CN113804448B - Two-stage helical gear closed planetary gear reducer and vortex paddle engine thereof - Google Patents
Two-stage helical gear closed planetary gear reducer and vortex paddle engine thereof Download PDFInfo
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- CN113804448B CN113804448B CN202111055408.5A CN202111055408A CN113804448B CN 113804448 B CN113804448 B CN 113804448B CN 202111055408 A CN202111055408 A CN 202111055408A CN 113804448 B CN113804448 B CN 113804448B
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 49
- 230000005540 biological transmission Effects 0.000 claims abstract description 99
- 230000007246 mechanism Effects 0.000 claims abstract description 39
- 239000003921 oil Substances 0.000 claims description 74
- 238000005259 measurement Methods 0.000 claims description 42
- 238000006073 displacement reaction Methods 0.000 claims description 17
- 239000010687 lubricating oil Substances 0.000 claims description 10
- 239000000446 fuel Substances 0.000 claims description 9
- 238000012545 processing Methods 0.000 abstract description 8
- 238000003466 welding Methods 0.000 abstract description 5
- 238000005457 optimization Methods 0.000 abstract description 4
- 238000009826 distribution Methods 0.000 description 8
- 239000000295 fuel oil Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 208000032370 Secondary transmission Diseases 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 125000004122 cyclic group Chemical group 0.000 description 1
- 239000010727 cylinder oil Substances 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/04—Testing internal-combustion engines
- G01M15/05—Testing internal-combustion engines by combined monitoring of two or more different engine parameters
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- General Details Of Gearings (AREA)
Abstract
The application discloses a two-stage helical gear closed planetary gear reducer and a vortex paddle engine thereof. The torque required to be transmitted by each component is further dispersed, the pressure born by each component is correspondingly reduced, and the contact stress of tooth surfaces is correspondingly reduced, so that the reliability and the transmission smoothness between the components are improved, the processing technology of welding the duplex gear is avoided, and the technology difficulty is low. Meanwhile, as the planet carrier and the second driving gear are the final driving parts of the first-stage driving mechanism and the second-stage driving mechanism respectively, the rotating speeds are the same, the calculation of the driving ratio is convenient, and meanwhile, all gears are meshed and driven through the bevel gears, the bevel gears can generate axial force in direct proportion to the torque, and further, the torque and the power of the turboprop can be conveniently measured, so that data support is provided for further optimization iteration of the turboprop.
Description
Technical Field
The application relates to the technical field of engines, in particular to a two-stage helical gear closed planetary gear reducer. In addition, the application also relates to a vortex propeller engine comprising the two-stage helical gear closed planetary gear reducer.
Background
Since the small turbine engine requires high power and high power-to-weight ratio, the speed reducer of the small turbine engine is required to have high transmission ratio, small gear modulus, and difficult strength and reliability to meet the use requirements, and therefore, the speed reducer of the small turbine engine with high power-to-weight ratio and proper processing level needs to be designed.
The existing speed reducer in the turboprop engine is generally connected with a propeller shaft by adopting a straight-tooth inner gear ring and welding a duplex gear, so that multi-point force transmission with compact structure is realized, but the connecting structure can lead to low strength of the inner gear ring and poor transmission smoothness, and the processing technology of electron beam welding of the duplex gear is high in difficulty, so that the speed reducer is not suitable for a small turboprop engine with high power and high rotating speed, and cannot measure torque and power of the turboprop engine, and further, the structure of the turboprop engine cannot be improved and optimized further.
Disclosure of Invention
The application provides a two-stage helical-tooth closed planetary gear reducer and a vortex-type propeller engine thereof, which are used for solving the technical problems that an inner gear ring of a reducer in the existing small-sized vortex-type propeller engine is low in strength, poor in transmission smoothness and high in processing technology difficulty, and meanwhile, torque and power of the vortex-type propeller engine cannot be measured, and further improvement and optimization of the structure of the vortex-type propeller engine cannot be carried out.
