A fan motor type of flade fan based planetary gear reduction transmission shaft fan motor

Abstract

The application relates to a Flade fan-based planetary gear type reduction transmission shaft fan engine model, and belongs to the field of aircraft power. The disclosed engine model comprises a turbo-shaft impeller (5), an internal guide vane (6), a Flade fan (7), a power output shaft (1), a planetary gear transmission mechanism (2), a mode conversion mechanism, a power turbine and a core engine. The Flade fan comprises a turbofan impeller and a fan on the turbofan impeller. The internal guide vane is matched with the turbo-shaft / turbofan impeller to continuously maintain the pressurization capacity of the internal guide flow channel of the two modes of the turbo-shaft and the turbofan. The power turbine drives a sun gear (25) on the planetary gear transmission mechanism, respectively drives the Flade fan fixed with an outer gear ring (22) and the power output shaft fixed with a planetary carrier (26) through speed reduction. The mode conversion mechanism comprises an auxiliary motor (4) and an electromagnetic clutch (3). The application realizes the single-mode maximum capacity reduction efficient transmission and the two-mode continuous smooth conversion based on the planetary gear transmission mechanism, the mode conversion mechanism and the internal guide flow channel.

Description

TECHNICAL FIELD

[0001] The application relates to a Flade fan-based planetary gear type speed reduction transmission shaft fan engine, and belongs to the field of aircraft power. BACKGROUND

[0002] The vertical take-off and landing high-speed aircraft with high load capacity has the ability of "rapid support and agile attack", and can well meet the future combat needs of our army.

[0003] In order to realize the vertical take-off of the large load capacity, a large force efficiency and low speed rotor needs to be relied on as a lift system. The utility model authorization patent with the publication number CN 219056579 U proposes a double-engine series vertical take-off aircraft, one engine is located at the front of the fighter, and the other engine is located at the rear of the fighter, so that the engine performance is more fully exerted and improved. The vertical take-off and cruise are both operated by the double engines, but the vertical take-off of the aircraft has the problems of low force efficiency (about 0.4 kg / kw) and large heat loss of the nozzle jet, and the fuel consumption rate is large. The force efficiency of the lift fan used by the F35 fighter as a design target is only 0.4 kg / kw, which is far lower than the force efficiency of 4.1 kg / kw of the AH-64 helicopter rotor with a diameter of 14 m and a speed of 290 rpm. This is not conducive to the maximum capacity of the aircraft, which reflects from one side that the vertical take-off of the large load capacity needs to rely on the large force efficiency and low speed rotor as a lift system.

[0004] The key to the success or failure of the vertical take-off and landing high-speed aircraft lies in its power system. The traditional turboshaft engine or turbofan engine cannot simultaneously meet the power demand of the vertical take-off and landing high-speed aircraft for shaft power output and cruise thrust output. The development of shaft fan engines has become the mainstream. The invention patent with the publication number CN106988926A proposes a turboshaft turbofan combined cycle engine with two Flade fan rotors in counter-rotation. The engine can be switched between the output shaft power and thrust generation modes through an adjustable guide vane and a clutch coupling. However, the clutch coupling has the problems of torque load mutation and friction temperature rise during mode conversion. Moreover, the power load of the outer bypass fan can only be reduced by 20% to 60% by closing the outer bypass, that is, the turboshaft single mode cannot be realized with the maximum capacity. The invention patent with the publication number CN113236441A proposes a turboshaft fan dual-mode engine and a regulating method thereof. However, the fan still rotates and consumes energy in the turboshaft mode, and the turboshaft mode cannot be realized with the maximum capacity.

[0005] The planetary transmission mechanism has the characteristics of double-path speed reduction transmission, but the planetary transmission mechanism has the problem that the power output process is difficult to consider the pressurization capacity of the inner bypass flow passage in the turboshaft / turbofan mode of the shaft fan engine, that is, the power output often hinders the inner bypass air intake.

