Aero-engine three-duct afterburner test inlet flow field simulation measurement device

Abstract

The present application specifically relates to a device for simulating and measuring the flow field of the test inlet of a three-ducted afterburner combustion chamber of an aircraft engine. In specific applications, the outer casing, the inner casing, the inner cone, and the rear end of the three-ducted air intake casing can be connected to the afterburner combustion chamber test piece, and the inner air is introduced into the inner duct of the afterburner combustion chamber through the inner air intake duct, the outer air is introduced into the afterburner combustion chamber through the outer air intake duct, and the three-ducted air is introduced into the three-ducted through the three-ducted air intake hole through the annular air collecting cavity, the air vent, and the rear three-ducted air intake duct, so as to simulate the inlet flow field of the afterburner combustion chamber, and the temperature, pressure and other measuring points arranged on the outer air intake flow field measurement strut and the inner air intake flow field measurement strut can be used to measure the temperature and pressure of the inner air intake duct and the outer air intake duct. In addition, cold air can be introduced into the inner cone interlayer through the cooling air intake pipe, and the cold air can be discharged from the air film holes on the inner cone, so as to protect the inner cone from being eroded by high-temperature inner air.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine three-duct afterburner combustion chamber testing, and specifically relates to an aircraft engine three-duct afterburner combustion chamber test inlet flow field simulation measurement device. Background Art

[0002] The afterburner test of an aircraft engine uses an inlet flow field simulation and measurement device to simulate the inlet flow field of the afterburner and measure the inlet flow field parameters.

[0003] Currently, the aircraft engine afterburner test inlet flow field simulation and measurement device can only simulate the inlet flow field of a double-duct afterburner, but cannot simulate the inlet flow field of a triple-duct afterburner, and cannot withstand higher temperature loads.

[0004] This application is proposed in view of the above-mentioned technical defects.

[0005] 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

[0006] The purpose of this application is to provide a device for simulating and measuring the flow field of the test inlet of a three-duct afterburner combustion chamber of an aircraft engine, so as to overcome or alleviate at least one of the technical defects that are known to exist.

[0007] The technical solution of this application is:

[0008] A device for simulating and measuring the flow field of a three-duct afterburner test inlet of an aircraft engine, comprising:

[0009] outer receiver;

[0010] The inner casing is arranged inside the outer casing, and forms an external air inlet duct between the inner casing and the outer casing;

[0011] The inner cone is arranged in the inner casing, forming an internal air intake duct between the inner casing and the inner casing, and is a sandwich structure, and its outer wall has multiple air film holes;

[0012] Multiple cooling air intake pipes are set through the outer casing and the inner casing, distributed along the circumference, and the outlet ends extend into the inner cone interlayer and are welded to the outer wall of the inner cone;

[0013] Multiple outer duct intake air flow field measurement struts are connected to the outer casing along the circumferential direction through the mounting base using bolts, penetrate the outer casing, extend into the outer duct intake duct, and extend into the windward surface of the outer duct intake duct to set temperature and pressure measurement points;

[0014] Multiple internal intake air flow field measurement struts are connected to the outer casing along the circumferential direction through the mounting base using bolts, penetrate the outer casing and the inner casing, and extend into the internal intake duct. Temperature and pressure measurement points are set on the windward surface of the internal intake duct.

[0015] The three-ducted air intake casing is sleeved on the rear end of the outer casing to form a rearward three-ducted air intake duct with the outer casing. The front end side wall of the three-ducted air intake casing has a plurality of vents distributed along the circumferential direction; each vent is connected to the rearward three-ducted air intake duct;

[0016] The air collecting casing is sleeved and connected to the outer periphery of the three-duct air intake casing, forming an annular air collecting cavity between the three-duct air intake casing, and its rear end side wall has multiple three-duct air intake holes distributed along the circumferential direction; the annular air collecting cavity is connected to each air vent and three-duct air intake hole.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, the inner cone is a hollow structure.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, the outer wall of the inner cone has a plurality of positioning holes distributed along the circumferential direction;

[0019] The aero-engine three-duct afterburner test inlet flow field simulation measurement device further includes:

[0020] A plurality of positioning blocks are welded on the inner wall of the inner cone along the circumferential direction and have positioning grooves thereon;

[0021] A plurality of positioning bosses are provided in each positioning hole and inserted into each positioning groove;

[0022] The baffle is connected to the outer wall and the rear end of the inner wall of the inner cone.

[0023] According to at least one embodiment of the present application, the aforementioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device further includes:

[0024] Multiple support plates are supported between the outer casing and the inner casing along the circumferential direction, are welded to the inner casing, and are connected to the outer casing by bolts.

