CN207773496U - A kind of turbo-propeller for general-purpose aircraft - Google Patents
A kind of turbo-propeller for general-purpose aircraft Download PDFInfo
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- CN207773496U CN207773496U CN201820017207.3U CN201820017207U CN207773496U CN 207773496 U CN207773496 U CN 207773496U CN 201820017207 U CN201820017207 U CN 201820017207U CN 207773496 U CN207773496 U CN 207773496U
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- shell
- propeller
- end outer
- turbo
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- 239000000446 fuel Substances 0.000 claims abstract description 30
- 239000003921 oil Substances 0.000 claims abstract description 12
- 238000005461 lubrication Methods 0.000 claims abstract description 10
- 239000010687 lubricating oil Substances 0.000 claims abstract description 5
- 239000012528 membrane Substances 0.000 claims description 3
- 230000000694 effects Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a kind of turbo-propellers for general-purpose aircraft, including shell, one side external surface of the shell is provided with fuel inlet, and the lower end outer surface of shell is installed with jet pipe shell, the upper end outer surface of the shell is installed with connection shell, and the side external surface for connecting shell is installed with lubrication oil box, the upper end outer surface of the connection shell is fixedly connected with propeller head, and propeller is internally provided with electric thermo-couple temperature inductor, the inside of the shell is installed with compressor and turbine, the inner surface of the shell is provided with heat-sink shell.A kind of turbo-propeller for general-purpose aircraft described in the utility model, equipped with flexible blade, lubrication oil box and electric thermo-couple temperature inductor, blade can be accepted when not in use in aircraft, save space, can conveniently lubricating oil be added for propeller shaft, propeller head is also prevented from because high temperature damages, brings better prospect of the application.
Description
Technical field
The utility model is related to turbo-propeller fields, more particularly to a kind of turbo-propeller for general-purpose aircraft.
Background technology
Turbo-propeller is a kind of propeller commonly used on aircraft.The driving principle of turbo-propeller generally with make
It is with the traditional propeller aircraft of piston engine as a source of power identical, it is that generated strength is made when being rotated with propeller
The propulsive force advanced for aircraft.Due to being relatively large in diameter for propeller, rotating speed is low more than turbine, only about 1000 revs/min, is
So that turbine and propeller is all operated in normal range, needs that a retarder is installed between them, secondary speed is dropped
To after 1/10th or so, propeller can be just driven；There are certain drawbacks when in use in existing turbo-propeller, first,
Propeller volume is larger, when aircraft does not use, very occupied space, secondly, to propeller do lubrication protection when
It waits, people's addition lubricating oil is very inconvenient, in addition, the turbo-propeller of transmission cannot carry out in fact the temperature on propeller head
When monitor, be unfavorable for people use, certain influence is brought using process to people, for this purpose, it is proposed that one kind is used for
The turbo-propeller of general-purpose aircraft.
Utility model content
The main purpose of the utility model is to provide a kind of turbo-propellers for general-purpose aircraft, can effectively solve
The problems in background technology.
To achieve the above object, the technical solution that the utility model is taken is：
One side external surface of a kind of turbo-propeller for general-purpose aircraft, including shell, the shell is provided with fuel
Entrance, and the lower end outer surface of shell is installed with jet pipe shell, the upper end outer surface of the shell is installed with connection shell,
And the side external surface for connecting shell is installed with lubrication oil box, the upper end outer surface of the connection shell is fixedly connected with propeller
Head, and propeller head is internally provided with electric thermo-couple temperature inductor, the inside of the shell is installed with compressor and whirlpool
Wheel, and turbine is located at the lower section of compressor, the inner surface of the shell is provided with heat-sink shell, and the side inner surface of heat-sink shell is solid
Dingan County is equipped with fuel chambers, and the heat-sink shell is internally provided with fuel nozzle, and the fuel chambers are entered by fuel nozzle and fuel
Mouth is fixedly connected, and the connection shell is internally provided with retarder, and the upper end outer surface of retarder is connected with main transmission
The upper end outer surface of axis, the main shaft is provided with rot, and a side external surface of rot is connected with blade and turns
Moving axis, a side external surface of the blade rotation axis are installed with sleeve, and sleeve is internally provided with flexible blade, described
Electric thermo-couple temperature inductor is located at the top of rot, and the jet pipe shell is internally provided with jet pipe.
