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

Abstract

The present application relates to a device for simulating and measuring the inlet flow field of a three-duct afterburner test inlet of an aircraft engine. In specific applications, the outer casing, inner casing, inner cone, and rear end of the three-duct air intake casing can be connected to the afterburner test piece, and inner air can be introduced into the inner duct of the afterburner through the inner air intake duct, and outer air can be introduced into the afterburner through the outer air intake duct, thereby simulating the inlet flow field of the afterburner. The temperature, pressure and other measuring points arranged on the outer air intake flow field measurement support rod and the inner air intake flow field measurement support rod 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 outer cold air intake duct through the annular diversion cavity and the inner cold air intake duct. The cold air can be discharged from the air film holes on the inner cone, and can cool the inner casing, the inner air intake duct support plate, and the inner cone along the way.

Description

Technical Field

[0001] The present application belongs to the technical field of three-duct afterburner test of aircraft engines, and specifically relates to a device for simulating and measuring the inlet flow field of a three-duct afterburner test of an aircraft engine. Background Art

[0002] The aircraft engine afterburner test uses an inlet flow field simulation and measurement device to simulate the afterburner inlet flow field 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 afterburner double-duct inlet flow field, cannot simulate the afterburner three-duct inlet flow field, 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 outer air inlet duct with the outer casing, and has an annular diversion cavity therein;

[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 outer duct inlet support plates are circumferentially supported between the outer casing and the inner casing, and contain outer duct cold air inlet ducts; each outer duct cold air inlet duct is connected to the outside of the outer casing through a vent hole, and is connected to the annular diversion cavity through the vent hole;

[0013] Multiple internal air intake duct support plates are circumferentially supported between the inner casing and the inner cone, and contain internal cold air intake ducts; each internal cold air intake duct is connected to the annular diversion cavity through a vent hole, and is connected to the inner cone interlayer through a vent hole;

[0014] 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;

[0015] 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.

[0016] The three-ducted air intake casing is mounted on the rear end of the outer casing, and its front end is tilted downward and connected to the outer wall of the outer casing, forming a three-ducted air intake duct between the outer casing and the outer casing. The front end side wall has multiple three-ducted air intake holes distributed along the circumferential direction.

[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, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, each outer duct inlet support plate is welded to the outer casing and the inner casing.

[0024] 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 upper edge plate and the lower edge plate of each internal inlet duct support plate are clamped in the grooves on the inner casing and the inner cone.

[0025] This application has at least the following beneficial technical effects:

[0026] Provided is a device for simulating and measuring the inlet flow field of a three-ducted afterburner test chamber of an aircraft engine. In specific applications, the outer casing, inner casing, inner cone, and rear end of the three-ducted air intake casing can be connected to the afterburner test piece, inner air is introduced into the inner duct of the afterburner through the inner air intake duct, outer air is introduced into the afterburner through the outer air intake duct, and three-ducted air is introduced into the three-ducted through the three-ducted air intake hole. In this way, the inlet flow field of the afterburner can be simulated, and the outer air intake flow can be used to simulate the inlet flow field of the afterburner. The temperature, pressure and other measuring points are arranged on the field measurement support rod and the inner intake flow field measurement support rod to measure the temperature and pressure of the inner air inlet duct and the outer air inlet duct. In addition, cold air can be introduced into the inner cone interlayer through the outer cold air inlet duct through the annular diversion cavity and the inner cold air inlet duct. The cold air can be discharged from the air film holes on the inner cone, thereby protecting the inner cone from being eroded by high-temperature inner air, and can cool the inner casing and the inner air inlet duct support plate along the way to protect the inner casing and the inner air inlet duct support plate from being eroded by high-temperature inner air. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 Schematic 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;

[0028] Figure 2 yes Figure 1 AA sectional view;

[0029] Figure 3 yes Figure 1 BB cross-sectional view;

[0030] in:

[0031] 1-outer casing; 2-inner casing; 3-inner cone; 4-outer intake duct support plate; 5-inner intake duct support plate; 6-outer intake flow field measurement support rod; 7-inner intake flow field measurement support rod; 8-three-duct intake casing; 9-positioning block; 10-positioning boss; 11-baffle.

[0032] 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

[0033] 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.

[0034] 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.

[0035] 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.

[0036] The following is combined with Figures 1 to 3 This application is described in further detail.

[0037] 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:

[0038] Outer receiver 1;

[0039] The inner casing 2 is arranged inside the outer casing 1, and forms an outer air inlet duct with the outer casing 1, and has an annular diversion cavity therein;

[0040] The inner cone 3 is arranged in the inner casing 2, and forms 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;

[0041] Multiple outer duct inlet support plates 4 are supported circumferentially between the outer casing 1 and the inner casing 2, and have outer duct cold air inlet ducts therein; each outer duct cold air inlet duct is connected to the outside of the outer casing 1 through a vent hole, and is connected to the annular diversion cavity through the vent hole;

[0042] Multiple internal air intake support plates 5 are circumferentially supported between the inner casing 2 and the inner cone 3 and can be used as a rectifying blade cascade. Each internal air intake duct is connected to the annular diverter cavity through a vent hole and is connected to the inner layer of the inner cone 3 through a vent hole.

[0043] Multiple outer duct 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 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;

[0044] Multiple internal intake air flow field measurement struts 7 are circumferentially connected to the outer casing 1 by bolts through a 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;

[0045] The three-duct air intake casing 8 is mounted on the rear end of the outer casing 1, and its front end is tilted downward and connected to the outer wall of the outer casing 1, forming a three-duct air intake duct between the outer casing 1 and the front end side wall thereof. There are multiple three-duct air intake holes distributed along the circumferential direction.

