CN111003154A - Propeller - Google Patents
Propeller Download PDFInfo
- Publication number
- CN111003154A CN111003154A CN201911385218.2A CN201911385218A CN111003154A CN 111003154 A CN111003154 A CN 111003154A CN 201911385218 A CN201911385218 A CN 201911385218A CN 111003154 A CN111003154 A CN 111003154A
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- CN
- China
- Prior art keywords
- propeller
- transmission shaft
- arc tooth
- surface gear
- gear
- 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.)
- Pending
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- 230000005540 biological transmission Effects 0.000 claims abstract description 51
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/48—Units of two or more coaxial propellers
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- 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
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
- B64D35/04—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
- B64D35/06—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors the propellers or rotors being counter-rotating
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Gear Transmission (AREA)
Abstract
A propeller comprises a transmission shaft, a first propeller, a second propeller and a second propeller transmission mechanism; a first propeller is fixedly arranged at the top of the transmission shaft, a second propeller transmission mechanism is arranged on the transmission shaft below the first propeller, and the second propeller is arranged on the second propeller transmission mechanism; compared with the traditional coaxial reverse rotation propeller structure, the propeller structure has the advantages that the stability of the propeller during high-speed operation can be effectively improved by adopting the design of matching the bevel gears and the face gears, and the power level of the airplane is improved.
Description
Technical Field
The invention belongs to the technical field of turboprops, and particularly relates to a propeller.
Background
Coaxial Contra-rotating propellers are a type of propeller that is unique to turboprop engines. The biggest difference from the common propeller is that two groups of propellers rotating in parallel are arranged on a single engine, the angular speeds of the two groups of propellers are opposite in direction, and therefore the propellers are called coaxial contra-rotating propellers.
The two sets of coaxial contra-rotating propellers are usually connected to the same engine and use a set of planetary gears to achieve the reverse rotation. The coaxial contra-rotating propeller is not a contra-rotating propeller, the latter refers to two different engines on both sides of the aircraft, the propellers of which rotate in opposite directions.
The biggest disadvantage of the prior coaxial contra-rotating propeller is that the noise generated during operation is too large. The noise in the axial direction is increased by 30 decibels, and the noise in the lateral direction is increased by 10 decibels, and the noise increase is particularly obvious when the blades rotate at high speed. Due to the disadvantage of loud noise, the coaxial contra-rotating propeller can not be well applied to the passenger plane, and can only be used on the military plane. In addition, the coaxial contra-rotating propeller has the disadvantages of increasing the design complexity of the engine and increasing the weight, so that it cannot be widely used in passenger aircraft.
Disclosure of Invention
The present invention aims to provide a propeller to solve the above problems.
In order to achieve the purpose, the invention adopts the following technical scheme:
a propeller comprises a transmission shaft, a first propeller, a second propeller and a second propeller transmission mechanism; a first propeller is fixedly arranged at the top of the transmission shaft, a second propeller transmission mechanism is arranged on the transmission shaft below the first propeller, and the second propeller is arranged on the second propeller transmission mechanism;
the second propeller transmission mechanism comprises an upper arc tooth surface gear, a lower arc tooth surface gear and a spiral bevel gear; the lower cambered surface gear is fixedly arranged on the transmission shaft, an upper cambered surface gear is arranged on the transmission shaft above the lower cambered surface gear through a bearing, two cambered bevel gears are arranged between the upper cambered surface gear and the lower cambered surface gear, and the cambered bevel gears are engaged with the upper cambered surface gear and the lower cambered surface gear.
Furthermore, a second propeller mounting disc is connected to the transmission shaft through a bearing, the second propeller mounting disc is fixedly connected with the upper arc-tooth-surface gear, and the second propeller is arranged on the second propeller mounting disc.
Further, the second propeller mounting plate and the upper arc-tooth-surface gear are fixedly connected through bolts.
Furthermore, a shell is arranged on the outer side of the second propeller transmission mechanism, and the two spiral bevel gears are fixed on the inner side wall of the shell through rotating shafts.
Further, the first propeller and the second propeller are both three-blade propellers.
Further, the transmission shaft is connected with a driving mechanism.
Compared with the prior art, the invention has the following technical effects:
compared with the traditional coaxial reverse rotation propeller structure, the propeller structure has the advantages that the stability of the propeller during high-speed operation can be effectively improved by adopting the design of matching the bevel gears and the face gears, and the power level of the airplane is improved.
Compared with common coaxial contrarotating propellers on the market, the coaxial contrarotating propeller has the advantages that the spiral bevel gears different from the common coaxial contrarotating propellers are adopted, the advantages of a coaxial contrarotating structure are further improved by utilizing the characteristics of high speed, good bearing capacity, stable transmission and low noise of the spiral bevel gears, and the common defect that the coaxial contrarotating propellers have large noise is overcome.
