Aero-engine afterburner with active cooling function

Abstract

The invention belongs to the technical field of aero-engine afterburner design, and particularly relates to an aero-engine afterburner with an active cooling function, when the aero-engine afterburner works, a cooling medium in a cooling medium storage tank can enter each cooling spray rod through an annular header pipe, and is sprayed into each support plate and an inner cone thereof through cooling nozzles on the cooling spray rods; the high-temperature fuel gas is exhausted through the cooling exhaust holes formed in the side walls of the supporting plate and the inner cone of the supporting plate, the supporting plate, the inner cone of the supporting plate and the high-temperature fuel gas are efficiently cooled, an afterburner is actively cooled, the backward radiation characteristic of an aero-engine can be greatly reduced within a short time by controlling the flow of the cooling medium, and the use scene of an aircraft is expanded.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine afterburner chamber design, and specifically relates to an aircraft engine afterburner chamber with an active cooling function. Background Art

[0002] The afterburner of an aircraft engine is the main source of backward radiation of the aircraft engine.

[0003] Currently, by-pass air is mainly used to cool the afterburner of an aircraft engine to suppress the backward radiation characteristics of the aircraft engine. However, this technical solution is limited by the flow rate of by-pass air, has limited cooling capacity for the afterburner of an aircraft engine, and does not have the ability to significantly reduce the backward radiation characteristics of an aircraft engine in a short period of time, which limits the use of aircraft in certain situations where efficient suppression of backward radiation characteristics is required.

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

[0005] The purpose of the present application is to provide an aircraft engine afterburner with an active cooling function to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] An aeroengine afterburner combustion chamber with active cooling function, comprising an outer casing, a confluence ring, an inner cone, a support plate, a radial flame stabilizer, an afterburner fuel supply pipe, an afterburner fuel supply spray rod, an annular anti-vibration heat insulation screen, an annular main pipe, a cooling spray rod, and a cooling medium storage tank;

[0008] The confluence ring is arranged in the outer casing, and forms an outer duct with the outer casing;

[0009] The inner cone is arranged in the confluence ring, and the side wall has a plurality of cooling exhaust holes, forming an inner channel between the inner cone and the confluence ring;

[0010] There are multiple support plates, which are supported between the confluence ring and the inner cone in the circumferential direction, and the side walls have multiple cooling exhaust holes, and the trailing edge is provided with a radial flame stabilizer;

[0011] The afterburner fuel supply pipe is annular, sleeved on the outer periphery of the outer casing, and connected to the fuel source through a pipeline;

[0012] There are multiple afterburner fuel supply spray rods, the top end of which is connected to the afterburner fuel supply pipe, and the end thereof passes through the outer casing and the confluence ring and extends into each radial flame stabilizer. The portion in the radial flame stabilizer is provided with a fuel nozzle;

[0013] An annular anti-vibration heat-insulating screen is arranged in the rear end of the outer casing and has a plurality of cooling exhaust holes thereon;

[0014] The annular main pipe sleeve is arranged on the outer periphery of the outer casing and is connected to the cooling medium storage tank through pipelines;

[0015] There are multiple cooling spray rods, the top ends of which are connected to the annular main pipe, and the tail ends pass through the outer casing, the confluence ring, and each support plate, and extend into the inner cone. Cooling nozzles are arranged in the support plates and the inner cone.

[0016] According to at least one embodiment of the present application, in the above-mentioned aircraft engine afterburner with active cooling function, the confluence ring gradually expands outward.

[0017] According to at least one embodiment of the present application, in the above-mentioned aircraft engine afterburner with active cooling function, an annular flame transfer groove is provided at the trailing edge of each radial flame stabilizer.

[0018] According to at least one embodiment of the present application, in the above-mentioned aircraft engine afterburner combustion chamber with active cooling function, there are two groups of afterburner fuel supply pipes and afterburner fuel supply nozzles, which are distributed front and back along the axial direction.

[0019] According to at least one embodiment of the present application, in the above-mentioned aircraft engine afterburner with active cooling function, the merging ring and the outer casing are supported along the circumferential direction by multiple tie rods.

[0020] According to at least one embodiment of the present application, in the above-mentioned aircraft engine afterburner with active cooling function, the cooling medium in the cooling medium storage tank is high-pressure, low-temperature gas or high-pressure, low-temperature water.

