CN218594581U - Wing tip gas injection gas generator - Google Patents
Wing tip gas injection gas generator Download PDFInfo
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- CN218594581U CN218594581U CN202223157385.1U CN202223157385U CN218594581U CN 218594581 U CN218594581 U CN 218594581U CN 202223157385 U CN202223157385 U CN 202223157385U CN 218594581 U CN218594581 U CN 218594581U
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- boosting agent
- inner chamber
- temperature tail
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Abstract
The utility model relates to a wing tip gas injection gas generator, a serial communication port, including gas generator casing, gas generator inner chamber, compressed air inlet, high temperature tail gas intake pipe, boosting agent conveyer pipe and gas outlet, the head region of gas generator inner chamber in the gas generator casing, the lateral wall of gas generator casing, the through gas generator inner chamber lateral wall face are passed to high temperature tail gas intake pipe, the antetheca central point of gas generator inner chamber puts and sets up the boosting agent conveyer pipe. The utility model discloses thereby utilize heavy oil piston engine high temperature tail gas heating hydrogen peroxide boosting agent among the driving system to make it carry out the exothermic reaction that vaporizes, give out oxygen and vapor, with the tail gas in the further burning of the oil gas of not burning out produce the higher energy gas, this fuel gas generator does not need complicated catalytic reaction system or ignition system, can adjust the jet-propelled required bleed volume of control rotor wing tip through the jet-propelled volume of control boosting agent, satisfies the jet-propelled required gas of rotor wing tip.
Description
Technical Field
The utility model relates to a gas generator designs technical field, concretely relates to use gas boosting agent and engine high temperature tail gas effect to produce a large amount of gases and heat for the jet-propelled gas generator of drive rotor wingtip.
Background
At present, the key and the bottleneck of the wingtip jet autorotation rotorcraft are power systems, and the power systems not only meet the requirements of releasing the autorotation of the rotor during high-speed cruising, but also meet the requirements of effectively driving the rotor during vertical take-off and landing. Therefore, in order to scientifically solve the problem that different power requirements are met in two working modes of a wing tip jet-driven rotor wing during vertical take-off and landing and a self-rotating rotor wing during high-speed flight, a composite power system suitable for the wing tip jet-driven rotor wing is needed, and the key technology to be realized by the power system is generation, control and utilization of fuel gas, namely, a fuel gas generator suitable for driving the rotor wing to rotate is designed.
The general gas generator is composed of parts such as a gas compressor, a fuel pump, a combustion chamber, a turbine and the like and auxiliary systems thereof, and is a working medium device capable of generating high-energy gas with certain pressure and temperature. However, such gasifiers are complex, heavy and costly. In a sense, rocket engines and jet engines are also fuel gas generators, and high-temperature fuel gas generated by the rocket engines and the jet engines is changed into high-speed airflow through a tail nozzle to be sprayed out to push rockets or airplanes to advance. However, if the rocket engine is used for a wing tip, the rocket engine is only suitable for work for a short time during take-off and landing, and a series of serious engineering technical problems need to be solved when the wing tip is used for a jet engine, for example, an engine rotor rotates around a rotor shaft together with blades at the rotating speed of thousands of revolutions per minute, a torque is generated, the torque tries to enable the whole engine to overturn upwards, when a huge centrifugal force enables lubricating oil to be thrown to one side of the engine, a high-rotating-speed bearing must be guaranteed to work normally, and the like. The cylinder part of a piston engine is also a gas generator, but the amount of gas is too small. At present, the gas generators can not meet the jet demand of the tip jet autorotation rotor wing.
In a composite power system taking an aviation piston heavy oil engine as a core, the technical problem to be solved by the technical staff in the field is how to fully utilize the high-temperature tail gas of the heavy oil piston engine to generate a large amount of gas required by wing tip gas injection for driving a rotor wing by the wing tip gas injection during lifting, landing and suspension.