[0046] For the aero-engine three-duct afterburner test inlet flow field simulation and measurement device disclosed in the above embodiment, in specific application, the outer casing 1, the inner casing 2, the inner cone 3, and the rear end of the three-duct air intake casing 8 can be connected to the afterburner test piece, and the inner air is introduced into the inner duct of the afterburner through the inner air intake duct, the outer air is introduced into the afterburner through the outer air intake duct, and the three-duct air is introduced into the three-duct through the three-duct air intake hole. In this way, the afterburner inlet flow field can be simulated, and the outer air intake flow can be used. The temperature, pressure and other measuring points arranged on the field measurement support rod 6 and the inner intake flow field measurement support rod 7 are used to measure the temperature and pressure of the inner air inlet duct and the outer air inlet duct. In addition, cold air can be introduced into the interlayer of the inner cone 3 through the outer cold air inlet duct via the annular diversion cavity and the inner cold air inlet duct. The cold air can be discharged from the air film holes on the inner cone 3, thereby protecting the inner cone 3 from being eroded by high-temperature inner air, and can cool the inner casing 2 and the inner air inlet duct support plate 5 along the way to protect the inner casing 2 and the inner air inlet duct support plate 5 from being eroded by high-temperature inner air.

[0047] The above-mentioned embodiment discloses a three-duct afterburner test inlet flow field simulation and measurement device for an aircraft engine. In the device, cold air is designed to pass through the outer duct cold air inlet on each outer duct support plate 4 into the annular diverter cavity on the inner casing 2. After being diverted by the annular diverter cavity, the cold air passes through the inner duct cold air inlet on each inner duct support plate 5 into the interlayer of the inner cone 3, and is finally discharged from the air film holes on the inner cone 3. On the one hand, the cold air can be used to cool the inner casing 2 and the inner duct support plate 5 along the way to protect the inner casing 2 and the inner duct support plate 5 from being eroded by high-temperature inner air. On the other hand, the cold air can be diverted multiple times to increase the turbulence of the cold air, so that the cold air entering the interlayer of the inner cone 3 is evenly distributed in the circumferential direction, thereby ensuring the cooling effect on the inner cone 3.

[0048] The above-mentioned embodiment discloses an aircraft engine three-duct afterburner test inlet flow field simulation and measurement device, and designs a three-duct air intake casing 8 to be mounted on the rear end of the outer casing 1, and designs a three-duct air intake casing 8 to be tilted downward and connected to the outer wall of the outer casing 1 at the front end, thereby forming a three-duct air intake duct between the outer casing 1, and the three-duct air intake holes on the three-duct air intake casing 8 are located on the front end side wall thereof, and three-duct air is introduced into the three-duct air intake duct through the three-duct air intake holes. Under the effect of the tilt of the front end of the three-duct air intake casing 8, when it flows backward and enters the three-duct of the afterburner test piece, expansion pressure will occur, so that it can achieve uniform distribution within a short distance, well simulate the afterburner inlet flow field, and the overall structure is simple and compact.

[0049] 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.

[0050] 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;

[0051] The aero-engine three-duct afterburner test inlet flow field simulation measurement device further includes:

[0052] 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;

[0053] A plurality of positioning bosses 10 are provided in each positioning hole and inserted into each positioning groove;

[0054] 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 3 As shown, in order to facilitate assembly and ensure the stability of the overall structure.

[0055] In some optional embodiments, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, each outer duct inlet support plate 4 is welded to the outer casing 1 and the inner casing 2.

[0056] In some optional embodiments, in the above-mentioned aircraft engine three-duct afterburner test inlet flow field simulation measurement device, the upper edge plate and the lower edge plate of each inner inlet support plate 5 are clamped in the grooves on the inner casing 2 and the inner cone 3.

[0057] 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.

[0058] 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); An inner casing (2) is arranged inside the outer casing (1) and forms an outer air inlet duct with the outer casing (1), wherein the inner casing has an annular diversion cavity; 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 outer duct inlet support plates (4) are supported circumferentially between the outer casing (1) and the inner casing (2), and have outer duct cold air inlet ducts therein; each outer duct cold air inlet duct is connected to the outside of the outer casing (1) through a vent hole, and is connected to the annular diversion cavity through the vent hole; A plurality of internal air intake duct support plates (5) are supported circumferentially between the inner casing (2) and the inner cone (3), and have internal cold air intake ducts therein; each internal cold air intake duct is connected to the annular diversion cavity through a vent hole, and is connected to the inner layer of the inner cone (3) through a vent hole; A plurality of outer duct intake air flow field measurement struts (6) 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 (7) 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 (8) is sleeved on the rear end of the outer casing (1), and its front end is tilted downward and connected to the outer wall of the outer casing (1), forming a three-duct air intake duct between the outer casing (1), and a plurality of three-duct air intake holes distributed along the circumferential direction are provided on the front end side wall.

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: Each outer duct inlet support plate (4) is welded to the outer casing (1) and the inner casing (2).

5. The aircraft engine three-duct afterburner test inlet flow field simulation measurement device according to claim 1, characterized in that: The upper edge plate and the lower edge plate of each internal air inlet support plate (5) are clamped in the clamping grooves on the inner casing (2) and the inner cone (3).

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