Preferably, a side external surface of the connection shell is provided with bolt, and a side external surface of the lubrication oil box passes through
Bolt is fixedly connected with the side external surface for connecting shell, and the quantity of bolt is several groups, and the inner surface for lubricating oil box be coated with it is anti-
Leak film.
Preferably, the lower end outer surface of the propeller head is provided with pin, and the upper end outer surface of the connection shell passes through
Pin is fixedly connected with the lower end outer surface of propeller head, and the quantity of pin is several groups, and the outer surface of propeller head is coated with anti-
Tranish film.
Preferably, the retarder is internally provided with gear, and the main shaft passes through gear and connect with retarder activity
It connects, gear outer surface is coated with wear-resistant membrane, and the quantity of gear is two groups.
Preferably, the rot is internally provided with angular wheel, and the main shaft passes through angular wheel and blade
Rotation axis is flexibly connected, and the quantity of blade rotation axis is two groups, and the quantity of angular wheel is two groups.
Preferably, the outer surface of the shell is coated with rust-preventing film, and the quantity of the sleeve is two groups, the flexible blade
Quantity is two groups.
Compared with prior art, the utility model has the advantages that：A kind of turbine spiral shell for general-purpose aircraft
Paddle is revolved, is accepted propeller when aircraft leaves unused by the flexible blade of setting, is saved shared when aircraft leaves unused
Space can facilitate people to be lubricated protection to propeller by the lubrication oil box of setting, improve working efficiency, pass through heat
The setting of galvanic couple temperature inductor can monitor the temperature on propeller head in real time, prevent propeller head internal temperature
Excessively high the case where leading to parts damages, occurs, and can extend its service life, and easy to operate, the effect used is relative to traditional approach
More preferably.
Description of the drawings
Fig. 1 is a kind of overall structure diagram of turbo-propeller for general-purpose aircraft of the utility model.
Fig. 2 is a kind of partial view of turbo-propeller for general-purpose aircraft of the utility model.
Fig. 3 be a kind of turbo-propeller for general-purpose aircraft of the utility model Fig. 2 in A enlarged drawing.
Fig. 4 is a kind of internal structure chart of turbo-propeller for general-purpose aircraft of the utility model.
In figure：1, shell；2, jet pipe shell；3, shell is connected；4, oil box is lubricated；5, propeller head；6, fuel inlet；7, blade
Rotation axis；8, stretch blade；9, sleeve；10, turbine；11, fuel chambers；12, fuel nozzle；13, heat-sink shell；14, compressor；
15, retarder；16, main shaft；17, rot；18, electric thermo-couple temperature inductor；19, jet pipe.
Specific implementation mode
To make the technical means, creative features, achievement of purpose, and effectiveness of the utility model be easy to understand, below
In conjunction with specific implementation mode, the utility model is expanded on further.
