CN113804448A - Two-stage helical gear closed planetary gear reducer and turboprop engine thereof - Google Patents
Two-stage helical gear closed planetary gear reducer and turboprop engine thereof Download PDFInfo
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- CN113804448A CN113804448A CN202111055408.5A CN202111055408A CN113804448A CN 113804448 A CN113804448 A CN 113804448A CN 202111055408 A CN202111055408 A CN 202111055408A CN 113804448 A CN113804448 A CN 113804448A
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- 239000003638 chemical reducing agent Substances 0.000 title claims abstract description 53
- 230000005540 biological transmission Effects 0.000 claims abstract description 109
- 230000007246 mechanism Effects 0.000 claims abstract description 33
- 238000006073 displacement reaction Methods 0.000 claims description 17
- 238000009826 distribution Methods 0.000 claims description 12
- 239000000446 fuel Substances 0.000 claims description 11
- 238000005259 measurement Methods 0.000 claims description 9
- 208000032370 Secondary transmission Diseases 0.000 claims description 2
- 238000003754 machining Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 238000003466 welding Methods 0.000 abstract description 4
- 238000005457 optimization Methods 0.000 abstract description 3
- 239000003921 oil Substances 0.000 description 61
- 239000010687 lubricating oil Substances 0.000 description 9
- 239000010720 hydraulic oil Substances 0.000 description 5
- 238000012545 processing Methods 0.000 description 3
- 239000000295 fuel oil Substances 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010894 electron beam technology Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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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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- General Engineering & Computer Science (AREA)
- General Details Of Gearings (AREA)
Abstract
The invention discloses a two-stage helical tooth closed planetary gear reducer and a turboprop engine thereof. And the torque required to be transmitted by each part is further dispersed, and the pressure born by each part is correspondingly reduced, so that the contact stress of the tooth surface is correspondingly reduced, the reliability and the transmission smoothness between the parts are improved, the machining process for welding the duplicate gear is avoided, and the process difficulty is low. Meanwhile, the planet carrier and the second driving gear are final driving parts of the first-stage transmission mechanism and the second-stage transmission mechanism respectively, the rotating speeds of the planet carrier and the second driving gear are the same, the calculation of the transmission ratio is facilitated, meanwhile, all gears are in meshing transmission 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 engine are further conveniently measured, and therefore data support is provided for further optimization iteration of the turboprop engine.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a two-stage helical tooth closed planetary gear reducer. In addition, the invention also relates to a turboprop engine comprising the two-stage helical-tooth closed planetary gear reducer.
Background
The small turbine engine needs high power and high power-weight ratio, so the reducer of the small turboprop engine with high power-weight ratio and proper machining level needs to be designed because the reducer of the small turboprop engine has high transmission ratio requirement and small gear module, and the strength and reliability of the reducer are difficult to meet the use requirement.
The speed reducer in the existing turboprop usually adopts a straight-tooth inner gear ring to be connected with a propeller shaft, and a duplicate gear is welded to realize multi-point force transmission with compact structure, but the connection structure can cause low strength of the inner gear ring and poor transmission smoothness, the processing difficulty of electron beam welding of the duplicate gear is high, the speed reducer is not suitable for a small turboprop engine which needs high power and high rotation speed, and simultaneously the torque and the power of the turboprop engine can not be measured, so that the structure of the turboprop engine can not be further improved and optimized.
Disclosure of Invention
The invention provides a two-stage helical gear closed planetary gear reducer and a turboprop engine thereof, and aims to solve the technical problems that the reducer in the conventional small turboprop engine has low strength of an inner gear ring, poor transmission smoothness and high processing difficulty, cannot measure the torque and power of the turboprop engine, and further cannot improve and optimize the structure of the turboprop engine.
