A highly cooled jet engine

Abstract

The application provides a high-efficiency cooling jet engine, which comprises an inner cone and a cone tip connected with the inner cone; one end of the inner cone is provided with an inner cone front mounting edge, the other end is provided with an inner cone rear mounting edge, one end of the cone tip is provided with a cone tip mounting edge, and the cone tip mounting edge is connected with the inner cone rear mounting edge; an air film ring main body is arranged in the inner cone, one end of the air film ring main body is connected with the inner cone front mounting edge, and the other end is connected with the inner cone rear mounting edge through an air film ring baffle; a nozzle and a cooling cover are sequentially sleeved outside the inner cone, one end of the nozzle is provided with a nozzle front mounting edge, one end of the cooling cover is provided with a cooling cover front mounting edge, and the cooling cover front mounting edge is connected with the nozzle front mounting edge. The application has a double-mode cooling function, an air film ring with a large number of cooling air film holes is further designed in the cone cavity, a remarkable cooling effect can be achieved, the number of parts is small, the structure is simple, the work is reliable, the performance is excellent, the application range is wide, and the practicality is strong.

Description

TECHNICAL FIELD

[0001] The present application relates to a kind of high-efficiency cooling jet engine, belong to the field of aero-engine exhaust device structure design. BACKGROUND

[0002] Simple and reliable structure, high-efficiency enhanced cooling, accurate control wall temperature, more and more stringent requirements are put forward to jet engine exhaust device, especially with the exhaust temperature after turbine higher and higher, the temperature load that the inner cone of exhaust device bears is heavier and heavier, the wall temperature of nozzle is higher and higher, especially in engine core test, inner cone and nozzle directly bear higher temperature gas impact after turbine, the wall temperature of inner cone and nozzle has approached or even exceeded the temperature resistance limit of traditional material, and the temperature resistance ability and structural strength of exhaust device are required extremely.

[0003] Traditional jet engine exhaust device is not designed or only a small amount of cooling function is designed, especially in jet engine core test, traditional exhaust device cannot bear the thermal load generated by high-temperature gas after turbine. SUMMARY

[0004] To solve the above technical problems, the present application provides a kind of high-efficiency cooling jet engine, the high-efficiency cooling jet engine has the cooling function of double-mode cooling function of jet engine exhaust function, and the cooling effect is more excellent, the wall temperature is lower, the structure is simple, and the performance is more excellent.

[0005] The present application is realized by the following technical scheme.

[0006] The present application provides a kind of high-efficiency cooling jet engine, including inner cone and cone tip connected with inner cone;The one end of the inner cone is provided with inner cone front mounting edge, the other end is provided with inner cone rear mounting edge, the one end of cone tip is provided with cone tip mounting edge, and cone tip mounting edge is connected with inner cone rear mounting edge;The inner cone is provided with gas film ring main body, and the one end of gas film ring main body is connected with inner cone front mounting edge, and the other end is connected with inner cone rear mounting edge through gas film ring baffle;The outer surface of the inner cone is sequentially sleeved with nozzle and cooling cover, and the one end of nozzle is provided with nozzle front mounting edge, and the one end of cooling cover is provided with cooling cover front mounting edge, and cooling cover front mounting edge is connected with nozzle front mounting edge;The edge of the cooling cover is provided with a plurality of air inlet pipes, and the port of each air inlet pipe is provided with air inlet pipe plug cover.

[0007] The gap between the inner cone and nozzle is left, forming a gas film passage, and the gap between the cooling cover and nozzle is left, forming a cooling passage interlayer.

[0008] The inner cone, inner cone front mounting edge and inner cone rear mounting edge form the front section of inner cone, and the cone tip and cone tip mounting edge form the rear section of inner cone.

[0009] The inner cone front section and the inner cone rear section are combined into a complete cone.

[0010] The gas film ring body is composed of a gas film ring front mounting edge, a gas film ring, and a gas film ring rear mounting edge connected in sequence, the gas film ring front mounting edge is connected with the inner cone front mounting edge, and the gas film ring rear mounting edge is connected with the inner cone rear mounting edge through the gas film ring baffle.

[0011] A plurality of air inlet pipes are distributed along the central circumference of the cooling cover.

[0012] A plurality of uniformly distributed cooling gas film holes are arranged on the gas film ring, and a plurality of uniformly distributed exhaust holes are arranged on the cone tip.

