A bi-directional power output engine

Abstract

The application relates to a bidirectional power output engine in the technical field of aero-engines, which comprises an accessory drive device, an air inlet device, a gas generating device, an exhaust device and a speed reduction transmission device arranged along the axial direction of the bidirectional power output engine in sequence, the inner side of the air inlet end of the exhaust device is provided with a bidirectional power output device which sequentially penetrates through the gas generating device, the air inlet device and the accessory drive device, the bidirectional power transmission device extracts the power of the gas generating device, and the end of the speed reduction transmission device which extends into the exhaust flow channel of the exhaust device is connected with the end of the bidirectional power transmission device which is far away from the gas generating device. The bidirectional power output of the free turbine can not only meet the power demand of a propeller, but also provide an interface for driving a high-power motor, thereby meeting the power demand of an airplane.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, and specifically relates to a bidirectional power output engine. Background Technology

[0002] Currently, conventional aviation gas turbine propeller engines drive the propeller to rotate through a gearbox, generating thrust or pull. Mechanical power is extracted from the gas generator by accessory drives to start the generator to generate electricity for aircraft equipment. If necessary, a small power extraction device, such as a hydraulic pump, is installed on the gearbox.

[0003] With technological advancements, the demand for radar, machine vision, and electronic countermeasures is increasing, leading to a growing number of electronic devices installed on aircraft. In fields such as civil emergency rescue, geographical surveying, and fire prevention and disaster relief, aircraft are also required to carry more electrical equipment, such as airborne communication base stations, electromagnetic instruments, magnetometers, and pods, which increases the demand for electricity and extends over long periods. The existing starting generators cannot provide sufficient power to meet the electrical power requirements of aircraft.

[0004] To address the aforementioned problems, this invention provides a bidirectional power output engine that, while meeting the propeller's power requirements, also provides an interface for driving a high-power motor, thus satisfying the aircraft's electrical needs and enabling the engine to operate in an economical and efficient manner. Summary of the Invention

[0005] To address the aforementioned problems, this invention provides a bidirectional power output engine, comprising an accessory transmission device, an intake device, a gas generator, an exhaust device, and a reduction transmission device arranged sequentially along the axial direction of the bidirectional power output engine. The invention is characterized in that a bidirectional power output device is provided inside the intake end of the exhaust device, passing sequentially through the gas generator, the intake device, and the accessory transmission device. The bidirectional power output device extracts power from the high-temperature, high-pressure gas discharged from the gas generator. One end of the reduction transmission device extending into the exhaust channel of the exhaust device is connected to the end of the bidirectional power output device furthest from the gas generator.

[0006] The bidirectional power output device includes a free turbine located inside the intake end of the exhaust device and a turbine transmission shaft connecting the free turbine and the reduction gear transmission device.

[0007] The turbine transmission shaft includes a connecting shaft and a power output shaft connected sequentially along the axial direction. The power output shaft is connected to the input end of the speed reduction transmission device. The free turbine is disposed on the connecting shaft. The end of the connecting shaft away from the power output shaft is provided with a power output shaft.

[0008] Furthermore, the aspect ratio of the connecting shaft is greater than 25.

[0009] Furthermore, the connecting shaft includes an elongated shaft, a mounting flange, and a turbine shaft connected sequentially along the axial direction. The mounting flange is connected to the free turbine. The power front output shaft is disposed on the elongated shaft, and the power rear output shaft is connected to the turbine shaft.

[0010] Furthermore, the end of the slender shaft away from the mounting flange is provided with a first spline, and the power front output shaft is disposed on the first spline.

[0011] Furthermore, the slender shaft is provided with a balancing boss at the location between the first spline and the mounting flange.

[0012] Furthermore, the slender shaft is provided with an anti-collision boss at the location between the balancing boss and the mounting flange.

[0013] Furthermore, the gas generating device includes a compressor connected to the intake end of the intake device, a combustion chamber connected to the compressor, a gas turbine disposed at the exhaust end of the combustion chamber, and a tie rod connecting the gas turbine and the compressor.

[0014] Furthermore, the anti-collision protrusion is housed within the pull rod, and the inner wall of the pull rod is provided with a limiting ring corresponding to the position of the anti-collision protrusion.

