Wing tip jet gas generator

Abstract

The present invention relates to a wingtip jet gas generator, characterized in that it includes a gas generator shell, a gas generator inner cavity, a compressed air inlet, a high-temperature exhaust gas intake pipe, a propellant delivery pipe and a gas outlet, wherein the gas generator inner cavity is in the head area of ​​the gas generator shell, the high-temperature exhaust gas intake pipe passes through the side wall of the gas generator shell and directly reaches the side wall surface of the gas generator inner cavity, and a propellant delivery pipe is arranged at the center position of the front wall surface of the gas generator inner cavity. The present invention utilizes the high-temperature exhaust gas of the heavy oil piston engine in the power system to heat the hydrogen peroxide propellant so that it undergoes a vaporization exothermic reaction, releases oxygen and water vapor, and further burns with the unburned oil and gas in the exhaust gas to produce a higher energy fuel gas. The gas generator does not require a complex catalytic reaction system or an ignition system, and can adjust the amount of bleed air required for the rotor wingtip jet by controlling the injection amount of the propellant to meet the fuel gas required by the wingtip jet rotor.

Description

Technical Field

[0001] The present invention relates to the technical field of gas generator design, and in particular to a gas generator which uses a gas propellant to react with high-temperature engine exhaust gas to generate a large amount of gas and heat for driving a rotor wing tip jet. Background Art

[0002] At present, the key and bottleneck of wingtip jet autogyro lies in the power system, which must not only release the rotor rotation during high-speed cruising, but also effectively drive the rotor during vertical take-off and landing. Therefore, in order to scientifically solve the problem of different power requirements in the two working modes of wingtip jet-driven rotors during vertical take-off and landing and autogyro during high-speed flight, a composite power system suitable for wingtip jet-driven rotors is needed, and the core key technology to be achieved by this power system is the generation and control of gas, that is, a gas generator suitable for driving the rotor rotation must be designed.

[0003] A common gas generator is composed of a compressor, a fuel pump, a combustion chamber, a turbine and other components and their auxiliary systems. It is a working medium device that can produce high-energy gas with a certain pressure and temperature. However, this type of gas generator has a complex structure, heavy weight and high cost. In a sense, rocket engines and jet engines are also a type of gas generator. The high-temperature gas they produce is converted into a high-speed airflow and ejected through the tail nozzle to propel the rocket or aircraft forward. However, if a rocket engine is used at the wing tip, it is only suitable for a short period of work during takeoff and landing. When a jet engine is used at the wing tip, a series of serious engineering and technical problems need to be solved. For example, the engine rotor rotates around the rotor shaft with the blades at a speed of several thousand revolutions per minute, which will generate a torque that tries to turn the entire engine upside down, and when the huge centrifugal force throws the lubricating oil to one side of the engine, it is necessary to ensure that the high-speed bearing can work normally, etc. The cylinder part of a piston internal combustion engine is also a gas generator, but the amount of gas is too small. At present, these gas generators cannot meet the needs of wing tip jet autogyro jet.

[0004] In a hybrid power system with an aviation piston heavy oil engine as the core, how to make full use of the high-temperature exhaust gas of the heavy oil piston engine to produce a large amount of gas required for wingtip jet driving of the rotor during takeoff, landing and hovering is a technical problem that needs to be solved urgently by technicians in this field. Summary of the invention

[0005] In view of the shortcomings of the prior art, the present invention provides a wingtip jet gas generator, which aims to solve the problem of different gas volume requirements for driving the rotation of the rotor in two working modes: wingtip jet driven rotor during vertical take-off and landing and autorotating rotor during high-speed flight, thereby simplifying the structure and reducing the fuel consumption rate. In particular, it can provide sufficient gas to drive the rotor rotation during the take-off, landing and hovering stage of the wingtip jet rotor.

[0006] The present invention is achieved through the following technical solutions.

[0007] A wingtip jet gas generator, characterized in that it includes a gas generator shell, a gas generator inner cavity, a compressed air inlet, a high-temperature exhaust gas inlet pipe, a propellant delivery pipe and a gas outlet, the gas generator inner cavity is in the head area inside the gas generator shell, the high-temperature exhaust gas inlet pipe passes through the side wall of the gas generator shell and directly reaches the side wall of the gas generator inner cavity, the propellant delivery pipe is arranged at the center of the front wall of the gas generator inner cavity, the front wall of the gas generator shell is composed of the compressed air inlet and the front wall of the gas generator inner cavity, and the gas generator shell is tapered from the compressed air inlet to the gas outlet.