According to one aspect of the present application there is provided a two-stage helical gear closed pinion gear reducer for transmitting power to a rotor shaft, comprising a first stage transmission mechanism and a second stage transmission mechanism for transmitting power to the rotor shaft; the first-stage transmission mechanism comprises a power turbine shaft, a first driving gear, a first transmission gear and a planetary frame, wherein the power turbine shaft is used for connecting a power turbine to transmit power, the first driving gear is fixedly connected with the power turbine shaft and used for transmitting power, the first transmission gear is meshed with the first driving gear, and the planetary frame is coaxially arranged with the power turbine shaft and is fixedly connected with the first transmission gear and the paddle shaft respectively; the second-stage transmission mechanism comprises a first transmission gear, a first annular gear meshed with the first transmission gear and used for transmitting power, a second driving gear fixedly connected with the first annular gear and sleeved on the planet carrier and used for transmitting power, a second transmission gear meshed with the second driving gear and used for transmitting power, and a second annular gear meshed with the second transmission gear and fixedly connected with the paddle shaft and used for transmitting power; the first driving gear, the first transmission gear, the first annular gear, the second driving gear, the second transmission gear and the second annular gear are all in helical gear meshed transmission.
Further, the torque measuring system comprises a first annular gear and a second driving gear, a wheel-step bearing which is movably arranged on the pinion rack along the axial direction and used for supporting the wheel-step assembly, an axial torque measuring piston which is connected with the first annular gear and used for axially pushing the first annular gear towards the direction close to the paddle shaft, a linear displacement sensor which is connected with the axial torque measuring piston and used for detecting the displacement of the axial torque measuring piston, a torque measuring pressure sensor which is used for detecting the oil pressure of a torque measuring cylinder in the axial torque measuring piston, and a controller which is respectively connected with the linear displacement sensor and the torque measuring pressure sensor.
Further, the torque measurement system also comprises a torque measurement oil inlet electromagnetic valve for controlling the external oil pipe to pressurize the oil inlet of the torque measurement oil cylinder in the axial torque measurement piston, and a clutch friction disc bearing connected with the axial torque measurement piston and used for supporting the straddle assembly when the torque measurement system is used for measuring torque.
Further, the secondary transmission mechanism further comprises a first connecting web plate fixedly connected with the first annular gear and the second driving gear respectively and a second connecting web plate fixedly connected with the second annular gear and the paddle shaft respectively.
Further, a first elastic clamping ring is arranged at the joint of the first annular gear, and a first clamping plate which is connected with the first elastic clamping ring and used for limiting the axial movement of the first annular gear is arranged on the first connecting web plate; and/or the joint of the second annular gear is provided with a second elastic clamping ring, and the second connecting web plate is provided with a second clamping plate which is connected with the second elastic clamping ring and used for limiting the axial movement of the second annular gear.
Further, the device also comprises a lightening hole which is arranged along the axial direction of the speed reducer and an oil hole which is arranged along the radial direction of the speed reducer and is used for connecting an external oil pipe.
Further, the device also comprises a gear frame for installing a second transmission gear, an oil distribution plunger which is arranged in the inner cavity of the planetary frame along the axial direction of the speed reducer and communicated with the inner cavity of the propeller shaft, and an oil distribution bushing which is sleeved on the planetary frame and communicated with the oil distribution plunger, wherein an oil path in the gear frame which is communicated with the oil hole is arranged in the gear frame, and an oil path in the second transmission gear which is respectively communicated with the oil path in the gear frame and the oil distribution bushing is arranged in the second transmission gear.
Further, the device also comprises a fuel heat exchanger pipe joint used for connecting the fuel heat exchanger to convey fuel into the oil way in the gear rack.
Further, the bottom of the speed reducer also comprises an oil collecting tank for collecting lubricating oil.
According to another aspect of the application there is also provided a turboprop engine comprising a two-stage helical gear closed-loop pinion reducer as described above.