According to one aspect of the invention, a two-stage helical tooth closed planetary gear reducer is provided for transmitting power to a propeller shaft, and comprises a first-stage transmission mechanism and a second-stage transmission mechanism for transmitting power to the propeller shaft; the first-stage transmission mechanism comprises a power turbine shaft, a first driving gear, a first transmission gear and a planet carrier, wherein the power turbine shaft is used for being connected with the power turbine to transmit power; the second-stage transmission mechanism comprises a first transmission gear, a first inner gear ring which is engaged with the first transmission gear and used for transmitting power, a second driving gear which is fixedly connected with the first inner gear ring and sleeved on the planet carrier and used for transmitting power, a second transmission gear which is engaged with the second driving gear and used for transmitting power, and a second inner gear ring which is engaged with the second transmission gear and fixedly connected with the propeller shaft and used for transmitting power; the first driving gear, the first transmission gear, the first inner gear ring, the second driving gear, the second transmission gear and the second inner gear ring are all in helical tooth meshing transmission.
The torque measuring system comprises a wheel-spanning bearing which is movably arranged on the planet carrier along the axial direction and is used for supporting the wheel-spanning assembly, an axial torque measuring piston which is connected with the first inner gear ring and is used for axially pushing the first inner gear ring towards the direction close to the propeller shaft, a linear displacement sensor which is connected with the axial torque measuring piston and is 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 oil 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.
Furthermore, the torsion measuring system also comprises a torsion measuring oil inlet electromagnetic valve for controlling oil inlet pressurization of an external oil pipe to a torsion measuring oil cylinder in the axial torsion measuring piston and a clutch friction disc bearing which is connected with the axial torsion measuring piston and used for supporting the cross-wheel stage assembly during torsion measurement of the torsion measuring system.
Furthermore, the secondary transmission mechanism also comprises a first connecting web plate fixedly connected with the first inner gear ring and the second driving gear respectively and a second connecting web plate fixedly connected with the second inner gear ring and the propeller shaft respectively.
Furthermore, a first elastic clamping ring is arranged at the joint of the first inner gear ring, and a first clamping plate which is connected with the first elastic clamping ring and used for limiting the axial movement of the first inner gear ring is arranged on the first connecting web plate; and/or a second elastic clamping ring is arranged at the joint of the second inner gear ring, and a second clamping plate which is connected with the second elastic clamping ring and used for limiting the axial movement of the second inner gear ring is arranged on the second connecting web plate.
Furthermore, the oil-saving device also comprises lightening holes distributed along the axial direction of the speed reducer and oil holes distributed along the radial direction of the speed reducer and used for connecting an external oil pipe.
The planetary gear set further comprises a gear carrier used for mounting a second transmission gear, an oil distribution plunger which is mounted in an inner cavity of the planetary carrier along the axial direction of the speed reducer and communicated with an inner cavity of the propeller shaft, and an oil distribution lining which is sleeved on the planetary carrier and communicated with the oil distribution plunger, an oil path in the gear carrier communicated with the oil hole is arranged in the gear carrier, and an oil path in the second transmission gear which is respectively communicated with the oil path in the gear carrier and the oil distribution lining is arranged in the second transmission gear.
And further, a fuel heat exchanger pipe joint for connecting the fuel heat exchanger to convey fuel to the oil way in the gear carrier is also included.
Further, the bottom of the speed reducer also comprises an oil collecting pool for collecting lubricating oil.
According to another aspect of the invention, there is also provided a turboprop engine including the two-stage helical-tooth enclosed pinion gear reducer described above.
The invention has the following beneficial effects:
the invention discloses a two-stage helical gear closed planetary gear reducer and a turboprop engine thereof. The second-stage transmission mechanism transmits torque sequentially through the 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 the first-stage transmission mechanism and the second-stage transmission mechanism are provided with the common first transmission gear of the transmission parts and finally transmit the torque to the paddle shaft, so that the torque required to be transmitted by each part is dispersed, the pressure born by each part is correspondingly reduced, the contact stress of the tooth surface is correspondingly reduced, the reliability and the transmission smoothness between the parts are improved, the machining process of welding the duplicate gears is avoided, and the process difficulty is low. Meanwhile, the planet carrier and the second driving gear are final driving parts of the first-stage transmission mechanism and the second-stage transmission mechanism respectively, the rotating speeds of the planet carrier and the second driving gear are the same, the calculation of the transmission ratio is facilitated, meanwhile, all gears are in meshing transmission 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 engine are further conveniently measured, and therefore data support is provided for further optimization iteration of the turboprop engine.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural view of a two-stage helical tooth closed planetary gear reducer according to a preferred embodiment of the present invention.
