A cooling structure for the afterburner of an aircraft engine turbine

Abstract

The present application belongs to the technical field of aircraft engine cooling design, and specifically relates to an aircraft engine turbine after-combustion chamber cooling structure, which can introduce cooling gas from a cooling gas source through an inlet pipe nozzle through a pipeline from a four-way pipe joint to a main pipe, and the cooling gas flows to each section of the main pipe through each pipe joint, and then flows out from the outlet end of each pipe joint, passes through an adapter and an adapter tube, enters each spray rod, and is sprayed into the combustion chamber support plate and inner cone through a nozzle or a nozzle, and is discharged through the cooling exhaust holes provided on the side walls of the support plate and the inner cone, so as to efficiently cool the support plate, inner cone and inner duct high-temperature combustion gas of the combustion chamber, and can significantly reduce the rearward radiation characteristics of the aircraft engine in a short time by controlling the flow rate of the cooling gas, thereby expanding the use scenarios of the aircraft.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft engine cooling design, and specifically relates to an aircraft engine turbine after-combustion chamber cooling structure. Background Art

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

[0003] Currently, by-pass air is mainly used to cool the after-combustion chamber of aircraft engine turbines to suppress the backward radiation characteristics of aircraft engines. However, this technical solution is limited by the flow rate of by-pass air, has limited cooling capacity for the after-combustion chamber of aircraft engine turbines, and does not have the ability to significantly reduce the backward radiation characteristics of aircraft engines 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 turbine post-combustion chamber cooling structure to overcome or alleviate at least one of the known technical deficiencies.

[0006] The technical solution of this application is:

[0007] An aircraft engine turbine afterburner cooling structure comprises a main pipe and a spray bar assembly;

[0008] The main pipe is bent at both ends, wrapped around the outer casing, and divided into multiple sections;

[0009] Pipe joints are arranged at both ends of the main pipe and between each section, wherein the pipe joints at both ends of the main pipe are right-angle pipe joints, one pipe joint between two sections of the main pipe is a four-way pipe joint, and the remaining pipe joints are three-way pipe joints;

[0010] The inlet end of the right-angle pipe joint is connected to the main pipe;

[0011] The four-way pipe joint is located in the middle of the main pipe, the two flow ends of the four-way pipe joint are connected between the corresponding two sections of the main pipe, the inlet end is connected with an inlet pipe nozzle, and the inlet pipe nozzle is connected to the cooling air source through a pipeline;

[0012] The two flow ends of the three-way pipe joint are connected between the corresponding two sections of the main pipe;

[0013] Each pipe joint outlet end is provided with a pressure cap, and an annular pin is provided between the pressure cap and the pipe joint outlet end, and the annular pin can limit the axial movement of the pressure cap relative to the pipe joint outlet end, and the pressure cap can rotate circumferentially relative to the pipe joint outlet end;

[0014] The spray bar assembly has a number corresponding to the number of pipe joints, including an adapter, an adapter tube, and a spray bar;

[0015] The adapter is connected to the inlet end of the adapter tube, and the adapter is connected to the pressure cap through threads. After the pressure cap is tightened, the adapter is butt-jointed with the outlet end of the pipe joint;

[0016] The top of the spray rod is connected to the outlet end of the transfer tube, and the end passes through the outer casing and the confluence ring of the combustion chamber and extends into the inner cone; the spray rod is provided with multiple nozzles or nozzles in the inner channel of the combustion chamber and the inner cone, and multiple cooling exhaust holes are provided on the side wall of the inner cone.

[0017] Optionally, in the above-mentioned aircraft engine turbine after-combustion chamber cooling structure, the main pipe is a metal hose.

[0018] Optionally, in the above-mentioned aircraft engine turbine after-combustion chamber cooling structure, the adapter and the pipe joint outlet end are matched through the ball head cone surface.

[0019] Optionally, in the above-mentioned aircraft engine turbine after-combustion chamber cooling structure, the cross-section of the spray rod is elliptical.

[0020] Optionally, in the above-mentioned cooling structure for the turbine afterburner of the aircraft engine, a spray rod is arranged through the support plate, and a plurality of cooling exhaust holes are arranged on the side wall of the support plate.

