Self-centered, merged pre-swirl nozzle structure

Abstract

The application provides a self-centering fusion type pre-rotation nozzle structure, which comprises a rear casing section, a swirl vane being integrally arranged on the rear casing section, the rear casing section being provided with a first stop opening and a first air guide hole; a front casing section being provided with a second stop opening and a second air guide hole, the second stop opening abutting against the first stop opening, the first air guide hole being connected with the second air guide hole and being in conduction, and the front casing section and the rear casing section being connected through bolts. The first stop opening and the second stop opening are connected, so that self-centering can be realized when being connected, the risk of collision and friction with a rotor part is reduced, the rear casing section is integrally provided with the swirl vane, so that welding of parts is not needed, thereby simplifying the part machining process, and the rear casing section and the front casing section are fused into one through stop opening clamping and bolt connection, so that assembly and disassembly are more simple.

Description

TECHNICAL FIELD

[0001] The present specification relates to the technical field of aero-engine, in particular to a self-centering fusion type pre-rotation nozzle structure. BACKGROUND

[0002] The working principle of an aero-engine is to use the heat energy generated by the combustion of compressed air and fuel in the compressor to drive the turbine to rotate at high speed, and the turbine drives the compressor through the turbine shaft, thereby forming a continuous operation. In the design process of an aero-engine, in order to improve the cooling efficiency of the turbine disc, a pre-rotation nozzle is often designed on the adjacent casing to change the flow direction of the cooling air, and thus becomes an indispensable structure in the design of the turbine part of the engine.

[0003] The commonly used pre-rotation nozzle structure is composed of a pre-rotation blade, an upper wall and a lower wall, and the upper wall has a grid structure. The upper end of the pre-rotation blade is fixed by brazing and welding to the upper wall, and the lower end of the pre-rotation blade is also fixed by welding to the lower wall. The front end is fixed to the inner support by argon arc welding, and the upper part is connected to the mounting edge by bolts.

[0004] During processing, the pre-rotation blade needs to be inserted into the inner cavity formed by the upper wall and the lower wall in sequence, and then welded between the upper wall and the lower wall after being fixed. During assembly, due to high-temperature welding, on the one hand, the bolt holes on the upper wall are deformed due to the release of welding thermal stress, resulting in a large change between the actual position and the design position; on the other hand, the size of the grid also changes greatly, resulting in a large difference between the pre-rotation nozzle and the center of rotation.

[0005] From the above processing process, it can be seen that the common pre-rotation nozzle structure has the following disadvantages:

[0006] 1. The brazing and argon arc welding processing methods used cause the bolt holes to deform greatly after the parts are processed, making assembly difficult;

[0007] 2. The radial deformation of the grid is also large during the release of thermal stress, increasing the risk of collision and friction with the rotor; in severe cases, it can further affect the normal operation of the engine;

[0008] 3. The pre-rotation blade needs to be welded one by one, the process is complicated, and the consistency of the quality of the processed parts is difficult to guarantee. SUMMARY

[0009] Therefore, the self-centering fusion type pre-rotation nozzle structure is provided to solve the problem of engine rotor collision and friction caused by large thermal deformation of parts in the prior art.

[0010] The technical scheme of the present application is: a self-centering fusion type pre-rotation nozzle structure, comprising: a rear section of a casing, integrally provided with a swirl vane, the rear section of the casing being provided with a first stop opening and a first air guide hole; a front section of the casing, provided with a second stop opening and a second air guide hole, the second stop opening abutting against the first stop opening, the first air guide hole being connected with the second air guide hole and being in communication, and the front section of the casing and the rear section of the casing being connected through bolts.

[0011] Further, the rear section of the casing comprises a first inner cavity, a second inner cavity, a third inner cavity and a fourth inner cavity arranged in sequence.

[0012] Further, the rear section of the casing further comprises a first honeycomb and a second honeycomb, the first honeycomb being arranged at an inner wall of the second inner cavity, and the second honeycomb being arranged at an inner wall of the fourth inner cavity.

[0013] Further, the front section of the casing comprises a fifth inner cavity and a sixth inner cavity arranged in sequence.

[0014] Further, the front section of the casing further comprises a third honeycomb and a fourth honeycomb, the third honeycomb being arranged at an inner wall of the fifth inner cavity, and the fourth honeycomb being arranged at an inner wall of the sixth inner cavity.

[0015] Further, the swirl vane is a plurality of swirl vanes, and the swirl vanes are arranged at a cavity wall of the third inner cavity in a circumferential direction.

[0016] Compared with the prior art, the above at least one technical scheme adopted by the embodiments of the present application can achieve at least the following beneficial effects: through the connection of the first stop opening and the second stop opening, self-centering can be achieved during connection, the risk of collision and abrasion with the rotor part is reduced, the rear section of the casing is integrally provided with the swirl vane, and welding of the parts is not required, thereby simplifying the part processing process, and the rear section of the casing and the front section of the casing are fused into one through the stop opening clamping and bolt connection, thereby making the assembly and disassembly more simple. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0018] Figure 1 is a schematic diagram of the overall assembly structure of the embodiment of the present application;

[0019] Figure 2 is a schematic diagram of the installation position of the swirl vane;

[0020] Figure 3 is a schematic diagram of the structure of the rear section of the casing;

[0021] Figure 4This is a schematic diagram of the structure of the rear mounting holes;

[0022] Figure 5 This is a schematic diagram of the front section of the casing;

[0023] Figure 6 This is a schematic diagram of the front mounting holes.