[0013] The cooling cover front mounting edge and the nozzle front mounting edge are provided with a baffle ring, and a gap is left between the baffle ring and the cooling cover and the nozzle.

[0014] The nozzle front mounting edge is provided with an air passage hole in the circumferential direction.

[0015] The gas film ring and the cone form an annular cooling channel.

[0016] The beneficial effects of the present application are as follows: the double-mode cooling function is provided, when the temperature behind the turbine is low, the additional cooling gas is not connected, only the outer-duct air flow is introduced to cool the nozzle, the nozzle is cooled by the outer-duct air flow, when the temperature behind the turbine is high, the additional cooling gas is connected, in addition to the introduction of the outer-duct cooling gas, the additional cooling gas is introduced into the stand, the cabin or other additional cooling gas through the air inlet pipe, and the nozzle is further cooled after mixing with the outer-duct cooling gas; a gas film ring with a large number of cooling gas film holes is designed in the cone cavity, the cooling gas from the turbine support is introduced into the gas film ring and impacts the cooling cone through the gas film holes, so that the high-temperature cone is cooled; the cooling effect is remarkable, the number of parts is small, the structure is simple, the work is reliable, the performance is excellent, the application range is wide, and the practicality is strong. BRIEF DESCRIPTION OF DRAWINGS

[0017] Figure 1 is a structural schematic diagram of the present application;

[0018] Figure 2 is Figure 1 a sectional view of the present application;

[0019] Figure 3 is Figure 2 an enlarged view of A in the present application;

[0020] Figure 4 is Figure 2 an enlarged view of B in the present application;

[0021] Figure 5 is Figure 2 an enlarged view of C in the present application;

[0022] Figure 6This is the cooling principle flow path when the intake pipe is not open;

[0023] Figure 7 This is the cooling principle flow path when the intake pipe is open;

[0024] In the diagram: 1-front mounting edge of cooling shroud, 2-intake pipe plug, 3-intake pipe, 4-baffle ring, 5-front mounting edge of nozzle, 6-cooling shroud, 7-nozzle, 8-inner cone, 9-cone tip, 10-front mounting edge of inner cone, 11-front mounting edge of film gas ring, 12-film gas ring, 13-film gas ring baffle, 14-rear mounting edge of film gas ring, 15-rear mounting edge of inner cone, 16-cone tip mounting edge. Detailed Implementation

[0025] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0026] Example 1

[0027] like Figures 1 to 5 The illustrated high-efficiency cooled jet engine includes an inner cone 8 and a cone tip 9 connected to the inner cone 8. One end of the inner cone 8 has a front mounting edge 10, and the other end has a rear mounting edge 15. One end of the cone tip 9 has a cone tip mounting edge 16, which is connected to the rear mounting edge 15. A film film ring body is located inside the inner cone 8. One end of the film film ring body is connected to the front mounting edge 10, and the other end is connected to the rear mounting edge 15 via a film film ring baffle 13. A nozzle 7 and a cooling shroud 6 are sequentially fitted around the inner cone 8. One end of the nozzle 7 has a front mounting edge 5, and one end of the cooling shroud 6 has a front mounting edge 1, which is connected to the front mounting edge 5. Multiple air intake pipes 3 are located along the edge of the cooling shroud 6, and each air intake pipe 3 has an air intake pipe plug 2 at its port.

[0028] A gap is left between the inner cone 8 and the nozzle 7 to form an air film channel, and a gap is left between the cooling shroud 6 and the nozzle 7 to form a cooling channel interlayer.

[0029] The inner cone 8, the front mounting edge 10 of the inner cone, and the rear mounting edge 15 of the inner cone form the front section of the inner cone, while the cone tip 9 and the cone tip mounting edge 16 form the rear section of the inner cone.

[0030] The front and rear sections of the inner cone combine to form a complete cone.

[0031] The main body of the air film ring is composed of a front mounting edge 11, an air film ring 12, and a rear mounting edge 14 connected in sequence. The front mounting edge 11 of the air film ring is connected to the front mounting edge 10 of the inner cone, and the rear mounting edge 14 of the air film ring is connected to the rear mounting edge 15 of the inner cone through the air film ring baffle 13.

[0032] A plurality of air inlet pipes 3 are distributed along the central circumference of the cooling cover 6.

[0033] The gas film ring 12 is provided with a plurality of uniformly distributed cooling gas film holes, and the cone tip 9 is provided with a plurality of uniformly distributed exhaust holes. The cooling gas flow in the cone is discharged through the exhaust holes on the surface of the cone tip.

