Self-adjusting aviation turbine

Abstract

The utility model discloses a self-adjusting aviation turbine which is mainly composed of a turbine, a gas compressor, an electric valve, a first pipeline temperature sensor, a first differential pressure sensor, a second pipeline temperature sensor, a third pipeline temperature sensor, a second differential pressure sensor, a first flow meter, a second flow meter, a third flow meter and a controller. The controller adjusts the opening degree of the electric valve by receiving the temperature, the pressure and the flow at the inlet and the outlet of the turbine and the inlet and the outlet of the gas compressor, and therefore the gas flow at the inlet of the turbine is controlled. According to the utility model, the turbine product can meet the flight large envelope performance of an airplane, the conversion efficiency and the reliability of the turbine are synchronously improved, and the problems of continuously increasing the working speed of the turbine, increasing the size of the turbine and reducing the reliability of the turbine in order to improve the expansion ratio and the pressure ratio of the turbine product are solved to a certain extent.

Description

Technical Field

[0001] The utility model relates to a self-regulating aviation turbine component, which is suitable for the fields of aviation environmental control systems and electromechanical / oxygen systems, in particular to a comprehensive environmental control system combining pressure boosting, oxygenation and cooling. Background Art

[0002] The turbine is an important component of the aircraft environmental control system and the electromechanical / oxygen system. It is mainly used to cool down and reduce the pressure or heat up and increase the pressure of the gas introduced into the system to meet the use requirements of the system. The boosting, cooling efficiency and reliability of turbine products and the inclusiveness of large flight envelopes have always been difficult problems in the domestic aviation field, especially the application of miniaturized, lightweight, high-efficiency and high-reliability turbine products is the focus of research. In order to solve the problems of miniaturization, lightweight, high efficiency, high precision and high reliability of turbines, the utility model proposes a self-regulating aviation turbine assembly. Summary of the invention

[0003] In view of the problems existing in the background technology, the utility model aims to provide a self-regulating aviation turbine, so that the turbine product can meet the large envelope performance of the aircraft flight while simultaneously improving the conversion efficiency and reliability of the turbine, and to a certain extent alleviate the problem of turbine products continuously increasing the turbine operating speed, increasing the turbine volume, and reducing the turbine reliability in order to improve the expansion ratio and pressure ratio.

[0004] In order to solve the above problems, the utility model adopts the following technical solutions:

[0005] A self-regulating aviation turbine, comprising a coaxially connected turbine and compressor, and further comprising:

[0006] An electric valve installed at the inlet of the turbine;

[0007] A first flow meter and a first pipeline temperature sensor, wherein the first flow meter and the first pipeline temperature sensor are arranged at the inlet of the electric valve and the inlet of the compressor;

[0008] A second flow meter and a second pipeline temperature sensor, wherein the second flow meter and the second pipeline temperature sensor are arranged at the outlet of the compressor;

[0009] a third flow meter and a third pipe temperature sensor, wherein the third flow meter and the third pipe temperature sensor are arranged at the outlet of the turbine;

[0010] A first differential pressure sensor and a second differential pressure sensor, wherein the first differential pressure sensor is arranged at the inlet and outlet of the compressor, and the second differential pressure sensor is arranged at the inlet of the electric valve and the outlet of the turbine;

[0011] A controller is connected to the first flow meter, the second flow meter, the third flow meter, the first pipeline temperature sensor, the second pipeline temperature sensor, the first differential pressure sensor, the second differential pressure sensor and the electric valve.

[0012] As a solution, the electric valve includes:

[0013] A valve support, the valve support being connected to an inlet pipeline of the turbine;

[0014] A valve rod and a valve plate, wherein the valve rod is rotatably connected in the valve support, and the valve plate is located in the valve support and fixed on the valve rod;

[0015] A DC motor, wherein the output end of the DC motor is coaxially connected to the valve rod, and the DC motor is connected to the controller.

[0016] As a solution,

[0017] The turbine comprises a turbine volute, a turbine impeller, a straightening window and an air baffle;

[0018] The compressor comprises a diffuser, a compressor impeller and a compressor casing;

[0019] The turbine impeller and the compressor impeller are connected at both ends of the same shaft. The turbine impeller is located in the turbine volute, the compressor impeller is located in the compressor casing, the straightening window and the air baffle are located at the intake end of the turbine impeller, and the diffuser is located at the exhaust end of the compressor impeller.

[0020] As a solution, the self-regulating aviation turbine also includes:

[0021] A casing assembly, two ends of which are respectively connected to the turbine volute and the compressor casing;

[0022] A bearing housing assembly is provided in the housing assembly, and the shaft is rotatably connected in the bearing housing assembly via a bearing.