The application has the following beneficial effects:
according to the two-stage helical gear closed planetary gear reducer and the vortex paddle engine thereof, the torque of the power turbine shaft is transmitted to the paddle shaft through the first-stage transmission mechanism and the second-stage transmission mechanism, the first-stage transmission mechanism sequentially transmits the torque to the paddle shaft through the power turbine shaft, the first driving gear, the first transmission gear and the planetary rack, and the second-stage transmission mechanism sequentially transmits the torque to the paddle shaft through the first transmission gear, the first annular gear, the second driving gear, the second transmission gear and the second annular gear. The second-stage transmission mechanism sequentially transmits torque through a plurality of transmission parts, the transmission ratio is greatly improved after multiple transmissions, so that the input high rotating speed of the power turbine shaft is converted into the output low rotating speed of the rotating shaft, and as the first-stage transmission mechanism and the second-stage transmission mechanism are provided with the first transmission gears of the common transmission parts, the torque is finally transmitted to the propeller shaft, the torque required to be transmitted by each part is further dispersed, the pressure born by each part is correspondingly reduced, the contact stress of tooth surfaces is correspondingly reduced, the reliability and the transmission smoothness between the parts are improved, the processing technology of welding the duplex gears is avoided, and the technology difficulty is low. Meanwhile, as the planet carrier and the second driving gear are the final driving parts of the first-stage driving mechanism and the second-stage driving mechanism respectively, the rotating speeds are the same, the calculation of the driving ratio is convenient, and meanwhile, all gears are meshed and driven through the bevel gears, the bevel gears can generate axial force in direct proportion to the torque, and further, the torque and the power of the turboprop can be conveniently measured, so that data support is provided for further optimization iteration of the turboprop.
In addition to the objects, features and advantages described above, the present application has other objects, features and advantages. The present application will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic diagram of a two-stage helical gear closed pinion gear reducer in accordance with a preferred embodiment of the present application.
Legend description:
1. a first stage transmission mechanism; 11. a power turbine shaft; 12. a first drive gear; 13. a planet carrier; 2. a second stage transmission mechanism; 21. a first transmission gear; 22. a first ring gear; 23. a first connecting web; 24. a second drive gear; 25. a second transmission gear; 26. a second ring gear; 27. a second connecting web; 3. a paddle shaft; 4. a torsion measuring system; 41. a step wheel bearing; 42. an axial torsion measuring piston; 43. a linear displacement sensor; 44. a torque measurement pressure sensor; 45. a torque-measuring oil inlet electromagnetic valve; 46. clutch friction disc bearings; 5. an oil hole; 6. a gear frame; 7. an oil separating plunger; 8. an oil distribution bushing; 9. a fuel oil heat exchanger pipe joint; 10. and (5) an oil collecting tank.
Detailed Description
Embodiments of the application are described in detail below with reference to the attached drawing figures, but the application can be practiced in a number of different ways, as defined and covered below.
FIG. 1 is a schematic diagram of a two-stage helical gear closed pinion gear reducer in accordance with a preferred embodiment of the present application.