[0024] The reference numerals in the diagram are as follows: 1. Rear section of the casing; 11. Swirl vane; 12. First honeycomb; 13. Second honeycomb; 14. First stop; 15. First air vent; 16. Rear section bolt hole; 2. Front section of the casing; 21. Second stop; 22. Third honeycomb; 23. Fourth honeycomb; 24. Second air vent; 25. Front section bolt hole; 3. Bolt; 4. Bushing; 5. Mating joint; 6. Nut. Detailed Implementation

[0025] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0026] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0027] like Figures 1 to 5 As shown, this embodiment of the invention provides a self-centering fusion pre-swirl nozzle structure, including a rear section 1 of the casing and a front section 2 of the casing. The rear section 1 of the casing is integrally provided with a swirl vane 11, and is provided with a first stop 14 and a first air intake 15; the front section 2 of the casing is provided with a second stop 21 and a second air intake 24, the second stop 21 abutting against the first stop 14 to form a mating part 5, the first air intake 15 connecting and communicating with the second air intake 24, and the front section 2 of the casing and the rear section 1 of the casing being connected by bolts.

[0028] The rear section 1 and the front section 2 of the casing are connected by the first stop 14 and the second stop 21, which can achieve self-centering during connection, reducing the risk of collision and rubbing with the rotor components. The rear section 1 of the casing is integrally provided with the swirl vane 11, eliminating the need for welding of parts and simplifying the parts processing. The rear section 1 and the front section 2 of the casing are integrated by the stop engagement and bolt connection, making assembly and disassembly simpler.

[0029] It should be noted that the first stop 14 and the second stop 21 in the embodiment of the application are both rotary structures with L-shaped cross sections.

[0030] The rear section 1 of the casing comprises a first inner cavity, a second inner cavity, a third inner cavity and a fourth inner cavity arranged in sequence. The first inner cavity, the second inner cavity, the third inner cavity and the fourth inner cavity are arranged in sequence from top to bottom as shown. Figure 3 The rear section 1 of the casing further comprises a first honeycomb 12 and a second honeycomb 13. The first honeycomb 12 is arranged at the inner wall of the second inner cavity, and the second honeycomb 13 is arranged at the inner wall of the fourth inner cavity.

[0031] The first honeycomb 12 and the second honeycomb 13 are cylindrical structures with rectangular cross sections, which are used for sealing the corresponding inner cavities of the rear section 1 of the casing.

[0032] The front section 2 of the casing comprises a fifth inner cavity and a sixth inner cavity arranged in sequence. The front section 2 of the casing further comprises a third honeycomb 22 and a fourth honeycomb 23. The third honeycomb 22 is arranged at the inner wall of the fifth inner cavity, and the fourth honeycomb 23 is arranged at the inner wall of the sixth inner cavity. The third honeycomb 22 and the fourth honeycomb 23 are cylindrical structures with rectangular cross sections, which are used for sealing the corresponding inner cavities of the front section 2 of the casing. At the same time, since the sizes of the first honeycomb 12, the second honeycomb 13, the third honeycomb 22 and the fourth honeycomb 23 change little, the risk of collision with the engine rotor is further reduced.

[0033] The swirl vanes 11 are a plurality of vanes arranged at the cavity wall of the third inner cavity in a circumferential direction. The swirl vanes 11 in the embodiment of the application are sheet-shaped structures formed by stretching a curve with a circular arc line and a straight line connected in cross section.

[0034] During assembly, the first stop 14 of the rear section 1 of the casing is clamped and connected with the second stop 21 of the front section 2 of the casing, the bolt 3 is inserted into the front section bolt hole 25 and the rear section bolt hole 16, then the nut 6 is fixed, and finally the bushing 4 is assembled. During disassembly, the nut 6 and the bolt 3 are sequentially disassembled, so that the rear section 1 of the casing and the front section 2 of the casing can be disassembled. The assembly and disassembly processes are relatively simple.

[0035] During operation, the cold air flowing through the first bleed air hole 15 of the rear section 1 of the casing changes the airflow through the rotation of the swirl vanes 11, thereby improving the cooling efficiency.

[0036] The above is only a specific embodiment of the present application, but the protection scope of the present application is not limited thereto. Any changes or replacements within the technical range disclosed in the present application can be easily thought of by those skilled in the art, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A self-centering, merged, pre-swirl nozzle structure, characterized by, The utility model relates to a turbine casing, comprising: a rear casing section (1) integrally provided with a swirl vane (11), the rear casing section (1) being provided with a first stop opening (14) and a first bleed hole (15); a front casing section (2) provided with a second stop opening (21) and a second bleed hole (24), the second stop opening (21) abutting against the first stop opening (14), the first bleed hole (15) being connected with the second bleed hole (24) and in communication, and the front casing section (2) being connected with the rear casing section (1) by bolts; the rear casing section (1) comprising a first inner cavity, a second inner cavity, a third inner cavity and a fourth inner cavity arranged in sequence; the rear casing section (1) further comprising a first honeycomb (12) and a second honeycomb (13), the first honeycomb (12) being arranged at an inner wall of the second inner cavity, and the second honeycomb (13) being arranged at an inner wall of the fourth inner cavity; the swirl vane (11) being a plurality of swirl vanes arranged at intervals in a circumferential direction at a cavity wall of the third inner cavity; the first stop opening (14) and the second stop opening (21) each being a rotary structure with an L-shaped cross section.

2. The self-centering merged pre-swirl nozzle structure of claim 1, wherein, the front casing section (2) comprising a fifth inner cavity and a sixth inner cavity arranged in sequence.

3. The self-centering merged pre-swirl nozzle structure of claim 2, wherein, the front casing section (2) further comprising a third honeycomb (22) and a fourth honeycomb (23), the third honeycomb (22) being arranged at an inner wall of the fifth inner cavity, and the fourth honeycomb (23) being arranged at an inner wall of the sixth inner cavity.

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