Aero-engine pre-swirl structure based on hot and cold swirl separation and aero-engine

Abstract

The present application provides an aircraft engine pre-swirl structure and an aircraft engine based on hot and cold swirl separation, wherein the pre-swirl structure comprises: a pre-swirl body, one side of which is evenly provided with a first hot end outlet along the circumferential direction, and the other side is correspondingly provided with a pre-swirl nozzle along the circumferential direction, the middle part of the outer peripheral wall of the pre-swirl body is provided with an air intake collecting cavity connected to the bleed air source, and the end of the inner peripheral wall close to the first hot end outlet is provided with a hot air outlet; a swirl separation tube is evenly provided on the pre-swirl body along the circumferential direction, one end of which is coaxially provided with an axial through hole connected to the first hot end outlet, and the other end is coaxially provided with a cold end outlet connected to the pre-swirl nozzle, and the outer peripheral wall of the swirl separation tube close to the cold end outlet is provided with an airflow inlet connected to the air intake collecting cavity; and a regulating device is provided on one side of the pre-swirl body and cooperates with the first hot end outlet to regulate the airflow outlet temperature and flow rate. The present application can simultaneously meet the needs of turbine blade cooling and turbine disk core heating.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft engine complete machines, and in particular, to an aircraft engine pre-swirl structure based on cold and hot swirl separation and an aircraft engine. Background Art

[0002] As the advancement of aircraft engines continues to improve, new requirements are constantly being put forward for engine performance and safety. In aircraft engines, there are parts that need to be cooled, such as the risk of turbine blades being eroded by high-temperature combustion gases. There are also parts that need to be heated, such as the large temperature gradient between the center and edge of the turbine disk, which leads to large thermal stress and anti-icing of the air inlet support plate. Gas turbine blades work in a high-temperature combustion environment and their reliability must be guaranteed, which puts forward new requirements for the cooling airflow. A high cooling-to-temperature ratio has a better cooling effect, and reducing the cooling airflow is a reliable and convenient way. Among the safety issues of aircraft engines, the strength of the turbine disk is an extremely important issue, and the situation where the thermal stress is too large due to the large temperature difference between the center and edge of the disk should be avoided.

[0003] The existing pre-swirl structure has a single way of using bleed air, and is only used as a resistance-reducing structure for radial airflow. A single airflow and a single temperature can only be used for a single function. In addition, only the pre-swirled cold air needs to flow from the center of the disk to the edge of the disk. The temperature rise of the cooling air of the turbine blades is too high, and the temperature of the cooling airflow flowing into the turbine blades is too high, resulting in poor cooling effect. Now the temperature of the center of the turbine disk is too low, and there is no special solution, which may have a potential impact on the safety of the turbine disk. Summary of the invention

[0004] The present application provides an aircraft engine pre-swirl structure based on cold and hot swirl separation, aiming to solve the technical problem that the single function of the existing pre-swirl structure cannot simultaneously meet the needs of turbine blade cooling and turbine disk core heating.

[0005] The technical solution adopted by the present invention is as follows:

[0006] An aero-engine pre-swirl structure based on cold and hot swirl separation, comprising:

[0007] The pre-swirl body is annular in shape as a whole, one side of the pre-swirl body is evenly provided with a first hot end outlet along the circumferential direction, and the other side is correspondingly provided with a pre-swirl nozzle along the circumferential direction, an air intake collecting cavity connected to an air source adjacent to the combustion chamber is provided in the middle of the outer peripheral wall of the pre-swirl body, and a hot air outlet is provided at one end of the inner peripheral wall close to the first hot end outlet;

[0008] A cyclone separation tube is evenly arranged on the pre-cyclone body along the circumferential direction, one end of the cyclone separation tube is coaxially provided with an axial through hole connected to the first hot end outlet, and the other end is coaxially provided with a cold end outlet connected to the pre-cyclone nozzle, an air flow inlet connected to the air intake collecting cavity is arranged on the outer peripheral wall of the cyclone separation tube near the cold end outlet, and a second hot end outlet connected to the hot air outlet is arranged on the outer peripheral wall of the cyclone separation tube near one end of the first hot end outlet;

[0009] The regulating device is arranged on one side of the pre-swirl body and cooperates with the first hot end outlet, and is used to regulate the air flow outlet temperature and flow ratio.

[0010] Furthermore, the number of the second hot end outlets is more than two, and they are evenly arranged circumferentially along the outer peripheral wall of the cyclone separation tube.