[0025] According to at least one embodiment of the present application, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, each internal inlet flow field measurement support rod is set through each support plate. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1Schematic diagram of a test inlet flow field simulation measurement device for a three-duct afterburner of an aircraft engine provided in an embodiment of the present application;

[0027] Figure 2 yes Figure 1 AA sectional view;

[0028] Figure 3 This is a partial schematic diagram of a device for simulating and measuring the flow field in a three-duct afterburner test inlet of an aircraft engine provided by an embodiment of the present application;

[0029] in:

[0030] 1-outer casing; 2-inner casing; 3-inner cone; 4-cooling intake pipe; 5-outer intake air flow field measurement support rod; 6-inner intake air flow field measurement support rod; 7-three-duct intake casing; 8-air collecting casing; 9-positioning block; 10-positioning boss; 11-baffle; 12-support plate.

[0031] 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

[0032] 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.

[0033] 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.

[0034] 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.

[0035] The following is combined with Figures 1 to 3 This application is described in further detail.

[0036] A device for simulating and measuring the flow field in the test inlet of a three-duct afterburner combustion chamber of an aircraft engine, such as Figure 1 As shown, including:

[0037] Outer receiver 1;

[0038] The inner casing 2 is arranged inside the outer casing 1 and forms an outer air intake duct with the outer casing 1;

[0039] The inner cone 3 is arranged in the inner casing 2, forming an internal air intake duct between the inner casing 2 and the inner casing 2. The inner cone 3 is a sandwich structure, and its outer wall has multiple air film holes;

[0040] Multiple cooling air inlet pipes 4 are provided through the outer casing 1 and the inner casing 2, distributed along the circumferential direction, with the outlet ends extending into the interlayer of the inner cone 3 and being welded to the outer wall of the inner cone 3;

[0041] Multiple outer duct intake air flow field measurement struts 5 are connected to the outer casing 1 along the circumferential direction by bolts through the mounting base, penetrate the outer casing 1, and extend into the outer duct intake duct. Temperature and pressure measurement points are set on the windward surface of the outer duct intake duct, and airflow angle measurement points can also be set;

[0042] Multiple internal intake air flow field measurement struts 6 are connected to the outer casing 1 along the circumferential direction by bolts through the mounting base, penetrate the outer casing 1 and the inner casing 2, and extend into the internal intake duct. Temperature and pressure measurement points are set on the windward surface of the internal intake duct, and airflow angle measurement points can also be set;

[0043] The three-ducted air intake casing 7 is sleeved on the rear end of the outer casing 1 to form a rearward three-ducted air intake duct with the outer casing 1. The front end side wall of the three-ducted air intake casing 7 has a plurality of vents distributed along the circumferential direction; each vent is connected to the rearward three-ducted air intake duct;

[0044] The air collecting casing 8 is sleeved on the outer periphery of the three-duct air intake casing 7, and forms an annular air collecting cavity between the three-duct air intake casing 7. The rear end side wall thereof has multiple three-duct air intake holes distributed along the circumferential direction; the annular air collecting cavity is connected to each air vent and the three-duct air intake hole.

[0045] The above-mentioned embodiment discloses an aircraft engine three-duct afterburner test inlet flow field simulation and measurement device. In specific applications, the outer casing 1, inner casing 2, inner cone 3, and the rear end of the three-duct air intake casing 7 can be connected to the afterburner test piece, and inner air is introduced into the inner duct of the afterburner through the inner air intake duct, and outer air is introduced into the afterburner through the outer air intake duct, and three-duct air is introduced into the three-duct through the three-duct air intake hole through the annular air collecting cavity, the air vent, and the rear three-duct air intake duct, so as to simulate the afterburner inlet flow field. The temperature, pressure and other measuring points arranged on the outer air intake flow field measurement support rod 5 and the inner air intake flow field measurement support rod 6 can be used to measure the temperature and pressure of the inner air intake duct and the outer air intake duct. In addition, cold air can be introduced into the interlayer of the inner cone 3 through the cooling air intake pipe 4, and the cold air can be discharged from the air film holes on the inner cone 3, so as to protect the inner cone 3 from being eroded by high-temperature inner air.

[0046] The above embodiment discloses a device for simulating and measuring the flow field of the three-ducted afterburner test inlet of an aircraft engine. A rearward three-ducted air inlet is formed between the three-ducted air intake casing 7 and the outer casing 1, and an annular air collecting cavity is formed between the air collecting casing 8 and the three-ducted air intake casing 7. The three-ducted air introduced into the annular air collecting cavity through the three-ducted air intake holes on the air collecting casing 8 will flow forward, enter the three-ducted air intake through the various ventilation holes on the three-ducted air intake casing 7, and then pass backward into the three-ducted air intake of the afterburner test piece. Figure 3As shown, the three-ducted gas is dispersed many times through the three-ducted air inlet holes and air vents during the process of entering the three-ducted gas of the afterburner test piece, and flows back and forth many times in the annular gas collecting cavity and the three-ducted air inlet duct. This can ensure that the three-ducted gas entering the three-ducted gas of the afterburner test piece is evenly distributed in the circumferential direction within a short distance, and can well simulate and restore the inlet flow field of the afterburner test piece, making the overall structure simple and compact.

