Four-wheel type serial self-balancing aerial turbine

Abstract

The application discloses a four-wheel type serial self-balancing aviation turbine, which comprises a compressor end cover, a first support, a first flow guide shell, an outer shell, a flow straightening window, a partition plate, a second flow guide shell, a second support, a turbine end cover, a second turbine impeller, a fastening screw, a bearing, a second compressor impeller, a first turbine impeller, a shaft and a first compressor impeller. The two-stage turbine and the two-stage compressor in the aviation turbine are symmetrically distributed on the shaft, and the axial load self-balancing function can be realized. The aviation turbine product has the characteristics of small volume, compact structure, high efficiency, small flow, large pressure rise and load self-balancing, and can realize the functions of greatly improving the mechanical efficiency and the pressurization capacity of the aviation turbine product, reducing the working axial load of the bearing and improving the reliability of the aviation turbine product.

Description

Technical Field

[0001] This invention relates to a high-efficiency four-wheel tandem self-balancing aircraft turbine, belonging to the technical fields of aircraft environmental control systems and electromechanical / oxygen systems, and is particularly suitable for aircraft turbines in integrated environmental control systems that combine boosting, oxygenation, and cooling. Background Technology

[0002] Turbines are a crucial component of aircraft environmental control systems and electromechanical / oxygen systems, primarily used to cool, depressurize, or heat and pressurize the gas introduced into the system to meet its operational requirements. The pressurization, cooling efficiency, and reliability of turbine products have long been challenges in the domestic aviation industry, especially the application of miniaturized, lightweight, high-efficiency, and high-reliability turbines, which is a key research focus. To address the issues of turbine miniaturization, lightweighting, high efficiency, and high reliability, there is an urgent need to design a high-efficiency aviation turbine. Summary of the Invention

[0003] In view of the problems existing in the background technology, the present invention aims to provide a high-efficiency four-wheel tandem self-balancing aero-turbine turbine, which can reduce the size and weight of the turbine product while simultaneously improving the turbine's conversion efficiency and reliability, and to a certain extent alleviate the problem of reduced turbine reliability caused by the continuous increase of turbine operating speed and turbine volume in order to improve the expansion ratio and pressure ratio of current turbine products.

[0004] To solve the above problems, the present invention adopts the following solution:

[0005] A four-wheel tandem self-balancing aircraft turbine, comprising,

[0006] A first compressor impeller, a first turbine impeller, a second compressor impeller, and a second turbine impeller are connected in series on the same shaft. The air intake direction of the first compressor impeller and the second compressor impeller, as well as the air exhaust direction of the first turbine impeller and the second turbine impeller, are all parallel to the axis of the shaft.

[0007] The exhaust direction of the first compressor impeller, the exhaust direction of the second compressor impeller, the intake direction of the first turbine impeller, and the intake direction of the second turbine impeller are all perpendicular to the axis of the shaft.

[0008] In this configuration, the intake direction of the first compressor impeller is opposite to that of the second compressor impeller, the intake direction of the second compressor impeller is the same as that of the first turbine impeller, and the exhaust direction of the first turbine impeller is opposite to that of the second turbine impeller.

[0009] Furthermore, the four-wheeled tandem self-balancing aircraft turbine also includes,

[0010] The turbine inlet is located on a straight line perpendicular to the shaft;

[0011] A turbine outlet, wherein the turbine outlet is disposed at the first axial end of the shaft;

[0012] The compressor inlet is located at the second axial end of the shaft;

[0013] The compressor outlet is located on a straight line intersecting the vertical.

[0014] Alternatively, a non-unidirectional air intake channel is provided between the turbine inlet and the air intake end of the first turbine impeller. The air intake channel includes at least a channel parallel to the axis of the shaft and a channel perpendicular to the axis of the shaft.

[0015] Alternatively, a non-unidirectional exhaust passage is provided between the compressor outlet and the exhaust end of the second compressor impeller, the exhaust passage including at least a passage parallel to the axis of the shaft and a passage perpendicular to the axis of the shaft.

[0016] Alternatively, the intake passage may be equipped with a rectifier window.

