An air intake device for testing aerodynamic performance of a side-intake aircraft engine

Abstract

An air intake device for aerodynamic performance testing of a side-intake aircraft engine. In specific applications, air passes through a flow measurement section, a flow measurement rear diffuser section, a flow measurement rear bend neck, an intake front diffuser section, a round-to-square transition section, an intake pressure stabilizing and rectifying section, an intake contraction section, and an intake volute in sequence, and flows to the aircraft engine inlet for an aerodynamic performance test. The flow measurement section is a round tube, a straight section, and has a smaller diameter, and a flow measurement device can be easily arranged therein to achieve high-precision measurement of the aircraft engine intake flow rate; the intake pressure stabilizing and rectifying section is a square tube, a straight section, and has a larger radial dimension, and a honeycomb rectifier and two microporous rectifying nets are arranged therein in sequence. When air flows through the intake pressure stabilizing and rectifying section, the honeycomb rectifier can break up large vortices in the air, and the microporous rectifying net can further break up small vortices in the air, thereby ensuring the intake air flow field quality of the aircraft engine.

Description

Technical Field

[0001] The present application belongs to the technical field of aerodynamic performance test design for side-intake aircraft engines, and specifically relates to an air intake device for aerodynamic performance test of side-intake aircraft engines. Background Art

[0002] In the aerodynamic performance test of an aircraft engine, the intake environment of the aircraft engine is simulated by an intake device. Currently, for an aircraft engine with a side intake structure, a square cross-section intake pipe is designed as the intake device during the aerodynamic performance test. The intake pipe is connected to the inlet of the aircraft engine through an intake volute, and a honeycomb rectifier is set in the square cross-section intake pipe. Figure 1 As shown in the figure, in specific applications, air enters the square cross-section intake pipe, and the honeycomb rectifier breaks up the large vortices in the air. The air then flows to the aircraft engine inlet through the intake volute, thereby simulating the intake environment of the aircraft engine and conducting aerodynamic performance testing. This technical solution has the following defects:

[0003] 1) The honeycomb rectifier breaks up large vortices in the air, but cannot further process small-scale vortices in the air. This makes it difficult to ensure the quality of the aircraft engine's inlet flow field, affecting the aircraft engine's aerodynamic performance and making it difficult to obtain ideal test results.

[0004] 2) The square-section intake duct has a large cross-section, making it impossible to arrange a flow measurement device, making it impossible to measure the intake flow of the aircraft engine. This lacks important parameters for evaluating the aerodynamic performance of the aircraft engine, making it difficult to efficiently utilize the test results.

[0005] This application is proposed in view of the above-mentioned technical defects.

[0006] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of the present application. In the absence of clear evidence that the above content has been disclosed on the filing date of the present application, the above background technology should not be used to evaluate the novelty and creativity of the present application. Summary of the Invention

[0007] The purpose of the present application is to provide an air intake device for testing the aerodynamic performance of a side-intake aircraft engine, so as to overcome or alleviate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] An air intake device for testing the aerodynamic performance of a side-intake aircraft engine, comprising:

[0010] a flow measurement section, in which a flow measurement device is arranged;

[0011] The diffuser section after flow measurement has its inlet connected to the outlet of the flow measurement section;

[0012] The flow measurement rear bend neck has its inlet connected to the outlet of the flow measurement rear diffuser section;

[0013] The inlet of the diffuser section before the air intake is connected to the outlet of the bent neck after the flow measurement;

[0014] The circular-to-square transition section has its inlet butted against the outlet of the pre-intake diffuser section;

[0015] The inlet of the air intake pressure stabilizing and rectifying section is connected to the outlet of the round-to-square transition section;

[0016] The inlet of the air intake contraction section is connected to the outlet of the air intake pressure stabilization and rectification section;

[0017] The inlet of the air intake volute is connected to the outlet of the air intake contraction section, and the outlet is connected to the inlet of the aircraft engine; the axis of the aircraft engine is perpendicular to the axis of the flow measurement section;

[0018] Honeycomb rectifier, set in the intake pressure stabilization and rectification section;

[0019] Two microporous rectifier nets are set in the intake pressure stabilization and rectification section and are located downstream of the honeycomb rectifier.

[0020] According to at least one embodiment of the present application, in the above-mentioned air intake device for testing the aerodynamic performance of a side-intake aircraft engine, the flow measurement section is a flow measurement tube.

[0021] According to at least one embodiment of the present application, the aforementioned air intake device for aerodynamic performance testing of a side-intake aircraft engine further includes:

[0022] The dustproof net is spherical and connected to the inlet of the flow measurement section.

[0023] According to at least one embodiment of the present application, the aforementioned air intake device for aerodynamic performance testing of a side-intake aircraft engine further includes:

[0024] Multiple support frames are used to support the flow measurement section, the diffuser section after flow measurement, the bent neck after flow measurement, the diffuser section before intake, the round-to-square transition section, the intake pressure stabilizing and rectifying section, the intake contraction section, and the intake volute.

