict the structures related to the technical features of the present invention, and do not depict the complete structure and all details strictly according to actual scale. Detailed Implementation

[0039] The present invention will now be described in further detail with reference to specific embodiments and accompanying drawings.

[0040] The term "embodiment" as used herein means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment herein. The phrase appearing in various places in the specification does not necessarily refer to the same embodiment, nor is it limited to mutually exclusive, independent, or alternative embodiments. Those skilled in the art will understand that the embodiments herein can be combined with other embodiments without causing structural conflicts.

[0041] In this description, unless otherwise explicitly specified and limited, the technical terms "installation," "connection," "joining," etc., should be interpreted broadly, for example, referring to movable connections, fixed connections, or integration. Those skilled in the art can understand the specific meaning of the above terms in the embodiments of this application based on the specific circumstances.

[0042] In this description, terms such as "upper," "lower," "left," "right," "lateral," "longitudinal," "height," "length," and "width," which indicate orientation or positional relationships, are intended to accurately describe the embodiments and simplify the description, rather than limiting the parts or structures involved to have a specific orientation, or to be installed or operated in a specific orientation, and should not be construed as limiting the embodiments in this document.

[0043] In this description, terms such as "first" and "second" are used only to distinguish different objects and should not be construed as indicating relative importance or limiting the number, specific order, or primary / secondary relationship of the described technical features. In this description, "multiple" means at least two.

[0044] When an aircraft flies in icing conditions, ice can form on the engine's air intake, intake components, and power unit. This icing can significantly impact the engine. Icing in the intake system reduces the airflow area, decreasing the amount of air the compressor draws in, reducing engine thrust, and potentially causing compressor surge. If ice breaks off from the intake, it can damage the high-speed rotating fan or compressor blades, leading to even more serious safety incidents.

[0045] To ensure flight safety under icing weather conditions, a highly efficient and widely used inlet anti-icing technology is the flute-shaped hot air anti-icing system. A certain amount of hot air is drawn from the high-pressure compressor into the anti-icing chamber at the leading edge of the inlet. The air is then jetted through small holes in the flute-shaped tube, heating the surface of the leading edge of the inlet and preventing icing from affecting the aerodynamic shape, thus achieving the anti-icing effect.

[0046] The design parameters of the intake duct whistle anti-icing system are numerous, including the spatial position of the whistle within the anti-icing chamber, the size, number, and spacing of the openings on the whistle, etc. Ice wind tunnel testing is required to obtain design parameters with optimal anti-icing performance. When designing test specimens, on the one hand, it is difficult to accurately locate the relative position of the whistle within the anti-icing chamber; on the other hand, most designs use a fixed position for the whistle within the anti-icing chamber, making it impossible to adjust the relative position of the whistle. This hinders the selection and optimization of parameters for the intake duct whistle anti-icing system.

[0047] An embodiment of the present invention provides an air intake anti-icing test piece, which allows for adjustment of the position of the flute tube within the anti-icing cavity by replacing the side plate, facilitating the selection and optimization of parameters for the air intake flute tube anti-icing system.

[0048] like Figure 1 As shown, the test piece includes a curved skin 105 and multiple pairs of side plates. Each pair includes a first side plate 101 and a second side plate 102. The first side plate 101 and the second side plate 102 each provide an installation interface for mounting a flute-shaped tube 108. In a preferred embodiment, the installation interface is configured with multiple threaded holes. Both ends of the flute-shaped tube 108 are flanges 104, and each flange 104 has the same number of through holes as the threaded holes. The flute-shaped tube 108 is rigidly connected to the side plate pairs via fixing bolts on the flanges 104. The positions of the threaded holes differ in different side plate pairs, so that the jet holes of the flute-shaped tube 108 have different relative positions to the skin 105 when the flanges 104 of the flute-shaped tube 108 are mounted on the side plate pairs. An air vent is located at the center of the flange 104, with a diameter identical to the inner diameter of the flute-shaped tube 108. During the test, airflow is introduced into the flute-shaped tube 8 through the air vent and ejected from the jet holes of the flute-shaped tube 8.

[0049] Furthermore, in a preferred embodiment, the circumferential distribution of the threaded holes forms multiple different mounting positions. The flute tube 108 can be circumferentially adjusted around its own axis, allowing for the selection of different mounting positions for installation. This enables the jet orifice to face different circumferential positions, thereby achieving adjustment of the jet angle of the flute tube 108 during the experiment. Specifically, according to the experimental design requirements, the jet angle of the flute tube 108 can be adjusted within the range of 0-360°.