[0017] Alternatively, a first gas flow channel with a non-unidirectional flow direction is provided between the exhaust end of the first turbine impeller and the inlet end of the second turbine impeller. The first gas flow channel includes at least a flow channel parallel to the axis of the shaft and a flow channel perpendicular to the axis of the shaft, and the flow channel parallel to the axis of the shaft crosses the second compressor impeller.

[0018] Alternatively, a second gas flow channel with a non-unidirectional flow direction is provided between the exhaust end of the first compressor impeller and the inlet end of the second compressor impeller. The second gas flow channel includes at least a flow channel parallel to the axis of the turbine and a flow channel perpendicular to the axis of the turbine, and the flow channel parallel to the axis of the turbine passes over the first turbine impeller.

[0019] Alternatively, a rectifier window may be provided in the first gas flow channel.

[0020] As an alternative, the four-wheel tandem self-balancing aircraft turbine also includes a compressor end cover, a first support, a first guide shell, an outer shell, a partition, a second guide shell, a second support, a turbine end cover, and bearings, wherein:

[0021] The compressor end cover is coaxially mounted at the air inlet end of the first compressor impeller;

[0022] The first support is disposed between the first compressor impeller and the first turbine impeller, and the first support is connected to the shaft via a bearing;

[0023] The first flow guide housing is disposed between the first support and the first turbine impeller;

[0024] The turbine end cover is coaxially mounted at the exhaust end of the second turbine impeller;

[0025] The second support is located between the second compressor impeller and the second turbine impeller, and the second support is connected to the shaft via another bearing;

[0026] The second flow guide housing is disposed between the second support and the second compressor impeller;

[0027] A baffle is disposed between the first turbine impeller and the second compressor impeller;

[0028] The outer casing is located between the compressor end cover and the turbine end cover, and the shaft, the first compressor impeller, the first turbine impeller, the second compressor impeller, the second turbine impeller, the first support, the first guide housing, the partition, the second guide housing, the second support and the bearing are located in the space area formed by the outer casing, the compressor end cover and the turbine end cover.

[0029] A first gas flow channel with a non-unidirectional flow direction is formed between the first support, the first guide shell and the outer shell, between the exhaust end of the first turbine impeller and the inlet end of the second turbine impeller.

[0030] A second gas flow channel with a non-unidirectional flow direction is formed between the outer shell, the second guide shell, and the second support, between the exhaust end of the first compressor impeller and the inlet end of the second compressor impeller.

[0031] Alternatively, the outer casing is provided with a turbine inlet and a compressor outlet, the compressor end cover is provided with a compressor inlet, and the turbine end cover is provided with a turbine outlet.

[0032] Alternatively, the first compressor impeller and the second turbine impeller are fixed to the axial ends of the shaft by fastening screws.

[0033] Compared with existing technologies, this invention can be applied to the internal systems of aircraft environmental control systems or oxygen generation systems. Compared with the turbine products currently used on aircraft, the aircraft turbine product of this invention has a compact structure, smaller external dimensions and weight, and higher efficiency than the old turbine. The four-wheel "back-to-back" mounting structure can effectively reduce the axial load of the turbine product during operation, and can significantly improve the operational reliability of the aircraft turbine product.

[0034] This invention is applied inside the oxygen supply subsystem of an aircraft's oxygen system. As an accessory to the oxygen supply subsystem, it can pressurize and heat the gas introduced into the system for use by the next stage molecular sieve. This aerospace turbine has the characteristics of small flow rate, large pressure rise, and high efficiency.

[0035] The aero-turbine product of this invention adopts a four-wheel coaxial series structure, changing the traditional design approach of increasing turbine operating speed and turbine volume. This invention contains two-stage turbines and two-stage compressors, which can perform two-stage expansion work on the gas entering the turbine side, maximizing the conversion of the gas's internal energy into mechanical energy. This mechanical energy is then coaxially driven to compress the entering gas into the two-stage compressor impellers, supplying the compressed air to the oxygen system. The two-stage turbines and two-stage compressors are symmetrically distributed on the shaft, enabling axial load self-balancing. The aero-turbine product of this invention features small size, compact structure, high efficiency, low flow rate, large pressure rise, and load self-balancing, significantly improving the mechanical efficiency and pressurization capacity of aero-turbine products, reducing the axial load on bearings, and enhancing the reliability of aero-turbine products. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of the structure of the aircraft turbine of the present invention;