As shown in fig. 1, the two-stage helical gear closed planetary gear reducer of the present embodiment is used for transmitting power to a paddle shaft 3, and comprises a first-stage transmission mechanism 1 and a second-stage transmission mechanism 2 for transmitting power to the paddle shaft 3; the first-stage transmission mechanism 1 comprises a power turbine shaft 11 for connecting a power turbine to transmit power, a first driving gear 12 fixedly connected with the power turbine shaft 11 and used for transmitting power, a first transmission gear 21 meshed with the first driving gear 12, and a planet carrier 13 coaxially arranged with the power turbine shaft 11 and fixedly connected with the first transmission gear 21 and the paddle shaft 3 respectively; the second-stage transmission mechanism 2 comprises a first transmission gear 21, a first annular gear 22 meshed with the first transmission gear 21 and used for transmitting power, a second driving gear 24 fixedly connected with the first annular gear 22 and sleeved on the planet carrier 13 and used for transmitting power, a second transmission gear 25 meshed with the second driving gear 24 and used for transmitting power, and a second annular gear 26 meshed with the second transmission gear 25 and fixedly connected with the paddle shaft 3; the first driving gear 12, the first transmission gear 21, the first annular gear 22, the second driving gear 24, the second transmission gear 25 and the second annular gear 26 are all in helical gear engagement transmission. Specifically, the two-stage helical gear closed planetary gear reducer and the vortex paddle engine thereof transmit torque of a power turbine shaft 11 to a paddle shaft 3 through a first-stage transmission mechanism 1 and a second-stage transmission mechanism 2 respectively, the first-stage transmission mechanism 1 sequentially transmits the torque to the paddle shaft 3 through the power turbine shaft 11, a first driving gear 12, a first transmission gear 21 and a planetary frame 13, and the second-stage transmission mechanism 2 sequentially transmits the torque to the paddle shaft 3 through the first transmission gear 21, a first annular gear 22, a second driving gear 24, a second transmission gear 25 and a second annular gear 26. The second-stage transmission mechanism 2 sequentially transmits torque through a plurality of transmission components, the transmission ratio is greatly improved after multiple transmissions, so that the input high rotation speed of the power turbine shaft 11 is converted into the output low rotation speed of the rotating shaft, and as the first-stage transmission mechanism 1 and the second-stage transmission mechanism 2 are provided with the first transmission gear 21 which is a common transmission component and finally transmit the torque to the propeller shaft 3, the torque required to be transmitted by each component is further dispersed, the pressure born by each component is correspondingly reduced, the contact stress of tooth surfaces is correspondingly reduced, the reliability and the transmission smoothness between the components are improved, the processing technology of welding the duplex gears is avoided, and the process difficulty is low. Meanwhile, as the planet carrier 13 and the second driving gear 24 are the final driving parts of the first-stage driving mechanism 1 and the second-stage driving mechanism 2 respectively, the rotating speeds are the same, the calculation of the driving ratio is facilitated, meanwhile, all gears are meshed and driven through the bevel gears, the bevel gears can generate axial force in direct proportion to the torque, the torque and the power of the turboprop can be conveniently measured, and data support is provided for further optimization iteration of the turboprop. Optionally, the first driving gears 21 are provided with 4, the first driving gears 12 are respectively meshed with the 4 first driving gears 21 for transmission, the contact ratio is high, the transmission is stable, and the axial force generated by the helical gears on the first driving gears 12 can be partially offset with the axial force of the power turbine, so that the service life of the power turbine shaft 11 is prolonged.
As shown in fig. 1, the present embodiment further includes a torsion measurement system 4 and a jumper stage assembly, the jumper stage assembly includes a first ring gear 22 and a second driving gear 24, and the torsion measurement system 4 includes a jumper stage bearing 41 movably mounted on the pinion carrier 13 in an axial direction for supporting the jumper stage assembly, an axial torsion measurement piston 42 connected to the first ring gear 22 for axially pushing the first ring gear 22 in a direction approaching the paddle shaft 3, a linear displacement sensor 43 connected to the axial torsion measurement piston 42 for detecting a displacement of the axial torsion measurement piston 42, a torsion measurement pressure sensor 44 for detecting an oil pressure of a torsion measurement cylinder in the axial torsion measurement piston 42, and a controller connected to the linear displacement sensor 43 and the torsion measurement pressure sensor 44, respectively. Specifically, when the cross-wheel stage assembly is pushed to the propeller shaft 3 by the axial torque measuring piston 42, the axial force generated by the helical gear is unloaded through the axial movement of the cross-wheel stage bearing 41, and the axial force of the cross-wheel stage assembly is equal to the oil pressure in the hydraulic cylinder of the axial torque measuring piston 42, then the controller controls the linear displacement sensor 43 and the torque measuring pressure sensor 44 to measure in real time so as to obtain the relation curve of the displacement of the axial torque measuring piston 42 and the oil pressure in the hydraulic cylinder thereof, and further obtain the value of the axial force of the cross-wheel stage assembly, so that the torque of the propeller shaft 3 is converted. Optionally, the torque measurement system 4 further includes a display screen connected to the controller for displaying measurement data of the linear displacement sensor 43 and the torque measurement pressure sensor 44, and a converter for interpreting real-time torque according to the measurement data of the linear displacement sensor 43 and the torque measurement pressure sensor 44, where the display screen is further configured to display the real-time torque interpreted and converted by the converter, so that the display screen displays the real-time torque when the torque measurement is performed.