Illustration of the drawings:
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 drive gear; 22. a first ring gear; 23. a first connecting web; 24. a second driving gear; 25. a second transmission gear; 26. a second ring gear; 27. a second connecting web; 3. a paddle shaft; 4. a torque measuring system; 41. a wheel-spanning stage bearing; 42. an axial torque measuring piston; 43. a linear displacement sensor; 44. a torque measuring pressure sensor; 45. a torsion measuring oil inlet electromagnetic valve; 46. a clutch friction disc bearing; 5. an oil hole; 6. a gear carrier; 7. an oil distributing plunger; 8. oil distribution lining; 9. a pipe joint of the fuel oil heat exchanger; 10. an oil collecting tank.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
Fig. 1 is a schematic structural view of a two-stage helical tooth closed planetary gear reducer according to a preferred embodiment of the present invention.
As shown in fig. 1, the two-stage helical gear closed planetary gear reducer of the present embodiment, which is used for transmitting power to a propeller shaft 3, includes a first-stage transmission mechanism 1 and a second-stage transmission mechanism 2 for transmitting power to the propeller shaft 3; the first-stage transmission mechanism 1 comprises a power turbine shaft 11 used for being connected with 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 which is coaxially arranged with the power turbine shaft 11 and respectively fixedly connected with the first transmission gear 21 and a propeller shaft 3 and used for transmitting power; the second-stage transmission mechanism 2 comprises a first transmission gear 21, a first inner gear ring 22 which is engaged with the first transmission gear 21 and used for transmitting power, a second driving gear 24 which is fixedly connected with the first inner gear ring 22 and sleeved on the planet carrier 13 and used for transmitting power, a second transmission gear 25 which is engaged with the second driving gear 24 and used for transmitting power, and a second inner gear ring 26 which is engaged with the second transmission gear 25 and fixedly connected with the propeller shaft 3 and used for transmitting power; the first driving gear 12, the first transmission gear 21, the first inner gear ring 22, the second driving gear 24, the second transmission gear 25 and the second inner gear ring 26 are all in helical gear meshing transmission. Specifically, the two-stage helical gear closed planetary gear reducer and the turboprop engine thereof respectively transmit the torque of the power turbine shaft 11 to the propeller shaft 3 through the first-stage transmission mechanism 1 and the second-stage transmission mechanism 2, the first-stage transmission mechanism 1 transmits the torque to the propeller shaft 3 through the power turbine shaft 11, the first driving gear 12, the first transmission gear 21 and the planetary carrier 13 in sequence, and the second-stage transmission mechanism 2 transmits the torque to the propeller shaft 3 through the first transmission gear 21, the first inner gear ring 22, the second driving gear 24, the second transmission gear 25 and the second inner gear ring 26 in sequence. The second-stage transmission mechanism 2 transmits torque sequentially 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 11 is converted into the output low rotating speed of the rotating shaft, and the first-stage transmission mechanism 1 and the second-stage transmission mechanism 2 are provided with the first transmission gear 21 of the common transmission part and finally transmit the torque to the paddle shaft 3, so that the torque required to be transmitted by each part is dispersed, the pressure born by each part is correspondingly reduced, the contact stress of the tooth surface is correspondingly reduced, the reliability and the transmission smoothness between the parts are improved, the machining process of welding the duplicate gear is avoided, and the process difficulty is low. Meanwhile, the planet carrier 13 and the second driving gear 24 are final transmission parts of the first-stage transmission mechanism 1 and the second-stage transmission mechanism 2 respectively, the rotation speeds of the final transmission parts are the same, the calculation of the transmission ratio is facilitated, meanwhile, all the gears are in meshing transmission 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 engine are further conveniently measured, and therefore data support is provided for further optimization iteration of the turboprop engine. Optionally, 4 first transmission gears 21 are provided, the first driving gear 12 is respectively meshed with the 4 first transmission gears 21 for transmission, the contact ratio is high, the transmission is stable, and the axial force generated by the helical gear on the first driving gear 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, in the present embodiment, the torque measuring system 4 further includes a cross-wheel stage assembly, the cross-wheel stage assembly includes a first inner gear ring 22 and a second driving gear 24, the torque measuring system 4 includes a cross-wheel stage bearing 41 which is