[0011] Furthermore, the axial direction of the second hot end outlet is tangent to the outer peripheral wall of the cyclone separation tube, and the opening direction is the same as the rotation direction of the pre-cyclone body.

[0012] Furthermore, the axial direction of the air flow inlet is tangent to the outer peripheral wall of the cyclone separation tube, and the opening direction is opposite to the rotation direction of the pre-cyclone body.

[0013] Furthermore, the pre-swirl body and the swirl separation tube are an integrated structure.

[0014] Furthermore, the adjusting device comprises:

[0015] An adjusting cone is inserted into the first hot end outlet with a clearance fit at one end, and is provided with a flat plate at the other end. An adjusting pad for adjusting the air outlet gap between the flat plate and the pre-swirl body is provided between the flat plate and the pre-swirl body.

[0016] Furthermore, the adjusting device comprises:

[0017] An adjusting cone, one end of which is inserted into the first hot end outlet with a clearance fit, and the other end of which is provided with a flat plate portion;

[0018] The electric adjustment mechanism is fixedly arranged on the pre-rotation body, and the output end is drivingly connected to the flat plate part, and is used for adjusting the air outlet gap between the flat plate part and the pre-rotation body.

[0019] Furthermore, the electrical adjustment mechanism comprises:

[0020] A rotating motor is fixed on the pre-spinning body;

[0021] A rotating screw has one end connected to the output end of the rotating motor and the other end threadably matched with the threaded hole arranged on the flat plate.

[0022] Furthermore, the electrical adjustment mechanism comprises:

[0023] A linear motor is fixed on the pre-rotation body;

[0024] A push-pull rod has one end connected to the output end of the linear motor and the other end fixedly connected to the flat plate portion.

[0025] The present application also provides an aircraft engine, comprising:

[0026] The aero-engine pre-swirl structure as described above;

[0027] The turbine shaft cooperates with the center hole of the aircraft engine pre-swirl structure. The outer peripheral wall of the turbine shaft is provided with a sealing grate ring that cooperates with the inner wall of the center hole of the aircraft engine pre-swirl structure. The aircraft engine pre-swirl structure, the sealing grate ring and the turbine shaft together form a hot end air collecting chamber. The turbine shaft is also provided with an axial flow hole connected to the hot end air collecting chamber.

[0028] Compared with the prior art, this application has the following beneficial effects:

[0029] The present application provides an aircraft engine pre-swirl structure and an aircraft engine based on cold and hot swirl separation, wherein the pre-swirl structure comprises a pre-swirl body, a swirl separation tube, and an adjusting device. In existing engines, the existence of the pre-swirl structure is mainly to reduce the huge flow loss caused when the cooling airflow passes through the narrow channel of the disk core. The present application is a targeted improvement on the defects of the existing pre-swirl structure, and the cold and hot swirl separation tube is integrated with the pre-swirl body to obtain a swirl separation pre-swirl structure, thereby improving the situation where the pre-swirl structure has a single function; the present application can reduce the number of parts and make the structure compact while meeting the requirements of the cooling and heating functions; the present application separates the single-source airflow through a swirl, performs temperature compensation on the existing air system, and achieves the purpose of cooling the existing cooling airflow and heating the heating structure; the present application can adjust the flow ratio of the cold and hot airflows according to the current temperature, and has strong adaptability, flexibility and reliability.

[0030] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings:

[0032] Figure 1 It is a cross-sectional schematic diagram of an aircraft engine pre-swirl structure based on cold and hot swirl separation according to a preferred embodiment of the present application.

[0033] Figure 2This is a schematic diagram of the three-dimensional structure of the cyclone separation tube according to the preferred embodiment of the present application.

[0034] Figure 3 It is a schematic diagram of the three-dimensional structure of the aircraft engine pre-swirl structure based on cold and hot swirl separation according to the preferred embodiment of the present application.

[0035] Figure 4 It is a schematic cross-sectional structural diagram of an aircraft engine pre-swirl structure based on cold and hot swirl separation according to another preferred embodiment of the present application.

