CN110486165A - Turbo oar engine and unmanned plane - Google Patents
Turbo oar engine and unmanned plane Download PDFInfo
- Publication number
- CN110486165A CN110486165A CN201910698325.4A CN201910698325A CN110486165A CN 110486165 A CN110486165 A CN 110486165A CN 201910698325 A CN201910698325 A CN 201910698325A CN 110486165 A CN110486165 A CN 110486165A
- Authority
- CN
- China
- Prior art keywords
- gear
- gas generator
- generator
- casket
- turbo oar
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000446 fuel Substances 0.000 claims abstract description 24
- 239000000126 substance Substances 0.000 claims abstract description 7
- 239000007789 gas Substances 0.000 claims description 71
- 239000003921 oil Substances 0.000 claims description 30
- 230000005540 biological transmission Effects 0.000 claims description 22
- 238000009434 installation Methods 0.000 claims description 16
- 239000010687 lubricating oil Substances 0.000 claims description 16
- 239000003595 mist Substances 0.000 claims description 16
- 239000000295 fuel oil Substances 0.000 claims description 10
- 238000006243 chemical reaction Methods 0.000 claims description 9
- 239000000567 combustion gas Substances 0.000 claims description 7
- 238000007514 turning Methods 0.000 claims description 7
- 238000004519 manufacturing process Methods 0.000 description 7
- 238000005516 engineering process Methods 0.000 description 3
- 241000251468 Actinopterygii Species 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000005662 electromechanics Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000010304 firing Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/10—Aircraft characterised by the type or position of power plants of gas-turbine type
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
-
- 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
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/20—Adaptations of gas-turbine plants for driving vehicles
- F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
-
- 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
- F02C7/32—Arrangement, mounting, or driving, of auxiliaries
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
- Supercharger (AREA)
Abstract
The present invention provides a kind of turbo oar engine and unmanned planes, turbo oar engine includes host casket, the front end that host casket is arranged in and the alternating current generator for driving the paddle shaft of propeller rotation, the rear end of host casket is arranged in and being used to convert the gas generator of mechanical energy for the chemical energy of fuel and be arranged in the rear end of host casket and be used to convert the mechanical energy that gas generator exports to electric energy, paddle shaft and alternating current generator are laid in the top of host casket, and gas generator is laid in the lower part of host casket.By the way that paddle shaft and gas generator are staggered laying, so that the pulling force of propeller avoids gas generator stress deformation without going past gas generator.Paddle shaft and gas generator, which are staggered to lay, can also reserve the space for installing alternating current generator, by the rear end that alternating current generator and gas generator are compactly laid in host casket, and alternating current generator is avoided to protrude from host casket, it can solve small-sized turbo oar engine and be difficult to the problem of installing powerful alternating current generator.
Description
Technical field
The present invention relates to turbo oar engine technical fields, particularly, are related to a kind of turbo oar engine.In addition, the present invention is also
It is related to a kind of unmanned plane including above-mentioned turbo oar engine.
Background technique
Lock on needs high powered radar and electromagnetic jammer or superpower laser, and uses full Flying by wire, electricity
The technologies such as dynamic auxiliary landing increase generated output demand.Next-generation scout in China hits integrated fixed-wing unmanned plane requirement
Start function electromechanics alliance, mechanical output demand is 400 kilowatts~500 kilowatts, and generated output demand is 20 kilowatts~50 kilowatts.
The design of small-sized turbo oar engine have power to weight ratio, front face area, intake and exhaust direction, transmission efficiency, structure complexity, reliability,
Manufacturing cost etc. is various to be comprehensively considered.PRACTICE OF DESIGN shows to install the small-sized turbo oar engine of high power alternator
Design difficulty is very big, and the small-sized turbo oar engine generated output of Earlier designs is insufficient, and increasing generated output will then change greatly, therefore at present
The small-sized turbo oar engine of generated output requirement is not met.
Summary of the invention
The present invention provides a kind of turbo oar engine and unmanned plane, with solve small-sized turbo oar engine be difficult to install it is high-power
Alternating current generator the problem of.
The technical solution adopted by the invention is as follows:
One aspect of the present invention provides a kind of turbo oar engine, including host casket, the front end of host casket is arranged in and is used for
It drives the paddle shaft of propeller rotation, the rear end of host casket is set and the combustion gas for converting the chemical energy of fuel to mechanical energy
Generator and be arranged in host casket rear end and for by the mechanical energy that gas generator export be converted into electric energy exchange hair
Motor, paddle shaft and alternating current generator are laid in the top of host casket, and gas generator is laid in the lower part of host casket.