[0015] Furthermore, the end of the pull rod away from the compressor is connected to the accessory transmission device.

[0016] Furthermore, a second spline is provided at the end of the turbine shaft away from the mounting flange, and the power output shaft is connected to the second spline.

[0017] Compared with the prior art, the beneficial effects of the present invention are:

[0018] 1) The free turbine of the present invention can output power in both directions, which not only meets the power requirements of the propeller, but also provides an interface for driving a high-power motor, thus meeting the aircraft's power requirements.

[0019] 2) This invention extracts power from a free turbine, which does not affect the overall performance of the engine.

[0020] 3) This invention enables the engine to operate in an economical and efficient state, thereby improving fuel economy.

[0021] 4) The invention provides bidirectional power output, which improves overall stability.

[0022] Other features and advantages of the invention will be set forth in the description which follows, and will be apparent in part from the description, or may be learned by practicing the invention. The objects and other advantages of the invention may be realized and obtained by means of the structures pointed out in the description, claims and drawings. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 A schematic diagram of the structure according to an embodiment of the present invention is shown;

[0025] Figure 2 It shows Figure 1 A magnified view of part A in the image;

[0026] Figure 3 It shows Figure 2 A magnified view of part B in the image;

[0027] Figure 4 A schematic diagram of the turbine transmission shaft is shown.

[0028] Figure 5 A schematic diagram of the accessory drive chain within the accessory drive device is shown;

[0029] Reference numerals: 1. Intake device; 11. Intake passage; 2. Compressor; 21. Tie rod; 22. Limiting ring; 23. Compressor rotor; 3. Combustion chamber; 31. Gas generator rotor; 4. Gas turbine; 41. Gas rotor; 5. Free turbine; 51. Turbine rotor; 6. Exhaust device; 61. Exhaust passage; 62. Exhaust port; 7. Reduction gearbox; 71. Reducer; 711. Input shaft; 72. Bearing system; 73. Stator structure; 8. Turbine transmission shaft; 81. Power output shaft; 82. Connecting shaft; 821. Turbine shaft; 8211. Connecting bearing assembly; 8212. Mounting bearing assembly; 8213. Second spline; 822 823. Mounting flange; 823. Slender shaft; 8231. Anti-collision boss; 8232. Balancing boss; 8233. First spline; 83. Power front output shaft; 831. Support bearing assembly; 9. Accessory transmission device; 91. Accessory transmission chain; 92. First transmission chain; 921. Za gear; 922. Zb transmission gear; 923. Zc transmission gear; 924. Zd transmission gear; 925. Ze gear; 926. Zf gear; 927. Zg gear; 928. Zh gear; 93. Second transmission chain; 931. Zi spur gear; 932. Zj transmission gear; 933. Zk gear; 94. Starter generator; 10. Extraction equipment. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] Figure 1 A schematic diagram of the structure according to an embodiment of the present invention is shown. Figure 1 As shown, a bidirectional power output engine includes an accessory transmission device 9, an intake device 1, a gas generator, an exhaust device 6, and a reduction transmission device 7 arranged sequentially along the axial direction of the bidirectional power output engine. The characteristic feature is that a bidirectional power output device is provided inside the intake end of the exhaust device 6, passing sequentially through the gas generator, the intake device 1, and the accessory transmission device 9. The bidirectional power output device extracts power from the high-temperature, high-pressure gas discharged from the gas generator. One end of the reduction transmission device 7, extending into the exhaust passage 61 of the exhaust device 6, is connected to the end of the bidirectional power output device away from the gas generator.

[0032] The bidirectional power output device includes a free turbine 5 located inside the intake end of the exhaust device 6 and a turbine transmission shaft 8 connecting the free turbine 5 and the reduction transmission device 7.

[0033] The turbine transmission shaft 8 includes a connecting shaft 82 and a power output shaft 81 connected sequentially along the axial direction. The power output shaft 81 is connected to the input end of the speed reduction transmission device 7. The free turbine 5 is disposed on the connecting shaft 82. The end of the connecting shaft 82 away from the power output shaft 81 is provided with a power output shaft 83.

