CN217080622U - Helicopter jet rotor power system - Google Patents
Helicopter jet rotor power system Download PDFInfo
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- CN217080622U CN217080622U CN202221218853.9U CN202221218853U CN217080622U CN 217080622 U CN217080622 U CN 217080622U CN 202221218853 U CN202221218853 U CN 202221218853U CN 217080622 U CN217080622 U CN 217080622U
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- electromagnetic directional
- combustion engine
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Abstract
The utility model discloses a helicopter jet-propelled rotor power system, including the internal-combustion engine, the pressure boost turbine, centrifugal compressor, wing tip jet-propelled rotor, the high-temperature high-speed gas of internal-combustion engine lets in centrifugal compressor through the pressure boost turbine, centrifugal compressor's gas outlet is linked together with the entrance point of first electromagnetic directional valve, two exit ends of first electromagnetic directional valve are linked together with internal-combustion engine and wing tip jet-propelled rotor respectively, the gas outlet of pressure boost turbine is linked together with the entrance point of second electromagnetic directional valve, two exit ends of second electromagnetic directional valve are linked together with gas vent and wing tip jet-propelled rotor respectively. The utility model adopts the above structure a helicopter jet-propelled rotor driving system utilizes turbocharging to produce the gas and to the jet-propelled drive of wingtip, still has the tail gas of higher pressure and temperature to cause the wingtip to jet-propelled simultaneously, and the common drive rotor produces lift for aircraft driving system is light and handy and does not produce the moment of torsion, improves driving system's power-to-weight ratio and energy utilization.
Description
Technical Field
The utility model relates to an aerocraft power technical field especially relates to a helicopter jet-propelled rotor driving system.
Background
Compared with the traditional helicopter, the autorotation helicopter has good high speed, high efficiency and safety, is a new development direction of the current and future helicopters, and has unique requirements on a power system: when vertically taking off, landing and suspending, wing tip air injection is needed to drive the rotor wing; during forward flight, the rotor spins to accommodate high-speed flight.
The utility model aims at studying a take pressurized turbine to increase helicopter wingtip jet-propelled power system of gas generator can be ingenious utilize the engine from the pressurized turbine booster who takes as gas generator, be used for the jet-propelled drive rotor of wingtip when VTOL, both overcome other drive methods and can produce the moment of torsion, need the balanced problem of tail-rotor, also can guarantee steady when rotor drive passes through with the rotation, simple structure simultaneously, driving system merit weight ratio.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a helicopter jet rotor driving system to solve above-mentioned background art in the helicopter to driving system's unique requirement.
In order to realize the above object, the utility model provides a helicopter jet rotor power system, including internal-combustion engine, pressure boost turbine, centrifugal compressor, wing tip jet rotor, the high-temperature high-speed gas warp of internal-combustion engine the pressure boost turbine lets in the centrifugal compressor, the gas outlet of centrifugal compressor is linked together with the entrance point of first electromagnetic directional valve, two exit ends of first electromagnetic directional valve respectively with the internal-combustion engine with wing tip jet rotor is linked together, pressure boost turbine's gas outlet is linked together with the entrance point of second electromagnetic directional valve, two exit ends of second electromagnetic directional valve respectively with the gas vent with wing tip jet rotor is linked together.
Preferably, the centrifugal compressor is provided with an air inlet for pressurizing intake air.
Preferably, the internal combustion engine is provided with a turbo charger.
Preferably, the booster turbine is provided with a drive shaft, and the drive shaft is connected with a propeller.
Therefore, the utility model adopts the above structure a helicopter jet rotor driving system has following beneficial effect:
1. aiming at the problems that the power required by vertical take-off of the autorotation helicopter is large, the power required by horizontal forward flight is small, and the torque cannot be generated due to the rotation of a rotor wing, a small-power engine can be selected according to the horizontal flight requirement, and gas generated by supercharging of a supercharging turbine is utilized to jet and drive the wing tip during take-off, so that an airplane power system can be lighter and does not generate torque, and the power-weight ratio of the power system is improved.
2. The tail gas with higher pressure and temperature after being expanded by the booster turbine is also led to the wing tip for jetting, the tail gas drives the rotor wing to generate lift force together, and the energy utilization rate is improved.
The technical solution of the present invention is further described in detail by the accompanying drawings and examples.
Drawings
FIG. 1 is a schematic structural view of an embodiment of a helicopter jet rotor power system of the present invention;
figure 2 is a schematic view of a typical jet rotor system of an embodiment of a helicopter jet rotor power system of the present invention.
Fig. 3 is a schematic view of a tip jet rotor configuration of an embodiment of a helicopter jet rotor power system of the present invention;
in the figure: 1. an internal combustion engine; 2. a booster turbine; 3. a centrifugal compressor; 4. an exhaust port; 5. an air inlet; 6. a wingtip air jet rotor; 7. a second electromagnetic directional valve; 8. a first electromagnetic directional valve; 9. a drive shaft.
Detailed Description
The technical solution of the present invention is further explained by the accompanying drawings and examples.
Unless defined otherwise, technical or scientific terms used herein shall have the ordinary meaning as understood by those of ordinary skill in the art to which the invention belongs. The use of "first," "second," and similar terms in the description herein do not denote any order, quantity, or importance, but rather the terms are used to distinguish one element from another. The word "comprising" or "comprises", and the like, means that the element or item listed before the word covers the element or item listed after the word and its equivalents, but does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", and the like are used merely to indicate relative positional relationships, and when the absolute position of the object being described is changed, the relative positional relationships may also be changed accordingly.