Further, host casket is equipped with attachment, and the mechanical energy for exporting gas generator is equipped in host casket and is passed
It passs the under drive gear of paddle shaft and alternating current generator and the mechanical energy for exporting gas generator passes to attachment
Accessory drive gear, under drive gear is laid in the side of host casket, and attachment and accessory drive gear are laid in host casket
The other side.
Further, host casket includes front housing and the rear housing that is fastened and connected with front housing, and paddle shaft is arranged in preceding machine
On casket, gas generator is arranged on rear housing, and alternating current generator is arranged on rear housing.
Further, gas generator includes for exporting mechanical energy to the power turbine of under drive gear and use
It exports in by mechanical energy to the gas turbine of accessory drive gear；The combustion gas of the power turbine and gas turbine of power turbine
The direction of rotation of turbine rotor is opposite.
Further, attachment includes the oil pump for being arranged on front housing and be used to provide lubricating oil, is arranged in front housing
And for from the oil mist separator of lubricating oil is separated and recovered in mist of oil, be arranged on front housing and for provide the fuel pump of fuel with
And the starter-generator on rear housing and for starting gas generator is set；Rear housing is equipped with for adjusting propeller
Blade angle is to guarantee the propeller governor of the invariablenes turning speed of propeller.
Further, under drive gear includes the deceleration transmission master being set in the power turbine shaft of power turbine
Gear, the second intermediate gear engaged with the first intermediate gear, is arranged the first intermediate gear engaged with deceleration transmission master gear
The governor drive gear that is engaged in the drive shaft of propeller governor and with the second intermediate gear, be set in paddle shaft and with
The paddle shaft driving gear of second intermediate gear engagement, the third intermediate gear and being set in engaged with the second intermediate gear exchange
The friendship hair driving gear engaged in the drive shaft of generator and with third intermediate gear.
Further, the first intermediate gear is equipped with hydraulic survey and turns round piston, and front housing is equipped with lives for turning round with hydraulic survey
Plug cooperates to measure the pressure transducer of the torque of the first intermediate gear；Front housing is equipped with for measuring the revolving speed of paddle shaft suddenly
That sensor.
Further, accessory drive gear includes the accessory drive master being set on the gas turbine shaft of reaction wheel
Gear, is set in the separator for being set in the drive shaft of oil mist separator and engaging with accessory drive master gear driving gear
The lubricating oil pump driver gear that engage in the drive shaft of oil pump and with separator driving gear drives gear to engage with separator
4th intermediate gear, the fuel oil pump driver gear for being set in the drive shaft of fuel pump and being engaged with the 4th intermediate gear and combustion
5th intermediate gear of oily pump driver gear engagement and be set in the drive shaft of starter-generator and with the 5th intermediate gear
The starting of engagement drives gear.
Further, rear housing is saved equipped with main installation, and main installation section is connected by the load-bearing frame of mounting bracket and fuselage
It connects.
Another aspect of the present invention provides a kind of unmanned plane, including above-mentioned turbo oar engine.
The invention has the following advantages:
Turbo oar engine of the invention, including host casket, paddle shaft, gas generator and alternating current generator.Fuel is firing
Burning, gas generator can convert mechanical energy for the chemical energy of fuel in gas generator.Propeller, paddle are installed in paddle shaft
Axis rotates under the action of mechanical energy and propeller is driven to rotate.The mechanical energy that alternating current generator can export gas generator
It is converted into electric energy, to supply the electrical equipment on unmanned plane.Paddle shaft and alternating current generator are all laid in the top of host casket, and divide
It is not laid in the front-end and back-end of host casket；Gas generator is laid in the rear end of host casket, and gas generator is laid in master
The lower part of casing.By the way that paddle shaft and gas generator are staggered laying, so that the pulling force of propeller is without going past gas generator,
Gas generator stress deformation is avoided, is conducive to gas generator and improves power and carry out technology innovation.Meanwhile paddle shaft and combustion gas
Generator, which is staggered to lay, can also reserve the space for installing alternating current generator, by the way that alternating current generator is compact with gas generator
Ground is laid in the rear end of host casket, and alternating current generator is avoided to protrude from host casket, can solve small-sized turbo oar engine and is difficult to
The problem of installing powerful alternating current generator.The main body of turbo oar engine of the invention using host casket as turbo oar engine,
Subordinate body using paddle shaft, gas generator and alternating current generator as turbo oar engine, with setting for traditional turbo oar engine
Meter theory is totally different, and general shape and structure design have certain symmetry, meets aeronautical engineering aesthetic theory, and ensure whirlpool
Paddle motor is compact-sized, outer dimension is small, can be perfectly suitable for unmanned plane.Turbo oar engine structure design of the invention
It simplifies, number of parts is few, and power to weight ratio is high, significantly reduces manufacturing cost.