[0021] Optionally, in the above-mentioned aircraft engine turbine after-combustion chamber cooling structure, the spray rod is curved.

[0022] Optionally, in the above-mentioned aircraft engine turbine afterburner cooling structure, the spray bar assembly further includes a mounting plate;

[0023] The mounting plate is sleeved on the transfer tube and connected to the outer casing of the combustion chamber.

[0024] Optionally, in the above-mentioned aircraft engine turbine afterburner cooling structure, the spray bar assembly further includes a positioning block;

[0025] The positioning block is sleeved on the end of the spray rod and is arranged in the positioning hole opened on the inner cone wall surface, and is clearance-matched with the positioning hole.

[0026] This application has at least the following beneficial technical effects:

[0027] Provided is a cooling structure for an aircraft engine turbine afterburner chamber, in which cooling air can be introduced from a cooling air source through an inlet pipe nozzle through a pipeline from a four-way pipe joint to a main pipe, the cooling air flows through each pipe joint to each section of the main pipe, and then flows out from the outlet end of each pipe joint, passes through an adapter and an adapter pipe, enters each spray rod, is sprayed into a combustion chamber support plate and an inner cone through a nozzle or a nozzle, and is discharged through cooling exhaust holes provided on the support plate and the side wall of the inner cone, so as to efficiently cool the support plate, the inner cone and the inner duct high-temperature combustion gas of the combustion chamber, and can significantly reduce the rearward radiation characteristics of the aircraft engine in a short time by controlling the flow rate of the cooling air, thereby expanding the use scenarios of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 It is a working schematic diagram of the cooling structure of the after-combustion chamber of the aircraft engine turbine provided by an embodiment of the present application;

[0029] Figure 2 is a schematic diagram of a cooling structure for a turbine post-combustion chamber of an aircraft engine provided in an embodiment of the present application;

[0030] Figure 3 is a schematic diagram of a main pipe provided in an embodiment of the present application;

[0031] Figure 4 It is a schematic diagram of the outlet end of the pipe joint, the pressure cap, and the annular pin provided in the embodiment of the present application;

[0032] Figure 5 is a schematic diagram of a spray bar assembly provided in an embodiment of the present application;

[0033] Figure 6 is a schematic diagram of a cross section of a spray bar provided in an embodiment of the present application;

[0034] Figure 7 It is a schematic diagram of the cooperation between the spray bar, the positioning block and the inner cone provided in the embodiment of the present application;

[0035] in:

[0036] 1-outer casing; 2-merging ring; 3-support plate; 4-inner cone; 5-main pipe; 6-spray rod assembly; 7-right-angle pipe joint; 8-four-way pipe joint; 9-tee pipe joint; 10-inlet pipe nozzle; 11-pressure cap; 12-ring pin; 13-adapter tube; 14-spray rod; 15-positioning block; 16-mounting plate; 17-adapter.

[0037] 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

[0038] 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.

[0039] 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.

[0040] 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.

[0041] Aircraft engine turbine afterburner, such as Figure 1 As shown, it mainly includes an outer casing 1, a merging ring 2, a support plate 3, and an inner cone 4, wherein the merging ring 2 is arranged in the outer casing 1, and forms an outer duct between the outer casing 1; the inner cone 4 is arranged in the merging ring 2, and forms an inner duct between the merging ring 2; there are multiple support plates 3, which are supported circumferentially between the merging ring 2 and the inner cone 4, and a stabilizer can be set at the trailing edge of each support plate 4.

[0042] Based on the structure of the existing aircraft engine turbine afterburner, the present application provides an aircraft engine turbine afterburner cooling structure, such as Figure 2 As shown, it includes a main pipe 5 and a spray rod assembly 6.

[0043] The main pipe 5 is a metal hose with two bent ends, surrounding the outer circumference of the outer casing 1 and divided into multiple sections.