[0036] In the figure: 1. air source; 2. adjustment pad; 3. air flow inlet; 4. adjustment cone; 5. first hot end outlet; 6. second hot end outlet; 7. hot end air collecting chamber; 8. axial flow hole; 9. turbine shaft; 10. sealing grate ring; 11. cyclone separation tube; 12. cyclone separation chamber; 13. pre-swirl nozzle; 14. cold end outlet; 15. pre-swirl body; 16. intake air collecting chamber; 17. combustion chamber; 18. electric adjustment mechanism. DETAILED DESCRIPTION

[0037] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0038] Reference Figure 1 and Figure 3 The preferred embodiment of the present invention provides an aircraft engine pre-swirl structure based on cold and hot swirl separation, comprising:

[0039] The pre-swirl body is annular as a whole, and a first hot end outlet 5 is evenly arranged on one side of the pre-swirl body along the circumferential direction, and a pre-swirl nozzle 13 is correspondingly arranged on the other side along the circumferential direction. An air intake collecting cavity 16 connected to the bleed air source 1 adjacent to the combustion chamber 17 is arranged in the middle of the outer peripheral wall of the pre-swirl body, and a hot air outlet is arranged at one end of the inner peripheral wall close to the first hot end outlet 5;

[0040] The cyclone separation tube 11 is evenly arranged on the pre-cyclone body 15 along the circumferential direction, one end of the cyclone separation tube 11 is coaxially provided with an axial through hole connected to the first hot end outlet 5, and the other end is coaxially provided with a cold end outlet 14 connected to the pre-cyclone nozzle 13, an air flow inlet 3 connected to the air intake collecting chamber 16 is arranged on the outer peripheral wall of the cyclone separation tube 11 near the cold end outlet 14, and a second hot end outlet 6 connected to the hot air outlet is arranged on the outer peripheral wall of the cyclone separation tube 11 near the first hot end outlet 5;

[0041] An adjusting device is arranged on one side of the pre-swirl body and cooperates with the first hot end outlet 5, and is used to adjust the air flow outlet temperature and flow ratio. In this embodiment, the adjusting device includes an adjusting cone 4, one end of the adjusting cone 4 is inserted and arranged in the first hot end outlet 5 with a gap fit, and the other end is provided with a flat plate portion, and an adjusting pad 2 for adjusting the air outlet gap between the flat plate portion and the pre-swirl body 15 is provided between the flat plate portion and the pre-swirl body 15. By pre-arranging the adjusting pad 2 with different thicknesses, the air outlet gap between the flat plate portion and the pre-swirl body 15 can be adjusted to achieve the purpose of adjusting the air flow outlet temperature and flow ratio.

[0042] The present embodiment provides an aircraft engine pre-swirl structure based on cold and hot swirl separation, the pre-swirl structure comprising a pre-swirl body 15, a swirl separation tube 11, and an adjusting device. In existing engines, the existence of the pre-swirl structure is mainly to reduce the huge flow loss caused by the cooling airflow passing through the narrow channel of the disk core. The present embodiment is a targeted improvement on the defects of the existing pre-swirl structure, and the cold and hot swirl separation tube is integrated with the pre-swirl body to obtain a swirl separation pre-swirl structure, thereby improving the situation where the pre-swirl structure has a single function; the present embodiment can reduce the number of parts while meeting the requirements of the cooling and heating functions, making the structure compact; the present embodiment separates the single-source airflow through a swirl, performs temperature compensation on the existing air system, and achieves the purpose of cooling the existing cooling airflow and heating the heating structure; the present application can adjust the flow ratio of the cold and hot airflows according to the current temperature, and has strong adaptability, flexibility and reliability.

[0043] like Figure 2 As shown, in a preferred embodiment of the present application, the number of the second hot end outlets 6 is more than two, and they are evenly arranged circumferentially along the outer peripheral wall of the cyclone separation tube 11. For example, in this embodiment, four second hot end outlets 6 are arranged circumferentially along the outer peripheral wall of the cyclone separation tube 11 in pairs symmetrically. The airflow flows into the cyclone separation tube 11 from the air source 1 and the airflow inlet 3 in sequence, and forms two cold and hot airflows through the separation effect of the cyclone separation tube 11 and flows out from both ends of the cyclone separation tube 11. The purpose of setting multiple second hot end outlets 6 in this embodiment is to facilitate the continuous and smooth output of the hot airflow from the cyclone separation tube 11 and avoid accumulation in the cyclone separation tube 11.

[0044] Specifically, the axial direction of the second hot end outlet 6 is tangent to the outer peripheral wall of the cyclone separation tube 11, and the opening direction is the same as the rotation direction of the pre-cyclone body 15. Its purpose and benefit are to reduce the flow resistance of the airflow and reduce the flow loss.

[0045] Specifically, the air flow inlet 3 is tangent to the outer peripheral wall of the cyclone separation tube 11 in the axial direction, and the opening direction is opposite to the rotation direction of the pre-cyclone body 15, the purpose of which is to reduce the flow velocity and increase the static pressure.