[0037] Figure 2 This is a schematic diagram illustrating the working principle of the aircraft turbine of this invention;

[0038] Figure 3 This is a schematic diagram of the self-balancing matching principle of the axial load of the aero-turbine in this invention;

[0039] In the figure: 1. Compressor end cover, 2. First support, 3. First guide shell, 4. Outer shell, 5. Rectifier window, 6. Baffle, 7. Second guide shell, 8. Second support, 9. Turbine end cover, 10. Second turbine impeller, 11. Fastening screw, 12. Bearing, 13. Second compressor impeller, 14. First turbine impeller, 15. Shaft, 16. First compressor impeller. Detailed Implementation

[0040] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. However, it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments. All modifications, substitutions and alterations made based on ordinary technical knowledge and common practices in the art without departing from the above-described technical concept of the present invention are included within the scope of the present invention.

[0041] like Figure 1 As shown, this is a high-efficiency four-wheel tandem self-balancing aircraft turbine. The entire aircraft turbine shaft includes a compressor end cover 1, a first support 2, a first guide shell 3, an outer shell 4, a flow rectifier window 5, a baffle 6, a second guide shell 7, a second support 8, a turbine end cover 9, a second turbine impeller 10, fastening screws 11, a bearing 12, a second compressor impeller 13, a first turbine impeller 14, a shaft 15, and a first compressor impeller 16.

[0042] The baffle 6 is press-fitted inside the outer shell 4. The flow-rectifying window 5 is placed on the end face of the baffle 6 and is fixed by the first flow guide shell 3. The first support 2, the second support 8, and the second flow guide shell 7 are respectively installed inside the outer shell 4 and distributed on both sides of the baffle 6. They are pressed and fixed inside the outer shell 4 by the compressor end cover 1 and the turbine end cover 9. The first turbine impeller 14, the second turbine impeller 10, the first compressor impeller 16, the second compressor impeller 13, and the bearing 12 are respectively strung on both sides of the baffle 6 on the shaft 15 and are symmetrically distributed about the center of the baffle 6. That is, the distance from the second turbine impeller 10 and the first compressor impeller 16 to the baffle 6 is equal (symmetrical distribution), and the distance from the second compressor impeller 13 and the first turbine impeller 14 to the baffle 6 is equal (symmetrical distribution).

[0043] This invention is a high-efficiency four-wheel tandem self-balancing aero turbine design, which adopts a four-wheel coaxial tandem structure. The first turbine impeller 14, the second turbine impeller 10, the first compressor impeller 16, the second compressor impeller 13 and two bearings 12 are respectively tandemly mounted on both sides of the shaft 15.

[0044] like Figure 2 As shown, in the design of this invention, the assembly relationship (spatial position relationship, such as the second flow guide shell 7 and the second support 8) between the outer shell 4, the first flow guide shell 3, the second support 8, the second flow guide shell 7, and the first support 2, the external outline (the cavity constructed by the external outlines of different components, such as the cavity between the outer shell 4 and the first support 2), and the structural cavity (the cavity designed by the components themselves, such as...) are all considered in this design. Figure 2 The cavity parallel to shaft 15 near the turbine inlet of the outer casing 4 forms an air passage, namely... Figure 2 The channels indicated by the solid and dashed arrows.