[0006] It is necessary to develop corresponding turboshaft engines and planetary transmission mechanisms to realize maximum shaft power output or fan propulsion and to realize turbo / turboshaft mode internal convection pressurization capacity under high-efficiency deceleration transmission. SUMMARY

[0007] The application aims to provide a Flade fan-based planetary gear deceleration transmission shaft fan engine mechanism, and aims to develop a Flade fan-based planetary gear deceleration transmission shaft fan engine based on a mode conversion mechanism composed of an auxiliary motor and an electromagnetic clutch and a planetary gear transmission mechanism, and to continuously maintain the pressurization capacity of the internal convection flow channels of the turbo / turboshaft two modes through the ingenious cooperation of the internal convection guide vanes and the turbo / turboshaft impellers, solve the problem of internal convection air intake hindered by the planetary gear transmission mechanism, realize maximum shaft power high-efficiency deceleration output or fan deceleration propulsion, and realize continuous and smooth transition between the two modes, which is beneficial to the high-efficiency driving of the large-efficiency rotor and the large-bypass-ratio fan.

[0008] To achieve the above-mentioned purpose, the application provides the following technical scheme:

[0009] A Flade fan-based planetary gear deceleration transmission shaft fan engine mechanism, comprising: double-sided S-bend air inlet channels, a turbo impeller, internal convection guide vanes, a Flade fan, a power output shaft, a planetary gear transmission mechanism, a mode conversion mechanism, a power turbine, a core engine and an adjustable nozzle, the power output shaft and the planet carrier are fixedly connected, an air inlet cone and the turbo impeller are sequentially installed from the direction of the engine air flow inlet, the internal convection guide vanes are installed on a lubricating oil tank, the top of the internal convection guide vanes is provided with a crown, and a support rib is installed at the crown, the internal convection guide vanes play the roles of flow guiding and supporting, and the bearing force of the lubricating oil tank of the planetary gear mechanism is transmitted to the outer convection casing through the support rib, the Flade fan comprises a turbofan impeller and a fan on the turbofan impeller, the turbofan impeller is connected to an outer ring gear through a Flade fan connecting member, the Flade fan connecting member is a double-end ring structure, the turbo impeller, the internal convection guide vanes and the turbofan guide vanes constitute a new internal convection pressurization stage, the pressurization capacity of the internal convection flow channels of the turbo / turboshaft two modes is continuously maintained through the ingenious cooperation of the internal convection guide vanes and the turbo / turboshaft impellers, the power turbine drives a sun gear on the planetary gear transmission mechanism, respectively drives the Flade fan fixedly connected with the outer ring gear and the power output shaft fixedly connected with the planet carrier through deceleration, and the mode conversion mechanism comprises an auxiliary motor and an electromagnetic clutch.

[0010] The auxiliary motor is installed in the motor cylinder protruding from the left end of the oil lubrication tank and is driven by the motor driving gear meshing with the outer gear ring. When the engine is switched from the turbo-shaft mode to the turbo-fan mode, the auxiliary motor actively drives the outer gear ring to accelerate, and when the engine is switched from the turbo-fan mode to the turbo-shaft mode, the auxiliary motor actively brakes the outer gear ring to decelerate, thereby speeding up the mode switching process.

[0011] The electromagnetic clutch is composed of an armature, a coil, an iron core, and a spring, and is connected to the inner wall of the ring on the left end of the oil lubrication tank through a mounting head. The electromagnetic clutch includes a turbo-fan mode without current locking the planetary carrier state, a transition state with intermediate current unlocking state, and a turbo-shaft mode with maximum current locking the outer gear ring state. The turbo-fan mode without current is beneficial to high-speed economic cruising.

[0012] The oil lubrication tank is a cylindrical structure with two side rings. The oil lubrication tank surrounds the planetary gear transmission mechanism and the mode switching mechanism. The oil lubrication tank adopts the ring under-oil technology of uniformly throwing from the inner ring of the bearing to the outer ring and from the sun gear to the outer gear ring, and adopts multi-path oil supply technology to lubricate and cool the bearings, gears, auxiliary motor, and electromagnetic clutch, respectively. Finally, the oil returns to the bottom of the oil tank under the action of gravity, playing the role of lubricating and cooling the planetary gear transmission mechanism and the mode switching mechanism. The Flade fan connecting member, the first sealing grate, and the second sealing grate ensure the sealing of the right end of the oil lubrication tank. The first sealing grate is installed on the right end ring of the oil lubrication tank, and the first sealing grate seals the end of the oil lubrication tank. The second sealing grate is installed on the stationary part near the engine intermediate nacelle. The second sealing grate seals the double rotating parts composed of the power turbine shaft and the Flade fan connecting member, ensuring the oil path sealing of the right end of the oil lubrication tank. The oil lubrication tank left end is installed with an oil baffle and an oil cover. The oil baffle is fixed to the center of the oil lubrication tank and is sleeved on the power output shaft. The oil cover and the auxiliary motor are coaxially installed, which is convenient for the installation, disassembly, and maintenance of the auxiliary motor, and plays the role of oil lubrication tank left end oil path sealing.