[0023] As an option, a controller is provided on the outer surface of the turbine volute.

[0024] As an option, the inlet of the electric valve is connected to the first branch, the inlet of the compressor is connected to the second branch, the first branch and the second branch are connected to the main line after being merged, and the main line is provided with a first flow meter and a first pipeline temperature sensor.

[0025] The utility model can adjust the turbine expansion ratio in real time by adjusting the air intake volume and pressure at the turbine inlet in real time, so as to achieve the optimal working condition requirements at various altitudes.

[0026] Compared with the prior art, the utility model is applied to the aircraft environmental control system or oxygen production system. Compared with the turbine products currently used on aircraft, the performance of the aviation turbine product of the utility model is suitable for different working conditions within the flight envelope, and the turbine performance can be adjusted to the optimal under different working conditions, meeting the requirements of the aircraft for air source pressurization at different altitudes during large envelope flight, while avoiding the over-speed problem of the aviation turbine at the extreme altitude, and improving the reliability of the aviation turbine product. The utility model has the following characteristics:

[0027] (1) The highly efficient self-regulating aviation turbine adopts an electronically controlled joint adjustment structure. An adjustable electric valve is provided at the turbine volute inlet of the aviation turbine. Temperature sensors, differential pressure sensors and flow meters are installed on the inlet and outlet pipes on both sides of the aviation turbine. The controller is also provided to adjust the opening of the electric valve at the turbine volute inlet by processing the collected temperature, pressure and flow parameters, thereby realizing the self-regulation of the aviation turbine performance, meeting the requirements of air source supercharging at different altitudes during large envelope flight of the aircraft, and avoiding the over-speed problem of the aviation turbine at the extreme altitude, thereby improving the reliability of the aviation turbine product;

[0028] (2) The turbine impeller, compressor impeller and bearings of the self-regulating aviation turbine are installed in series on both sides of the shaft. The air introduced from the system enters the turbine side through the turbine volute, and then enters the turbine impeller radially after being rectified by the rectifier window to expand and do work, converting the internal energy of the gas into mechanical energy, and reducing the temperature and pressure of the gas, and then the gas is discharged from the axial outlet of the turbine impeller. The mechanical energy converted from the expansion work of the turbine impeller is coaxially transmitted through the shaft and bearings, driving the compressor impeller to compress the gas entering the impeller from the axial direction, pressurizing and heating the gas, and then the gas flows into the diffuser from the radial outlet of the compressor impeller, and flows out through the outlet of the compressor casing to reach the gas pressure and gas temperature that meet the system use requirements.

[0029] (3) The electric valve is installed at the inlet of the turbine volute and is used to adjust the inlet flow of the turbine side. It has a valve support, a valve rod and a valve plate from the outside to the inside. The valve support is connected to the outer shell of the DC motor and the inlet of the turbine volute. The valve plate is installed on the valve rod and placed inside the valve support. It is connected to the DC motor through the valve rod.

[0030] (4) The first pipeline temperature sensor and the second pipeline temperature sensor are used to collect the compressor casing inlet and outlet temperatures of the system, the third pipeline temperature sensor is used to collect the turbine casing outlet air temperature, the first differential pressure sensor and the second differential pressure sensor are used to collect the turbine volute inlet (equivalent to the electric valve inlet) and outlet differential pressures and the compressor casing inlet and outlet differential pressures, respectively, and the first flowmeter, the third flowmeter and the second flowmeter are used to collect the turbine volute inlet and outlet flow and the compressor casing outlet flow, respectively. The controller is used to collect and process the measured data of the first pipeline temperature sensor, the second pipeline temperature sensor, the third pipeline temperature sensor, the first differential pressure sensor, the second differential pressure sensor, the first flowmeter, the second flowmeter and the third flowmeter, and output a control signal to the DC motor after reading, to control the electric valve opening, thereby controlling the aviation turbine inlet flow, and achieving the purpose of self-regulating the aviation turbine performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a working principle diagram of the self-regulating aviation turbine in the utility model, and the arrow direction in the figure is the gas flow direction;

[0032] Figure 2 It is a structural schematic diagram of the aviation turbine in the utility model;

[0033] Figure 3 It is a schematic diagram of the structure of the electric valve in the utility model;

[0034] In the figure: 1-turbine; 2-compressor; 3-electric valve; 4-first flow meter; 5-first pipeline temperature sensor; 6-second flow meter; 7-first differential pressure sensor; 8-second pipeline temperature sensor; 9-second differential pressure sensor; 10-third flow meter; 11-third pipeline temperature sensor; 12-turbine volute; 13-turbine impeller; 14-rectifier window; 15-air baffle; 16-housing assembly; 17-bearing housing assembly; 18-diffuser; 19-compressor impeller; 20-compressor housing; 21-bearing; 22-shaft; 23-DC motor; 24-valve plate; 25-valve support; 26-valve rod. DETAILED DESCRIPTION

[0035] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments, but it should not be understood that the scope of the subject matter described in the present invention is limited to the following embodiments. Without departing from the above-mentioned technical ideas of the present invention, various modifications, substitutions and changes made according to the common technical knowledge and customary means in the field are included in the scope of the present invention.