[0046] Specifically, the pre-swirl body 15 and the cyclone separation tube 11 are an integrated structure. In this embodiment, the cyclone separation tube 11 is integrated with the pre-swirl body 15 to form an integrated cyclone separation pre-swirl structure, which improves the single function of the pre-swirl structure and can meet the requirements of cooling and heating functions while reducing the number of parts to make the structure more compact.

[0047] like Figure 4 As shown, in a preferred embodiment of the present application, the adjusting device comprises:

[0048] An adjusting cone 4, one end of which is inserted into the first hot end outlet 5 with a clearance fit, and the other end of which is provided with a flat plate portion;

[0049] The electric adjustment mechanism 18 is fixedly arranged on the pre-rotation body 15 , and the output end is drivingly connected to the flat plate part, so as to adjust the air outlet gap between the flat plate part and the pre-rotation body 15 .

[0050] Different from the above-mentioned embodiment, the regulating device in this embodiment is mainly composed of an adjusting cone 4 provided with a flat plate portion and an electric regulating mechanism 18. The electric regulating mechanism 18 can automatically adjust the air outlet gap between the flat plate portion and the pre-swirl body 15 according to temperature requirements. If the sensor detects that the hot air flow rate and temperature to the heated component are insufficient, the electric regulating mechanism 18 will automatically increase the size of the air outlet gap between the flat plate portion and the pre-swirl body 15 to allow more hot air to flow to the heated component, such as heating the turbine disk center so that the temperature gradient between the turbine disk center and the disk edge will not be too large, resulting in a large thermal stress. In addition, the air inlet support plate is heated to prevent ice from falling. Otherwise, the electric regulating mechanism 18 will automatically reduce the size of the air outlet gap between the flat plate portion and the pre-swirl body 15 to reduce the hot air flow to the heated component.

[0051] Specifically, the electrical adjustment mechanism 18 includes:

[0052] A rotating motor, fixed on the pre-spinning body 15;

[0053] A rotating screw has one end connected to the output end of the rotating motor and the other end threadably matched with the threaded hole arranged on the flat plate.

[0054] Specifically, the electrical adjustment mechanism 18 includes:

[0055] A linear motor is fixed on the pre-spin body 15;

[0056] A push-pull rod has one end connected to the output end of the linear motor and the other end fixedly connected to the flat plate portion.

[0057] Another preferred embodiment of the present application further provides an aircraft engine, comprising:

[0058] The aero-engine pre-swirl structure;

[0059] The turbine shaft 9 cooperates with the center hole of the aircraft engine pre-swirl structure. The outer peripheral wall of the turbine shaft 9 is provided with a sealing grate ring 10 that cooperates with the inner wall of the center hole of the aircraft engine pre-swirl structure. The aircraft engine pre-swirl structure, the sealing grate ring 10 and the turbine shaft 9 together form a hot end air collecting chamber 7. The turbine shaft 9 is also provided with an axial flow hole 8 connected to the hot end air collecting chamber 7.

[0060] The process principle of this embodiment is:

[0061] The airflow from the casing of the combustion chamber 17 and the external high pressure air source 1 of the combustion chamber 17 enters the air intake plenum 16, and reaches each cyclone separation tube 11 through the airflow inlet 3. Through the cyclone separation effect, the introduced airflow is divided into a cold airflow flowing to the right and a hot airflow flowing to the left. The airflow outlet temperature and flow ratio can be adjusted by the regulating device, such as by adjusting the thickness of the adjusting pad 2 or the electric adjustment mechanism 18 to control the opening of the outlet. There are two types of hot end outlets, one is the gap outlet between the hot end flat plate and the cyclone separation tube 11, and the other is the second hot end outlet 6 tangentially arranged at the hot end of the cyclone separation tube 11. The airflow of the second hot end outlet 6 tangentially arranged at the hot end flows into the hot end plenum 7 and then flows downward through the axial flow hole 7 to converge with another hot end airflow and flow to the center of the turbine disk, so as to achieve the purpose of heating the center of the disk. The right end cold air outlet flows out through the pre-swirl nozzle 13 and merges with the mainstream cold air, so as to reduce the overall temperature level of the turbine blade cooling air and improve the cold air cooling effect.

