Engine conformal jet

Abstract

The application provides an engine conformal jet plane and relates to the technical field of jet planes.The jet plane comprises a fuselage, a wing and a multi-branch converging turbocharged engine; the engine comprises a plurality of supercharging pipes and a multi-way pipe; the supercharging pipes are sequentially connected through the multi-way pipe, and a turbocharged fan is arranged in each supercharging pipe; a gas inlet is arranged at the head end of a primary supercharging pipe, and a gas outlet is arranged at the tail end of a final supercharging pipe; the supercharging pipes and the multi-way pipe are laid in the wing, the gas inlet is located at the front end of the wing, and the gas outlet is located at the rear end of the wing; a gas inlet hole is arranged at the front end of the wing, and a gas outlet hole is arranged at the rear end of the wing; the plane is equipped with a pressurized turbofan duct power system, the jet flow speed of the tail of the plane is faster, is much higher than the jet flow speed of a conventional engine, the limit flight speed of the plane is faster, the engine is conformally arranged in the wing, the plane can be fully covered with a stealth coating, and the stealth and high-speed flight functions of the plane are realized.

Description

Technical Field

[0001] This invention relates to the field of jet aircraft technology, and more specifically to a conformal jet aircraft engine. Background Technology

[0002] Traditional aircraft fuel is typically aviation kerosene. The exhaust gases produced by the combustion of this fuel, such as carbon dioxide, carbon monoxide, unburned hydrocarbons, particulate matter, and nitrogen oxides, are all sources of air pollution. High-speed conventional fuel-powered aircraft often leave behind "white smoke," also known as condensation contrails, which are formed by the condensation of water vapor and particles from the exhaust gases into ice crystals in cold air. Research has found that condensation contrails can form cirrus clouds (a type of high-altitude cloud). These clouds hinder the dissipation of heat radiation from the Earth's surface, thus exacerbating global warming.

[0003] The engine pylons of traditional aircraft are critical load-bearing components, and their design and manufacturing are complex and costly. During flight, the engine pylons experience significant stress, and the stress concentration at the connection point with the wing makes them highly susceptible to wing fatigue damage.

[0004] The engine pylons and engine nacelles are suspended under the wings, which causes high drag on the aircraft and consequently leads to high operating costs.

[0005] Traditional propeller-driven aircraft engines have propellers that cause low airflow disturbance, making it difficult to achieve high-speed flight. Furthermore, the propellers are mostly exposed and reflect radar waves, making it impossible to achieve complete coverage of the aircraft's stealth coating, including the propellers. Summary of the Invention

[0006] (a) Technical problems to be solved

[0007] To address the shortcomings of existing technologies, this invention provides a conformal jet aircraft that solves the problem of aircraft being unable to achieve full stealth and high-speed flight.

[0008] (II) Technical Solution

[0009] To achieve the above objectives, the present invention provides the following technical solution:

[0010] A conformal jet aircraft, the jet aircraft comprising: a fuselage, wings and a multi-path merging turbocharged engine;

[0011] The engine includes: several booster pipes and multi-port pipes;

[0012] The booster pipes are connected in stages through multiple pipes, and each booster pipe is equipped with a turbo booster fan.

[0013] The primary booster pipe has an air inlet at the head end, and the final booster pipe has an air outlet at the end.

[0014] The pressurization pipe and multi-port pipe are laid flat inside the wing, with the air inlet located at the front end of the wing and the air outlet located at the rear end of the wing; the front end of the wing has an air inlet corresponding to the air inlet, and the rear end of the wing has an air outlet corresponding to the air outlet.

[0015] Preferably, a flow regulating valve is provided at the air outlet, which can adjust the jet area of ​​the air outlet according to the airflow and air pressure in the final stage booster pipe, thereby adjusting the gas flow rate ejected from the engine.

[0016] Preferably, a one-way check valve is installed in the air inlet pipe of each multi-port pipe.

[0017] Preferably, the turbocharger fans in all boost pipes are the same size.

[0018] Preferably, the onboard power supply for the engine consists of multiple individual power supply modules; each module supplies power to each stage of the turbocharger fan, and from the primary stage to the final stage, the operating current of the turbocharger fan remains basically constant, while the speed, voltage, energy conversion, and power output density of the turbocharger fan all increase progressively.

[0019] Preferably, each turbocharger fan of the engine is equipped with a current monitoring module. The output voltage of each individual power supply module of the onboard power supply is controlled by the current measurement value of the corresponding turbocharger fan motor. When the current measurement value of the turbocharger fan motor is too low, the current monitoring module adjusts the output voltage of the corresponding power supply module in real time to increase the voltage. Conversely, when the current measurement value of the turbocharger fan motor is too high, the current monitoring module adjusts the output voltage of the corresponding power supply module in real time to decrease the voltage. This ensures that each stage of the turbocharger fan motor achieves a dynamic balance of voltage and current, maximizing the kinetic energy conversion efficiency of each stage of the engine's turbocharger motor.