[0044] Pipe joints are provided at both ends of the main pipe 5 and between each section, wherein the pipe joints at both ends of the main pipe 5 are right-angle pipe joints 7, a pipe joint between two sections of the main pipe 5 is a four-way pipe joint 8, and the remaining pipe joints are three-way pipe joints 9. Figure 3 shown.

[0045] The inlet end of the right-angle pipe joint 7 is welded to the main pipe 5 .

[0046] The four-way pipe joint 8 is located in the middle of the main pipe 5. The two flow ends of the four-way pipe joint 8 are welded between the corresponding two sections of the main pipe 5. The inlet end is welded with an inlet pipe nozzle 10, and the inlet pipe nozzle 10 is connected to the cooling air source through a pipeline.

[0047] The two flow ends of the three-way pipe joint 9 are welded between the corresponding two sections of the main pipe 5.

[0048] Each pipe joint includes two right-angle pipe joints 7, a four-way pipe joint 8, and a plurality of three-way pipe joints 9. A pressure cap 11 is provided on the outer sleeve of the outlet end. An annular pin 12 is provided between the pressure cap 11 and the outlet end of the pipe joint. The annular pin 12 can limit the axial movement of the pressure cap 11 relative to the outlet end of the pipe joint, but does not limit the circumferential rotation of the pressure cap 11 relative to the outlet end of the pipe joint. Figure 4 As shown, to facilitate structural assembly.

[0049] The spray bar assembly 6 has a plurality of pipe joints corresponding to the number of pipe joints, including an adapter 17, an adapter tube 13, a spray bar 14, a positioning block 15, and a mounting plate 16. Figure 5 shown.

[0050] The adapter 17 is welded to the inlet end of the adapter tube 13, and the adapter 17 is connected to the pressure cap 11 through a threaded connection. After the pressure cap 11 is tightened, the adapter 17 is docked with the outlet end of the pipe joint. The adapter 17 and the outlet end of the pipe joint can be matched through the ball head cone surface to ensure the sealing effect.

[0051] The top of the spray rod 14 is welded to the outlet end of the transfer tube 13, and is distributed at approximately 90 degrees with the transfer tube 13. The end passes through the outer casing 1 and the confluence ring 2 of the combustion chamber and extends into the inner cone 4. The spray rod 14 is provided with multiple nozzles or nozzles in the inner channel of the combustion chamber and the inner cone 4, and multiple cooling exhaust holes are provided on the side wall of the inner cone 4. In order to ensure the strength of the spray rod 14, the cross section of the spray rod 14 can be set to be elliptical, such as Figure 6 In order to ensure efficient cooling of the support plate 3 , a spray bar 14 may be provided to penetrate the support plate 3 , and a plurality of cooling exhaust holes may be provided on the side wall of the support plate 3 .

[0052] The mounting plate 16 is sleeved on the transfer tube 13 and can be welded to the transfer tube 13 . The mounting plate 16 can be connected to the outer casing 1 of the combustion chamber by bolts.

[0053] The positioning block 15 is sleeved on the end of the spray rod 14 and is set in the positioning hole opened on the wall of the inner cone 4. The positioning block 15 is matched with the clearance between the positioning holes so that a small range of movement can be performed in the positioning holes. Figure 7As shown, the outer casing 1, the confluence ring 2 and the inner cone 4 of the combustion chamber are adapted to the uncoordinated deformation. The spray bar 14 can be further designed to be curved to have a larger deformation margin to adapt to the uncoordinated deformation of the outer casing 1, the confluence ring 2 and the inner cone 4 of the combustion chamber.

[0054] The cooling structure of the afterburner of the aircraft engine turbine disclosed in the above-mentioned embodiment can connect the pipeline through the inlet pipe nozzle 10, and the cooling gas is introduced from the cooling gas source to the main pipe 5 through the four-way pipe joint 8. The cooling gas flows to each section of the main pipe 5 through each three-way pipe joint 9, and then flows out from the outlet end of each pipe joint, passes through the adapter 17 and the adapter pipe 13, enters each spray rod 14, and is sprayed into the combustion chamber support plate 3 and the inner cone 4 through the nozzle or nozzle, and is discharged through the cooling exhaust holes provided on the side walls of the support plate 3 and the inner cone 4, so as to efficiently cool the support plate 3, the inner cone 4 and the high-temperature combustion gas in the inner duct of the 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 gas, thereby expanding the use scenarios of the aircraft.