[0062] The aircraft engine of this embodiment includes the aircraft engine pre-swirl structure of the above-mentioned embodiment, which combines the swirl cold and hot separation structure with the engine pre-swirl structure, thereby separating a single airflow into cold and hot airflows and applying them to cooling the turbine blades and increasing the temperature of the turbine disk core, thereby reducing the risk of the turbine blades being eroded by high-temperature combustion gas, and preventing the temperature gradient between the center and the edge of the turbine disk from being too large, resulting in large thermal stress, thereby extending the service life of the engine, reducing the failure rate of the engine, and improving the reliability and stability of the engine.

[0063] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft engine pre-swirl structure based on cold and hot swirl separation, characterized in that: include: The pre-swirl body (15) is annular in shape as a whole, and a first hot end outlet (5) is evenly arranged on one side of the pre-swirl body (15) along the circumferential direction, and a pre-swirl nozzle (13) is correspondingly arranged on the other side along the circumferential direction. An air intake collecting cavity (16) connected to an air bleed source (1) adjacent to a combustion chamber (17) is arranged in the middle of the outer peripheral wall of the pre-swirl body (15), and a hot air outlet is arranged at one end of the inner peripheral wall close to the first hot end outlet (5); A cyclone separation tube (11) is evenly arranged on the pre-cyclone body (15) along the circumferential direction; one end of the cyclone separation tube (11) is coaxially provided with an axial through hole connected to the first hot end outlet (5); the other end is coaxially provided with a cold end outlet (14) connected to the pre-cyclone nozzle (13); an air flow inlet (3) connected to the air intake collecting chamber (16) is arranged on the outer peripheral wall of the cyclone separation tube (11) near the cold end outlet (14); and a second hot end outlet (6) connected to the hot air outlet is arranged on the outer peripheral wall of one end of the cyclone separation tube (11) near the first hot end outlet (5); The regulating device is arranged on one side of the pre-swirl body and cooperates with the first hot end outlet (5) and is used to regulate the air flow outlet temperature and flow ratio.

2. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 1, characterized in that: The number of the second hot end outlets (6) is more than two, and they are evenly arranged circumferentially along the outer peripheral wall of the cyclone separation tube (11).

3. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 1 or 2, characterized in that: The axial direction of the second hot end outlet (6) is tangent to the outer peripheral wall of the cyclone separation tube (11), and the opening direction is the same as the rotation direction of the pre-cyclone body (15).

4. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 1, characterized in that: The air flow inlet (3) is tangent to the outer peripheral wall of the cyclone separation tube (11) in an axial direction, and the opening direction is opposite to the rotation direction of the pre-cyclone body (15).

5. The aircraft engine pre-swirl structure based on hot and cold swirl separation according to claim 1, characterized in that: The pre-swirl body (15) and the swirl separation tube (11) are an integrated structure.

6. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 1, characterized in that: The regulating device comprises: An adjustment cone (4) is provided with one end inserted into the first hot end outlet (5) with a clearance fit, and a flat plate portion is provided at the other end, and an adjustment pad (2) is provided between the flat plate portion and the pre-swirl body (15) for adjusting the air outlet gap between the flat plate portion and the pre-swirl body (15).

7. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 1, characterized in that: The regulating device comprises: An adjusting cone (4) has one end which is inserted into the first hot end outlet (5) with a clearance fit, and the other end of which is provided with a flat plate portion; The electric adjustment mechanism (18) is fixedly arranged on the pre-rotation body (15), and the output end is drivingly connected to the flat plate part, and is used to adjust the air outlet gap between the flat plate part and the pre-rotation body (15).

8. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 7, characterized in that: The electrical adjustment mechanism (18) comprises: A rotating motor fixed on the pre-rotating body (15); A rotating screw has one end connected to the output end of the rotating motor and the other end threadably matched with the threaded hole arranged on the flat plate.

9. The aircraft engine pre-swirl structure based on cold and hot swirl separation according to claim 7, characterized in that: The electrical adjustment mechanism (18) comprises: A linear motor is fixed on the pre-rotating body (15); A push-pull rod has one end connected to the output end of the linear motor and the other end fixedly connected to the flat plate portion.

10. An aircraft engine, characterized in that: include: The aircraft engine pre-swirl structure according to any one of claims 1 to 9; A turbine shaft (9) is matched with the center hole of the aircraft engine pre-swirl structure. The outer peripheral wall of the turbine shaft (9) is provided with a sealing grate ring (10) that matches with the inner wall of the center hole of the aircraft engine pre-swirl structure. The aircraft engine pre-swirl structure, the sealing grate ring (10) and the turbine shaft (9) together form a hot end air collecting chamber (7). The turbine shaft (9) is also provided with an axial flow hole (8) that is connected to the hot end air collecting chamber (7).

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