Other than objects, features and advantages described above, there are also other objects, features and advantages by the present invention.
Below with reference to accompanying drawings, the present invention is described in further detail.
Detailed description of the invention
The attached drawing constituted part of this application is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
Fig. 1 is the side view of the turbo oar engine of the preferred embodiment of the present invention；
Fig. 2 is the front view of the turbo oar engine of the preferred embodiment of the present invention；
Fig. 3 is the rearview of the turbo oar engine of the preferred embodiment of the present invention；
Fig. 4 is the bottom view of the turbo oar engine of the preferred embodiment of the present invention；
Fig. 5 is the transmission block plan of the turbo oar engine of the preferred embodiment of the present invention；
Fig. 6 is one of structural schematic diagram of turbo oar engine of the preferred embodiment of the present invention；
Fig. 7 is the second structural representation of the turbo oar engine of the preferred embodiment of the present invention；
Fig. 8 is the gear drive link figure of the turbo oar engine of the preferred embodiment of the present invention.
Description of symbols:
1, host casket；11, front housing；12, rear housing；2, paddle shaft；21, propeller governor；3, gas generator；31,
Power turbine；311, power turbine；32, gas turbine；321, reaction wheel；4, alternating current generator；51, lubricating oil
Pump；52, oil mist separator；53, fuel pump；54, starter-generator；61, deceleration transmission master gear；62, the first intermediate gear；
63, the second intermediate gear；64, governor drive gear；65, paddle shaft drives gear；66, third intermediate gear；67, hair driving is handed over
Gear；71, accessory drive master gear；72, separator drives gear；73, lubricating oil pump driver gear；74, the 4th intermediate gear；
75, fuel oil pump driver gear；76, the 5th intermediate gear；77, starting drives gear；81, pressure transducer；82, hall sensing
Device；91, main installation section；92, mounting bracket.
Specific embodiment
It should be noted that in the absence of conflict, the features in the embodiments and the embodiments of the present application can phase
Mutually combination.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is the side view of the turbo oar engine of the preferred embodiment of the present invention；Fig. 2 is the whirlpool paddle of the preferred embodiment of the present invention
The front view of engine；Fig. 3 is the rearview of the turbo oar engine of the preferred embodiment of the present invention；Fig. 4 is preferred implementation of the present invention
The bottom view of the turbo oar engine of example；Fig. 5 is the transmission block plan of the turbo oar engine of the preferred embodiment of the present invention；Fig. 6 is this
One of the structural schematic diagram of turbo oar engine of invention preferred embodiment；Fig. 7 is the turbo oar engine of the preferred embodiment of the present invention
Second structural representation；Fig. 8 is the gear drive link figure of the turbo oar engine of the preferred embodiment of the present invention.
As shown in Figure 1, Figure 2, Figure 3 and Figure 4, the turbo oar engine of the present embodiment, including host casket 1, setting are in host casket 1
Front end and paddle shaft 2 for driving propeller to rotate, the rear end of host casket 1 is set and for converting the chemical energy of fuel
For mechanical energy gas generator 3 and the rear end of host casket 1 be set and turn for the mechanical energy that exports gas generator 3
The alternating current generator 4 of electric energy is turned to, paddle shaft 2 and alternating current generator 4 are laid in the top of host casket 1, and gas generator 3 is laid in
The lower part of host casket 1.