The transmission of the two propellers is realized by driving a transmission shaft on the spiral bevel gear by the spiral bevel gear, and the transmission shafts of the two propellers adopt a sleeve type design, so that the space is further saved, and the transmission efficiency is improved.
Drawings
Fig. 1 is an overall structural view of the present invention.
Fig. 2 is a view of the curved-flank gear of the present invention.
FIG. 3 is a spiral bevel gear diagram of the present invention.
The propeller comprises a propeller body, a first propeller, a second propeller, a third propeller, a fourth propeller, a fifth propeller, a sixth propeller, a fourth propeller, a sixth.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
referring to fig. 1 to 3, a propeller includes a transmission shaft 4, a first propeller 1, a second propeller 5 and a second propeller transmission mechanism; the top of the transmission shaft 4 is fixedly provided with a first propeller 1, a transmission shaft 4 below the first propeller 1 is provided with a second propeller transmission mechanism, and a second propeller 5 is arranged on the second propeller transmission mechanism;
the second propeller transmission mechanism comprises an upper arc tooth surface gear 2, a lower arc tooth surface gear 6 and a spiral bevel gear 3; lower cambered surface gear 6 is fixed to be set up on transmission shaft 4, is provided with cambered surface gear 2 through the bearing on the transmission shaft 4 of lower cambered surface gear 6 top, goes up and is provided with two spiral bevel gears 3 between cambered surface gear 2 and the lower cambered surface gear 6, and spiral bevel gear 3 and last cambered surface gear 2, lower cambered surface gear 6 all mesh.
The transmission shaft 4 is further connected with a second propeller mounting disc 7 through a bearing, the second propeller mounting disc 7 is fixedly connected with the upper arc-tooth-surface gear 2, and the second propeller 5 is arranged on the second propeller mounting disc 7.
The second propeller mounting disk 7 and the upper arc tooth surface gear 2 are fixedly connected through bolts.
The outer side of the second propeller transmission mechanism is provided with a shell, and the two spiral bevel gears 3 are fixed on the inner side wall of the shell through rotating shafts.
The first propeller 1 and the second propeller 5 are both three-blade propellers.
The transmission shaft 4 is connected with a driving mechanism.
The coaxial contra-rotating propeller is different from the conventional propeller in appearance that two groups of propellers which are arranged side by side and rotate oppositely are arranged on a single engine shaft, and compared with the conventional propeller, the coaxial contra-rotating propeller eliminates air vortex at the blade tip mutually, the efficiency can be increased by about 6% -16%, and the problem that the torque brought by the conventional propeller is useless torque along with the rotating direction of the propeller is solved.
The coaxial contra-rotating propeller designed by the invention is mainly applied to an airplane turbine engine, the lift force of an airplane is improved, the efficiency of the propeller in the rotating process is improved through the structural design of coaxial contra-rotating, the transmission stability is improved by adopting the spiral bevel gear, and the noise of the coaxial contra-rotating transmission is reduced. The product has the advantages of simple structure, reliable movement, low noise and the like.
1. The product mainly comprises two arc tooth surface gears, two arc tooth bevel gears and six propeller blades.
2. The two arc tooth surface gears control the rotation of the upper propeller blade through the middle transmission shaft respectively. The structure is compact and simple, and the movement action is easy to realize.
3. External force drives the two arc tooth surface gears to rotate through the two spiral bevel gears, so that the transmission efficiency can be improved, the noise can be reduced, and meanwhile, larger torque can be transmitted.
The airplane flying-off device comprises a 2-spiral bevel gear and a 3-spiral bevel gear which are in meshed transmission, a lower spiral bevel gear transmits power, a transmission shaft 4 on the lower spiral bevel gear drives a first pair of blades 1 to rotate, two spiral bevel gears 3 are driven to rotate at the same time, the two spiral bevel gears 3 drive an upper spiral bevel gear to rotate, so that blades 5 are driven, the two blades rotate to generate lift force, and the generated torque is counteracted with each other, so that the airplane is driven to take off rapidly.
Claims (6)
1. A propeller is characterized by comprising a transmission shaft (4), a first propeller (1), a second propeller (5) and a second propeller transmission mechanism; a first propeller (1) is fixedly arranged at the top of the transmission shaft (4), a second propeller transmission mechanism is arranged on the transmission shaft (4) below the first propeller (1), and a second propeller (5) is arranged on the second propeller transmission mechanism;
the second propeller transmission mechanism comprises an upper arc tooth surface gear (2), a lower arc tooth surface gear (6) and a spiral bevel gear (3); the lower arc tooth surface gear (6) is fixedly arranged on the transmission shaft (4), the upper arc tooth surface gear (2) is arranged on the transmission shaft (4) above the lower arc tooth surface gear (6) through a bearing, two arc tooth bevel gears (3) are arranged between the upper arc tooth surface gear (2) and the lower arc tooth surface gear (6), and the arc tooth bevel gears (3) are all meshed with the upper arc tooth surface gear (2) and the lower arc tooth surface gear (6).