The following describes embodiments of the present invention with reference to the accompanying drawings. As shown in fig. 1 and 3, a helicopter jet rotor power system comprises an internal combustion engine 1, a booster turbine 2, a centrifugal compressor 3 and a wing tip jet rotor 6, wherein the internal combustion engine 1 is provided with a booster turbine 2, high-temperature high-speed gas of the internal combustion engine 1 is introduced into the centrifugal compressor 3 through the booster turbine 2, the centrifugal compressor 3 is provided with an air inlet 5 for air inlet boosting, an air outlet of the centrifugal compressor 3 is communicated with an inlet end of a first electromagnetic directional valve 8, two outlet ends of the first electromagnetic directional valve 8 are respectively communicated with the internal combustion engine 1 and the wing tip jet rotor 6, an air outlet of the booster turbine 2 is communicated with an inlet end of a second electromagnetic directional valve 7, and two outlet ends of the second electromagnetic directional valve 7 are respectively communicated with an air outlet 4 and the wing tip jet rotor 6. The booster turbine 2 is provided with a drive shaft 9, and the drive shaft 9 is connected with a propeller. Referring to fig. 2, which is a block diagram of a typical jet rotor system, a control structure of a helicopter jet rotor system comprises an effusion nozzle, a main shaft pipeline, blade pipelines, a rotor and a wing tip, wherein jet flows enter the main shaft pipeline from a tail nozzle of an internal combustion engine 1 and a tail nozzle of a booster turbine 2, are divided into two parts through a Y-shaped pipeline at a hub and respectively enter the rotating blade pipelines, and then are ejected at a high speed at a nozzle of a jet rotor 6 at the wing tip to generate a reaction force to drive the rotor to rotate, and the effusion nozzle can prevent the back pressure from being too large to cause engine surge.
The utility model discloses a concrete implementation process does: when the gyroplane normally flies, the rotor rotates to generate lift force, the driving shaft 9 drives the propeller to generate thrust, the centrifugal compressor 3 compresses air to enter the internal combustion engine 1, and the internal combustion engine 1 is in a supercharging working mode of the supercharging turbine 2.
When the rotor wing takes off, the power required by the airplane is high, the rotor wing 6 is driven by the jet of the wing tip to generate enough lift force, at the moment, the booster turbine 2 absorbs the energy of high-temperature and high-speed gas from the internal combustion engine 1 to drive the centrifugal compressor 3 to operate, meanwhile, the centrifugal compressor 3 is boosted through the air inlet 5, finally, the generated high-pressure gas passes through the jet rotor wing 6 of the wing tip through the first electromagnetic directional valve 8, the energy generated by combustion is used for driving the jet of the wing tip, the power of the whole power system is greatly improved, the rotating torque of the rotor wing is not generated, and the high-pressure gas can also be introduced into the internal combustion engine 1 through the first electromagnetic directional valve 8 to realize the boosting and air intake of the internal combustion engine 1 and improve the power and the efficiency of the internal combustion engine 1; waste gas that pressure boost turbine 2 produced is discharged through its gas outlet, and second electromagnetic directional valve 7 can pass through exhaust port 4 with waste gas and discharge, also can let in wing tip jet-propelled rotor 6 with waste gas, provides power for wing tip jet-propelled rotor 6.
Therefore, the utility model adopts the above structure a helicopter jet-propelled rotor driving system utilizes pressure boost turbocharging to produce the gas and to the jet-propelled drive of wingtip when taking off, still has the tail gas of higher pressure and temperature to also cause the wingtip to jet-propelled simultaneously, and the drive rotor produces lift jointly for aircraft driving system is light and handy and do not produce the moment of torsion, improves driving system's power-to-weight ratio and energy utilization.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention and not to limit the same, and although the present invention is described in detail with reference to the preferred embodiments, those of ordinary skill in the art should understand that: the technical solution of the present invention can still be modified or replaced by other equivalent means, and the modified technical solution can not be separated from the spirit and scope of the technical solution of the present invention.
Claims (4)
1. A helicopter jet rotor power system characterized in that: including internal-combustion engine, turbo, centrifugal compressor, wing tip jet-rotor, the high-temperature high-speed gas warp of internal-combustion engine turbo lets in the centrifugal compressor, the gas outlet of centrifugal compressor is linked together with the entrance point of first electromagnetic directional control valve, two exit ends of first electromagnetic directional control valve respectively with the internal-combustion engine with wing tip jet-rotor are linked together, turbo's gas outlet is linked together with the entrance point of second electromagnetic directional control valve, two exit ends of second electromagnetic directional control valve respectively with the gas vent with wing tip jet-rotor is linked together.
2. A helicopter jet rotor power system as claimed in claim 1, further comprising: the centrifugal compressor is provided with an air inlet for air inlet pressurization.
3. A helicopter jet rotor power system as claimed in claim 1, further comprising: the internal combustion engine is provided with a turbocharger.
4. A helicopter jet rotor power system according to claim 1, further comprising: the booster turbine is provided with a driving shaft, and the driving shaft is connected with the propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221218853.9U CN217080622U (en) | 2022-05-20 | 2022-05-20 | Helicopter jet rotor power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221218853.9U CN217080622U (en) | 2022-05-20 | 2022-05-20 | Helicopter jet rotor power system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217080622U true CN217080622U (en) | 2022-07-29 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221218853.9U Active CN217080622U (en) | 2022-05-20 | 2022-05-20 | Helicopter jet rotor power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217080622U (en) |
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2022
- 2022-05-20 CN CN202221218853.9U patent/CN217080622U/en active Active
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