[0034] The bidirectional power output engine achieves bidirectional power output through the turbine transmission shaft 8. The power output shaft 81 can drive the propeller to provide conventional power, while the power output shaft 83 can provide a power interface for the aircraft to carry large electrical equipment, thus meeting the aircraft's power requirements.

[0035] Specifically, the free turbine 5 is supported and fixed to the inside of the intake end of the exhaust device 6 by a cantilever structure. The cantilever structure is existing technology and will not be described in detail here.

[0036] Specifically, the intake device 1, the gas generator, the exhaust device 6, and the speed reduction transmission device 7 are existing technologies, so they will not be described in detail here.

[0037] Figure 5 A schematic diagram of the accessory drive chain 91 within the accessory drive device 9 is shown. (As shown...) Figure 5As shown, in some embodiments, the accessory transmission device 9 includes an accessory transmission chain 91 and a starter generator 94. The accessory transmission chain 91 includes a first transmission chain 92 and a second transmission chain 93. The starter generator 94 is connected to the first transmission chain 92, and the second transmission chain 93 is connected to the pull rod 21. The starter generator 94 can drive the gas generator rotor 31 to rotate, thereby realizing the starting of the engine.

[0038] Specifically, the accessories that need to extract power in the first transmission chain 92 include a fuel electronic control regulator, an oil pump, an alternator, and a gas generator rotor 31. The first transmission chain 92 includes a Za gear 921 mounted on the gas generator rotor 31 of the gas turbine 4, a Zg gear 927 mounted on the starter generator 94, a Zf gear 926 mounted on the fuel electronic control regulator, a Ze gear 925 mounted on the oil pump, a Zh gear 928 mounted on the alternator, a Zb transmission gear 922, a Zc transmission gear 923, and a Zd transmission gear 924. When the engine starts, the Zg gear 927 drives the Za gear 921 to start the engine. When the engine is running normally, it drives the Zb transmission gear 922, Zc transmission gear 923, Zd transmission gear 924, Ze gear 925, Zf gear 926, Zg gear 927, and Zh gear 928 to operate.

[0039] Specifically, the accessories that need to extract power in the second transmission chain 93 include the extraction device 10. The second transmission chain 93 includes a Zk gear 933 set on the extraction device 10, a Zi spur gear 931 set on the slender shaft 823, and a Zj transmission gear 932. The Zi spur gear 931 transmits power to the Zk gear 933 through the Zj transmission gear 932 so that the extraction device 10 can extract power.

[0040] Specifically, the Zi spur gear 931 is mounted on the tie rod 21.

[0041] In some embodiments, the length-to-diameter ratio of the connecting shaft 82 is greater than 25, and the transmission length is long enough to drive the power front output shaft 83 to rotate.

[0042] In some embodiments, the power front output shaft 83 is provided with an extraction device 10; the power of the power front output shaft 83 is extracted to provide power for the aircraft to hit large electrical equipment.

[0043] Specifically, the extraction device 10 can be fixed on the accessory transmission device 9, which can reduce the impact on the engine's frontal area and the aircraft's starting layout.

[0044] Specifically, the extraction device 10 can be selected from, but is not limited to, a high-power generator or a hydraulic pump; the high-power generator provides electricity to the aircraft, and the hydraulic pump provides power to the aircraft.

[0045] Figure 4 A schematic diagram of the turbine transmission shaft 8 is shown. Figure 4 As shown, in some embodiments, the connecting shaft 82 includes an elongated shaft 823, a mounting flange 822, and a turbine shaft 821 connected sequentially along the axial direction. The mounting flange 822 is connected to the free turbine 5. The power front output shaft 83 is disposed on the elongated shaft 823, and the power rear output shaft 81 is connected to the turbine shaft 821. The elongated shaft 823, the mounting flange 822, and the turbine shaft 821 all serve a connecting function.

[0046] Specifically, a support bearing assembly 831 is provided on the power front output shaft 83 and is connected to the casing through the support bearing assembly 831. A connecting bearing assembly 8211 and a mounting bearing assembly 8212 are sequentially provided on the transverse center line of the turbine shaft 821. The support bearing assembly 831, the connecting bearing assembly 8211 and the mounting bearing assembly 8212 are used to support the shaft of the free turbine 5.

[0047] Specifically, the support bearing assembly 831 includes a support bearing and a support bearing housing, the support bearing housing being connected to the housing.