[0021] This application has at least the following beneficial technical effects:

[0022] Provided is an aircraft engine afterburner combustion chamber with an active cooling function. When in operation, the cooling medium in the cooling medium storage tank can enter each cooling spray rod through an annular main pipe, be sprayed into each support plate and its inner cone by the cooling nozzle on the cooling spray rod, and be discharged through the cooling exhaust holes arranged on the side walls of the support plate and its inner cone, so as to efficiently cool the support plate and its inner cone as well as the high-temperature combustion gas, actively cool the afterburner combustion chamber, and can significantly reduce the backward radiation characteristics of the aircraft engine in a short time by controlling the flow rate of the cooling medium, thereby expanding the use scenarios of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic diagram of an aircraft engine afterburner with active cooling function provided in an embodiment of the present application;

[0024] in:

[0025] 1-outer casing; 2-merging ring; 3-inner cone; 4-support plate; 5-radial flame stabilizer; 6-annular flame transfer groove; 7-fuel supply pipe; 8-fuel supply spray rod; 9-pull rod; 10-annular anti-vibration heat insulation screen; 11-annular main pipe; 12-cooling spray rod; 13-cooling medium storage tank.

[0026] In order to better illustrate the present 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 construed as limitations on the present application. DETAILED DESCRIPTION

[0027] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience 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.

[0028] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application indicates that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0029] In addition, it should be noted that, unless otherwise clearly specified and limited, the words "installation", "connection" 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 or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0030] An aircraft engine afterburner with active cooling function, such as Figure 1 As shown, it includes an outer casing 1, a confluence ring 2, an inner cone 3, a support plate 4, a radial flame stabilizer 5, an annular flame transfer groove 6, a booster oil supply pipe 7, a booster oil supply spray rod 8, a pull rod 9, an annular anti-vibration and heat insulation screen 10, an annular main pipe 11, a cooling spray rod 12, and a cooling medium storage tank 13.

[0031] The merging ring 2 is arranged in the outer casing 1, and forms an outer duct with the outer casing 1, and the merging ring 2 gradually expands outwards.

[0032] The inner cone 3 is arranged in the merging ring 2, and the side wall has a plurality of cooling exhaust holes, forming an inner channel between the inner cone 3 and the merging ring 2.

[0033] There are multiple support plates 4, which are supported between the confluence ring 2 and the inner cone 3 in the circumferential direction, and the side walls have multiple cooling exhaust holes, and the trailing edges are provided with radial flame stabilizers 5. The trailing edges of each radial flame stabilizer 5 are provided with an annular flame transfer groove 6.

[0034] The booster fuel supply pipe 7 is annular, sleeved on the outer periphery of the outer casing 1, and connected to the fuel source through a pipeline.

[0035] There are multiple afterburner fuel spray rods 8, the top ends of which are connected to the afterburner fuel pipes 7, and the tail ends pass through the outer casing 1 and the confluence ring 2 and extend into each radial flame stabilizer 5. The part in the radial flame stabilizer 5 is provided with a fuel nozzle.

[0036] There are two groups of booster oil supply pipes 7 and booster oil supply spray rods 8, which are distributed front and back along the axial direction.

[0037] There are multiple tie rods 9 connected between the merging ring 2 and the outer casing 1 along the circumferential direction to support the merging ring 2 .

[0038] The annular anti-vibration and heat-insulating shield 10 is arranged in the rear end of the outer casing 1 and has a plurality of cooling exhaust holes thereon.

[0039] The annular main pipe 11 is sleeved on the outer periphery of the outer casing 1 and is connected to a cooling medium storage tank 13 through a pipeline. The cooling medium in the cooling medium storage tank 13 is high-pressure low-temperature gas or high-pressure low-temperature water.

[0040] There are multiple cooling spray bars 12, the top ends of which are connected to the annular main pipe 11, and the tail ends pass through the outer casing 1, the confluence ring 2, and each support plate 4, and extend into the inner cone 3. Cooling nozzles are arranged at the positions between the support plates 4 and the inner cone 3.

[0041] In the aircraft engine afterburner with active cooling function disclosed in the above-mentioned embodiment, when working, the outer duct air from the outer duct and the inner duct air from the inner duct will be mixed at the tail end of the merging ring 2, and a recirculation zone will be formed in each radial flame stabilizer 5, and the fuel can enter each afterburner fuel supply nozzle 8 through the afterburner fuel supply pipe 7, and be sprayed into each radial flame stabilizer 5 by the fuel nozzle on the afterburner fuel supply nozzle 8, and then diffuse into the recirculation zone for ignition and combustion, and the annular flame transfer groove 6 is used to transfer the flame in the circumferential direction to organize the combustion. At the same time, the outer duct air will partially flow into the flow channel formed between the outer casing 1 and the annular anti-vibration and heat insulation shield 10, and partially be discharged through the cooling exhaust holes on the annular anti-vibration and heat insulation shield 10, which can reduce the temperature of the high-temperature combustion gas in the afterburner and suppress backward radiation.