[0047] In some optional embodiments, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, the inner cone 3 is a hollow structure.

[0048] In some optional embodiments, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, the outer wall of the inner cone 3 has a plurality of positioning holes distributed along the circumferential direction;

[0049] The aero-engine three-duct afterburner test inlet flow field simulation measurement device further includes:

[0050] A plurality of positioning blocks 9 are welded to the inner wall of the inner cone 3 along the circumferential direction and have positioning grooves thereon;

[0051] A plurality of positioning bosses 10 are provided in each positioning hole and inserted into each positioning groove;

[0052] The baffle 11 is connected to the outer wall and the rear end of the inner wall of the inner cone 3, as shown in FIG. Figure 2 As shown, in order to facilitate assembly and ensure the stability of the overall structure.

[0053] In some optional embodiments, the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device further includes:

[0054] A plurality of support plates 12 are circumferentially supported between the outer casing 1 and the inner casing 2 , are welded to the inner casing 2 , and are bolted to the outer casing 1 , thereby reliably supporting the outer casing 1 and the inner casing 2 .

[0055] In some optional embodiments, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, each internal inlet flow field measurement support rod 6 is set through each support plate 12, and the bolts of the mounting seat connected to the outer casing 1 can be shared with the bolts connecting the outer casing 1 to the support plate 12.

[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. A device for simulating and measuring the flow field at the inlet of a three-ducted afterburner test chamber of an aircraft engine, characterized in that: include: Outer casing (1); The inner casing (2) is arranged inside the outer casing (1) and forms an outer air intake duct between the inner casing (2) and the outer casing (1); The inner cone (3) is arranged in the inner casing (2) and forms an internal air intake duct between the inner casing (2). The inner cone (3) is a sandwich structure, and its outer wall has a plurality of air film holes. A plurality of cooling air inlet pipes (4) are provided through the outer casing (1) and the inner casing (2), distributed along the circumferential direction, and the outlet ends extend into the interlayer of the inner cone (3) and are welded to the outer wall of the inner cone (3); A plurality of outer duct intake air flow field measurement struts (5) are connected to the outer casing (1) along the circumferential direction by bolts through a mounting seat, are arranged through the outer casing (1), extend into the outer duct intake duct, and extend into a portion of the windward surface of the outer duct intake duct to set temperature and pressure measurement points; A plurality of internal intake air flow field measurement struts (6) are connected to the outer casing (1) along the circumferential direction by bolts through a mounting seat, penetrate the outer casing (1) and the inner casing (2), extend into the internal intake duct, and extend into a portion of the internal intake duct on the windward surface to set temperature and pressure measurement points; The three-duct air intake casing (7) is sleeved on the rear end of the outer casing (1) to form a rearward three-duct air intake duct between the outer casing (1), and the front end side wall thereof has a plurality of vent holes distributed along the circumferential direction; each vent hole is connected to the rearward three-duct air intake duct; The air collecting casing (8) is sleeved on the outer periphery of the three-duct air intake casing (7) to form an annular air collecting cavity with the three-duct air intake casing (7), and its rear end side wall has a plurality of three-duct air intake holes distributed along the circumferential direction; the annular air collecting cavity is connected to each vent hole and the three-duct air intake hole.

2. The aircraft engine three-duct afterburner test inlet flow field simulation measurement device according to claim 1, characterized in that: The inner cone (3) is a hollow structure.

3. The aircraft engine three-duct afterburner test inlet flow field simulation measurement device according to claim 1, characterized in that: The outer wall of the inner cone (3) is provided with a plurality of positioning holes distributed along the circumferential direction; The aero-engine three-duct afterburner test inlet flow field simulation measurement device further includes: A plurality of positioning blocks (9) are welded to the inner wall of the inner cone (3) along the circumferential direction and have positioning grooves thereon; A plurality of positioning bosses (10) are arranged in each positioning hole and inserted into each positioning groove; The baffle (11) is connected to the outer wall and the rear end of the inner wall of the inner cone (3).

4. The aircraft engine three-duct afterburner test inlet flow field simulation measurement device according to claim 1, characterized in that: Also includes: A plurality of support plates (12) are supported between the outer casing (1) and the inner casing (2) along the circumferential direction, are connected to the inner casing (2) by welding, and are connected to the outer casing (1) by bolts.

5. The aircraft engine three-duct afterburner test inlet flow field simulation measurement device according to claim 1, characterized in that: Each internal intake airflow field measurement support rod (6) is arranged through each support plate (12).

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