[0048] Specifically, the connecting bearing assembly 8211 includes a roller bearing and a connecting bearing housing, which is connected to the housing.

[0049] Specifically, the bearing mounting assembly 8212 includes an angular contact ball bearing and a bearing mounting housing, which is connected to the housing.

[0050] In some embodiments, the turbine shaft 821 is a hollow structure to achieve weight reduction.

[0051] In some embodiments, the end of the slender shaft 823 away from the mounting flange 822 is provided with a first spline 8233, and the power front output shaft 83 is disposed on the first spline 8233; the first spline 8233 can transmit the mechanical torque of the slender shaft 823 to the power front output shaft 83.

[0052] In some embodiments, the slender shaft 823 is provided with a balancing boss 8232 at the position between the first spline 8233 and the mounting flange 822; the balancing boss 8232 serves to balance the slender shaft 823.

[0053] In some embodiments, the slender shaft 823 is provided with an anti-collision boss 8231 at the position between the balance boss 8232 and the mounting flange 822; the anti-collision boss 8231 can prevent the slender shaft 823 from colliding with the gas generator, thus ensuring the stability of the slender shaft 823.

[0054] In some embodiments, the gas generating device includes a compressor 2 connected to the intake end of the intake device 1, a combustion chamber 3 connected to the compressor 2, a gas turbine 4 disposed at the exhaust end of the combustion chamber 3, and a tie rod 21 connecting the gas turbine 4 and the compressor 2; the tie rod 21 serves to connect the gas turbine 4 and the compressor 2, ensuring the stability of the gas turbine 4 and the compressor 2.

[0055] Figure 2 It shows Figure 1 A magnified view of part A in the image. (For example...) Figure 2 As shown, the gas rotor 41 of the gas turbine 4 is connected to the compressor rotor 23 of the compressor 2 via a tie rod 21.

[0056] Figure 3 It shows Figure 2 A magnified view of part B in the image. (See image below.) Figure 3 As shown, in some embodiments, the anti-collision protrusion 8231 is housed within the tie rod 21, and the inner wall of the tie rod 21 is provided with a limiting ring 22 corresponding to the position of the anti-collision protrusion 8231; the tie rod 21 provides installation conditions for the limiting ring 22; when the turbine transmission shaft 8 experiences excessive deflection, the limiting ring 22 limits the deflection to prevent the turbine transmission shaft 8 from becoming unstable and to protect the stability of the rotor dynamics system of the engine rotor system.

[0057] Specifically, the distance between the limiting ring 22 and the anti-collision protrusion 8231 can be selected but is not limited to 2-4mm.

[0058] In some embodiments, the end of the pull rod 21 away from the compressor 2 is connected to the accessory transmission device 9; the pull rod 21 serves to connect the compressor 2 and the accessory transmission device 9, and the pull rod 21 provides a space for the slender shaft 823, providing the conditions for the power front output shaft 83 to transmit power.

[0059] In some embodiments, the turbine shaft 821 is provided with a second spline 8213 at the end away from the mounting flange 822, and the power output shaft 81 is connected to the second spline 8213; the second spline 8213 can transmit the mechanical torque of the turbine shaft 821 to the power output shaft 81, and the power output shaft 81 can drive the reduction gear 7 to rotate.

[0060] In some embodiments, the speed reduction transmission device 7 includes a speed reducer 71, the output end of which is provided with a bearing system 72 and a stator structure 73 in sequence, and the power output shaft 81 is connected to the input shaft 711 of the speed reducer 71; the power output shaft 81 transmits power to the speed reducer 71.

[0061] Specifically, the power output shaft 81 is optional but not limited to an eccentric compensation shaft.