[0034] The front mounting edge 1 of the cooling cover is provided with a baffle ring 4 between the front mounting edge 5 of the nozzle, and a gap is left between the cooling cover 6 and the nozzle 7.

[0035] The front mounting edge 5 of the nozzle is provided with air holes along the circumference.

[0036] The gas film ring 12 and the cone form an annular cooling channel, and the gas flow from the turbine support impacts the cooling cone through the cooling gas film holes on the gas film ring.

[0037] The device has a dual-mode cooling mode. When the turbine afterburner gas temperature is low, the nozzle is cooled by the outer-duct gas flow in the cooling channel interlayer between the cooling cover and the nozzle; when the turbine afterburner gas temperature is high, the nozzle is cooled by the mixed flow of the outer-duct gas flow in the cooling channel interlayer between the cooling cover and the nozzle and the additional cooling gas flow flowing in through the air inlet pipe.

[0038] Example 2

[0039] The scheme of Example 1 is adopted, and:

[0040] The cooling cover front mounting edge 1 is connected with the nozzle 7, and is connected with the upstream of the exhaust device (low-pressure turbine support) through the cooling cover front mounting edge 1. In the non-air state, the air inlet pipe cover 2 covers the air inlet pipe 3, and in the air state, the air inlet pipe cover 2 is opened, the air inlet pipe 3 is connected with the nozzle 7, the front end of the annular baffle ring 4 is connected with the nozzle 7, and a certain gap is left between the nozzle 7 and the inner cone 8, which can pass through the gas flow; the nozzle front mounting edge 5 is connected with the nozzle 7, and is connected with the cooling cover front mounting edge 1, and is connected with the upstream of the exhaust device together; the inner cone 8 forms an inner cone front segment through the connection of the inner cone front mounting edge 10 and the inner cone rear mounting edge 15, the cone tip 9 forms an inner cone rear segment through the connection with the cone tip mounting edge 16, and the inner cone front segment and the inner cone rear segment are combined into a complete cone; the gas film ring front mounting edge 11, the gas film ring 12 and the gas film ring rear mounting edge 14 constitute the main body of the gas film ring, and the gas film baffle 13 is connected with the gas film ring rear mounting edge 14 to block the rear end of the gas film ring.

[0041] As Figure 6As shown, the additional cooling gas is not connected state, the air inlet pipe plug 2 blocks the air inlet pipe 3, the bench, the cabin or other additional source of cooling gas cannot pass through the air inlet pipe 3 into the cooling channel interlayer between the cooling cover 6 and the nozzle 7, the interlayer can only pass through the cooling gas flow from the outer canister through the nozzle front mounting edge 5, to cool the nozzle 7 wall temperature, the high temperature gas after the turbine passes through the gas passage between the nozzle 7 and the inner cone 8 to discharge; The gas film ring 12 has a certain number of cooling film holes with different diameters on its surface, and the gas film ring baffle 13 blocks the tail of the gas film ring body. The high temperature gas from the turbine support enters the inner cavity of the gas film ring and cannot pass through the gas film baffle 13, and then flows into the cone tip 9 through the gas film passage between the gas film ring body and the nozzle 7, and finally discharges through the exhaust hole on the surface of the cone tip 9.

[0042] As shown in Figure 7 , the additional cooling gas is connected state, the air inlet pipe plug 2 does not block the air inlet pipe 3, the cooling gas from the bench, the cabin or other additional source passes through the air inlet pipe 3 into the cooling channel interlayer between the cooling cover 6 and the nozzle 7, the blocking ring 4 is located in the interlayer, and a certain gap is maintained between the cooling cover 6 and the nozzle 7, and they do not interfere with each other. The cooling gas flow from the outer canister flowing through the nozzle front mounting edge 5 and the additional cooling gas flowing through the air inlet pipe 3 mix after the blocking ring 4 and cool the nozzle 7 through the cooling channel interlayer, and then discharge, the cooling of the cone and the flow path of the gas flow in the gas film ring body are the same as Figure 6 shown in the additional cooling gas is not connected state.

[0043] Example 3

[0044] The scheme of example 2 is adopted, and:

[0045] The gas film ring body and the front segment of the inner cone are connected to the turbine support through the corresponding mounting holes of each front mounting, the gas film baffle 13 and the gas film ring rear mounting edge 14 are connected through the corresponding mounting holes of each other, and the rear segment of the inner cone is connected through the corresponding mounting holes of the inner cone rear mounting edge 15 and the cone tip mounting edge 16.