axially movably mounted on the planet carrier 13 and is used for supporting the cross-wheel stage assembly, an axial torque measuring piston 42 which is connected with the first inner gear ring 22 and is used for axially pushing the first inner gear ring 22 towards the direction close to the 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 a 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. Specifically, when the wheel span stage assembly is pushed to the propeller shaft 3 by the axial torque measuring piston 42, the axial force generated by the bevel gear is axially moved and unloaded through the wheel span stage bearing 41, and the axial force of the wheel span stage assembly is equal to the oil pressure in the hydraulic oil 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 to obtain a relation curve between the displacement of the axial torque measuring piston 42 and the oil pressure in the hydraulic oil cylinder thereof, and further obtain the value of the axial force of the wheel span stage assembly, so as to convert the torque of the propeller shaft 3. Optionally, the torque measuring system 4 further comprises a display screen connected to the controller for displaying the measured data of the linear displacement sensor 43 and the torque measuring pressure sensor 44, and a converter for interpreting and converting the real-time torque according to the measured data of the linear displacement sensor 43 and the torque measuring pressure sensor 44, and the display screen is further used for displaying 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.
In the embodiment, as shown in fig. 1, the torque measuring system 4 further includes a torque measuring oil inlet solenoid valve 45 for controlling oil inlet pressurization of an external oil pipe to a torque measuring oil cylinder in the axial torque measuring piston 42, and a clutch friction disc bearing 46 connected to the axial torque measuring piston 42 for supporting a cross-wheel stage assembly when the torque measuring system 4 measures torque. Specifically, when the speed reducer does not measure the torque, the hydraulic oil pipe of the axial torque measuring piston 42 is communicated with the oil return pump, the pressure is slightly negative, at this time, the clutch friction disc bearing 46 is not in contact with the first inner gear ring 22, the axial force of the wheel-spanning stage assembly is borne by the wheel-spanning stage bearing 41, and the torque measuring system 4 does not work, consumes no energy, and does not display real-time torque. When the speed and power of the speed reducer change and the torque needs to be measured, the controller controls the torque measuring oil inlet electromagnetic valve 45 to be opened, so that the oil is fed into and pressurized from the torque measuring oil cylinder in the axial torque measuring piston 42 through the external oil pipe, the displacement and the internal oil pressure of the axial torque measuring piston 42 are detected simultaneously, and when the displacement of the axial torque measuring piston 42 changes suddenly or changes back and forth, a relation curve of the displacement of the axial torque measuring piston 42 and the oil pressure in the hydraulic oil cylinder is obtained, so that the axial force of the wheel-span stage assembly is obtained, the torque of the propeller shaft 3 is converted through the converter, and the torque is displayed on the display screen. When the torque measuring system 4 works, the axial force of the wheel-spanning stage assembly is born by the clutch friction disc bearing 46, so that the leakage of lubricating oil of the hydraulic oil cylinder of the axial torque measuring piston 42 is less, the energy consumption is also less, and the power loss of the torque measuring system 4 during torque measurement is reduced to the maximum extent.
As shown in fig. 1, in the present embodiment, the two-stage transmission further includes a first connecting web 23 fixedly connected to the first ring gear 22 and the second driving gear 24, respectively, and a second connecting web 27 fixedly connected to the second ring gear 26 and the paddle shaft 3, respectively. Specifically, the first connecting web 23 is obliquely arranged to be fixedly connected with the first ring gear 22 and the second driving gear 24 respectively, so as to realize power transmission; the second connecting web 27 is obliquely arranged to be fixedly connected with the second ring gear 26 and the propeller shaft 3, respectively, so as to realize power transmission.
In the present embodiment, as shown in fig. 1, a first elastic collar is provided at the connection of the first internal gear 22, and the first connecting web 23 is provided with a first clamping plate connected with the first elastic collar for limiting the axial movement of the first internal gear 22. In particular, the first clamping plate clamps the first elastic collar by a ring of screws, in order to determine the axial position of the first internal toothing 22. Optionally, the first connecting web 23 and the first inner gear ring 22 are welded into a whole, so that the weight is reduced, and the processing technology is simplified.