[0062] The working principle of the bidirectional power output engine is as follows:

[0063] Bidirectional power output is achieved using the free turbine 5 and turbine transmission shaft 8. Air enters the compressor 2 through the intake passage 11 of the intake device 1. The compressor 2 drives the air along the passage to compress it and connect it to the combustion chamber 3. In the combustion chamber 3, the air mixes and burns with fuel to form high-temperature and high-pressure gas. The gas turbine 4 extracts power from the gas and drives the rotor of the gas turbine 4 and the compressor 2 to rotate continuously. The free turbine 5 extracts power from the gas and drives the rotor of the free turbine 5 and the reducer 71 to rotate. The gas flowing through the power output device is discharged through the exhaust passage 61 of the exhaust device 6 and the exhaust port 62 connected to the exhaust passage 61. Because the turbine rotor 51 of the free turbine 5... Power is extracted from the gas. The turbine shaft 821 extracts power from the free turbine 5 and transmits the power to the reducer 71 through the power output shaft 81. It also transmits the power to the power output shaft 83 through the slender shaft 823, that is, to the extraction device 10. The power output shaft 81 outputs the engine's power, and the power output shaft 83 also outputs the engine's power, realizing bidirectional output. During the operation of the turbine transmission shaft 8, when the turbine transmission shaft 8 has excessive deflection, the limiting ring 22 limits the deflection to prevent the turbine transmission shaft 8 from becoming unstable and to protect the stability of the rotor dynamics system of the engine rotor system.

[0064] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A bidirectional power output engine, comprising an accessory transmission device (9), an intake device (1), a gas generator, an exhaust device (6), and a reduction transmission device (7) arranged sequentially along the axial direction of the bidirectional power output engine, characterized in that, The inner side of the air inlet end of the exhaust device (6) is provided with a bidirectional power output device that passes through the gas generator, the air inlet device (1), and the accessory transmission device (9) in sequence. The bidirectional power output device extracts power from the high temperature and high pressure gas discharged from the gas generator. One end of the deceleration transmission device (7) extends into the exhaust flow channel (61) of the exhaust device (6) and is connected to the end of the bidirectional power transmission device away from the gas generator. The bidirectional power output device includes a free turbine (5) located inside the intake end of the exhaust device (6) and a turbine transmission shaft (8) connecting the free turbine (5) and the reduction transmission device (7). The turbine transmission shaft (8) includes a connecting shaft (82) and a power output shaft (81) connected in sequence along the axial direction. The power output shaft (81) is connected to the input end of the speed reduction transmission device (7). The free turbine (5) is set on the connecting shaft (82). The end of the connecting shaft (82) away from the power output shaft (81) is provided with a power output shaft (83).

2. The bidirectional power output engine according to claim 1, characterized in that, The length-to-diameter ratio of the connecting shaft (82) is >25.

3. The bidirectional power output engine according to claim 1, characterized in that, The connecting shaft (82) includes an slender shaft (823), a mounting flange (822), and a turbine shaft (821) connected sequentially along the axial direction. The mounting flange (822) is connected to the free turbine (5). The power front output shaft (83) is disposed on the slender shaft (823), and the power rear output shaft (81) is connected to the turbine shaft (821).

4. A bidirectional power output engine according to claim 3, characterized in that, The slender shaft (823) has a first spline (8233) at one end away from the mounting flange (822), and the power front output shaft (83) is disposed on the first spline (8233).

5. A bidirectional power output engine according to claim 4, characterized in that, The slender shaft (823) is provided with a balancing boss (8232) at the position between the first spline (8233) and the mounting flange (822).

6. A bidirectional power output engine according to claim 5, characterized in that, The slender shaft (823) is provided with an anti-collision boss (8231) at the position between the balance boss (8232) and the mounting flange (822).

7. A bidirectional power output engine according to any one of claims 1 to 6, characterized in that, The gas generating device includes a compressor (2) connected to the intake end of the intake device (1), a combustion chamber (3) connected to the compressor (2), a gas turbine (4) located at the exhaust end of the combustion chamber (3), and a tie rod (21) connecting the gas turbine (4) and the compressor (2).

8. A bidirectional power output engine according to claim 6, characterized in that, The anti-collision protrusion (8231) is housed in the pull rod (21), and the inner wall of the pull rod (21) is provided with a limiting ring (22) corresponding to the position of the anti-collision protrusion (8231).

9. A bidirectional power output engine according to claim 7, characterized in that, The end of the pull rod (21) away from the compressor (2) is connected to the accessory transmission device (9).

10. A bidirectional power output engine according to claim 3, characterized in that, The turbine shaft (821) has a second spline (8213) at one end away from the mounting flange (822), and the power output shaft (81) is connected to the second spline (8213).

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