Turbo oar engine of the invention, including host casket 1, paddle shaft 2, gas generator 3 and alternating current generator 4.Fuel
It burns in gas generator 3, gas generator 3 can convert mechanical energy for the chemical energy of fuel.Spiral shell is installed in paddle shaft 2
Paddle is revolved, paddle shaft 2 rotates under the action of mechanical energy and propeller is driven to rotate.Alternating current generator 4 can be defeated by gas generator 3
Mechanical energy out is converted into electric energy, to supply the electrical equipment on unmanned plane.Paddle shaft 2 and alternating current generator 4 are all laid in host
The top of casket 1, and it is laid in the front-end and back-end of host casket 1 respectively；Gas generator 3 is laid in the rear end of host casket 1, and fires
Gas generator 3 is laid in the lower part of host casket 1.By the way that paddle shaft 2 and gas generator 3 are staggered laying, so that the drawing of propeller
Power avoids 3 stress deformation of gas generator without going past gas generator 3, is conducive to gas generator 3 and improves power and progress
Technology innovation.Meanwhile paddle shaft 2 is staggered with gas generator 3 and lays the space that can also reserve installation alternating current generator 4, passes through
Alternating current generator 4 and gas generator 3 are compactly laid in the rear end of host casket 1, and alternating current generator 4 is avoided to protrude from master
Casing 1 can solve small-sized turbo oar engine and be difficult to the problem of installing powerful alternating current generator.Whirlpool paddle of the invention starts
Main body of the machine using host casket 1 as turbo oar engine is sent out using paddle shaft 2, gas generator 3 and alternating current generator 4 as whirlpool paddle
The subordinate body of motivation, totally different with the design concept of traditional turbo oar engine, general shape and structure design have certain pair
Title property, meets aeronautical engineering aesthetic theory, and ensure that turbo oar engine is compact-sized, outer dimension is small, can fit well
For unmanned plane.Turbo oar engine structure design of the invention is simplified, and number of parts is few, and power to weight ratio is high, significantly reduces manufacture
Cost.Optionally, the windward side of host casket 1 is circle, and the windward side of the paddle shaft driving gear 65 in paddle shaft 2 and paddle shaft 2 is circle
Shape, the windward side of gas generator 3 are circle, and the windward side of alternating current generator 4 is circle.Optionally, the diameter of host casket 1 is about
For 540mm, it is about 300mm that paddle shaft, which drives the diameter of gear 65, and the diameter of gas generator 3 is about 370mm, alternating current generator 4
Diameter be about 170mm, between gas generator 3 and alternating current generator 4 retain 3mm~5mm safe distance, turbo oar engine
The diameter of the fuselage of applicable unmanned plane is about 600mm.Optionally, paddle shaft 2 and the coaxial laying of alternating current generator 4 or not coaxial cloth
If.
As shown in figure 5, in the present embodiment, host casket 1 is equipped with attachment, is equipped in host casket 1 for by gas generator 3
The mechanical energy of output passes to the under drive gear of paddle shaft 2 and alternating current generator 4 and for exporting gas generator 3
Mechanical energy passes to the accessory drive gear of attachment, and under drive gear is laid in the side of host casket 1, attachment and accessory drive
Gear is laid in the other side of host casket 1.Under drive gear and accessory drive gear, deceleration transmission tooth are equipped in host casket 1
Wheel is used for driven accessary for being driven paddle shaft 2 and alternating current generator 4, accessory drive gear.Under drive gear is laid in host
The side of casket 1, attachment and accessory drive gear are laid in the other side of host the casket 1, " yin-yang of layout and " taiji schemata "
The layout of fish " is similar in a measure.Under drive gear, which is concentrated, to be laid, and attachment and accessory drive gear are concentrated and laid, and makes host casket 1
Outer diameter reduce as far as possible, I& M workload is few, and the performance of turbo oar engine is good, high reliablity.Optionally, deceleration transmission
Gear and accessory drive gear are all made of roller gear.
As shown in fig. 6, host casket 1 includes front housing 11 and the rear machine being fastened and connected with front housing 11 in the present embodiment
Casket 12, paddle shaft 2 are arranged on front housing 11, and gas generator 3 is arranged on rear housing 12, and alternating current generator 4 is arranged in rear machine
On casket 12.The shape of front housing 11 and rear housing 12 is all truncated cone, and front housing 11 and rear housing 12 are fastened and connected to form master
The faying face of casing 1, front housing 11 and rear housing 12 is annular plane, and the conical space inside host casket 1 is passed as gear
Dynamic room, for accommodating under drive gear and accessory drive gear.It is internal spacious since host casket 1 has cone wall, it fits
It closes and uses high speed number Milling Machining, reduce manufacturing cost, and the light-weight of host casket 1, intensity are high.Optionally, host casket 1
Circular conical surface is equipped with many places and is used for as the port for installing paddle shaft 2, gas generator 3, alternating current generator 4 and attachment.It is optional
Ground bores or mills out oil duct and nozzle opening on host casket 1, and is connected to bushing, passes through for fuel or lubricating oil；In front housing 11
Multiple perforative bushing intercommunicating pores are equipped with rear housing 12, are passed through for cable.It can make the exterior line of turbo oar engine
Quantity is few, and oil leakage phenomenon is few, and shape is clean and tidy, and manufacturing cost is low.