SUMMERY OF THE UTILITY MODEL
The utility model provides a not enough to prior art, the utility model provides a wing tip gas injection gas generator aims at solving when VTOL the problem to the rotatory different tolerance demands of drive rotor under the two kinds of mode of rotation rotor when the jet-propelled drive rotor of wing tip and high-speed flight, realizes simplifying the structure, reduces the oil consumption rate, especially can provide the rotatory gas of sufficient drive rotor for the stage of hovering of the jet-propelled rotor of wing tip.
The utility model discloses a following technical scheme realizes.
The utility model provides a wing tip gas injection gas generator, its characterized in that, includes gas generator casing, gas generator inner chamber, compressed air inlet, high temperature tail gas intake pipe, boosting agent conveyer pipe and gas outlet, the head region of gas generator inner chamber in the gas generator casing, the lateral wall of gas generator casing is passed in the high temperature tail gas intake pipe, and direct gas generator inner chamber lateral wall face, the leading wall central point of gas generator inner chamber puts and sets up the boosting agent conveyer pipe, the leading wall of gas generator casing comprises the leading wall of compressed air inlet and gas generator inner chamber, and the gas generator casing is the convergent from compressed air inlet to gas outlet.
Furthermore, the gas generator has three inputs, the first input is high-pressure compressed air generated by a turbocharger, the high-pressure compressed air is directly butted with an annular compressed air inlet on the front wall surface of the gas generator shell along an annular passage through an annular diffuser, and the high-pressure compressed air can protect and cool the gas generator shell; the second path of input is high-temperature tail gas of the heavy oil piston engine, which is sent into the inner cavity of the gas generator at the head part in the gas generator shell from the side wall surface of the gas generator shell through a high-temperature tail gas inlet pipe and is used for heating the catalytic boosting agent; the third path of input is a boosting agent which is delivered to a central reaction area at the head of the inner cavity of the gas generator through a boosting agent delivery pipe, and the boosting agent is released and vaporized under the action of high-temperature tail gas to form high-temperature and high-pressure mixed gas which is discharged from a gas outlet.
Further, the boosting agent is high-concentration hydrogen peroxide or a mixture thereof.
Furthermore, in the wingtip gas injection gas generator, the vaporization decomposition reaction of the boosting agent in the central reaction area of the inner cavity of the gas generator is basically completed, and an ignition catalytic system is not needed in the process; the boosting agent conveying pipe can be provided with a control valve, the air entraining amount required by the air jet of the wing tip of the control rotor wing is adjusted by controlling the jet amount of the boosting agent, and the requirement of the air jet driving rotor wing in the vertical take-off, landing and hovering stage is met.
Furthermore, the wing tip jet gas generator just uses the power of a heavy oil engine for wing tip jet driving in the form of compressed air when propelling work is not needed in the taking-off and landing stages of the rotorcraft.
Furthermore, in the wing tip gas injection gas generator, high-temperature and high-pressure gas generated in a central reaction area of an inner cavity of the gas generator can be injected into high-temperature tail gas for afterburning if necessary, and oxygen in the high-temperature tail gas is further combusted to generate the high-temperature and high-pressure gas; the generated fuel gas is more uniform in the middle rear part of the fuel gas generator shell and then is discharged out of the fuel gas generator from the fuel gas outlet and is sent to the wing tips of the rotor wings for spraying.
Compared with the prior art, the utility model has the advantages that: the utility model discloses thereby utilize heavy oil piston engine high temperature tail gas heating boosting agent (hydrogen peroxide or its mixture) to make it carry out the exothermic reaction that vaporizes, oxygen and steam are emitted, further burn with the interior unburned oil gas of tail gas and produce the higher energy gas, this fuel gas generator does not need complicated catalytic reaction system or ignition system, the jet-propelled required bleed amount of control rotor wing tip can be adjusted through the jet-propelled injection quantity of control boosting agent simultaneously, satisfy the required gas of the jet-propelled rotor wing of wing tip, moreover, the steam generator is simple in structure, and simultaneously, the combustion efficiency can be improved, the pollution emission is reduced.