[0020] Preferably, all turbocharger fans are of the same model.

[0021] (III) Beneficial Effects

[0022] This invention provides a conformal jet aircraft. Compared with the prior art, it has the following advantages:

[0023] In this invention, the jet aircraft includes: a fuselage, a wing, and a multi-branch merging turbocharged engine; the engine includes: several booster pipes and a multi-port pipe; the booster pipes are connected and merged in stages through the multi-port pipe, and each booster pipe is equipped with a turbocharged fan; the primary booster pipe has an air inlet at its head end, and the final booster pipe has an air outlet at its tail end; the booster pipes and multi-port pipes are laid flat inside the wing, with the air inlet located at the front end of the wing and the air outlet located at the rear end of the wing; the front end of the wing has air intake holes corresponding to the air inlets, and the rear end of the wing has air outlet holes corresponding to the air outlets; the aircraft is equipped with a pressurized turbine-bypass propulsion system, whose tail-exhaust airflow speed is much faster than that of traditional engines, resulting in a higher maximum flight speed; and the engine is conformally arranged inside the wing, allowing the aircraft to be fully covered with a stealth coating, achieving stealth and high-speed flight capabilities. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 This is a schematic diagram of the internal structure of a jet aircraft in an embodiment of the present invention;

[0026] Figure 2 This is a schematic diagram of the engine structure in an embodiment of the present invention;

[0027] Figure 3 This is a partial structural diagram of the engine in an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram of the one-way check valve in an embodiment of the present invention. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention are described clearly and completely. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0030] This application provides a conformal jet aircraft with an engine, which solves the problem that aircraft cannot achieve full stealth and high-speed flight.

[0031] The technical solution in this application is to solve the above-mentioned technical problems, and the general idea is as follows:

[0032] In this embodiment of the invention, the jet aircraft includes: a fuselage, a wing, and a multi-branch merging turbocharged engine; the engine includes: several booster pipes and a multi-port pipe; the booster pipes are connected and merged in stages through the multi-port pipe, and each booster pipe is equipped with a turbocharged fan; the primary booster pipe has an air inlet at its head end, and the final booster pipe has an air outlet at its end; the booster pipes and multi-port pipes are laid flat inside the wing, with the air inlet located at the front end of the wing and the air outlet located at the rear end of the wing; the front end of the wing has air inlets corresponding to the air inlets, and the rear end of the wing has air outlets corresponding to the air outlets; the aircraft is equipped with a pressurized turbine-bypass propulsion system, whose tail-exhaust airflow speed is much faster than that of traditional engines, resulting in a higher maximum flight speed; and the engine is conformally arranged inside the wing, allowing the aircraft to be fully covered with a stealth coating, achieving stealth and high-speed flight capabilities.

[0033] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0034] Example:

[0035] like Figures 1-3 As shown, the present invention provides a conformal jet aircraft, the jet aircraft comprising: a fuselage, wings and a multi-branch merging turbocharged engine;

[0036] The engine includes: a plurality of booster pipes 10 and a multi-port pipe 20;

[0037] The booster pipes 10 are connected and merged in stages through multi-port pipes 20, and each booster pipe 10 is equipped with a turbocharger fan 30.

[0038] The primary booster pipe 10 has an air inlet at its head and the final booster pipe 10 has an air outlet at its end.

[0039] The booster pipe 10 and the multi-port pipe 20 are laid flat inside the wing, with the air inlet located at the front end of the wing and the air outlet located at the rear end of the wing; the front end of the wing has an air inlet 40 corresponding to the air inlet, and the rear end of the wing has an air outlet 50 corresponding to the air outlet.

[0040] Compared to aircraft equipped with traditional open-type propeller engines, the aircraft is equipped with a pressurized turbine-ducted propulsion system, which produces a faster exhaust flow at the tail, far exceeding the exhaust flow speed of traditional engines, resulting in a higher maximum flight speed. Furthermore, the engine is conformally mounted within the wing, allowing the aircraft to be fully covered with a stealth coating, thus achieving stealth and high-speed flight capabilities.

[0041] By leveraging the multi-inlet turbocharged engine and the flexible arrangement of the engine booster pipe 10 and multi-pass pipe 20, the engine and wing are tightly integrated to form a conformal design. The conformal design allows the engine and wing to be seamlessly integrated, eliminating the need for engine pylons and saving on the overall manufacturing cost of the aircraft.

[0042] Traditional engine nacelle pylons experience high stress concentration during flight, making them highly susceptible to wing fatigue damage. Conformal design improves the bonding strength between the aircraft and the engine, avoiding the sustained stress and vibration caused by long-term exposure to high-altitude jet streams, turbulence, or other external impacts. This eliminates the risk of engine nacelle pylon damage due to vibration fatigue failure.