[0008] Furthermore, the gas generator has three inputs. The first input is high-pressure compressed air generated by a turbocharger, which is directly connected to the annular compressed air inlet on the front wall of the gas generator shell through an annular diffuser along an annular channel. The compressed gas can protect and cool the gas generator shell; the second input is the high-temperature exhaust gas of the heavy oil piston engine, which is sent from the side wall of the gas generator shell through the high-temperature exhaust gas inlet pipe into the gas generator inner cavity at the head of the gas generator shell to heat the catalytic propellant; the third input is the propellant, which is sent to the central reaction zone of the head of the gas generator inner cavity through the propellant delivery pipe, and is vaporized under the action of the high-temperature exhaust gas to form a high-temperature and high-pressure mixed gas, which is discharged from the gas outlet.

[0009] Furthermore, the booster is high-concentration hydrogen peroxide or a mixture thereof.

[0010] Furthermore, in the wingtip jet gas generator, the vaporization and decomposition reaction of the propellant is basically completed in the central reaction zone of the gas generator cavity, and no ignition catalytic system is required during the process; the propellant delivery pipe can be provided with a control valve, and the amount of bleed air required for the rotor wingtip jet is adjusted by controlling the injection amount of the propellant, thereby meeting the requirements of the jet-driven rotor in the vertical take-off and hovering stage.

[0011] Furthermore, the wingtip jet gas generator can utilize the power of the heavy oil engine in the form of compressed air for wingtip jet drive when propulsion power is not required during take-off and landing of the rotorcraft.

[0012] Furthermore, the wingtip jet gas generator can generate high-temperature and high-pressure fuel gas in the central reaction zone of the gas generator inner cavity. If necessary, it can be considered to inject fuel into the high-temperature exhaust gas for supplementary combustion, and further burn the oxygen therein to generate high-temperature and high-pressure fuel gas; the generated fuel gas is more evenly distributed in the rear part of the gas generator shell and then discharged from the gas generator through the gas outlet to be sent to the rotor wing tip for injection.

[0013] Compared with the prior art, the advantages of the present invention are as follows: the present invention utilizes the high-temperature exhaust gas of a heavy oil piston engine to heat the propellant (hydrogen peroxide or a mixture thereof) so as to cause it to undergo a vaporization exothermic reaction, releasing oxygen and water vapor, which are further burned with the unburned oil and gas in the exhaust gas to produce a higher-energy combustion gas. The gas generator does not require a complex catalytic reaction system or an ignition system, and can adjust the amount of bleed air required for the rotor wingtip jet by controlling the injection amount of the propellant to meet the combustion gas required by the wingtip jet rotor. The structure is simple, and at the same time, the combustion efficiency can be improved and pollution emissions can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a structural schematic diagram of the present invention;

[0015] Figure 2 is a cross-sectional view of the present invention;

[0016] In the figure: 1. Gas generator shell; 2. Gas generator inner cavity; 3. Compressed air inlet; 4. Propellant delivery pipe; 5. High-temperature exhaust gas inlet pipe; 6. Gas outlet. DETAILED DESCRIPTION

[0017] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0018] The following is a description of the implementation of the present invention by specific embodiments. People familiar with the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0019] In order to solve the relevant technical problems existing in the prior art, an embodiment of the present application provides a wingtip jet gas generator, which aims to solve the problem of different gas volume requirements for driving the rotor rotation in two working modes: wingtip jet driven rotor during vertical take-off and landing and autorotating rotor during high-speed flight, thereby simplifying the structure and reducing the fuel consumption rate, and especially providing sufficient gas to drive the rotor rotation during the take-off, landing and hovering stage of the wingtip jet rotor.

[0020] like Figure 1 and Figure 2As shown, a wingtip jet gas generator is characterized in that it includes a gas generator shell 1, a gas generator inner cavity 2, a compressed air inlet 3, a propellant delivery pipe 4, a high-temperature exhaust gas inlet pipe 5 and a gas outlet 6, the gas generator inner cavity 2 is in the head area of ​​the gas generator shell 1, the high-temperature exhaust gas inlet pipe 5 passes through the side wall of the gas generator shell 1 and directly reaches the side wall of the gas generator inner cavity 2, the propellant delivery pipe 4 is arranged at the center of the front wall of the gas generator inner cavity 2, the front wall of the gas generator shell 1 is composed of the compressed air inlet 3 and the front wall of the gas generator inner cavity 2, and the gas generator shell 1 is tapered from the compressed air inlet 3 to the gas outlet 6.