Drawings
Fig. 1 is a schematic structural view of the present invention;
fig. 2 is a cross-sectional view of the present invention;
in the figure: 1. a gasifier shell; 2. a gasifier chamber; 3. a compressed air inlet; 4. a propellant transfer tube; 5. a high-temperature tail gas inlet pipe; 6. and a gas outlet.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments, which are not intended to limit the present invention.
The present invention is described in detail with reference to the specific embodiments, and other advantages and effects of the present invention will be apparent to those skilled in the art from the disclosure herein. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In order to solve the related technical problems in the prior art, the embodiment of the application provides a wing tip jet gas fuel gas generator, which aims to solve the problem that the requirement for different air volumes of the rotation of a driving rotor wing is met in two working modes of a wing tip jet driving rotor wing in vertical take-off and landing and a self-rotation rotor wing in high-speed flight, simplify the structure and reduce the oil consumption rate, and especially can provide enough air for driving the rotation of the rotor wing in the stage of hovering the wing tip jet rotor wing in take-off and landing.
As shown in fig. 1 and 2, a wingtip jet gas gasifier is characterized by comprising a gasifier shell 1, a gasifier inner cavity 2, a compressed air inlet 3, a booster conveying pipe 4, a high-temperature tail gas inlet pipe 5 and a gas outlet 6, wherein the gasifier inner cavity 2 is arranged in the head area of the gasifier shell 1, the high-temperature tail gas inlet pipe 5 penetrates through the side wall of the gasifier shell 1 and reaches the side wall surface of the gasifier inner cavity 2, the booster conveying pipe 4 is arranged at the center of the front wall surface of the gasifier inner cavity 2, the front wall surface of the gasifier shell 1 consists of the compressed air inlet 3 and the front wall surface of the gasifier inner cavity 2, and the gasifier shell 1 is tapered from the compressed air inlet 3 to the gas outlet 6.
Furthermore, the gas generator has three inputs, the first input is high-pressure compressed air generated by a turbocharger, the high-pressure compressed air is directly butted with an annular compressed air inlet 3 on the front wall surface of the gas generator shell 1 along an annular passage through an annular diffuser, and the high-pressure compressed air can protect and cool the gas generator shell 1; the second path of input is high-temperature tail gas of a heavy oil piston engine, and the high-temperature tail gas is sent into the inner cavity 2 of the gas generator at the head part in the gas generator shell 1 from the side wall surface of the gas generator shell 1 through a high-temperature tail gas inlet pipe 5 and is used for heating the catalytic boosting agent; the third path of input is a boosting agent, the boosting agent is conveyed to a central reaction area at the head of the inner cavity 2 of the fuel gas generator through a boosting agent conveying pipe 4, heat is released under the action of high-temperature tail gas to release oxygen and water vapor, oil can be injected to ignite and afterburning as required, high-temperature and high-pressure mixed gas is finally formed and is discharged from a fuel gas outlet 6, the outlet gas can enter the rotor wing through a gas path system and is sprayed out from the wing tip to drive the rotor wing to rotate at a high speed, and the rotor wing generates enough lift force. When the flying speed is enough to enable the rotor wing to generate enough lift force, the boosting agent conveying pipe is closed, the air compressor is disconnected to work, the air injection of the rotor wing is stopped, and the rotor wing is in a self-rotating state at the moment, so that two working modes of the wing tip air injection rotary-wing aircraft are realized.
Further, the boosting agent is high-concentration hydrogen peroxide or a mixture thereof.
Furthermore, in the wingtip gas injection gas generator, the vaporization decomposition reaction of the boosting agent in the central reaction area of the inner cavity of the gas generator is basically finished, and an ignition catalytic system is not needed in the process; the boosting agent conveying pipe can be provided with a control valve, and the air entraining amount required by the air jet of the wing tip of the rotor wing is adjusted and controlled by controlling the jet amount of the boosting agent, so that the requirement of driving the rotor wing by the air jet in the vertical take-off, landing and hovering stage is met.