As shown in fig. 1, in this embodiment, the torque measurement system 4 further includes a torque measurement oil inlet solenoid valve 45 for controlling the external oil pipe to pressurize the torque measurement oil cylinder oil inlet in the axial torque measurement piston 42, and a clutch friction disc bearing 46 connected to the axial torque measurement piston 42 for supporting the straddle carrier assembly during torque measurement of the torque measurement system 4. Specifically, when the speed reducer does not measure torsion, the hydraulic oil pipe of the axial torsion measurement piston 42 is mutually communicated with the oil return pump, and slight negative pressure is generated, at this time, the clutch friction disc bearing 46 is not contacted with the first annular gear 22, the axial force of the wheel-span assembly is borne by the wheel-span bearing 41, the torsion measurement system 4 does not work, no energy is consumed, and no real-time torque is displayed. When the speed and the power of the speed reducer change and torque is required to be measured, the controller controls the torque measuring oil inlet electromagnetic valve 45 to be opened, so that an external oil pipe pressurizes oil inlet of a torque measuring cylinder in the axial torque measuring piston 42, and meanwhile, displacement of the axial torque measuring piston 42 and internal oil pressure are detected, so that a relation curve between the displacement of the axial torque measuring piston 42 and oil pressure in a hydraulic cylinder of the axial torque measuring piston 42 is obtained when the displacement of the axial torque measuring piston 42 suddenly changes or changes back and forth, and further, axial force of the wheel-span assembly is obtained, and torque of the propeller shaft 3 is converted through a converter and is displayed on a display screen. When the torque measurement system 4 works, the axial force of the cross wheel stage assembly is borne by the clutch friction disc bearing 46, so that the oil leakage amount of the hydraulic oil cylinder of the axial torque measurement piston 42 is small, the consumed energy is also small, and the power loss during torque measurement of the torque measurement system 4 is reduced to the greatest extent.
As shown in fig. 1, in this embodiment, the secondary transmission mechanism further includes a first connecting web 23 fixedly connected to the first ring gear 22 and the second driving gear 24, and a second connecting web 27 fixedly connected to the second ring gear 26 and the propeller shaft 3. Specifically, the first connecting web 23 is obliquely arranged to be fixedly connected with the first annular gear 22 and the second driving gear 24 respectively, so that power transmission is realized; the second connecting web 27 is obliquely arranged to be fixedly connected with the second annular gear 26 and the paddle shaft 3 respectively, so that power transmission is realized.
As shown in fig. 1, in this embodiment, the connection portion of the first ring gear 22 is provided with a first elastic collar, and the first connecting web 23 is provided with a first clamping plate connected to the first elastic collar for limiting the axial movement of the first ring gear 22. Specifically, the first clamping plate clamps the first elastic collar by a ring of samming screws to determine the axial position of the first ring gear 22. Optionally, the first connecting web 23 and the first ring gear 22 are welded as one body to reduce weight and simplify the processing process.
As shown in fig. 1, in this embodiment, the connection portion of the second ring gear 26 is provided with a second elastic collar, and the second connecting web 27 is provided with a second clamping plate connected to the second elastic collar for limiting the axial movement of the second ring gear 26. Specifically, the second clamping plate clamps the second elastic collar by a ring of samming screws to determine the axial position of the second ring gear 26. Optionally, the second connecting web 27 and the second ring gear 26 are welded as one body to reduce weight and simplify the processing process.