[0025] According to at least one embodiment of the present application, in the above-mentioned air intake device for aerodynamic performance testing of a side-intake aircraft engine, rollers are installed on a support frame supporting the flow measurement section, the diffuser section after flow measurement, the neck after flow measurement, the diffuser section before intake, the round-to-square transition section, the intake pressure stabilizing and rectifying section, and the intake contraction section;

[0026] The support frame supporting the intake volute is fixed.

[0027] This application has at least the following beneficial technical effects:

[0028] Provided is an air intake device for aerodynamic performance test of a side-intake aircraft engine. In specific applications, air passes through a flow measurement section, a flow measurement rear diffuser section, a flow measurement rear bend neck, an intake front diffuser section, a round-to-square transition section, an intake pressure stabilizing and rectifying section, an intake contraction section, and an intake volute in sequence, and flows to the aircraft engine inlet for an aerodynamic performance test. The flow measurement section is a round tube, a straight section, and has a smaller diameter, and a flow measurement device can be easily arranged therein, thereby achieving high-precision measurement of the aircraft engine intake flow rate; the intake pressure stabilizing and rectifying section is a square tube, a straight section, and has a larger radial dimension, and a honeycomb rectifier and two microporous rectifying nets are arranged therein in sequence. When air flows through the intake pressure stabilizing and rectifying section, the honeycomb rectifier can break up large vortices in the air, and the microporous rectifying net can further break up small vortices in the air, thereby ensuring the intake flow field quality of the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of the structure of an air intake device used in aerodynamic performance testing of existing aircraft engines;

[0030] Figure 2 This is a front view of an air intake device for aerodynamic performance testing of a side-intake aircraft engine provided in an embodiment of the present application;

[0031] Figure 3 This is a side view of a partial structure of an air intake device for aerodynamic performance testing of a side-intake aircraft engine provided by an embodiment of the present application;

[0032] in:

[0033] 1-Flow measurement section; 2-Diffuser section after flow measurement; 3-Neck after flow measurement; 4-Intake diffuser section; 5-Circular to square transition section; 6-Intake pressure stabilization and rectification section; 7-Intake contraction section; 8-Intake volute; 9-Aircraft engine; 10-Honeycomb rectifier; 11-Microporous rectifier net; 12-Dustproof net; 13-Support frame.

[0034] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0035] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0036] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0037] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0038] The following is combined with Figures 1 to 3 This application is described in further detail.

[0039] An air intake device for testing the aerodynamic performance of a side-intake aircraft engine, comprising:

[0040] The flow measurement section 1 is a straight section of a circular tube with a relatively small diameter, in which a flow measurement device is arranged; the flow measurement device can be a flow measurement tube or other device for measuring flow;

[0041] The diffuser section 2 after flow measurement is a circular tube with a gradually increasing diameter, and its inlet is connected to the outlet of the flow measurement section 1;

[0042] The flow measurement rear bend neck 3 is a bend pipe, and its inlet is connected to the outlet of the flow measurement rear diffuser section 2;

[0043] The front-intake diffuser section 4 is a circular tube with a gradually increasing diameter, and its inlet is connected to the outlet of the flow measurement rear bend neck 3; the flow measurement rear bend neck 3 is connected between the flow measurement rear diffuser section 2 and the front-intake diffuser section 4;

[0044] The round-to-square transition section 5 has a round inlet and a square outlet with a smooth transition in the middle. Its inlet is connected to the outlet of the pre-intake diffuser section 4;

[0045] The air intake pressure stabilizing and rectifying section 6 is a square tube with a straight section. Its inlet is connected to the outlet of the round-to-square transition section 5. A honeycomb rectifier 10 and two microporous rectifying nets 11 are arranged inside it. The two microporous rectifying nets 11 are located downstream of the honeycomb rectifier 10.

[0046] The air intake contraction section 7 is a square tube with a gradually shrinking diameter, and its inlet is connected to the outlet of the air intake pressure stabilization and rectification section 6;

[0047] The inlet of the air intake volute 8 is square and docked with the outlet of the air intake contraction section 7, and its outlet docked with the inlet of the aircraft engine 9; the axis of the aircraft engine 9 is perpendicular to the axis of the flow measurement section 1, and based on the bent neck design, the overall structure is compact.