[0013] The planetary gear type reduction transmission shaft fan engine based on the Flade fan is characterized in that, in order to ensure efficient reduction transmission from the power turbine to the power output shaft, a new type of internal content supercharging stage is used to output the power output shaft forward. The new type of internal content supercharging stage continuously maintains the supercharging capacity of the internal flow passage of the turbo-shaft and turbo-fan modes through the clever cooperation of the internal content guide vane with the turbo-shaft / turbo-fan impeller.

[0014] I turbo-shaft mode: the power output shaft drives the turbo-shaft impeller to rotate forward, the electromagnetic clutch locks the turbo-shaft impeller on the outer ring gear, the inner guide vane and the turbo-fan impeller are static, the airflow enters the inner channel under the turbo-shaft impeller boost, accelerates the inlet airflow into airflow with tangential component, under the effect of the inner guide vane diffuser and the turbo-fan impeller, the tangential component is guided into the axial boost airflow, which ensures the turbo-shaft mode of the inner channel boost capability;

[0015] II turbo-fan mode: the electromagnetic clutch locks the turbo-shaft impeller on the power output shaft, the turbo-shaft impeller and the inner guide vane are static, the inlet airflow is guided into airflow with tangential component, the outer ring gear drives the turbo-fan impeller to work in reverse rotation, which just offsets the tangential component into the axial boost airflow, ensuring the turbo-fan mode of the inner channel boost capability;

[0016] III turbo-shaft mode Turbo-fan mode: the planetary carrier drives the turbo-shaft impeller to rotate forward, the outer ring gear drives the turbo-fan impeller to rotate in reverse, the inner guide vane is static, the turbo-shaft impeller and the turbo-fan impeller form a counter-rotation, which boosts and accelerates the inlet airflow into axial airflow, continuously maintaining the inner channel boost capability of the transition state

[0017] The planetary gear type reduction transmission shaft fan engine based on Flade fan is characterized in that the shaft fan engine is embedded in the aircraft fuselage, the power output shaft passes through the double-sided S-shaped air inlet channel, the power is transmitted vertically 90 degrees upward by the bevel gear at the end of the power output shaft, the diameter of the bevel gear at the bottom of the steering shaft is 1-3 times that of the bevel gear at the end of the power output shaft, which is used for speed reduction transmission, the bevel gear at the top of the rotating shaft drives the counter-rotation bevel gear, which respectively drives the first drive shaft and the second drive shaft, the first drive shaft drives the left rotor to rotate forward, and the second drive shaft drives the right rotor to rotate in reverse to offset the gyroscopic moment;

[0018] The aircraft adopts tiltable, foldable and variable-pitch counter-rotating rotors and shaft fan engines as the power system of the aircraft, which fully utilizes the advantages of high force efficiency of turbo-shaft rotors and high lift of turbo-fan in economic cruise, and skips the fixed-wing take-off stage with high thrust demand, realizes the maximum capacity of the aircraft, and takes the fixed-wing transport aircraft as an example. During take-off and climb, the thrust-to-weight ratio is about 0.3, and only about 0.1 is needed to overcome resistance during cruise, that is, the original 1000kgf propulsion 1500kW power system can only take off a 3.33-ton fixed-wing transport aircraft. By using a turbo-shaft rotor aircraft with a force efficiency of 4.1kg / kW, the tilt rotor horizontal propulsion is flown to a speed limit of more than 500km / h, and then converted into a turbo-fan fixed-wing high-speed economic cruise, directly skipping the take-off and climb stage of the turbo-fan fixed-wing aircraft that can only take off 3.33 tons, thereby increasing the design weight of the aircraft from 3.33 tons to 6.15 tons;

[0019] The working modes of the aircraft are as follows:

[0020] ① The shaft fan engine works in the turbo-shaft mode, the rotor of the aircraft is tilted to the vertical position, the rotor is used to provide the lift, the aircraft has the advantages of high power efficiency and strong take-off load capacity, and vertical take-off and landing of the aircraft is realized;

[0021] ② The shaft fan engine works in the turbo-shaft mode, the rotor of the aircraft is tilted forward, and the aircraft flies at a low speed of about 200-300 km / h;

[0022] ③ The shaft fan engine works in the turbo-shaft mode, the rotor of the aircraft is tilted to the horizontal position, the aircraft flies at a medium speed of about 400-500 km / h, and the medium-speed economic flight is realized in the propeller mode;

[0023] ④ The shaft fan engine is converted from the turbo-shaft mode to the turbo-fan mode, the rotor of the aircraft is folded, the aircraft flies at a high speed of about 700-1000 km / h, and the aircraft has the advantages of high efficiency and prominent stealth combat.

[0024] Compared with the prior art, the advantages of the present application are that a planetary gear type speed reduction transmission shaft fan engine structure based on a Flade fan is provided, the pressurization capacity of the internal flow passages of the turbo-shaft and turbo-fan modes is continuously maintained through the ingenious cooperation of the internal guide vanes and the turbo-shaft / turbo-fan impellers, the maximum driving capacity of the two modes of large-bypass-ratio fan propulsion and high shaft power efficient speed reduction output can be realized, and the continuous and smooth conversion of the turbo-shaft / turbo-fan mode can be realized; the high power efficiency contra-rotating rotor which can be tilted, folded and variable-pitch and the integrated shaft fan variable cycle engine which can be used as a power system are adopted, the vertical take-off with strong load capacity, the economic cruise at low, medium and high speeds are realized; the advantages of the turbo-shaft rotor in high power efficiency and strong take-off load capacity and the turbo-fan in economic cruise lift are fully utilized, the take-off and climb stage of the large turbo-fan fixed-wing which seeks large propulsion is directly skipped, and the maximum capacity of the aircraft is realized. BRIEF DESCRIPTION OF DRAWINGS

[0025] Figure 1 The present application is a planetary gear type speed reduction transmission shaft fan engine structure based on a Flade fan.

[0026] Figure 2 The present application is a structural schematic view of the planetary gear transmission mechanism and the mode conversion mechanism.

[0027] Figure 3 The present application is a working schematic view of the new internal pressurization stage in the turbo-shaft mode and the turbo-fan mode.

[0028] Figure 4 The present application is a schematic view of the turbo-shaft engine driving the contra-rotating bevel gears to realize the contra-rotation.

[0029] Figure 5 Schematic diagram of the shaft fan engine mounted on a tiltable foldable variable pitch contra-rotating rotor aircraft.

[0030] In the figure: 1-power output shaft, 2-planetary gear mechanism, 21-oil lubrication tank, 22-outer ring gear, 23-planet wheel, 24-Flade fan connecting member, 25-sun gear, 26-carrier, 27-oil retaining ring, 3-electromagnetic clutch, 4-assistant motor, 5-turboshaft impeller, 6-inner guide vane, 7-Flade fan, 71-turboshaft impeller, 72-fan, 8-supporting rib, 9-outer casing, 10-fan guide vane, 11-high pressure compressor, 12-combustion chamber, 13-gas turbine, 14-power turbine, 15-adjustable nozzle, 16-double side S-bend air inlet, 17-rotor, 18-tilting mechanism, 19-contra-rotating drive shaft, 20-vertically taking off and landing high speed stealth aircraft. DETAILED DESCRIPTION

[0031] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.

[0032] Please refer to Figure 1The Flade fan-based planetary gear type reduction transmission shaft fan engine structure in the embodiment of the present application comprises: double-sided S-shaped air inlet channel 16, turbo shaft impeller 5, inner duct guide vane 6, Flade fan 2, power output shaft 1, planetary gear transmission mechanism 2, mode conversion mechanism, power turbine 14, core engine and adjustable tail nozzle, the power output shaft 1 and the planet carrier 26 are fixedly connected, an air inlet cone and the turbo shaft impeller 5 are sequentially installed from the direction of the engine air flow inlet, the inner duct guide vane 6 is installed on the lubricating oil tank 21, the inner duct guide vane 6 is provided with a crown at the top of the blade, the support rib 8 is installed at the crown, the inner duct guide vane 6 plays a role of guiding flow and supporting, and the load of the lubricating oil tank 21 of the planetary gear mechanism is transmitted to the outer duct casing 9 through the support rib 8, the Flade fan 7 comprises turbo fan impeller 71 and fan 72 on the turbo fan impeller, the turbo fan impeller 71 is connected to the outer ring gear 22 through the Flade fan connecting member 24, the Flade fan connecting member 24 is a double-end ring structure, the turbo shaft impeller 5, the inner duct guide vane 6 and the turbo fan impeller 71 constitute a new type of inner duct supercharging stage, the supercharging capacity of the inner duct flow channel in the turbo shaft mode and the turbo fan mode is continuously maintained through the ingenious cooperation of the inner duct guide vane 6 and the turbo shaft / turbo fan impeller, the power turbine 14 drives the sun gear 25 on the planetary gear transmission mechanism, respectively drives the Flade fan 7 fixedly connected with the outer ring gear 22 and the power output shaft 1 fixedly connected with the planet carrier 26 at different speeds, the mode conversion mechanism comprises an auxiliary motor 4 and an electromagnetic clutch 3;

[0033] Please refer to Figure 2 In the embodiment of the present application, the auxiliary motor 4 is installed in the motor cylinder 211 protruding at the left end of the lubricating oil tank 21 and is driven by the motor driving gear 44 engaged with the outer ring gear 22, when the engine is switched from the turbo shaft mode to the turbo fan mode, the auxiliary motor 4 actively drives the outer ring gear 22 to accelerate, when the engine is switched from the turbo fan mode to the turbo shaft mode, the auxiliary motor 4 actively brakes the outer ring gear 22 to decelerate, thereby speeding up the mode conversion process.

[0034] Please refer to Figure 2 In the embodiment of the present application, the electromagnetic clutch 3 is composed of an armature 31, a coil 32, an iron core 33 and a spring 34 and is connected to the inner wall surface of the left end ring of the lubricating oil tank 21 through a mounting head, the power output shaft 1 and the outer ring gear 22 are both provided with electromagnetic clutch locking holes, the electromagnetic clutch 3 comprises a turbo fan mode state of locking the planet carrier without current, a transition state of not locking in the middle current, a turbo shaft mode state of locking the outer ring gear with maximum current and a turbo fan mode state of no current, which is beneficial to high-speed economic cruising.

[0035] Please refer to Figure 1, the embodiment of the present application, the oil lubrication tank 21 is a cylinder structure with two side end ring, oil lubrication tank 21 is surrounded in planetary gear transmission mechanism 2 and mode conversion mechanism, adopt from the bearing inner ring even to the outer ring and from the sun wheel even to the outer ring ring under the oil supply technology, and adopt multi-path oil supply technology respectively oil lubrication bearing, gear, auxiliary motor and electromagnetic clutch, finally under the action of gravity back to the oil tank bottom back oil, play the role of oil lubrication cooling planetary gear transmission mechanism and mode conversion mechanism, the Flade fan connecting member 24, first sealing grate and second sealing grate ensure the sealing of the right end of oil lubrication tank 21, the first sealing grate is installed on the right end ring of oil lubrication tank 21, the first sealing grate seals the end of oil lubrication tank 21, the second sealing grate is installed on the stationary part close to the engine intermediate nacelle, the second sealing grate seals the double rotating parts composed of power turbine shaft and Flade fan connecting member 24, ensure the oil circuit sealing of the right end of oil lubrication tank 21, the left end of oil lubrication tank 21 is provided with oil baffle ring 27 and oil baffle cover 41, the oil baffle ring 27 is fixedly connected in the center of oil lubrication tank 21 and is sleeved on the power output shaft 1, the oil baffle cover 41 is coaxially installed with the auxiliary motor 4, which is convenient for the dismounting and maintenance of the auxiliary motor, and plays the effect of oil circuit sealing of the left end of oil lubrication tank 21;

[0036] Please refer to Figure 3 , the embodiment of the present application, in order to ensure that the power turbine to power output shaft is high efficiency speed reduction transmission, the new type of internal pressure stage is used to output the power output shaft 1 forward, the new type of internal pressure stage continuously maintains the internal pressure of the two modes of the internal flow channel of the turbine shaft and the turbofan through the ingenious cooperation of the internal guide vane 6 and the turbine / turbofan impeller, and the method is:

[0037] I turbine mode; the power output shaft 1 drives the turbine impeller 5 to rotate forward, the electromagnetic clutch 3 locks the turbine impeller 5 on the outer ring gear, the internal guide vane 6 and the turbofan impeller 71 are static, the airflow enters the internal flow channel under the pressure of the turbine impeller 5, accelerates the inlet airflow into airflow with tangential component, under the effect of the internal guide vane 6 and the turbofan impeller 71, the tangential component is guided into the axial pressure airflow, which ensures the internal pressure of the turbine mode;

[0038] II turbofan mode: the electromagnetic clutch 3 locks the turbine impeller 5 on the power output shaft 1, the turbine impeller 5 and the internal guide vane 6 are static, the inlet airflow is guided into airflow with tangential component, the outer ring gear reversely rotates to drive the turbofan impeller 71 to work and accelerate the gas, which just offsets the tangential component into the axial pressure airflow, which ensures the internal pressure of the turbofan mode;

[0039] III turbine mode The turbofan mode: the planetary gear 26 drives the turbo shaft impeller 5 to rotate forward, the outer gear ring drives the turbo fan impeller 71 to rotate reversely, the inner guide vane 6 is static, the turbo shaft impeller 5 and the turbo fan impeller 71 form a counter-rotation, the inlet airflow is pressurized and accelerated into an axial airflow, and the internal conical pressurization capacity in the transition state is continuously maintained;

[0040] Please refer to Figure 4 In the embodiment of the application, the axial fan engine is embedded in the aircraft 20 body, the power output shaft (1) passes through the double-sided S-shaped air inlet channel, and the power is transmitted vertically upward by 90 degrees through the bevel gear meshing at the end of the power output shaft 1 to the steering shaft 191, the bevel gear at the bottom of the steering shaft 191 has a diameter of 1-3 times that of the bevel gear at the end of the power output shaft 1, and is used for speed reduction transmission, the bevel gear at the top of the steering shaft 191 drives the counter-rotating bevel gear, and drives the first drive shaft 192 and the second drive shaft 193 respectively, the first drive shaft 192 drives the left rotor to rotate forward, and the second drive shaft 193 drives the right rotor to rotate reversely, so as to offset the gyroscopic moment;

[0041] Please refer to Figure 5 In the embodiment of the application, the aircraft 20 adopts the tiltable, foldable and variable-pitch counter-rotating rotor 17 and the axial fan engine as the power system of the aircraft 20, the two sides of the counter-rotating rotor are installed on the tilting mechanism 18, the rotor 17 is folded by the motor installed near the blade root, and the rotor 17 is pitch-adjusted by the hydraulic pitch-adjusting system, so that the advantages of the turbo shaft rotor, such as high force efficiency and strong take-off load capacity, and the advantages of the turbo fan, such as high economic cruise lift, are fully exerted, the fixed-wing take-off stage with high thrust demand is skipped, the maximum capacity of the aircraft 20 is realized, and for example, in the case of a fixed-wing transport aircraft, the thrust-to-weight ratio is about 0.3 during take-off and climb, and only about 0.1 is needed during cruise to overcome resistance, that is, the original 1000kgf propulsion 1500kW power system can only take off a 3.33-ton fixed-wing transport aircraft, through the use of the aircraft 20 with a force efficiency of 4.1kg / kW, the counter-rotating rotor, after horizontal propulsion flight to a speed limit of more than 500km / h, is converted into a turbo fan fixed-wing high-speed economic cruise, directly skipping the take-off and climb stage of the turbo fan fixed-wing aircraft that can only take off 3.33 tons, so that the design weight of the aircraft 20 is increased from 3.33 tons to 6.15 tons;

[0042] The designed aircraft 20 has the following working modes:

[0043] ① The axial fan engine works in the turbo shaft mode, the rotor 17 of the aircraft 20 is tilted to the vertical position, the rotor provides lift with the advantages of high force efficiency and strong take-off load capacity, and the vertical take-off and landing of the aircraft 20 is performed;

[0044] ②Shaft fan engine works in turbo-shaft mode, the rotor 17 of the aircraft 20 is forward inclined, the aircraft 20 flies at a low speed of about 200-300km / h;

[0045] ③Shaft fan engine works in turbo-shaft mode, the rotor 17 of the aircraft 20 is inclined to a horizontal position, the aircraft 20 flies at a medium speed of about 400-500km / h, and realizes medium-speed economic flight in propeller mode;

[0046] ④Shaft fan engine is converted from turbo-shaft to turbo-fan mode, fan propulsion is utilized, the rotor (17) of the aircraft 20 is folded, the aircraft 20 flies at a high speed of about 700-1000km / h, and the aircraft 20 has prominent stealth combat advantages due to the engine being embedded in the fuselage and the double-side S-bend air inlet.

[0047] The present application is not limited to the above-mentioned embodiments, and on the basis of the technical solutions disclosed in the present application, some simple modifications, equivalent changes and modifications can be made to some technical features by those skilled in the art according to the disclosed technical content without creative labor, which are all within the scope of the technical solutions of the present application.

Claims

1. A Flade fan based planetary geared reduction drive shaft fan engine configuration comprising: Bilateral S-bend air intake (16), turbo-shaft impeller (5), inner guide vane (6), Flade fan (2), power output shaft (1), planetary gear transmission mechanism (2), mode conversion mechanism, power turbine (14), core engine and adjustable nozzle, the power output shaft (1) and planet carrier (26) are fixedly connected, an air inlet cone and a turbo-shaft impeller (5) are sequentially installed from the direction of the engine air flow inlet, the inner guide vane (6) is installed on the lubricating oil tank (21), the inner guide vane (6) has a crown at the top of the blade, a support rib (8) is installed at the crown, the inner guide vane (6) plays a role of guiding and supporting, and force of the lubricating oil tank (21) of the planetary gear mechanism is transmitted to the outer casing (9) through the support rib (8), the Flade fan (7) comprises a turbofan impeller (71) and a fan (72) on the turbofan impeller, the turbofan impeller (71) is connected to the outer ring gear (22) through a Flade fan connecting member (24), the Flade fan connecting member (24) is a double-end ring structure, the turbo-shaft impeller (5), the inner guide vane (6) and the turbofan impeller (71) constitute a new inner-duct supercharging stage, the turbo-shaft and turbofan two-mode inner-duct flow channel supercharging capacity is continuously maintained through the ingenious cooperation of the inner guide vane (6) and the turbo-shaft / turbofan impeller, the power turbine (14) drives a sun gear (25) on the planetary gear transmission mechanism, respectively drives the Flade fan (7) fixedly connected with the outer ring gear (22) and the power output shaft (1) fixedly connected with the planet carrier (26) at different speeds, the mode conversion mechanism comprises an auxiliary motor (4) and an electromagnetic clutch (3); The auxiliary motor (4) is installed in a motor cylinder (211) protruding from the left end of the lubricating oil tank (21) and is driven by a motor driving gear (44) engaged with the outer ring gear (22), when the engine is switched from the turbo-shaft mode to the turbofan mode, the auxiliary motor (4) actively drives the outer ring gear (22) to accelerate, when the engine is switched from the turbofan mode to the turbo-shaft mode, the auxiliary motor (4) actively brakes the outer ring gear (22) to decelerate, thereby speeding up the mode conversion process; The electromagnetic clutch (3) is composed of an armature (31), a coil (32), an iron core (33) and a spring (34), and is connected to the inner wall surface of the left end ring of the lubricating oil tank (21) through a mounting head (31), electromagnetic clutch lock holes are formed on the power output shaft (1) and the outer ring gear (22), the electromagnetic clutch (3) comprises a turbofan mode without current locking planet carrier state, a transition state of intermediate current without locking state, a turbo-shaft mode of maximum current locking outer ring gear state, and a turbofan mode without current state is conducive to high-speed economic cruising. The oil lubrication tank (21) is a cylindrical structure with two end rings, the oil lubrication tank (21) surrounds the planetary gear transmission mechanism (2) and the mode conversion mechanism, adopts the ring oil supply technology of uniformly throwing from the bearing inner ring to the outer ring and uniformly throwing from the sun gear to the outer ring gear, and adopts the multi-path oil supply technology to lubricate and cool the bearings, gears, auxiliary motor and electromagnetic clutch, and finally returns to the oil tank bottom under the action of gravity to return oil, which plays a role of lubricating and cooling the planetary gear transmission mechanism and the mode conversion mechanism, the Flade fan connecting member (24), the first sealing grate and the second sealing grate ensure the sealing of the right end of the oil lubrication tank (21), the first sealing grate is installed on the right end ring of the oil lubrication tank (21), and the first sealing grate seals the end of the oil lubrication tank (21), the second sealing grate is installed on the stationary part close to the engine intermediate casing, and the second sealing grate seals the double rotating parts composed of the power turbine shaft and the Flade fan connecting member (24), which ensures the oil circuit sealing of the right end of the oil lubrication tank (21), the oil lubrication tank (21) is provided with an oil baffle (27) and an oil baffle cover (41) at the left end, the oil baffle (27) is fixedly connected to the center of the oil lubrication tank (21) and is sleeved on the power output shaft (1), and the oil baffle cover (41) is coaxially installed with the auxiliary motor (4), which is convenient for dismounting and repairing the auxiliary motor and plays a role of sealing the oil circuit at the left end of the oil lubrication tank (21).

2. A Flade fan based planetary geared reduction drive shaft fan engine type as claimed in claim 1 characterized by, In order to ensure high-efficiency deceleration transmission from the power turbine to the power output shaft, a new type of internal pressure boosting stage is used to output the power output shaft (1) forward, the new type of internal pressure boosting stage continuously maintains the internal pressure boosting capacity of the internal flow channel in the two modes of the turbo shaft and the turbo fan through the ingenious cooperation of the internal guide vane (6) and the turbo shaft / turbo fan impeller, and the method is as follows: I. Turbo shaft mode: the power output shaft (1) drives the turbo shaft impeller (5) to rotate forward, the electromagnetic clutch (3) locks the turbo shaft impeller (5) on the outer ring gear, the internal guide vane (6) and the turbo fan impeller (71) are static, the airflow enters the internal flow channel under the boosting of the turbo shaft impeller (5), accelerates the inlet airflow into airflow with tangential component, and under the effects of the internal guide vane (6) and the turbo fan impeller (71), the tangential component is guided into axial boosting airflow, which ensures the internal pressure boosting capacity of the turbo shaft mode; II. Turbo fan mode: the electromagnetic clutch (3) locks the turbo shaft impeller (5) on the power output shaft (1), the turbo shaft impeller (5) and the internal guide vane (6) are static, the inlet airflow is guided into airflow with tangential component, the outer ring gear reversely rotates to drive the turbo fan impeller (71) to work and accelerate the gas, which just offsets the tangential component into axial boosting airflow, which ensures the internal pressure boosting capacity of the turbo fan mode. III vortex-shaft mode Vortex-fan mode: the planetary carrier (26) drives the vortex-shaft impeller (5) to rotate forward, the outer ring gear drives the vortex-fan impeller (71) to rotate reversely, the inner guide vanes (6) are static, the vortex-shaft impeller (5) and the vortex-fan impeller (71) form counter-rotation, the inlet airflow is pressurized and accelerated into axial airflow, and the inner guide vanes maintain the pressurization ability of the transition state.

3. A Flade fan based planetary geared reduction drive shaft fan motor configuration as claimed in claim 1, wherein, The shaft fan engine is embedded in the aircraft body, the power output shaft (1) passes through the double-sided S-bend air inlet, the power is transmitted vertically 90 degrees upward by the bevel gear meshing the steering shaft (191) at the end of the power output shaft (1) secondary speed reduction, the bevel gear diameter at the bottom of the steering shaft (191) is 1-3 times that of the bevel gear at the end of the power output shaft (1) for speed reduction transmission, the bevel gear at the top of the steering shaft (191) drives the counter rotating bevel gear, which respectively drives the first drive shaft (192) and the second drive shaft (193), the first drive shaft (192) drives the left rotor forward rotation, and the second drive shaft (193) drives the right rotor reverse rotation to offset the gyroscopic moment; The aircraft adopts tiltable, foldable and variable pitch counter rotating rotors (17) and shaft fan engines as the power system of the aircraft, which fully utilizes the advantages of large lift force of the turboshaft rotor and large lift of the turbofan in economic cruise, and skips the fixed wing take-off stage with large thrust demand, realizes the maximum capacity of the aircraft, and the aircraft has the following working modes: ①The engine works in turboshaft mode, the rotor (17) of the aircraft is tilted to the vertical position, the rotor provides lift, has the advantages of large lift force and strong take-off load capacity, and the aircraft is vertically taken off and landed; ②The engine works in turboshaft mode, the rotor (17) of the aircraft is tilted forward, and the aircraft flies at a speed of 200-300 km / h; ③The engine works in turboshaft mode, the rotor (17) of the aircraft is tilted to the horizontal position, the aircraft flies at a speed of 400-500 km / h, and realizes medium-speed economic flight in propeller mode; ④The engine is converted from turboshaft to turbofan mode, the rotor (17) of the aircraft is folded, the aircraft flies at a speed of 700-1000 km / h, and due to the engine embedded in the body and the double-sided S-bend air inlet, the stealth combat advantage is prominent.

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