As shown in fig. 1, in the present embodiment, a weight reducing hole arranged in the axial direction of the speed reducer and an oil hole 5 for connecting an external oil pipe arranged in the radial direction of the speed reducer are further included. Specifically, the weight of the speed reducer is reduced through the weight reducing holes, the comprehensive performance of the speed reducer is improved, lubricating oil is conveyed to each part in the speed reducer through the oil holes 5, the transmission smoothness is improved, the oil holes 5 which are arranged radially and the weight reducing holes which are arranged axially are avoided, and the inner space of the speed reducer is utilized to the greatest extent.
As shown in fig. 1, the embodiment further comprises a gear frame 6 for mounting a second transmission gear 25, an oil distributing plunger 7 which is mounted in the inner cavity of the planet frame 13 along the axial direction of the speed reducer and is communicated with the inner cavity of the paddle shaft 3, and an oil distributing bushing 8 which is sleeved on the planet frame 13 and is communicated with the oil distributing plunger 7, wherein an oil way in the gear frame 6 which is communicated with the oil hole 5 is arranged in the gear frame 6, and an oil way in the second transmission gear 25 which is respectively communicated with the oil way in the gear frame 6 and the oil way in the second transmission gear 25 is arranged in the gear frame 25. Specifically, the gear rack 6 is fixed on the reducer casing by a plurality of pins that are arranged in radial direction, and the lubricating oil circulates in proper order in the gear rack 6 oil circuit, in the second transmission gear 25 oil circuit, in the oil distribution bushing 8 and in the oil distribution plunger 7 through the oil distribution plunger 7, and the lubricating oil splashes when the gear is driven, thereby accomplishing the lubrication of each part.
As shown in fig. 1, the present embodiment further includes a fuel heat exchanger pipe joint 9 for connecting the fuel heat exchanger to deliver fuel into the oil passage in the carrier 6. Specifically, the fuel oil heat exchanger conveys low-temperature fuel oil into the oil way in the gear rack 6 through the fuel oil heat exchanger pipe joint 9 so as to reduce the temperature of the lubricating oil when the speed reducer works, avoid the deformation of each part caused by the over-high temperature, and further prolong the service life of the speed reducer.
As shown in fig. 1, in this embodiment, the bottom of the decelerator further includes an oil collection tank 10 for collecting the lubricating oil. Specifically, the oil collecting tank 10 collects the lubricating oil, and the collected lubricating oil is input into the internal oil path of the speed reducer again, so that the cyclic reciprocating utilization of the lubricating oil is realized.
The turboprop engine is applied to an aviation aircraft, and the two-stage helical gear closed planetary gear reducer is adopted. Specifically, the speed reducer adopts the first-stage transmission mechanism 1, the second-stage transmission mechanism 2 and the bevel gear to transmit power in a meshed manner, so that the transmission efficiency of the turboprop engine is high, the process difficulty is low, the structure is reliable, the service life is long, the maintenance guarantee is convenient and fast, the economy is good, and the turboprop engine is suitable for wide popularization and application.