In the present embodiment, as shown in fig. 1, the connection of the second internal gear ring 26 is provided with a second elastic collar, and the second connecting web 27 is provided with a second clamping plate connected with the second elastic collar for limiting the axial movement of the second internal gear ring 26. In particular, the second clamping plate clamps the second elastic collar by a ring of screws, so as to determine the axial position of the second internal toothing 26. Optionally, the second connecting web 27 and the second ring gear 26 are welded into a whole, so as to reduce weight and simplify the machining process.
As shown in fig. 1, the present embodiment further includes lightening holes arranged in the axial direction of the reducer and oil holes 5 arranged in the radial direction of the reducer for connecting external oil pipes. Specifically, the weight of the speed reducer is reduced through the lightening 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 smoothness of transmission is improved, the oil holes 5 distributed in the radial direction and the lightening holes distributed in the axial direction are mutually avoided, and the internal space of the speed reducer is utilized to the maximum extent.
As shown in fig. 1, in the present embodiment, the transmission device further includes a carrier 6 for mounting the second transmission gear 25, an oil distributing plunger 7 mounted in the inner cavity of the planet carrier 13 along the axial direction of the reducer and communicated with the inner cavity of the propeller shaft 3, and an oil distributing bush 8 sleeved on the planet carrier 13 and communicated with the oil distributing plunger 7, an oil path in the carrier 6 communicated with the oil hole 5 is provided in the carrier 6, and an oil path in the second transmission gear 25 communicated with the oil path in the carrier 6 and the oil distributing bush 8 respectively is provided in the second transmission gear 25. Specifically, the gear carrier 6 is fixed to the speed reducer casing by a plurality of pins arranged in the radial direction, the lubricating oil sequentially flows through an oil path in the gear carrier 6, an oil path in the second transmission gear 25, the oil distribution bush 8 and the oil distribution plunger 7 through the oil path, and then flows through the propeller shaft 3 and the first transmission gear 21 through the oil distribution plunger 7, and during gear transmission, the lubricating oil splashes, so that lubrication of each component is completed.
As shown in fig. 1, the present embodiment further comprises a fuel heat exchanger pipe joint 9 for connecting the fuel heat exchanger to supply fuel to the oil path in the carrier 6. Specifically, the fuel heat exchanger conveys low-temperature fuel oil into an oil circuit in the gear carrier 6 through a fuel heat exchanger pipe joint 9, so that the lubricating oil temperature of the speed reducer during working is reduced, the thermal deformation of each component caused by overhigh temperature is avoided, and the service life of the speed reducer is further prolonged.
As shown in fig. 1, in the present embodiment, the bottom of the speed reducer further includes an oil collection pool 10 for collecting oil. Specifically, the lubricating oil is collected by the oil collecting pool 10, and then the collected lubricating oil is input into the internal oil path of the speed reducer again, so that the circulating and reciprocating utilization of the lubricating oil is realized.
The turboprop engine of the embodiment is applied to an aviation aircraft, and the two-stage helical-tooth closed planetary gear reducer is adopted. Specifically, the speed reducer adopts a first-stage transmission mechanism 1, a second-stage transmission mechanism 2 and a bevel gear to transmit power in a meshed mode, 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 and the guarantee are convenient and fast, the economy is good, and the turboprop is suitable for wide popularization and application.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A two-stage helical gear closed planetary gear reducer is used for transmitting power to a paddle shaft (3), and is characterized by comprising a first-stage transmission mechanism (1) and a second-stage transmission mechanism (2) which are used for transmitting the power to the paddle shaft (3);
the first-stage transmission mechanism (1) comprises a power turbine shaft (11) used for being connected with 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) which is coaxially arranged with the power turbine shaft (11) and respectively fixedly connected with the first transmission gear (21) and a propeller shaft (3) and used for transmitting power;
the second-stage transmission mechanism (2) comprises a first transmission gear (21), a first inner gear ring (22) which is engaged with the first transmission gear (21) and used for transmitting power, a second driving gear (24) which is fixedly connected with the first inner gear ring (22) and sleeved on the planet carrier (13) and used for transmitting power, a second transmission gear (25) which is engaged with the second driving gear (24) and used for transmitting power, and a second inner gear ring (26) which is engaged with the second transmission gear (25) and fixedly connected with the propeller shaft (3) and used for transmitting power;
the first driving gear (12), the first transmission gear (21), the first inner gear ring (22), the second driving gear (24), the second transmission gear (25) and the second inner gear ring (26) are in helical gear meshing transmission.