As shown in Figs 1-4, a kind of turbo-propeller for general-purpose aircraft, including shell 1, a side external surface of shell 1
It is provided with fuel inlet 6, and the lower end outer surface of shell 1 is installed with jet pipe shell 2, peace is fixed in the upper end outer surface of shell 1
Equipped with connection shell 3, and the side external surface for connecting shell 3 is installed with lubrication oil box 4, and the upper end outer surface of connection shell 3 is fixed
It is connected with propeller head 5, and propeller head 5 is internally provided with electric thermo-couple temperature inductor 18, the inside of shell 1 is fixedly mounted
There are compressor 14 and turbine 10, and turbine 10 is located at the lower section of compressor 14, the inner surface of shell 1 is provided with heat-sink shell 13, and
The side inner surface of heat-sink shell 13 is installed with fuel chambers 11, and heat-sink shell 13 is internally provided with fuel nozzle 12, fuel chambers
11 are fixedly connected by fuel nozzle 12 with fuel inlet 6, and connection shell 3 is internally provided with retarder 15, and retarder 15
Upper end outer surface is connected with main shaft 16, and the upper end outer surface of main shaft 16 is provided with rot 17, and rot
17 side external surface is connected with blade rotation axis 7, and a side external surface of blade rotation axis 7 is installed with sleeve 9, and
Sleeve 9 is internally provided with flexible blade 8, and electric thermo-couple temperature inductor 18 is located at the top of rot 17, the inside of jet pipe shell 2
It is provided with jet pipe 19.
One side external surface of connection shell 3 is provided with bolt, lubricate a side external surface of oil box 4 by bolt with connect shell 3
A side external surface be fixedly connected, the quantity of bolt is several groups, and the inner surface for lubricating oil box 4 is coated with leakproof film, can be effective
Prevent lubrication oil box inside oil leakage；The lower end outer surface of propeller head 5 is provided with pin, connects the upper end of shell 3
Outer surface is fixedly connected by pin with the lower end outer surface of propeller head 5, and the quantity of pin is several groups, propeller head 5
Outer surface is coated with rust-preventing film；Retarder 15 is internally provided with gear, and main shaft 16 is connected by gear and 15 activity of retarder
It connects, gear outer surface is coated with wear-resistant membrane, and the quantity of gear is two groups, and the quenched processing of gear surface makes gear surface be hardened；Turn
Dynamic device 17 is internally provided with angular wheel, and main shaft 16 is flexibly connected by angular wheel with blade rotation axis 7, and blade
The quantity of rotation axis 7 is two groups, and the quantity of angular wheel is two groups；The outer surface of shell 1 is coated with rust-preventing film, the quantity of sleeve 9
It it is two groups, the quantity for the blade 8 that stretches is two groups.
It should be noted that the utility model is a kind of turbo-propeller for general-purpose aircraft, when in use, by turbine
The shell 1 of propeller is fixedly mounted on the suitable position of aircraft by link, and then external fuel pipe and fuel inlet 6 are connected
Connect, pass through heat-sink shell 13 to enter fuel chambers 11 by fuel nozzle 12 fuel, when aircraft starts, flexible blade 8 from
Sleeve 9 stretches out, and fuel burning in fuel chambers 11, the energy that fuel combustion provides makes compressor 14 operate, to 5 band of propeller head
The air entered is compressed, and the air of compression is by turbine 10, to drive turbine 10 to rotate, when the rotating speed of turbine 10 gradually becomes
The rotating speed control of turbine 10 is driven main shaft 16 to operate, compressed air is last by height by retarder 15 in suitable range
It is discharged from jet pipe 19, then main shaft 16 is rotated by rot 17 with movable vane piece rotation axis 7, before making blade rotation axis
The flexible blade 8 at end is also rotated, and to provide power for aircraft, makes to take off, more practical.
The advantages of basic principles and main features and the utility model of the utility model have been shown and described above.One's own profession
The technical staff of industry is it should be appreciated that the present utility model is not limited to the above embodiments, described in above embodiments and description
Only illustrate the principles of the present invention, on the premise of not departing from the spirit and scope of the utility model, the utility model is also
It will have various changes and improvements, these various changes and improvements fall within the scope of the claimed invention.The utility model
Claimed range is defined by the appending claims and its equivalent thereof.