The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (8)
1. A two-stage helical gear closed planetary gear reducer for transmitting power to a paddle shaft (3), which is characterized by comprising a first-stage transmission mechanism (1) and a second-stage transmission mechanism (2) for transmitting power to the paddle shaft (3);
the first-stage transmission mechanism (1) comprises a power turbine shaft (11) for connecting a power turbine to transmit power, a first driving gear (12) fixedly connected with the power turbine shaft (11) and used for transmitting power, a first transmission gear (21) meshed with the first driving gear (12) and a planet carrier (13) coaxially arranged with the power turbine shaft (11) and fixedly connected with the first transmission gear (21) and the paddle shaft (3) respectively;
the second-stage transmission mechanism (2) comprises a first transmission gear (21), a first annular gear (22) meshed with the first transmission gear (21) and used for transmitting power, a second driving gear (24) fixedly connected with the first annular gear (22) and sleeved on the planet carrier (13) and used for transmitting power, a second transmission gear (25) meshed with the second driving gear (24) and used for transmitting power, and a second annular gear (26) meshed with the second transmission gear (25) and fixedly connected with the propeller shaft (3);
the first driving gear (12), the first transmission gear (21), the first annular gear (22), the second driving gear (24), the second transmission gear (25) and the second annular gear (26) are all in helical tooth meshing transmission; the torque measuring system (4) comprises a jumper level bearing (41) which is axially movably arranged on a planet carrier (13) and is used for supporting the jumper level assembly, an axial torque measuring piston (42) which is connected with the first annular gear (22) and is used for axially pushing the first annular gear (22) towards a direction close to a propeller shaft (3), a linear displacement sensor (43) which is connected with the axial torque measuring piston (42) and is used for detecting the displacement of the axial torque measuring piston (42), a torque measuring pressure sensor (44) which is used for detecting the oil pressure of the torque measuring cylinder in the axial torque measuring piston (42), and a controller which is respectively connected with the linear displacement sensor (43) and the torque measuring pressure sensor (44);
the torque measurement system (4) further comprises a torque measurement oil inlet electromagnetic valve (45) for controlling the external oil pipe to pressurize oil inlet of the torque measurement oil cylinder in the axial torque measurement piston (42) and a clutch friction disc bearing (46) connected with the axial torque measurement piston (42) and used for supporting the straddle gear assembly during torque measurement of the torque measurement system (4).
2. The two-stage helical gear closed planetary gear reducer according to claim 1, characterized in that the two-stage transmission mechanism further comprises a first connecting web (23) fixedly connected with the first ring gear (22) and the second driving gear (24) respectively, and a second connecting web (27) fixedly connected with the second ring gear (26) and the paddle shaft (3) respectively.
3. The two-stage helical-tooth closed planetary gear reducer according to claim 2, characterized in that a first elastic clamping ring is arranged at the joint of the first annular gear (22), and the first connecting web (23) is provided with a first clamping plate which is connected with the first elastic clamping ring and used for limiting the axial movement of the first annular gear (22); and/or
The joint of the second annular gear (26) is provided with a second elastic clamping ring, and the second connecting web (27) is provided with a second clamping plate which is connected with the second elastic clamping ring and used for limiting the axial movement of the second annular gear (26).
4. A two-stage helical gear closed planetary gear reducer according to any of claims 1-3, further comprising a lightening hole running in the axial direction of the reducer and an oil hole (5) running in the radial direction of the reducer for connecting an external oil pipe.
5. The two-stage helical gear closed planetary gear reducer according to claim 4, further comprising a gear frame (6) for mounting a second transmission gear (25), an oil separating plunger (7) mounted in the inner cavity of the planetary frame (13) along the axial direction of the reducer and communicated with the inner cavity of the propeller shaft (3), and an oil separating bushing (8) sleeved on the planetary frame (13) and communicated with the oil separating plunger (7), wherein an oil path in the gear frame (6) communicated with the oil hole (5) is arranged in the gear frame (6), and an oil path in the second transmission gear (25) is respectively communicated with the oil path in the gear frame (6) and the oil separating bushing (8).
6. The two-stage helical gear closed planetary gear reducer according to claim 5, further comprising a fuel heat exchanger pipe joint (9) for connecting the fuel heat exchanger to deliver fuel into the oil path in the gear rack (6).
7. A two-stage helical gear closed planetary gear reducer according to any of claims 1-3, characterized in that the bottom of the reducer further comprises an oil collection sump (10) for collecting the lubricating oil.