[0046] The air inlet pipe plug 2 blocks the air inlet pipe 3, the air inlet pipe 3 is connected with the cooling cover 6, the blocking ring 4 is connected with the front end of the cooling cover 6 through welding, riveting, bolt and other connection methods, and does not interfere with the wall surface of the cooling cover 6; The cooling cover front mounting edge 1 is connected with the cooling cover 6 by opening connecting holes along the circumference, the nozzle front mounting edge 5 is connected with the nozzle 7 by opening air holes and connecting holes along the circumference, and the cooling cover front mounting edge 1 and the nozzle front mounting edge 5 are connected through the corresponding connecting holes and connecting pieces.

[0047] The present application introduces the cold gas from the inside of the turbine support into the inner cone by setting a gas film ring in the inner cone, and the cold gas ejected from the gas film hole impacts the inner surface of the inner cone to achieve the purpose of cooling the inner cone; the present application introduces the cooling gas from the outer can into the flow channel between the nozzle and the cooling cover by wrapping a ring-shaped cooling cover on the outer surface of the nozzle to achieve the purpose of cooling the outer surface of the nozzle; in the state of large thrust, large power or large heat load of the engine, the air inlet pipe cover installed on the outer surface of the cooling cover is opened to introduce the cooling gas from the stand, the cabin or other additional cooling gas into the flow channel between the nozzle and the cooling cover, so as to further reduce the wall temperature of the nozzle surface.

Claims

1. A high-efficiency cooled jet engine comprising an inner cone (8) and a cone tip (9) connected to the inner cone (8), characterized in that: One end of the inner cone (8) is provided with an inner cone front mounting edge (10), the other end is provided with an inner cone rear mounting edge (15), one end of the cone tip (9) is provided with a cone tip mounting edge (16), the cone tip mounting edge (16) is connected with the inner cone rear mounting edge (15); The inner cone (8) is provided with a gas film ring body, one end of the gas film ring body is connected with the inner cone front mounting edge (10), the other end is connected with the inner cone rear mounting edge (15) through the gas film ring baffle (13); The inner cone (8) is sequentially sleeved with a nozzle (7) and a cooling cover (6), one end of the nozzle (7) is provided with a nozzle front mounting edge (5), one end of the cooling cover (6) is provided with a cooling cover front mounting edge (1), the cooling cover front mounting edge (1) is connected with the nozzle front mounting edge (5); The edge of the cooling cover (6) is provided with a plurality of air inlet pipes (3), the port of each air inlet pipe (3) is provided with an air inlet pipe cover (2); The gas film ring body is composed of a gas film ring front mounting edge (11), a gas film ring (12) and a gas film ring rear mounting edge (14) connected in sequence, the gas film ring front mounting edge (11) is connected with the inner cone front mounting edge (10), the gas film ring rear mounting edge (14) is connected with the inner cone rear mounting edge (15) through the gas film ring baffle (13); The gas film ring (12) and the cone form an annular cooling channel; A plurality of uniformly distributed cooling gas film holes are arranged on the gas film ring (12), and a plurality of uniformly distributed exhaust holes are arranged on the cone tip (9); The cooling cover front mounting edge (1) and the nozzle front mounting edge (5) are provided with a blocking ring (4), and a gap is left between the blocking ring (4) and the cooling cover (6) and the nozzle (7); The nozzle front mounting edge (5) is provided with an air hole along the circumference.

2. The high-efficiency cooled jet engine of claim 1, wherein: A gap is left between the inner cone (8) and the nozzle (7) to form a gas film channel, and a gap is left between the cooling cover (6) and the nozzle (7) to form a cooling channel interlayer.

3. The high-efficiency cooled jet engine of claim 1, wherein: The inner cone (8), the inner cone front mounting edge (10) and the inner cone rear mounting edge (15) form an inner cone front section, and the cone tip (9) and the cone tip mounting edge (16) form an inner cone rear section.

4. The high-efficiency cooled jet engine of claim 3, wherein: The inner cone front section and the inner cone rear section are combined into a complete cone.

5. The highly-cooled jet engine of claim 1, wherein: A plurality of air inlet pipes (3) are distributed along the central circumference of the cooling cover (6).

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