Claims (6)
1. a kind of turbo-propeller for general-purpose aircraft, including shell (1), it is characterised in that：Outside the side of the shell (1)
Surface is provided with fuel inlet (6), and the lower end outer surface of shell (1) is installed with jet pipe shell (2), the shell (1)
Upper end outer surface is installed with connection shell (3), and the side external surface for connecting shell (3) is installed with lubrication oil box (4), institute
The upper end outer surface for stating connection shell (3) is fixedly connected with propeller head (5), and propeller head (5) is internally provided with thermocouple
The inside of temperature inductor (18), the shell (1) is installed with compressor (14) and turbine (10), and turbine (10) is located at
The inner surface of the lower section of compressor (14), the shell (1) is provided with heat-sink shell (13), and the side inner surface of heat-sink shell (13)
Fuel chambers (11) are installed with, the heat-sink shell (13) is internally provided with fuel nozzle (12), and the fuel chambers (11) are logical
It crosses fuel nozzle (12) to be fixedly connected with fuel inlet (6), the connection shell (3) is internally provided with retarder (15), and subtracts
The upper end outer surface of fast device (15) is connected with main shaft (16), and the upper end outer surface of the main shaft (16) is provided with
Rot (17), and a side external surface of rot (17) is connected with blade rotation axis (7), the blade rotation axis (7)
A side external surface be installed with sleeve (9), and sleeve (9) is internally provided with flexible blade (8), the electric thermo-couple temperature
Inductor (18) is located at the top of rot (17), and the jet pipe shell (2) is internally provided with jet pipe (19).
2. a kind of turbo-propeller for general-purpose aircraft according to claim 1, it is characterised in that：The connection shell
(3) a side external surface is provided with bolt, a side external surface of the lubrication oil box (4) by bolt with connect the one of shell (3)
Side external surface is fixedly connected, and the quantity of bolt is several groups, and the inner surface for lubricating oil box (4) is coated with leakproof film.
3. a kind of turbo-propeller for general-purpose aircraft according to claim 1, it is characterised in that：The propeller head
(5) lower end outer surface is provided with pin, and the upper end outer surface of the connection shell (3) passes through under pin and propeller head (5)
End outer surface is fixedly connected, and the quantity of pin is several groups, and the outer surface of propeller head (5) is coated with rust-preventing film.
4. a kind of turbo-propeller for general-purpose aircraft according to claim 1, it is characterised in that：The retarder
(15) be internally provided with gear, the main shaft (16) is flexibly connected by gear with retarder (15), gear outer surface
It is coated with wear-resistant membrane, the quantity of gear is two groups.
5. a kind of turbo-propeller for general-purpose aircraft according to claim 1, it is characterised in that：The rot
(17) be internally provided with angular wheel, the main shaft (16) is flexibly connected by angular wheel with blade rotation axis (7),
And the quantity of blade rotation axis (7) is two groups, the quantity of angular wheel is two groups.
6. a kind of turbo-propeller for general-purpose aircraft according to claim 1, it is characterised in that：The shell (1)
Outer surface be coated with rust-preventing film, the quantity of the sleeve (9) is two groups, and the quantity of the flexible blade (8) is two groups.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820017207.3U CN207773496U (en) | 2018-01-05 | 2018-01-05 | A kind of turbo-propeller for general-purpose aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820017207.3U CN207773496U (en) | 2018-01-05 | 2018-01-05 | A kind of turbo-propeller for general-purpose aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207773496U true CN207773496U (en) | 2018-08-28 |
Family
ID=63222540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820017207.3U Active CN207773496U (en) | 2018-01-05 | 2018-01-05 | A kind of turbo-propeller for general-purpose aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207773496U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113232853A (en) * | 2021-04-02 | 2021-08-10 | 陈�峰 | Short-distance take-off and landing aircraft |
-
2018
- 2018-01-05 CN CN201820017207.3U patent/CN207773496U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113232853A (en) * | 2021-04-02 | 2021-08-10 | 陈�峰 | Short-distance take-off and landing aircraft |
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| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20240624 Granted publication date: 20180828 |