[0043] The conformal engine design, integrated within the wing, reduces high-speed drag caused by traditional exposed engine pylons and nacelles. This allows for better lift output, improves overall aircraft energy conversion efficiency, and enhances flight economy.

[0044] The turbocharger fan 30 in the aircraft engine is fully electric, making it more energy-efficient and environmentally friendly than aircraft with traditional fuel-powered engines, and it does not produce pollution from the combustion of chemical fuels.

[0045] Traditional aircraft fuel is typically aviation kerosene. The exhaust gases produced by the combustion of this fuel, such as carbon dioxide, carbon monoxide, unburned hydrocarbons, particulate matter, and nitrogen oxides, are all sources of air pollution. High-speed conventional fuel-powered aircraft often leave behind "white smoke," also known as condensation contrails, which are formed by the condensation of water vapor and particles from the exhaust gases into ice crystals in cold air. Research has found that condensation contrails can form cirrus clouds (a type of high-altitude cloud). These clouds hinder the dissipation of heat radiation from the Earth's surface, thus exacerbating global warming.

[0046] Aircraft with fully electric tandem turbofan engines do not pose this pollution risk, are environmentally friendly, and are characterized by being green, low-carbon, and environmentally friendly.

[0047] like Figure 2 , Figure 3 As shown, a flow regulating valve 11 is provided at the air outlet, which can adjust the jet area of ​​the air outlet according to the airflow and air pressure in the final stage booster pipe 10, thereby adjusting the gas flow rate ejected by the engine.

[0048] like Figure 3 , Figure 4As shown, each multi-port pipe 20 is equipped with a one-way check valve 21 in its intake pipe. In the event of a turbocharger fan 30 malfunction, the corresponding multi-port pipe 20 intake pipe will not have intake pressure. The corresponding one-way check valve 21 will immediately close under the action of the air pressure in the multi-port pipe 20, preventing backflow and pressure leakage in the intake pipe of the multi-port pipe 20 corresponding to the malfunctioning turbocharger fan 30, and avoiding a sudden drop in the overall thrust of the engine.

[0049] like Figure 2 , Figure 3 As shown, all turbocharger fans 30 in the boost pipes 10 are the same size. With the gradual convergence of the boost pipes 10, the turbine duct can gradually shrink from the air inlet to the air outlet. Compared with the existing technology where multi-stage turbine fans of different diameters are distributed in the gradually shrinking duct, the development cost is greatly reduced.

[0050] The onboard power supply that powers the engine consists of multiple individual power supply modules; each module supplies power to the turbocharger fan 30 at each stage. From the primary stage to the final stage, the operating current of the turbocharger fan 30 remains basically constant, while the speed, voltage, energy conversion, and power output density of the turbocharger fan all increase progressively.

[0051] Each turbocharger fan 30 of the engine is equipped with a current monitoring module. The output voltage of each individual power supply module of the onboard power supply is controlled by the current measurement value of the corresponding turbocharger fan 30 motor. When the current measurement value of the turbocharger fan 30 motor is too low, the current monitoring module adjusts the output voltage of the corresponding power supply module in real time to increase the voltage. Conversely, when the current measurement value of the turbocharger fan 30 motor is too high, the current monitoring module adjusts the output voltage of the corresponding power supply module in real time to decrease the voltage. This ensures that the turbocharger fan 30 motors at each stage achieve a dynamic balance of voltage and current, maximizing the kinetic energy conversion efficiency of each stage of the engine's turbocharger motor.

[0052] All turbocharger fans in the 30 series are the same model, which reduces the cost of bulk procurement and customization and improves manufacturing efficiency.

[0053] In summary, compared with the prior art, the present invention has the following beneficial effects:

[0054] 1. In this embodiment of the invention, the jet aircraft includes: a fuselage, a wing, and a multi-branch merging turbocharged engine; the engine includes: several booster pipes and a multi-port pipe; the booster pipes are connected and merged in stages through the multi-port pipe, and each booster pipe is equipped with a turbocharged fan; the primary booster pipe has an air inlet at its head end, and the final booster pipe has an air outlet at its end; the booster pipes and multi-port pipes are laid flat inside the wing, with the air inlet located at the front end of the wing and the air outlet located at the rear end of the wing; the front end of the wing has air inlets corresponding to the air inlets, and the rear end of the wing has air outlets corresponding to the air outlets; the aircraft is equipped with a pressurized turbine-bypass propulsion system, whose tail-exhaust airflow speed is faster, much higher than that of traditional engines, making the aircraft's maximum flight speed faster; and the engine is conformally arranged inside the wing, allowing the aircraft to be fully covered with a stealth coating, realizing the aircraft's stealth and high-speed flight capabilities.