[0055] In addition, the cooling structure of the aero-engine turbine post-combustion chamber disclosed in the above-mentioned embodiment does not change the structural frame of the existing combustion chamber, and adopts an external mounting installation, which is easy to implement.

[0056] 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 turbine afterburner cooling structure, characterized in that: It comprises a main pipe (5) and a spray bar assembly (6); The main pipe (5) is bent at both ends, surrounds the outer circumference of the outer casing (1), and is divided into multiple sections; Pipe joints are provided at both ends of the main pipe (5) and between each section, wherein the pipe joints at both ends of the main pipe (5) are right-angle pipe joints (7), one pipe joint between two sections of the main pipe (5) is a four-way pipe joint (8), and the remaining pipe joints are three-way pipe joints (9); The inlet end of the right-angle pipe joint (7) is connected to the main pipe (5); A four-way pipe joint (8) is located in the middle of the main pipe (5), two flow ends of the four-way pipe joint (8) are connected between the corresponding two sections of the main pipe (5), and an inlet end is connected to an inlet pipe nozzle (10), and the inlet pipe nozzle (10) is connected to a cooling air source through a pipeline; The two flow ends of the three-way pipe joint (9) are connected between the corresponding two sections of the main pipe (5); Each pipe joint outlet end is provided with a pressing cap (11) on its outer sleeve, an annular pin (12) is provided between the pressing cap (11) and the pipe joint outlet end, the annular pin (12) can limit the axial movement of the pressing cap (11) relative to the pipe joint outlet end, and the pressing cap (11) can rotate circumferentially relative to the pipe joint outlet end; The spray bar assembly (6) has a plurality of pipe joints corresponding to the number of pipe joints, including an adapter (17), an adapter pipe (13), and a spray bar (14); The adapter (17) is connected to the inlet end of the adapter tube (13), and the adapter (17) and the pressure cap (11) are connected by threads. After the pressure cap (11) is tightened, the adapter (17) is butt-jointed with the outlet end of the pipe joint; The top end of the spray rod (14) is connected to the outlet end of the transfer tube (13), and the end thereof passes through the outer casing (1) and the confluence ring (2) of the combustion chamber and extends into the inner cone (4); a plurality of spray ports or nozzles are arranged at the spray rod (14) in the inner channel of the combustion chamber and in the inner cone (4), and a plurality of cooling exhaust holes are arranged on the side wall of the inner cone (4).

2. The cooling structure of the aero-engine turbine after-combustion chamber according to claim 1, characterized in that: The main pipe (5) is a metal hose.

3. The cooling structure of the turbine afterburner of an aircraft engine according to claim 2, characterized in that: The adapter (17) is matched with the outlet end of the pipe joint through the ball head cone surface.

4. The cooling structure for the turbine afterburner of an aircraft engine according to claim 3, characterized in that: The cross section of the spray bar (14) is elliptical.

5. The cooling structure for the afterburner of a turbine of an aircraft engine according to claim 4, characterized in that: The spray bar (14) is arranged to penetrate the support plate (3), and a plurality of cooling exhaust holes are arranged on the side wall of the support plate (3).

6. The cooling structure for the afterburner of a turbine of an aircraft engine according to claim 5, characterized in that: The spray bar (14) is in a curved shape.

7. The cooling structure for the afterburner of a turbine of an aircraft engine according to claim 6, characterized in that: The spray bar assembly (6) further includes a mounting plate (16); The mounting plate (16) is sleeved on the transfer tube (13) and connected to the outer casing (1) of the combustion chamber.

8. The cooling structure for the afterburner of a turbine of an aircraft engine according to claim 7, characterized in that: The spray bar assembly (6) further comprises a positioning block (15); The positioning block (15) is sleeved on the end of the spray rod (14) and is arranged in a positioning hole opened on the wall surface of the inner cone (4), with a clearance fit between the positioning hole and the positioning hole.

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