8. A turboprop comprising a two-stage helical gear closed pinion gear reducer according to any one of claims 1 to 7.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111055408.5A CN113804448B (en) | 2021-09-09 | 2021-09-09 | Two-stage helical gear closed planetary gear reducer and vortex paddle engine thereof |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111055408.5A CN113804448B (en) | 2021-09-09 | 2021-09-09 | Two-stage helical gear closed planetary gear reducer and vortex paddle engine thereof |
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| CN113804448A CN113804448A (en) | 2021-12-17 |
| CN113804448B true CN113804448B (en) | 2023-12-01 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2722493Y (en) * | 2004-06-24 | 2005-08-31 | 许晓华 | Monolayer gear reducing mechanism of motor |
| CN201739480U (en) * | 2010-08-06 | 2011-02-09 | 淄博市博山金博减速机厂 | Speed reducer of flat slurry mixer |
| CN202628954U (en) * | 2012-06-08 | 2012-12-26 | 沈阳金龟减速机厂有限公司 | Planetary reducer for large plate bending machine |
| CN109163902A (en) * | 2018-09-18 | 2019-01-08 | 株洲格斯特动力机械有限责任公司 | Electric-controlled hydraulic torque measuring mechanism for star-like retarder |
| CN110185760A (en) * | 2019-04-30 | 2019-08-30 | 中国航发南方工业有限公司 | The starshaped reducing gear of turbo oar engine |
| CN110617301A (en) * | 2019-10-24 | 2019-12-27 | 河南德豫重工有限公司 | Three-stage transmission helical gear planetary gear type speed reducer |
| TW202102766A (en) * | 2019-07-01 | 2021-01-16 | 格來得股份有限公司 | Rolling door power mechanism with changeable transmission ratio capable of selecting the combination of the first driven gear and the first drive gear or the combination of the second driven gear and the second drive gear according to the required transmission ratio |
| CN112284596A (en) * | 2020-11-26 | 2021-01-29 | 江苏工程职业技术学院 | Online torsion measuring method based on helical gear transmission system |
-
2021
- 2021-09-09 CN CN202111055408.5A patent/CN113804448B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2722493Y (en) * | 2004-06-24 | 2005-08-31 | 许晓华 | Monolayer gear reducing mechanism of motor |
| CN201739480U (en) * | 2010-08-06 | 2011-02-09 | 淄博市博山金博减速机厂 | Speed reducer of flat slurry mixer |
| CN202628954U (en) * | 2012-06-08 | 2012-12-26 | 沈阳金龟减速机厂有限公司 | Planetary reducer for large plate bending machine |
| CN109163902A (en) * | 2018-09-18 | 2019-01-08 | 株洲格斯特动力机械有限责任公司 | Electric-controlled hydraulic torque measuring mechanism for star-like retarder |
| CN110185760A (en) * | 2019-04-30 | 2019-08-30 | 中国航发南方工业有限公司 | The starshaped reducing gear of turbo oar engine |
| TW202102766A (en) * | 2019-07-01 | 2021-01-16 | 格來得股份有限公司 | Rolling door power mechanism with changeable transmission ratio capable of selecting the combination of the first driven gear and the first drive gear or the combination of the second driven gear and the second drive gear according to the required transmission ratio |
| CN110617301A (en) * | 2019-10-24 | 2019-12-27 | 河南德豫重工有限公司 | Three-stage transmission helical gear planetary gear type speed reducer |
| CN112284596A (en) * | 2020-11-26 | 2021-01-29 | 江苏工程职业技术学院 | Online torsion measuring method based on helical gear transmission system |
Non-Patent Citations (3)
| Title |
|---|
| Design of helical gear with carbon reinforced EN36 steel for two stage constant mesh gearbox weight reduction;Sarvesh Joshi等;《 materialstoday: PROCEEDINGS》;第46卷;626-633 * |
| 新型大扭矩桩机动力头硬齿面减速机;杨天益等;《科学与财富》(第8期);112-113 * |
| 直 升 机 动 力 传 动 系 统 中 两 级 行 星 齿 轮 减 速 器 的 优 化 设 计;邱菊等;《飞机设计》;第32卷(第4期);36-39 * |
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