As shown in fig. 6, turbo oar engine uses twin spool gas generator, specifically, gas generator in the present embodiment
3 include for exporting to the power turbine 31 of under drive gear and being used to export mechanical energy to accessory drive mechanical energy
The gas turbine 32 of gear.Fuel burns in gas generator 3, converts thermal energy for chemical energy, thermal energy does gas expansion
Function, being converted into mechanical energy revolves the power turbine 311 of power turbine 31 and the reaction wheel 321 of gas turbine 32
Turn, and then drives under drive gear and accessory drive gear.Specifically, under drive gear is driven by power turbine 31,
Accessory drive gear is driven by gas turbine 32.Optionally, the power turbine 311 of power turbine 31 and gas turbine 32
The direction of rotation of reaction wheel 321 is opposite.Power turbine 311 and reaction wheel 321 reversely rotate, defeated in the same direction
Out, under drive gear is driven using power turbine 311, accessory drive gear is driven using reaction wheel 321, is subtracted
Transmission between fast transmission gear and accessory drive gear is non-interference, and transmission efficiency is high, good reliability.Optionally, combustion gas is sent out
Gas generator 3 is arranged in close to one end of host casket 1 in the air inlet of raw device 3, and the exhaust outlet of gas generator 3 is arranged in combustion gas
The one end of generator 3 far from host casket 1.Air inlet is low-temperature end, and exhaust outlet is temperature end.Under drive gear and accessory drive
Gear is all disposed in the host casket 1 of low-temperature end, and there is no need to which provision for thermal insulation is arranged, and the component of temperature end is not by host
The limitation of casket 1 can free wxpansion backward, the temperature gradient design of complete machine is reasonable.
As shown in Figures 2 and 3, in the present embodiment, attachment includes being arranged on front housing 11 and for providing the cunning of lubricating oil
Oil pump 51, is arranged in front housing the oil mist separator 52 for being arranged on front housing 11 and being used to separate and recover lubricating oil from mist of oil
On 11 and it is used to provide the fuel pump 53 of fuel and the starting hair on rear housing 12 and for starting gas generator 3 is set
Motor 54.Oil pump 51, oil mist separator 52 and fuel pump 53 are arranged on front housing 11, and starter-generator 54 is arranged rear
On casing 12, in a limited space in realize the compact design of structure.Oil pump 51 can be the lubricating oil system of turbo oar engine
System provides lubricating oil.The heated rear volatile formation mist of oil of lubricating oil in oil system, oil mist separator 52 can use centrifuge separation
Principle lubricating oil is separated and recovered from mist of oil.Fuel pump 53 can provide fuel for gas generator 3.Gas generator 3 starts
When, the rotation of starter-generator 54 can drive gas generator 3 to accelerate to idling rating by stationary state.Optionally, rear housing
12 are equipped with the propeller governor 21 for guaranteeing the invariablenes turning speed of propeller for adjusting the blade angle of propeller.Propeller tune
The blade angle of the adjustable propeller of fast device 21, and then guarantee the invariablenes turning speed of propeller.
As shown in Figure 6 and Figure 8, in the present embodiment, under drive gear includes the power for being set in power turbine 311
Deceleration transmission master gear 61 on turbine wheel shaft, the first intermediate gear 62 engaged with deceleration transmission master gear 61, with first among
Second intermediate gear 63 of the engagement of gear 62 is set in the drive shaft of propeller governor 21 and nibbles with the second intermediate gear 63
The governor drive gear 64 of conjunction, the paddle shaft for being set in paddle shaft 2 and being engaged with the second intermediate gear 63 driving gear 65, with the
Two intermediate gears 63 engagement third intermediate gear 66 and be set in the drive shaft of alternating current generator 4 and with third center tooth
The friendship hair driving gear 67 of 66 engagement of wheel.Deceleration transmission master gear 61, the first intermediate gear 62, the second intermediate gear 63, speed regulation
Device drives gear 64, paddle shaft driving gear 65, third intermediate gear 66 and hair driving gear 67 mutually transmission composition is handed over to slow down
Transmission chain is used for drving sprial paddle governor 21, paddle shaft 2 and alternating current generator 4.The line of centres of each gear is in " Tai Ji
" Yang Yuqu " of schema " forms broken line, and broken line has branch to be connected respectively to propeller governor 21, paddle shaft 2 and alternative electric generation
The center of machine 4.By the first intermediate gear 62 of setting, the second intermediate gear 63 and third intermediate gear 66, spiral can be made
Paddle governor 21, paddle shaft 2 and alternating current generator 4 are in suitable position.The gear quantity of under drive gear is few, manufacture at
This is low, and transmission efficiency is high, high reliablity.