[0042] The aero-engine afterburner with active cooling function disclosed in the above embodiment, when working, the cooling medium in the cooling medium storage tank 13 can enter each cooling spray rod 12 through the annular main pipe 11, and be sprayed into each support plate 4 and its inner cone 3 by the cooling nozzle on the cooling spray rod 12, and discharged through the cooling exhaust holes set on the side walls of the support plate 4 and its inner cone 3, so as to efficiently cool the support plate 4 and its inner cone 3 and the high-temperature combustion gas, and actively cool the afterburner, and can significantly reduce the backward radiation characteristics of the aero-engine in a short time by controlling the flow rate of the cooling medium, thereby expanding the use scenarios of the aircraft. The control of the flow rate of the cooling medium can be achieved by setting a flow regulating valve on the corresponding pipeline.

[0043] In the afterburner combustion chamber of the aircraft engine with active cooling function disclosed in the above-mentioned embodiment, the cooling nozzle rod 12 is designed to be located in front of the afterburner fuel supply nozzle rod 8, and the merging ring 2 is designed to gradually expand outward, so that the inner channel formed between the inner cone 3 can become a larger diffusion flow path, and the medium discharged from the cooling exhaust holes arranged on the support plate 4 and the side wall of the inner cone 3 enters the inner channel and diffuses to a large extent along the way, thereby increasing the uniformity of the cooling medium at the rear end of the merging ring 2, thereby ensuring uniform cooling of the high-temperature combustion gas over a large range, and can effectively reduce the backward radiation characteristics of the aircraft engine.

[0044] 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 substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. An aircraft engine afterburner with active cooling function, characterized in that: It comprises an outer casing (1), a confluence ring (2), an inner cone (3), a support plate (4), a radial flame stabilizer (5), an afterburner oil supply pipe (7), an afterburner oil supply spray rod (8), an annular anti-vibration heat insulation screen (10), an annular main pipe (11), a cooling spray rod (12), and a cooling medium storage tank (13); The merging ring (2) is arranged inside the outer casing (1) and forms an outer duct with the outer casing (1); The inner cone (3) is arranged inside the merging ring (2), and has a plurality of cooling exhaust holes on its side wall, forming an inner channel between the inner cone and the merging ring (2); There are a plurality of support plates (4), which are supported between the confluence ring (2) and the inner cone (3) in the circumferential direction, and the side walls are provided with a plurality of cooling exhaust holes, and a radial flame stabilizer (5) is arranged at the trailing edge; The afterburner fuel supply pipe (7) is annular, sleeved on the outer circumference of the outer casing (1), and connected to the fuel source through a pipeline; There are a plurality of booster fuel supply spray rods (8), the top ends of which are connected to the booster fuel supply pipes (7), and the tail ends of which pass through the outer casing (1) and the confluence ring (2) and extend into each radial flame stabilizer (5), and the portion in the radial flame stabilizer (5) is provided with a fuel nozzle; An annular anti-vibration heat-insulating shield (10) is arranged inside the rear end of the outer casing (1) and has a plurality of cooling exhaust holes thereon; The annular main pipe (11) is sleeved on the outer periphery of the outer casing (1) and is connected to the cooling medium storage tank (13) through a pipeline; There are a plurality of cooling spray rods (12), the top ends of which are connected to the annular main pipe (11), and the tail ends of which pass through the outer casing (1), the confluence ring (2), and each support plate (4), and extend into the inner cone (3). Cooling nozzles are arranged at the positions between the support plates (4) and the inner cone (3).

2. The aircraft engine afterburner with active cooling function according to claim 1, characterized in that: The confluence ring (2) gradually expands outwards.

3. The aircraft engine afterburner with active cooling function according to claim 2, characterized in that: An annular flame transfer groove (6) is arranged at the rear edge of each radial flame stabilizer (5).

4. The aircraft engine afterburner with active cooling function according to claim 3, characterized in that: There are two groups of booster oil supply pipes (7) and booster oil supply spray rods (8), which are distributed front and back along the axial direction.

5. The aircraft engine afterburner with active cooling function according to claim 4, characterized in that: A plurality of tie rods (9) are used to support the merging ring (2) and the outer casing (1) along the circumferential direction.

6. The aircraft engine afterburner with active cooling function according to claim 5, characterized in that: The cooling medium in the cooling medium storage tank (13) is high-pressure low-temperature gas or high-pressure low-temperature water.

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