[0021] Furthermore, the gas generator has three inputs. The first input is high-pressure compressed air generated by a turbocharger, which is directly connected to the annular compressed air inlet 3 on the front wall of the gas generator housing 1 through an annular diffuser along an annular channel. The compressed gas can protect and cool the gas generator housing 1; the second input is the high-temperature exhaust gas of the heavy oil piston engine, which is sent from the side wall of the gas generator housing 1 through the high-temperature exhaust gas inlet pipe 5 into the gas generator inner cavity 2 at the head of the gas generator housing 1 for heating the catalytic propellant; the third input is the propellant, which is sent to the central reaction zone at the head of the gas generator inner cavity 2 through the propellant delivery pipe 4. Under the action of the high-temperature exhaust gas, it releases heat and vaporizes to release oxygen and water vapor. If necessary, it can also be sprayed with oil for ignition and supplementary combustion to finally form a high-temperature and high-pressure mixed gas, which is discharged from the gas outlet 6. This outlet gas can enter the rotor through the gas path system and be ejected from the wing tip to drive the rotor to rotate at high speed, so that the rotor generates sufficient lift. When the flight speed is sufficient to enable the rotor to generate sufficient lift, the propellant delivery pipe is closed, the compressor is disengaged, and the rotor jet is stopped. At this time, the rotor is in a state of autorotation, thus realizing the two operating modes of the wingtip jet rotorcraft.

[0022] Furthermore, the booster is high-concentration hydrogen peroxide or a mixture thereof.

[0023] Furthermore, in the wingtip jet gas generator, the vaporization and decomposition reaction of the propellant is basically completed in the central reaction zone of the gas generator cavity, and no ignition catalytic system is required during the process; the propellant delivery pipe can be provided with a control valve, and the amount of bleed air required for the rotor wingtip jet is adjusted by controlling the injection amount of the propellant, thereby meeting the requirements of the jet-driven rotor in the vertical take-off and hovering stage.

[0024] Furthermore, the wingtip jet gas generator can utilize the power of the heavy oil engine in the form of compressed air for wingtip jet drive when propulsion power is not required during take-off and landing of the rotorcraft.

[0025] Furthermore, the wingtip jet gas generator can generate high-temperature and high-pressure fuel gas in the central reaction zone of the gas generator inner cavity. If necessary, it can be considered to inject fuel into the high-temperature exhaust gas for supplementary combustion, and further burn the oxygen therein to generate high-temperature and high-pressure fuel gas; the generated fuel gas is more evenly distributed in the rear part of the gas generator shell and then discharged from the gas generator through the gas outlet to be sent to the rotor wing tip for injection.

[0026] Although the present invention has been described in detail above by general description and specific embodiments, it is obvious to those skilled in the art that some modifications or improvements can be made to the present invention. Therefore, these modifications or improvements made without departing from the spirit of the present invention all belong to the scope of protection claimed by the present invention.

Claims

1. A wingtip jet gas generator, It is characterized in that The invention comprises a gas generator housing (1), a gas generator inner cavity (2), a compressed air inlet (3), a propellant delivery pipe (4), a high-temperature exhaust gas inlet pipe (5) and a gas outlet (6), wherein the gas generator inner cavity (2) is located in a head region within the gas generator housing (1), the high-temperature exhaust gas inlet pipe (5) passes through a side wall of the gas generator housing (1) and directly reaches a side wall surface of the gas generator inner cavity (2), a propellant delivery pipe (4) is arranged at a central position of a front wall surface of the gas generator inner cavity (2), the front wall surface of the gas generator housing (1) is composed of a compressed air inlet (3) and a front wall surface of the gas generator inner cavity (2), and the gas generator housing (1) is tapered from the compressed air inlet (3) to the gas outlet (6); The gas generator has three inputs. The first input is high-pressure compressed air generated by a turbocharger, which directly connects to the annular compressed air inlet (3) on the front wall of the gas generator housing (1) through an annular diffuser along an annular channel. The compressed gas can protect and cool the gas generator housing (1). The second input is high-temperature exhaust gas from a heavy oil piston engine, which is fed from the side wall of the gas generator housing (1) through a high-temperature exhaust gas inlet pipe (5) into the gas generator inner cavity (2) at the head of the gas generator housing (1) for heating the catalytic propellant; the third input is propellant, which is fed through a propellant delivery pipe (4) to the central reaction zone at the head of the gas generator inner cavity (2), where it releases heat and vaporizes under the action of the high-temperature exhaust gas to form a high-temperature and high-pressure mixed gas, which is discharged from a gas outlet (6); The high-temperature exhaust gas intake pipe can enter the inner cavity of the gas generator in a single-tube manner, or can enter the inner cavity of the gas generator in a multi-tube manner along the circumference of the gas generator.

2. The wingtip jet gas generator according to claim 1, It is characterized in that The booster is high-concentration hydrogen peroxide or a mixture thereof.

3. The wingtip jet gas generator according to claim 1, It is characterized in that The propellant delivery pipe (4) is provided with a flow control valve.

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