2. The propeller as claimed in claim 1, wherein the transmission shaft (4) is further connected with a second propeller mounting plate (7) through a bearing, the second propeller mounting plate (7) is fixedly connected with the upper cambered-surface gear (2), and the second propeller (5) is arranged on the second propeller mounting plate (7).
3. A propeller according to claim 2, characterised in that the second propeller mounting plate (7) and the upper curved toothed gear (2) are fixedly connected by means of bolts.
4. A propeller according to claim 1, wherein the second propeller drive is provided with a housing on the outside, and the two spiral bevel gears (3) are fixed on the inner side wall of the housing through rotating shafts.
5. A propeller according to claim 1, wherein the first propeller (1) and the second propeller (5) are both three-bladed propellers.
6. A propeller according to claim 1, wherein the drive shaft (4) is connected to the drive mechanism.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911385218.2A CN111003154A (en) | 2019-12-28 | 2019-12-28 | Propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911385218.2A CN111003154A (en) | 2019-12-28 | 2019-12-28 | Propeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111003154A true CN111003154A (en) | 2020-04-14 |
Family
ID=70118136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911385218.2A Pending CN111003154A (en) | 2019-12-28 | 2019-12-28 | Propeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111003154A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114355088A (en) * | 2022-01-08 | 2022-04-15 | 饶子佳 | Hardware maintenance system through monitoring multiple information |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB449139A (en) * | 1934-12-04 | 1936-06-22 | Jean Jacques Trebucien | Improvements in aircraft propelling devices |
| US20130062463A1 (en) * | 2011-09-09 | 2013-03-14 | United Technologies Corporation | Transverse mounted gas turbine engine |
| CN107352024A (en) * | 2017-07-12 | 2017-11-17 | 重庆国飞通用航空设备制造有限公司 | The reverse rotor mechanism of coaxial double-oar and its aircraft |
| CN109334967A (en) * | 2018-11-22 | 2019-02-15 | 南京航空航天大学 | A kind of coaxial double-rotary wing reversing arrangement |
| CN109665096A (en) * | 2018-12-25 | 2019-04-23 | 南京航空航天大学 | A kind of shrouded propeller thrust coaxial double-rotor helicopter |
| US20190118961A1 (en) * | 2017-10-19 | 2019-04-25 | Bell Helicopter Textron Inc. | Rotor systems and methods |
| CN109720560A (en) * | 2019-01-22 | 2019-05-07 | 广东工业大学 | VTOL fixed-wing patrol UAV |
| US20190176980A1 (en) * | 2017-12-07 | 2019-06-13 | Bell Helicopter Textron Inc. | Dual Rotor Propulsion Systems for Tiltrotor Aircraft |
| CN211442738U (en) * | 2019-12-28 | 2020-09-08 | 长安大学 | Coaxial reverse propeller |
-
2019
- 2019-12-28 CN CN201911385218.2A patent/CN111003154A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB449139A (en) * | 1934-12-04 | 1936-06-22 | Jean Jacques Trebucien | Improvements in aircraft propelling devices |
| US20130062463A1 (en) * | 2011-09-09 | 2013-03-14 | United Technologies Corporation | Transverse mounted gas turbine engine |
| CN107352024A (en) * | 2017-07-12 | 2017-11-17 | 重庆国飞通用航空设备制造有限公司 | The reverse rotor mechanism of coaxial double-oar and its aircraft |
| US20190118961A1 (en) * | 2017-10-19 | 2019-04-25 | Bell Helicopter Textron Inc. | Rotor systems and methods |
| US20190176980A1 (en) * | 2017-12-07 | 2019-06-13 | Bell Helicopter Textron Inc. | Dual Rotor Propulsion Systems for Tiltrotor Aircraft |
| CN109334967A (en) * | 2018-11-22 | 2019-02-15 | 南京航空航天大学 | A kind of coaxial double-rotary wing reversing arrangement |
| CN109665096A (en) * | 2018-12-25 | 2019-04-23 | 南京航空航天大学 | A kind of shrouded propeller thrust coaxial double-rotor helicopter |
| CN109720560A (en) * | 2019-01-22 | 2019-05-07 | 广东工业大学 | VTOL fixed-wing patrol UAV |
| CN211442738U (en) * | 2019-12-28 | 2020-09-08 | 长安大学 | Coaxial reverse propeller |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114355088A (en) * | 2022-01-08 | 2022-04-15 | 饶子佳 | Hardware maintenance system through monitoring multiple information |
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