[0048] The above embodiment discloses an air intake device for aerodynamic performance test of a side-intake aircraft engine. In specific applications, air passes through the flow measurement section 1, the diffuser section 2 after flow measurement, the bent neck 3 after flow measurement, the diffuser section 4 before intake, the round-to-square transition section 5, the intake pressure stabilizing and rectifying section 6, the intake contraction section 7, and the intake volute 8 in sequence, and flows to the inlet of the aircraft engine 9 for aerodynamic performance test. The flow measurement section 1 is a round tube, a straight section, and has a small diameter. A flow measurement device can be easily arranged therein. After the air flow is fully developed, high-precision measurement of the intake flow of the aircraft engine is achieved by measuring parameters such as total pressure and static pressure. The flow measurement section 1 is followed by the diffuser section 2 after flow measurement, the diffuser section 4 before intake, and the intake contraction section 7. After flow measurement, the bent neck 3 and the round-to-square transition section 5 expand the inflowing air twice and then accelerate it, which can ensure the air supply and flow rate of the aircraft engine. The intake contraction section 7 can adopt a continuous monotonically smooth increase in axial speed to ensure that the outlet airflow is uniform, straight and stable. In addition, an intake pressure stabilizing and rectifying section 6 is arranged between the round-to-square transition section 5 and the intake contraction section 7. It is a square tube, a straight section, and has a large radial dimension. A honeycomb rectifier 10 and two microporous rectifying nets 11 are arranged therein in sequence. When the air flows through the intake pressure stabilizing and rectifying section 6, the honeycomb rectifier 10 can break up the large vortices in the air, and the microporous rectifying net 11 can further break up the small vortices in the air, thereby ensuring the quality of the intake air flow field of the aircraft engine 9.

[0049] In some optional embodiments, in the above-mentioned air intake device for testing the aerodynamic performance of a side-intake aircraft engine, the flow measurement section 1 is a flow measurement tube.

[0050] In some optional embodiments, the above-mentioned air intake device for testing the aerodynamic performance of a side-intake aircraft engine further includes:

[0051] The dustproof net 12 is spherical and connected to the inlet of the flow measurement section 1. It can filter the air entering the air intake device over a large area and ensure the air flow.

[0052] In some optional embodiments, the above-mentioned air intake device for testing the aerodynamic performance of a side-intake aircraft engine further includes:

[0053] Multiple support frames 13 are used to support the flow measurement section 1, the flow measurement rear diffuser section 2, the flow measurement rear bend neck 3, the intake front diffuser section 4, the round-to-square transition section 5, the intake pressure stabilizing and rectifying section 6, the intake contraction section 7, and the intake volute 8.

[0054] In some optional embodiments, in the above-mentioned air intake device for aerodynamic performance testing of a side-intake aircraft engine, rollers are installed on the support frame 13 supporting the flow measurement section 1, the flow measurement rear diffuser section 2, the flow measurement rear bent neck 3, the intake front diffuser section 4, the round-to-square transition section 5, the intake pressure stabilizing and rectifying section 6, and the intake contraction section 7 to facilitate movement and disassembly;

[0055] The support frame 13 supporting the air intake volute 8 is fixed, specifically, it can be fixed to the ground with bolts, so as to stably support the air intake volute 8 and position the air intake volute 8.

[0056] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0057] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. An air intake device for testing the aerodynamic performance of a side-intake aircraft engine, characterized in that: include: A flow measurement section (1) in which a flow measurement device is arranged; a flow measurement post-diffuser section (2), the inlet of which is connected to the outlet of the flow measurement section (1); A flow measurement rear bent neck (3), the inlet of which is connected to the outlet of the flow measurement rear diffuser section (2); The inlet of the front diffuser section (4) is connected to the outlet of the flow measurement rear bend neck (3); The circular-to-square transition section (5) has its inlet butted against the outlet of the pre-intake diffuser section (4); The inlet of the air intake pressure stabilizing and rectifying section (6) is connected to the outlet of the round-to-square transition section (5); The inlet of the air intake contraction section (7) is connected to the outlet of the air intake pressure stabilization and rectification section (6); An air intake volute (8), the inlet of which is connected to the outlet of the air intake contraction section (7), and the outlet of which is connected to the inlet of the aircraft engine (9); the axis of the aircraft engine (9) is perpendicular to the axis of the flow measurement section (1); A honeycomb rectifier (10) is provided in the intake pressure stabilizing and rectifying section (6); Two microporous rectifier nets (11) are provided in the intake pressure stabilizing rectifier section (6) and are located downstream of the honeycomb rectifier (10).

2. The air intake device for aerodynamic performance testing of a side-intake aircraft engine according to claim 1, characterized in that: The flow measuring device is a flow measuring tube.

3. The air intake device for aerodynamic performance testing of a side-intake aircraft engine according to claim 1, characterized in that: Also includes: The dust screen (12) is spherical and connected to the inlet of the flow measurement section (1).

4. The air intake device for aerodynamic performance testing of a side-intake aircraft engine according to claim 1, characterized in that: Also includes: A plurality of support frames (13) are used to support a flow measurement section (1), a flow measurement rear diffuser section (2), a flow measurement rear bend neck (3), an intake front diffuser section (4), a round-to-square transition section (5), an intake pressure stabilizing and rectifying section (6), an intake contraction section (7), and an intake volute (8).

5. The air intake device for aerodynamic performance testing of a side-intake aircraft engine according to claim 1, characterized in that: Rollers are installed on a support frame (13) supporting the flow measurement section (1), the flow measurement rear diffuser section (2), the flow measurement rear bent neck (3), the intake front diffuser section (4), the round-to-square transition section (5), the intake pressure stabilization and rectification section (6), and the intake contraction section (7); The support frame (13) supporting the intake volute (8) is fixed.

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