As shown in Figure 6 and Figure 7, in the present embodiment, the first intermediate gear 62 is equipped with hydraulic surveys torsion piston, on front housing 11
Equipped with for surveying the pressure transducer 81 for turning round piston cooperation to measure the torque of the first intermediate gear 62 with hydraulic.Among first
Hydraulic survey is installed on gear 62 and turns round piston, and the hydraulic pressure for surveying torsion piston is measured by pressure transducer 81, and then obtain
The torque of first intermediate gear 62.Optionally, front housing 11 is equipped with the Hall sensor 82 for measuring the revolving speed of paddle shaft 2.
Hall sensor 82 is installed on front housing 11 at paddle shaft driving gear 65, Hall sensor 82 can measure paddle shaft drive
The revolving speed of moving gear 65, and then the revolving speed of paddle shaft 2 is obtained, and by the speed feedback of paddle shaft 2 to propeller governor 21.Pass through ginseng
Number acquisition and data processing help to solve blade angle control, power control, fuel oil control, vibration control, compressor surge control
The problems such as processed, makes turbo oar engine efficient operation in security boundary.
As shown in Figure 6 and Figure 8, in the present embodiment, accessory drive gear includes the combustion gas for being set in reaction wheel 321
Accessory drive master gear 71 on turbine wheel shaft is set in the drive shaft of oil mist separator 52 and nibbles with accessory drive master gear 71
The separator driving gear 72 of conjunction, the oil pump for being set in the drive shaft of oil pump 51 and being engaged with separator driving gear 72
Driving gear 73, is set in the drive shaft of fuel pump 53 simultaneously the 4th intermediate gear 74 engaged with separator driving gear 72
The fuel oil pump driver gear 75 engaged with the 4th intermediate gear 74, the 5th intermediate gear 76 engaged with fuel oil pump driver gear 75
And the starting driving gear 77 for being set in the drive shaft of starter-generator 54 and being engaged with the 5th intermediate gear 76.Attachment passes
Dynamic master gear 71, separator driving gear 72, lubricating oil pump driver gear 73, the 4th intermediate gear 74, fuel oil pump driver gear 75,
5th intermediate gear 76 and the mutually transmission composition accessory drive chain of fuel oil pump driver gear 75, for being driven oil mist separator
52, the attachmentes such as oil pump 51, fuel pump 53, starter-generator 54." negative fish of the line of centres of each gear at " taiji schemata "
Area " forms broken line, the center that broken line has branch to be connected respectively to each attachment.By in the 4th intermediate gear 74 and the 5th of setting
Between gear 76, oil mist separator 52, oil pump 51, fuel pump 53 and starter-generator 54 can be made to be in suitable position.
The gear quantity of accessory drive gear is few, and manufacturing cost is low, and transmission efficiency is high, high reliablity.
As shown in Figure 3 and Figure 4, in the present embodiment, rear housing 12 is equipped with main installation section 91, and main installation section 91 passes through installation
Bracket 92 is connect with the load-bearing frame of fuselage.Main installation section 91 is arranged on rear housing 12, is parallel to the faying face of host casket 1,
And it is connect by mounting bracket 92 with the load-bearing frame of fuselage.The pulling force of propeller passes through rear housing 12, main installation section 91, installation
Bracket 92 and load-bearing frame are transferred to fuselage, do not need to design special power transmission casing, keep Path of Force Transfer shorter, reduce whirlpool
The weight of paddle motor is advantageously implemented the lightweight of turbo oar engine, is conducive to the power to weight ratio for improving turbo oar engine.Main peace
Dress section 91 and mounting bracket 92 will not protrude from host casket 1, will not dramatically increase front face area, turbo oar engine installation and removal
Shi Bubi opens side wall covering, convenient for disassembly and assembly.Optionally, mounting bracket 92 is formed by steel-pipe welding.Optionally, front housing 11 or
Rear housing 12 is equipped with multiple auxiliary installation section, for assisting main installation section 91 to carry out the installation of mounting bracket 92.
The preferred embodiment of the present invention additionally provides a kind of unmanned plane, including above-mentioned turbo oar engine.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, made any to repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of turbo oar engine, which is characterized in that
Front end and the paddle shaft (2) for driving propeller to rotate, setting including host casket (1), setting in the host casket (1)
In the rear end of the host casket (1) and the gas generator (3) for converting the chemical energy of fuel to mechanical energy and it is arranged
The host casket (1) rear end and for by the mechanical energy that the gas generator (3) exports be converted into electric energy exchange hair
Motor (4),
The paddle shaft (2) and the alternating current generator (4) are laid in the top of the host casket (1), the gas generator (3)
It is laid in the lower part of the host casket (1).