[0055] 2. By leveraging the features of multi-intake turbocharged engines and the flexible arrangement of engine booster pipes and multi-pass pipes, the engine and wing are tightly integrated to form a conformal design. The conformal design allows for seamless integration of the engine and wing, eliminating the need for engine pylons and saving on overall aircraft manufacturing costs.

[0056] 3. Traditional engine nacelle pylons experience high stress concentration during flight, making them highly susceptible to wing fatigue damage. The conformal design improves the bonding strength between the aircraft and the engine, avoiding the sustained stress and vibration caused by long-term exposure to high-altitude jet streams, turbulence, or other external impacts. This eliminates the risk of engine nacelle pylon damage due to vibration fatigue failure.

[0057] 4. The conformal engine design within the wing reduces high-speed wind resistance caused by traditional exposed engine mounts and nacelles. This allows for better lift output, improves overall aircraft energy conversion efficiency, and enhances flight economy.

[0058] 5. The turbocharger fan in the aircraft engine is fully electric, which is more energy-efficient and environmentally friendly than aircraft with traditional aviation fuel engines, and does not produce pollution from the combustion of chemical fuels.

[0059] Traditional aircraft fuel is typically aviation kerosene. The exhaust gases produced by the combustion of this fuel, such as carbon dioxide, carbon monoxide, unburned hydrocarbons, particulate matter, and nitrogen oxides, are all sources of air pollution. High-speed conventional fuel-powered aircraft often leave behind "white smoke," also known as condensation contrails, which are formed by the condensation of water vapor and particles from the exhaust gases into ice crystals in cold air. Research has found that condensation contrails can form cirrus clouds (a type of high-altitude cloud). These clouds hinder the dissipation of heat radiation from the Earth's surface, thus exacerbating global warming.

[0060] Aircraft with fully electric tandem turbofan engines do not pose this pollution risk, are environmentally friendly, and are characterized by being green, low-carbon, and environmentally friendly.

[0061] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0062] The above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A conformal jet aircraft, characterized in that, The jet aircraft includes: a fuselage, wings, and a multi-branched turbocharged engine; The engine is a fully electric turbofan engine, comprising: a plurality of booster pipes (10) and a plurality of multi-port pipes (20). The booster pipe (10) is connected in stages through a multi-port pipe (20). Each booster pipe (10) is equipped with a series of turbocharged fans (30), that is, the air outlet of the front turbocharged fan (30) is connected to the air inlet of the rear turbocharged fan (30). An air inlet is opened at the head end of the primary booster pipe (10), and an air outlet is opened at the end of the final booster pipe (10); the end of the primary booster pipe (10) is connected to a multi-port pipe (20), the outlet of the multi-port pipe (20) is connected to the head end of the next-stage booster pipe (10), the end of the next-stage booster pipe (10) is connected to the inlet of the next-stage multi-port pipe (20), and they are connected again through the multi-port pipe (20), and the outlet of the multi-port pipe (20) is connected to the head end of the final-stage booster pipe (10); The pressurization pipe (10) and the multi-port pipe (20) are laid flat inside the wing, with the air inlet located at the front end of the wing and the air outlet located at the rear end of the wing; the front end of the wing has an air inlet hole (40) corresponding to the air inlet, and the rear end of the wing has an air outlet hole (50) corresponding to the air outlet. A flow regulating valve (11) is provided at the air outlet, which can adjust the jet area of ​​the air outlet according to the airflow and air pressure in the final stage booster pipe (10), thereby adjusting the gas flow rate ejected by the engine. The onboard power supply that powers the engine consists of multiple individual power supply modules; each module powers the turbocharger fan (30) at each stage. From the primary stage to the final stage, the operating current of the turbocharger fan (30) remains constant, while the speed, voltage, energy conversion and power output density of the turbocharger fan increase step by step. Each turbocharger fan (30) of the engine is equipped with a current monitoring module. The output voltage of each individual power supply module of the onboard power supply is controlled by the current measurement value of the corresponding turbocharger fan (30) motor. When the current measurement value of the turbocharger fan (30) motor is too low, the current monitoring module adjusts the output voltage of the corresponding power supply module in real time to increase the voltage. Conversely, when the current measurement value of the turbocharger fan (30) motor is too high, the current monitoring module adjusts the output voltage of the corresponding power supply module in real time to decrease the voltage. This enables each stage of the turbocharger fan (30) motor to achieve a dynamic balance of voltage and current, maximizing the kinetic energy conversion efficiency of each stage of the engine's turbocharger motor. All turbocharged fans (30) are of the same model.

2. The conformal jet aircraft with an engine as described in claim 1, characterized in that, Each of the multi-port pipes (20) is equipped with a one-way check valve (21) in the air inlet pipe.

3. The conformal jet aircraft with an engine as described in claim 1, characterized in that, All turbo fans (30) within the boost pipes (10) are the same size.

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