2. A two-stage helical gear closed pinion gear reducer as claimed in claim 1 further comprising a torque measuring system (4) and a cross-wheel stage assembly comprising a first annulus gear (22) and a second drive gear (24), the torsion measuring system (4) comprises a wheel-spanning bearing (41) which is movably arranged on the planet carrier (13) along the axial direction and is used for supporting a wheel-spanning assembly, an axial torsion measuring piston (42) which is connected with the first inner gear ring (22) and is used for axially pushing the first inner gear ring (22) towards the direction close to the propeller shaft (3), a linear displacement sensor (43) which is connected with the axial torsion measuring piston (42) and is used for detecting the displacement of the axial torsion measuring piston (42), a torsion measuring pressure sensor (44) which is used for detecting the oil pressure of a torsion measuring oil cylinder in the axial torsion measuring piston (42), and a controller which is respectively connected with the linear displacement sensor (43) and the torsion measuring pressure sensor (44).
3. A two-stage skewed tooth closed pinion gear reducer as claimed in claim 2, wherein the torque measurement system (4) further comprises a torque measurement oil inlet solenoid valve (45) for controlling oil inlet pressurization of an external oil pipe to a torque measurement oil cylinder 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 cross-wheel stage assembly when the torque measurement system (4) measures torque.
4. A two-stage helical gear closed planetary gear reducer according to claim 1, wherein the secondary transmission further comprises a first connecting web (23) fixedly connected to the first inner ring gear (22) and the second driving gear (24), respectively, and a second connecting web (27) fixedly connected to the second inner ring gear (26) and the propeller shaft (3), respectively.
5. A two-stage helical gear closed planetary gear reducer according to claim 4, wherein the junction of the first internal ring gear (22) is provided with a first elastic collar, and the first connecting web (23) is provided with a first clamping plate connected with the first elastic collar for limiting the axial movement of the first internal ring gear (22); and/or
A second elastic clamping ring is arranged at the joint of the second inner gear ring (26), and a second clamping plate which is connected with the second elastic clamping ring and used for limiting the axial movement of the second inner gear ring (26) is arranged on the second connecting web plate (27).
6. A two-stage helical tooth closed pinion gear reducer according to any one of claims 1-5, further comprising lightening holes arranged in the axial direction of the reducer and oil holes (5) arranged in the radial direction of the reducer for connecting external oil pipes.
7. The two-stage helical gear closed planetary gear reducer according to claim 6, further comprising a gear carrier (6) for mounting a second transmission gear (25), an oil distribution plunger (7) mounted in the inner cavity of the planetary carrier (13) along the axial direction of the reducer and communicated with the inner cavity of the propeller shaft (3), and an oil distribution bush (8) sleeved on the planetary carrier (13) and communicated with the oil distribution plunger (7), wherein an oil passage in the gear carrier (6) communicated with the oil hole (5) is arranged in the gear carrier (6), and an oil passage in the second transmission gear (25) respectively communicated with the oil passage in the gear carrier (6) and the oil distribution bush (8) is arranged in the second transmission gear (25).
8. A two-stage helical gear closed pinion gear reducer according to claim 7, characterised in that it further comprises a fuel heat exchanger union (9) for connecting a fuel heat exchanger to feed fuel into the oil circuit in the carrier (6).
9. A two-stage helical gear closed pinion gear reducer according to any of claims 1-5 in which the bottom of the reducer further includes an oil collection sump (10) for collecting oil.
10. A turboprop comprising a two-stage helical gear enclosed pinion gear reducer according to any one of claims 1 to 9.
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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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| 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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| CN113804448B CN113804448B (en) | 2023-12-01 |
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