[0045] like Figure 2As shown, the working principle of the four-wheel tandem self-balancing aircraft turbine of the present invention is as follows: Air introduced from the system enters the turbine side through the outer casing 4, is rectified by the rectifier window 5, and then radially enters the first turbine impeller 14 for the first expansion and work, converting part of the gas's internal energy into mechanical energy and reducing the gas's temperature and pressure. The gas flowing out of the axial outlet of the first turbine impeller 14 flows into the rectifier window 5 through the channel formed by the first support 2, the first guide shell 3, and the outer casing 4, and then enters the tandem second turbine impeller 10 for the second expansion and work, further converting the gas's internal energy into mechanical energy and further reducing the gas's temperature and pressure. Finally, the gas is discharged from the axial outlet of the second turbine impeller 10. The mechanical energy converted from the expansion work of the first turbine impeller 14 and the second turbine impeller 10 is transmitted coaxially through the shaft 15 and the bearing 12, driving the first compressor impeller 16 to perform the first compression work on the gas entering the impeller from the axial direction, thereby increasing the gas pressure and temperature. Then, the gas flows from the radial outlet of the first compressor impeller 16 into the channel formed by the second support 8, the second guide shell 7 and the outer shell 4, and enters the second compressor impeller 13 connected in series for the second compression work, further increasing the gas pressure and temperature to meet the gas pressure and temperature requirements of the system.

[0046] Figure 2 In the diagram, the arrows indicate the direction of gas flow, with solid arrows indicating gas flow on the turbine side and dashed arrows indicating gas flow on the compressor side.

[0047] Inside the aircraft turbine, the first turbine impeller 14, the second turbine impeller 10, the first compressor impeller 16, and the second compressor impeller 13 are symmetrically distributed and mounted in series on both sides of the shaft. Furthermore, the first turbine impeller 14, the second turbine impeller 10, the first compressor impeller 16, and the second compressor impeller 13 are all installed back-to-back. Figure 3As shown in the figure, the first compressor impeller 16, the second compressor impeller 13, the first turbine impeller 14, and the second turbine impeller 10 are arranged "back-to-back" (here, "back" refers to the back of the impeller, and "back-to-back" means that the back of the first compressor impeller 16 is installed opposite the back of the second compressor impeller 13, and the back of the first turbine impeller 14 is installed opposite the back of the second turbine impeller 10. This installation arrangement can minimize the vector sum of axial aerodynamic loads, reduce the load on the bearings, and improve product reliability). F1 is... F1 represents the inward force of the first compressor impeller 16 blade, F2 represents the back force of the first compressor impeller 16 blade, F3 represents the inward force of the first turbine impeller 14 blade, F5 represents the back force of the first turbine impeller 14 blade, F4 represents the back force of the second compressor impeller 13 blade, F6 represents the inward force of the second compressor impeller 13 blade, F7 represents the back force of the second turbine impeller 10 blade, and F8 represents the inward force of the second turbine impeller 10 blade. The solid and dashed arrows are only used to distinguish directions. Therefore, the vector sum of the axial load resultant forces F1+F2+F3+F4+F5+F6+F7+F8 tends to 0. During operation, the aerodynamic axial loads generated by the aero-turbine turbine cancel each other out among the four impellers, causing the axial vector sum of the turbine to approach zero. This reduces the load borne by bearing 12 during operation, thereby improving the reliability of the aero-turbine turbine.