[0050] Furthermore, in a preferred embodiment, the first side plate 101 and the second side plate 102 are provided with positioning grooves 107. The shape and size of the positioning grooves 107 match the flange 104 at the end of the flute tube 108. When the flute tube 108 is fixedly installed between the first side plate 101 and the second side plate 102, the flange 104 at the end of the flute tube 108 can engage with the positioning grooves 107 to achieve radial limiting of the flute tube 108, which facilitates the installation and positioning of the flute tube 108.

[0051] Furthermore, in a preferred embodiment, a sealing gasket 109 is provided between the flange 104 and the positioning groove 107. The gasket 109 can improve the sealing performance of the test piece and prevent leakage at the connection point during the test.

[0052] Further, in a preferred embodiment, the edge of the skin 105 between the first side plate 101 and the second side plate 102 is fixed by a spacer 103 to maintain a stable curved surface structure of the skin 105. The skin 105 is connected to the first side plate 101 and the second side plate 102 via the spacer 103. In a further preferred embodiment, mounting holes are provided at the connection positions of the spacer 103 and the first side plate 101 and the second side plate 102, and the spacer 103 is fixedly connected to the first side plate 101 and the second side plate 102 by bolts. Specifically, the skin 105 is provided with protruding L-shaped ribs 106 and 110 at the positions where it connects with the first side plate 101, the second side plate 102 and the partition frame 103. The ribs 106 and 110 are provided with screw holes that match the mounting holes, so that bolts can be tightened in the screw holes to achieve a fixed connection between the skin 105 and the first side plate 101, the second side plate 102 and the partition frame 103.

[0053] In a preferred embodiment, the structure of the air intake anti-icing component is as follows: Figure 1 As shown. The skin 105 has two-dimensional features, obtained by stretching a cross-sectional profile of the engine intake duct, and can be used to verify the anti-icing performance of a specific cross-section of the intake duct. The profile of this cross-section can be optimized to ensure that the flow field outside the icing protection area of ​​the test piece is consistent with the flow in the actual intake duct. The flute tube 108 is a test piece designed to simulate the flute tube of a real intake duct anti-icing system in an ice tunnel; the size and spacing of its jet holes are consistent with those of a real intake duct flute tube.

[0054] The skin 105 is connected to the partition frame 103 via L-shaped ribs 110, forming an anti-icing test chamber. Threaded holes, 3-5 mm in diameter, are evenly distributed at the connection points, and the L-shaped ribs 103 are 5 mm thick. The first side plate 101 and the second side plate 102 have the same shape and are 5 mm thick. They are connected to the skin 105 via L-shaped ribs 106. Threaded holes, 3-5 mm in diameter, are evenly distributed along the edge at the connection between the skin 105 and the side plate, and the L-shaped ribs 106 are 5 mm thick. The diameter of the air inlet on the first side plate 101 and the second side plate 102 is the same as the inner diameter of the flute-shaped tube 108. A recessed layer is formed on the inner side of the side plate to create a positioning groove 107. The diameter of the positioning groove 107 is 1.3 times the inner diameter of the flute-shaped tube 108, and the positioning groove 107 is 1 mm lower than the side plate plane. This groove is used to install a 1 mm thick silicone gasket 109, connecting to the flange of the flute-shaped tube 108, ensuring the airtightness of the air inlet of the test piece. The silicone gasket 109 and the positioning groove 107 are the same size. The inner side of the side plate refers to the side of the side plate that forms the anti-icing cavity, and the outer side of the side plate refers to the side of the side plate that is close to the hot gas venting pipe. Nine corresponding 3mm threaded holes are evenly arranged on the positioning groove 107 of the first and second side plates, the silicone gasket 109, and the flange of the flute-shaped tube 108. More preferably, a recessed layer is provided on the outer side of the first side plate 101 and the second side plate 102. The diameter of the recessed layer is 1.3 times the inner diameter of the flute-shaped tube, and the recessed layer is 1mm lower than the plane of the side plate. This recessed layer is used to install a 1mm thick silicone gasket to connect the hot gas venting pipe and the exhaust pipe. The flute-shaped tube 108 can be further positioned by inserting a retaining block.