Furthermore, the wingtip jet gas generator just uses the power of a heavy oil engine in the form of compressed air for wingtip jet drive when no propulsion work is needed during the take-off and landing phases of the rotorcraft.
Furthermore, in the wing tip gas injection gas generator, high-temperature and high-pressure gas generated in a central reaction area of an inner cavity of the gas generator can be injected into high-temperature tail gas for afterburning if necessary, and oxygen in the high-temperature tail gas is further combusted to generate the high-temperature and high-pressure gas; the generated fuel gas is more uniform at the middle rear part of the shell of the fuel gas generator and then is discharged out of the fuel gas generator from a fuel gas outlet and sent to the wing tips of the rotor wings for injection.
Although the invention has been described in detail with respect to the general description and the specific embodiments, it will be apparent to those skilled in the art that modifications and improvements can be made based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of this invention without departing from the spirit thereof.
Claims (4)
1. The utility model provides a wing tip gas injection gas generator, its characterized in that, includes gas generator casing (1), gas generator inner chamber (2), compressed air inlet (3), boosting agent conveyer pipe (4), high temperature tail gas intake pipe (5) and gas outlet (6), the head region of gas generator inner chamber (2) in gas generator casing (1), the lateral wall of gas generator casing (1) is passed in high temperature tail gas intake pipe (5), reaches gas generator inner chamber (2) side wall face, the leading wall face central point of gas generator inner chamber (2) puts and sets up boosting agent conveyer pipe (4), the leading wall face of gas generator casing (1) comprises the leading wall face of compressed air inlet (3) and gas generator inner chamber (2), and gas generator casing (1) is the convergent from compressed air inlet (3) to gas outlet (6).
2. The wingtip-injection gas generator as claimed in claim 1, characterized in that the gas generator has three inputs, the first of which is high-pressure compressed air generated by a turbocharger, which is directly butted with the annular compressed air inlet (3) of the front wall surface of the gas generator shell (1) along an annular passage through an annular diffuser, and the high-pressure compressed air can carry out protective cooling on the gas generator shell (1); the second path of input is high-temperature tail gas from a heavy oil piston engine, and the high-temperature tail gas is sent into a gas generator inner cavity (2) at the head part in the gas generator shell (1) from the side wall surface of the gas generator shell (1) through a high-temperature tail gas inlet pipe (5) and is used for heating a catalytic boosting agent; the third path of input is a boosting agent which is delivered to a central reaction area at the head of the inner cavity (2) of the gas generator through a boosting agent delivery pipe (4), and the boosting agent is released and vaporized under the action of high-temperature tail gas to form high-temperature high-pressure mixed gas which is discharged from a gas outlet (6).
3. The wingtip gas generator of claim 2 wherein the booster is a high concentration of hydrogen peroxide or a mixture thereof.
4. The wingtip gas-jet gasifier according to claim 1 or 2, characterized in that the booster duct (4) is provided with a control flow valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223157385.1U CN218594581U (en) | 2022-11-28 | 2022-11-28 | Wing tip gas injection gas generator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223157385.1U CN218594581U (en) | 2022-11-28 | 2022-11-28 | Wing tip gas injection gas generator |
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| Publication Number | Publication Date |
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| CN218594581U true CN218594581U (en) | 2023-03-10 |
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| CN202223157385.1U Active CN218594581U (en) | 2022-11-28 | 2022-11-28 | Wing tip gas injection gas generator |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12091166B1 (en) | 2023-06-20 | 2024-09-17 | The United States Of America, As Represented By The Secretary Of The Navy | Offset propeller controlled rotor |
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2022
- 2022-11-28 CN CN202223157385.1U patent/CN218594581U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US12091166B1 (en) | 2023-06-20 | 2024-09-17 | The United States Of America, As Represented By The Secretary Of The Navy | Offset propeller controlled rotor |
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