[0048] The above description is merely one specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A four-wheeled, tandem, self-balancing aerial turbine, characterized in that: Comprising, a first compressor impeller (16), a first turbine impeller (14), a second compressor impeller (13) and a second turbine impeller (10) are sequentially connected in series on the same shaft (15), the intake direction of the first compressor impeller (16) and the second compressor impeller (13) and the exhaust direction of the first turbine impeller (14) and the second turbine impeller (10) are all parallel to the axial direction of the shaft (15); Wherein, the exhaust direction of the first compressor impeller (16), the exhaust direction of the second compressor impeller (13), the intake direction of the first turbine impeller (14) and the intake direction of the second turbine impeller (10) are all perpendicular to the axial direction of the shaft (15); Wherein, the intake direction of the first compressor impeller (16) is opposite to the intake direction of the second compressor impeller (13), the intake direction of the second compressor impeller (13) is the same as the exhaust direction of the first turbine impeller (14), and the exhaust direction of the first turbine impeller (14) is opposite to the exhaust direction of the second turbine impeller (10); Further comprising a compressor end cover (1), a first support (2), a first flow guide shell (3), an outer shell (4), a partition plate (6), a second flow guide shell (7), a second support (8), a turbine end cover (9) and a bearing (12), wherein: The compressor end cover (1) is coaxially arranged at the intake end of the first compressor impeller (16); The first support (2) is arranged between the first compressor impeller (16) and the first turbine impeller (14), and the first support (2) is connected with the shaft (15) through the bearing (12); The first flow guide shell (3) is arranged between the first support (2) and the first turbine impeller (14); The turbine end cover (9) is coaxially arranged at the exhaust end of the second turbine impeller (10); The second support (8) is arranged between the second compressor impeller (13) and the second turbine impeller (10), and the second support (8) is connected with the shaft (15) through another bearing (12); The second flow guide shell (7) is arranged between the second support (8) and the second compressor impeller (13); The partition plate (6) is arranged between the first turbine impeller (14) and the second compressor impeller (13); The outer shell (4) is arranged between the compressor end cover (1) and the turbine end cover (9), and the shaft (15), the first compressor impeller (16), the first turbine impeller (14), the second compressor impeller (13), the second turbine impeller (10), the first support (2), the first flow guide shell (3), the partition plate (6), the second flow guide shell (7), the second support (8) and the bearing (12) are located in the space region formed by the outer shell (4), the compressor end cover (1) and the turbine end cover (9); The first support (2), the first flow guide shell (3) and the outer shell (4) form a first gas flow channel between the exhaust end of the first turbine impeller (14) and the intake end of the second turbine impeller (10) with a non-single flow direction; The outer shell (4), the second flow guide shell (7) and the second support (8) form a second gas flow channel between the exhaust end of the first compressor impeller (16) and the intake end of the second compressor impeller (13), which is not a single flow direction.

2. A four-wheeled tandem self-balancing aerial turbine according to claim 1, characterized in that: Further comprising, A turbine inlet is arranged on a straight line perpendicular to the shaft (15); A turbine outlet is arranged on the axial first end of the shaft (15); A compressor inlet is arranged on the axial second end of the shaft (15); A compressor outlet is arranged on a straight line perpendicular to the shaft (15).

3. The four-wheeled serial self-balancing aviation turbine according to claim 2, characterized in that: A non-single flow direction intake channel is arranged between the turbine inlet and the intake end of the first turbine impeller (14), which at least includes a channel parallel to the axial direction of the shaft (15) and a channel perpendicular to the axial direction of the shaft (15); A non-single flow direction exhaust channel is arranged between the compressor outlet and the exhaust end of the second compressor impeller (13), which at least includes a channel parallel to the axial direction of the shaft (15) and a channel perpendicular to the axial direction of the shaft (15).

4. A four-wheeled, tandem, self-balancing aerial turbine according to claim 3, characterized in that: A flow straightening window (5) is arranged in the intake channel.

5. The four-wheeled serial self-balancing aviation turbine according to claim 1, characterized in that: A non-single flow direction first gas flow channel is arranged between the exhaust end of the first turbine impeller (14) and the intake end of the second turbine impeller (10), which at least includes a flow channel parallel to the axial direction of the shaft (15) and a flow channel perpendicular to the axial direction of the shaft (15), and the flow channel parallel to the axial direction of the shaft (15) passes through the second compressor impeller (13); A non-single flow direction second gas flow channel is arranged between the exhaust end of the first compressor impeller (16) and the intake end of the second compressor impeller (13), which at least includes a flow channel parallel to the axial direction of the shaft (15) and a flow channel perpendicular to the axial direction of the shaft (15), and the flow channel parallel to the axial direction of the shaft (15) passes through the first turbine impeller (14).

6. A four-wheeled, tandem, self-balancing aerial turbine according to claim 5, characterized in that: A flow straightening window (5) is arranged in the first gas flow channel.

7. The four-wheeled, tandem, self-balancing, aerial turbine of claim 1, wherein: The turbine inlet and the compressor outlet are arranged on the outer shell (4), the compressor inlet is arranged on the compressor end cover (1), and the turbine outlet is arranged on the turbine end cover (9).

8. The four-wheeled tandem self-balancing aerial turbine according to claim 1, wherein: The first compressor impeller (16) and the second turbine impeller (10) are fixed on the axial two ends of the shaft (15) by fastening screws (11).

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