[0036] like Figure 1As shown, the utility model provides a self-regulating aviation turbine, which is mainly composed of a turbine 1, a compressor 2, an electric valve 3, a first pipeline temperature sensor 5, a first pressure difference sensor 7, a second pipeline temperature sensor 8, a third pipeline temperature sensor 11, a second pressure difference sensor 9, a first flow meter 4, a second flow meter 6, a third flow meter 10 and a controller. The electric valve 3 is installed at the inlet of the turbine volute 12 of the aviation turbine, the first pipeline temperature sensor 5 and the second pipeline temperature sensor 8 are installed in the inlet and outlet pipelines of the compressor casing 20, the third pipeline temperature sensor 11 is installed in the outlet pipeline of the turbine volute 12, the first pressure difference sensor 7 and the second pressure difference sensor 9 are respectively installed at the inlet and outlet of the compressor casing 20, the inlet of the electric valve 3 and the outlet of the turbine volute 12, and the first flow meter 4, the third flow meter 10 and the second flow meter 6 are respectively installed at the inlet (equivalent to the inlet of the electric valve 3) and the outlet of the turbine volute 12 and the outlet of the compressor casing 20. The first flow meter 4 and the first pipeline temperature sensor 5 are arranged on the air passage common to the inlet of the electric valve 3 and the inlet of the compressor 2. The controller is installed outside the housing assembly 16. The controller can collect flow, pressure and temperature sensor signals, process them according to the program, and output the control signal type. Figure 1 In the figure, T represents the turbine side of the same component, and C represents the compressor side of the same component. Figure 1 A TC-style aviation turbine is displayed.

[0037] like Figure 2 From left to right, and from outside to inside, the aircraft turbine has a turbine volute 12, a turbine impeller 13, a flow window 14, an air baffle 15, a housing assembly 16, a bearing housing assembly 17, a diffuser 18, a compressor impeller 19, and a compressor housing 20. The bearing 21 is mounted on the shaft 22, and then assembled inside the bearing housing assembly 17. The bearing housing assembly 17 is mounted inside the housing assembly 16. The turbine impeller 13 and the compressor impeller 19 are respectively mounted at both ends of the shaft 22. After the complete flow window 14 and the diffuser 18 are assembled inside the turbine volute 12 and the compressor housing 20, they are respectively mounted on the outside of the turbine impeller 13 and the compressor impeller 19, and connected to the housing assembly 16.

[0038] The working principle of the self-regulating aviation turbine in the utility model is as follows: Figure 1 and Figure 2 As shown, Figure 1The middle arrow represents the direction and path of the airflow, the dotted line represents the connection of the first differential pressure sensor 7 and the second differential pressure sensor 9, and the dot-dash line represents the connection between the controller and the temperature sensor, the flow meter and the differential pressure sensor. The air introduced from the main pipeline of the system is divided into two channels, one of which enters the turbine side through the inlet of the turbine volute 12, and then enters the turbine impeller 13 radially after being rectified by the rectifier window 14 to expand and do work, convert the internal energy of the gas into mechanical energy, and reduce the temperature and pressure of the gas, and then discharge the gas from the axial outlet of the turbine impeller 13, and the other enters the compressor side through the compressor inlet. The mechanical energy converted from the expansion work of the turbine impeller 13 is coaxially transmitted through the shaft 22 and the bearing 21, driving the compressor impeller 19 to compress and do work on the gas entering the impeller from the axial direction, so that the gas is pressurized and heated, and then the gas flows out from the radial outlet of the compressor impeller 19 to reach the gas pressure and gas temperature that meet the system use requirements.