2. turbo oar engine according to claim 1, which is characterized in that
The host casket (1) is equipped with attachment, is equipped in the host casket (1) for exporting the gas generator (3)
Mechanical energy passes to the under drive gear of the paddle shaft (2) and the alternating current generator (4) and for sending out the combustion gas
The mechanical energy of raw device (3) output passes to the accessory drive gear of the attachment,
The under drive gear is laid in the side of the host casket (1), and the attachment and the accessory drive gear are laid
In the other side of the host casket (1).
3. turbo oar engine according to claim 2, which is characterized in that
The host casket (1) includes front housing (11) and the rear housing (12) being fastened and connected with the front housing (11), described
Paddle shaft (2) is arranged on the front housing (11), and the gas generator (3) is arranged on the rear housing (12), the friendship
Generator (4) are flowed to be arranged on the rear housing (12).
4. turbo oar engine according to claim 3, which is characterized in that
The gas generator (3) include for mechanical energy being exported to the power turbine (31) of the under drive gear and
For mechanical energy being exported to the gas turbine (32) of the accessory drive gear；
The power turbine (311) of the power turbine (31) and the reaction wheel (321) of the gas turbine (32)
Direction of rotation it is opposite.
5. turbo oar engine according to claim 4, which is characterized in that
The attachment includes the oil pump (51) for being arranged on the front housing (11) and be used to provide lubricating oil, is arranged before described
On casing (11) and for from mist of oil separate and recover lubricating oil oil mist separator (52), be arranged on the front housing (11) simultaneously
Fuel pump (53) and setting for providing fuel is on the rear housing (12) and for starting the gas generator (3)
Starter-generator (54)；
The rear housing (12) is equipped with for adjusting the blade angle of the propeller to guarantee the invariablenes turning speed of the propeller
Propeller governor (21).
6. turbo oar engine according to claim 5, which is characterized in that
The under drive gear includes the deceleration transmission master being set in the power turbine shaft of the power turbine (311)
Gear (61), the first intermediate gear (62) engaged with the deceleration transmission master gear (61) and first intermediate gear
(62) engage the second intermediate gear (63), be set in the drive shaft of the propeller governor (21) and with described second in
Between gear (63) engage governor drive gear (64), be set on the paddle shaft (2) and with second intermediate gear
(63) paddle shaft driving gear (65) engaged, the third intermediate gear (66) and set that are engaged with second intermediate gear (63)
The friendship hair driving gear for being located in the drive shaft of the alternating current generator (4) and being engaged with the third intermediate gear (66)
(67)。
7. turbo oar engine according to claim 6, which is characterized in that
First intermediate gear (62) be equipped with hydraulic surveys turn round piston, the front housing (11) equipped with for it is described hydraulic
Survey the pressure transducer (81) for turning round piston cooperation to measure the torque of first intermediate gear (62)；
The front housing (11) is equipped with the Hall sensor (82) for measuring the revolving speed of the paddle shaft (2).
8. turbo oar engine according to claim 5, which is characterized in that
The accessory drive gear includes the accessory drive master being set on the gas turbine shaft of the reaction wheel (321)
Gear (71), point for being set in the drive shaft of the oil mist separator (52) and being engaged with the accessory drive master gear (71)
From device driving gear (72), it is set in the drive shaft of the oil pump (51) and is engaged with separator driving gear (72)
Lubricating oil pump driver gear (73), with the separator driving gear (72) engage the 4th intermediate gear (74), be set in institute
State in the drive shaft of fuel pump (53) and engaged with the 4th intermediate gear (74) fuel oil pump driver gear (75), with it is described
5th intermediate gear (76) of fuel oil pump driver gear (75) engagement and the drive shaft for being set in the starter-generator (54)
Starting driving gear (77) that is upper and being engaged with the 5th intermediate gear (76).
9. turbo oar engine according to claim 3, which is characterized in that
The rear housing (12) passes through mounting bracket (92) and fuselage equipped with main installation section (91), the main installation section (91)
Load-bearing frame connection.