[0055] like Figure 2 As shown, in the preferred embodiment, the inner diameter D of the flute-shaped tube 108 ranges from 10mm to 50mm; the distance L between the outer surface of the flute-shaped tube 108 and the skin 105 ranges from 10mm to 50mm. The distance s between the axial projection point 202 of the jet orifice on the skin 105 and the leading edge point 201 of the skin is 50mm to 200mm. The included angles α and β between the jet orifice and the side orifices range from 30° to 60°.

[0056] During the intake anti-icing test, the installation position of this test piece is as follows: Figure 3 As shown. An airfoil test apparatus with the same shape as the complete cross-section of an aircraft wing is provided. The air intake anti-icing test piece is installed at the leading edge of the airfoil test apparatus to simulate the state of the engine air intake.

[0057] When it is necessary to adjust the angle of the jet hole of the flute tube 108, the bolts on the first side plate 101 and the second side plate 102 can be removed, the flute tube 108 can be rotated to change the correspondence between the through hole on the flange 104 and the threaded hole on the side plate, and the position of the projection point 202 will also change accordingly. The nine bolts can be tightened again to complete the fixation of the flute tube 108.

[0058] When it is necessary to adjust the relative position between the flute tube 108 and the skin 105, the first side plate 101 and the second side plate 102 can be replaced. For example... Figure 4 and Figure 5 As shown, by assembling side plates with positioning grooves 107 and induction holes at different positions, different relative positional relationships between the flute tube 108 and the skin 105 can be formed.

[0059] The intake anti-icing test piece provided in the above embodiments can provide firm support and stable positioning for the flute tube when used in intake anti-icing wind tunnel tests. The position of the flute tube can be adjusted by switching the side plates, which can effectively improve the accuracy of intake anti-icing tests and reduce errors caused by thermal stress and insufficient fixing strength of the flute tube.

[0060] The purpose of the above embodiments is to provide a further detailed description of the present invention in conjunction with the accompanying drawings, so that those skilled in the art can understand the technical concept of the present invention. Within the scope of the present invention, optimization or equivalent replacement of the involved part structures, as well as combination of implementation methods in different embodiments without causing structural and principle conflicts, all fall within the protection scope of the present invention.

Claims

1. An air intake anti-icing test piece, characterized in that, include: The skin is configured as a curved surface structure; Multiple sets of side panel pairs, each side panel pair providing an installation interface, with different installation interfaces for different side panel pairs; A flute-shaped tube with a jet hole, the flute-shaped tube being rigidly fixed to the mounting interface; The skin can be spliced ​​with each of the side plate pairs to define an anti-icing test chamber. When the flute tube is installed at the mounting interface of different side plate pairs, the jet hole and the skin have different relative positional relationships.

2. The intake duct anti-icing test piece according to claim 1, characterized in that, The mounting interface is configured with multiple threaded holes, and the flute-shaped tube is fixedly connected to the threaded holes by bolts.

3. The intake duct anti-icing test specimen according to claim 2, characterized in that, The plurality of threaded holes provide a plurality of mounting positions, and when the flute tube is mounted in different mounting positions, the jet hole faces different circumferential positions.

4. The intake anti-icing test piece according to claim 1, 2, or 3, characterized in that, The installation interface is provided with a positioning groove, which provides radial restraint for the flute-shaped tube.

5. The intake anti-icing test piece according to claim 1, 2, or 3, characterized in that, It also includes a sealing gasket disposed between the mounting interface and the flute tube.

6. The intake duct anti-icing test specimen according to claim 1, characterized in that, It also includes a partition frame, to which the edge of the skin between the side panel pairs is fixed.

7. The intake duct anti-icing test specimen according to claim 6, characterized in that, The partition frame and the side panel are provided with mounting holes at the connection positions, and are fixedly connected to the skin by bolts provided in the mounting holes.

8. The intake anti-icing test specimen according to claim 7, characterized in that, The skin is provided with raised ribs, and the ribs are provided with screw holes that match the mounting holes, so as to allow the bolts to be fixed in the screw holes.

9. The intake duct anti-icing test specimen according to claim 1, characterized in that, The diameter of the flute-shaped tube is 10mm-50mm, the distance between the surface of the flute-shaped tube and the skin is 10mm-50mm, and the distance between the axial projection of the jet hole of the flute-shaped tube to the skin and the leading edge of the skin is 50mm-200mm.

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