[0039] An adjustable electric valve 4 is provided at the inlet of the turbine volute 12. Figure 3 As shown, the electric valve 4 includes a valve support 25, a valve rod 26, a valve plate 24 and a DC motor 23. The valve rod 26 is rotatably connected in the valve support 25. The valve plate 24 is located in the valve support 25 and fixed on the valve rod 26. The output end of the DC motor 23 is coaxially connected to the valve rod 26. The DC motor 23 is connected to the controller to control the rotation of the valve plate 14, thereby adjusting the flow cross-section size of the air flow channel inside the valve support 25, that is, the opening. Temperature sensors, differential pressure sensors and flow meters are installed on the inlet and outlet pipelines on both sides of the aviation turbine, and a controller 11 is provided. The opening of the electric valve 4 at the inlet of the turbine volute 12 can be adjusted by processing the collected temperature, pressure and flow parameters, thereby realizing the self-regulation of the performance of the aviation turbine and meeting the requirements of air source pressurization at different altitudes when the aircraft flies in a large envelope.

[0040] The utility model can be applied to the oxygen supply subsystem of the oxygen system of an aircraft. As an accessory of the oxygen supply subsystem, the gas introduced into the system can be pressurized and heated to supply the next-level molecular sieve. The aviation turbine has the characteristics of small flow, large pressure rise, high efficiency and high precision.

[0041] The aviation turbine adopts an electronically controlled joint adjustment structure, which contains a turbine 1 and a compressor 2. It can expand the gas entering the turbine side and convert the internal energy of the gas into mechanical energy and coaxially drive the compressor impeller 19 to pressurize the incoming gas. The air entering the compressor side is pressurized and then supplied to the oxygen system.

[0042] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A self-regulating aviation turbine, comprising a turbine (1) and a compressor (2) connected coaxially, characterized in that: Also includes: An electric valve (3), the electric valve (3) being installed at the inlet of the turbine (1); A first flow meter (4) and a first pipeline temperature sensor (5), wherein the first flow meter (4) and the first pipeline temperature sensor (5) are arranged at the inlet of the electric valve (3) and the inlet of the compressor (2); A second flow meter (6) and a second pipeline temperature sensor (8), wherein the second flow meter (6) and the second pipeline temperature sensor (8) are arranged at the outlet of the compressor (2); A third flow meter (10) and a third pipe temperature sensor (11), wherein the third flow meter (10) and the third pipe temperature sensor (11) are arranged at the outlet of the turbine (1); a first differential pressure sensor (7) and a second differential pressure sensor (9), wherein the first differential pressure sensor (7) is arranged at the inlet and outlet of the compressor (2), and the second differential pressure sensor (9) is arranged at the inlet of the electric valve (3) and at the outlet of the turbine (1); A controller is connected to a first flow meter (4), a second flow meter (6), a third flow meter (10), a first pipeline temperature sensor (5), a second pipeline temperature sensor (8), a first differential pressure sensor (7), a second differential pressure sensor (9) and an electric valve (3).

2. The self-regulating aviation turbine according to claim 1, characterized in that: The electric valve (3) comprises: A valve support (25), wherein the valve support (25) is connected to an inlet pipeline of the turbine (1); A valve rod (26) and a valve plate (24), wherein the valve rod (26) is rotatably connected in the valve support (25), and the valve plate (24) is located in the valve support (25) and fixed on the valve rod (26); A DC motor (23), wherein the output end of the DC motor (23) is coaxially connected to the valve rod (26), and the DC motor (23) is connected to a controller.

3. The self-regulating aviation turbine according to claim 1, characterized in that: The turbine (1) comprises a turbine volute (12), a turbine impeller (13), a rectification window (14) and an air baffle (15); The compressor (2) comprises a diffuser (18), a compressor impeller (19) and a compressor casing (20); The turbine impeller (13) and the compressor impeller (19) are connected to the two ends of the same shaft (22), the turbine impeller (13) is located in the turbine volute (12), the compressor impeller (19) is located in the compressor housing (20), the rectifying window (14) and the air baffle (15) are located at the air inlet end of the turbine impeller (13), and the diffuser (18) is located at the exhaust end of the compressor impeller (19).

4. The self-regulating aviation turbine according to claim 3, characterized in that: Also includes: A casing assembly (16), wherein two ends of the casing assembly (16) are respectively connected to the turbine volute (12) and the compressor casing (20); A bearing housing assembly (17) is provided in a housing assembly (16), and the shaft (22) is rotatably connected in the bearing housing assembly (17) via a bearing (21).

5. The self-regulating aviation turbine according to claim 3 or 4, characterized in that: A controller is provided on the outer surface of the turbine volute (12).

6. The self-regulating aviation turbine according to claim 1, characterized in that: The inlet of the electric valve (3) is connected to the first branch, the inlet of the compressor (2) is connected to the second branch, the first branch and the second branch are connected to the main pipeline after being combined, and the main pipeline is provided with a first flow meter (4) and a first pipeline temperature sensor (5).

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