10. a kind of unmanned plane, which is characterized in that
Including turbo oar engine according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910698325.4A CN110486165B (en) | 2019-07-31 | 2019-07-31 | Turboprop engine and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910698325.4A CN110486165B (en) | 2019-07-31 | 2019-07-31 | Turboprop engine and unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110486165A true CN110486165A (en) | 2019-11-22 |
| CN110486165B CN110486165B (en) | 2021-05-07 |
Family
ID=68548990
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910698325.4A Active CN110486165B (en) | 2019-07-31 | 2019-07-31 | Turboprop engine and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110486165B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113639029A (en) * | 2021-08-16 | 2021-11-12 | 上海尚实能源科技有限公司 | Turboprop engine reduction box unit body |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230057234A1 (en) * | 2021-08-19 | 2023-02-23 | Pratt & Whitney Canada Corp. | Method and system for operating an aircraft having a turboprop engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030115885A1 (en) * | 2001-12-21 | 2003-06-26 | Macfarlane Ian Alexander | Offset drive for gas turbine engine |
| US20140225378A1 (en) * | 2013-02-13 | 2014-08-14 | Alenia Aermacchi S.P.A. | System for in-flight restarting of a multi-shaft turboprop engine |
| CN107000848A (en) * | 2014-11-27 | 2017-08-01 | 赛峰直升机发动机公司 | Propulsion unit with selective coupling arrangement |
| US20170314469A1 (en) * | 2016-04-29 | 2017-11-02 | Rolls-Royce Corporation | Reconfigurable lubrication system for multiple powertrain orientations |
| RU2645863C2 (en) * | 2016-08-19 | 2018-02-28 | Акционерное общество "Климов" | Turboprop engine |
| US20180058330A1 (en) * | 2016-08-29 | 2018-03-01 | Rolls-Royce North American Technologies, Inc. | Aircraft having a gas turbine generator with power assist |
-
2019
- 2019-07-31 CN CN201910698325.4A patent/CN110486165B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030115885A1 (en) * | 2001-12-21 | 2003-06-26 | Macfarlane Ian Alexander | Offset drive for gas turbine engine |
| US20140225378A1 (en) * | 2013-02-13 | 2014-08-14 | Alenia Aermacchi S.P.A. | System for in-flight restarting of a multi-shaft turboprop engine |
| CN107000848A (en) * | 2014-11-27 | 2017-08-01 | 赛峰直升机发动机公司 | Propulsion unit with selective coupling arrangement |
| US20170314469A1 (en) * | 2016-04-29 | 2017-11-02 | Rolls-Royce Corporation | Reconfigurable lubrication system for multiple powertrain orientations |
| RU2645863C2 (en) * | 2016-08-19 | 2018-02-28 | Акционерное общество "Климов" | Turboprop engine |
| US20180058330A1 (en) * | 2016-08-29 | 2018-03-01 | Rolls-Royce North American Technologies, Inc. | Aircraft having a gas turbine generator with power assist |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113639029A (en) * | 2021-08-16 | 2021-11-12 | 上海尚实能源科技有限公司 | Turboprop engine reduction box unit body |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110486165B (en) | 2021-05-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106394910B (en) | Hybrid electric drive system for vertical take-off and landing unmanned aerial vehicle | |
| CA2963776C (en) | Hybrid gas-electric turbine engine | |
| EP3246527B1 (en) | Low pressure generator for gas turbine engine | |
| EP2995555B1 (en) | Propulsion system | |
| RU2589532C1 (en) | Hybrid aircraft | |
| JP4115902B2 (en) | Electric auxiliary auxiliary and emergency drive | |
| EP3032075B1 (en) | Integrated apu generator constant speed drive | |
| US8857192B2 (en) | Accessory gearbox with a starter/generator | |
| US10710734B2 (en) | Hybrid aircraft propulsors having electrically-driven augmentor fans | |
| US20130239568A1 (en) | Turbo Assist | |
| CN107645221A (en) | The method of generator and assembling | |
| CN107816384B (en) | Aviation hybrid power system and its unmanned plane based on radial-piston motor | |
| EP3315747B1 (en) | Fan module with rotatable vane ring power system | |
| US9973058B2 (en) | Propeller in-hub power generation and control | |
| CN110486165A (en) | Turbo oar engine and unmanned plane | |
| US20210310412A1 (en) | External auxiliary power unit | |
| CN111009992B (en) | High-low voltage compatible built-in brushless direct current starting power generation system | |
| CA2982636A1 (en) | Fan module with adjustable pitch blades and power system | |
| US12037913B2 (en) | Electric machine assembly for a turbine engine | |
| CN109404139B (en) | Shell-free and shaft-free high-pressure high-speed starting power generation device for aircraft engine | |
| CN106043680B (en) | Aero-engine | |
| CN105736134B (en) | Hybrid-power combustion-gas screwed pipe rotary engine | |
| KR20210125009A (en) | Drives for main rotors of rotating aircraft | |
| RU2266236C2 (en) | Flying vehicle with electric drive | |
| CN106787436B (en) | Flywheel type generator |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |