Aero-engine
By combining a ramjet engine with an auxiliary starting device, the problems of high manufacturing difficulty and high fuel consumption of turbine engines are solved, and an aviation engine design with efficient combustion and low failure rate is achieved, which is suitable for a variety of aircraft.
Patent Information
- Application Number
- CN202510843728.9
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-23
- Publication Date
- 2025-09-16
AI Technical Summary
Existing turbojet engines and turbofan engines are difficult and expensive to manufacture. The temperature of the gas in the combustion chamber before the turbine limits the increase in thrust, the fuel consumption rate is high, and the turbine engine cannot be started when not in the takeoff state.
It adopts a ramjet engine combined with an auxiliary starting device, including a casing, nozzle, flame tube, spark plug, fuel injector, and air and water supply devices. It uses the principles of fluid mechanics to increase the jet volume. The auxiliary starting device retracts in the cabin to reduce flight resistance, and the flame tube increases the contact area between fuel and air to improve combustion efficiency.
It improves combustion efficiency, reduces fuel consumption, simplifies structure, reduces failure rate and maintenance cost, increases thrust, is suitable for starting multi-engine aircraft, and reduces flight resistance.
Smart Images
Figure CN120650076A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of aviation vehicles, and in particular to an aviation engine. Background Art
[0002] The mainstream power plants currently used in aircraft are turbojets and turbofans. These engines each have their own advantages and disadvantages, but a common drawback is their extreme manufacturing difficulty, primarily in turbine machining, which places extremely stringent requirements on materials and manufacturing processes. They must operate under extremely harsh conditions, exceeding 1500°C and operating at 15,000 rpm. All components must also operate safely, reliably, and without failure. Therefore, aircraft engines, considered the crown jewel of modern industry, are among the most technologically integrated and complex products. Currently, only a few countries can manufacture them, resulting in high costs and high maintenance costs. Another common drawback of these engines is that the combustion gas temperature in the turbine's combustion chamber must be kept high, otherwise it will damage the components. This limits further thrust increases. The only way to increase thrust is to add an afterburner after the turbine, where high temperatures will not damage the components. However, this increases manufacturing cost, weight, and fuel consumption, particularly high fuel consumption. For economic reasons, the afterburner must be activated only briefly when a thrust boost is needed during takeoff or combat. Long periods of idle afterburner activity become a burden. Summary of the Invention
[0003] The purpose of the present invention is to provide an aircraft engine in view of the above technical problems.
[0004] The technical solutions proposed by the present invention to solve the above technical problems are as follows: An aircraft engine comprising a ramjet engine and an auxiliary starting device; The ramjet engine includes a shell, a nozzle, a flame tube, a spark plug and a fuel injector; the shell is a straight cylinder or a trumpet-shaped cylinder; the nozzle is a straight cylinder or an expanded double-layer cylinder, with a gap between the inner layer and the outer layer, the front end of the inner layer is connected to the rear end of the shell, and the rear end of the inner layer is connected to the rear end of the outer layer; the flame tube is a truncated cone-shaped cylinder, the large end of the flame tube is connected to the rear end of the shell and the front end of the inner layer of the nozzle, the small end of the flame tube is closed and fixed with the spark plug and the fuel injector, the working end of the spark plug and the working end of the fuel injector both extend into the flame tube; a plurality of small holes are distributed on the side wall of the flame tube along the circumferential direction and the axial direction, the small holes are connected to the interior of the flame tube and the inlet end of the shell, and the total area of the small holes is larger than the cross-sectional area of the shell; the spark plug is connected to the electrical control device; the fuel injector is connected to the fuel supply system; The auxiliary starting device includes an air supply device and a water supply device; The air supply device includes a power machine, a fan and an air duct; the output shaft of the power machine is drivingly connected to the input shaft of the fan; one end of the air duct is connected to the air outlet of the fan, and the open end of the air duct is bent toward the inlet end of the housing; The water supply device includes a water tank, a water pump, a water pipe and a water nozzle; the water outlet of the water tank is connected and communicated with the water inlet of the water pump; the water outlet of the water pump is connected and communicated with one end of the water pipe; the other end of the water pipe is connected and communicated with the interface of the water nozzle; the water nozzle is arranged on the side wall of the inlet end of the shell, and the working end extends into the shell.
[0005] On the basis of the above technical solution, the present invention also makes the following improvements: Furthermore, a plurality of small holes are distributed on the inner side wall of the nozzle in the circumferential direction and the axial direction.
[0006] According to the principles of fluid mechanics, when the gas passes through the nozzle at high speed, it will produce an air suction effect, sucking the air outside the small hole into the nozzle. This not only increases the jet volume, but also forms a protective layer between the nozzle and the flame, protecting the nozzle from high temperature erosion.
[0007] Furthermore, the air duct is composed of several sections of pipes of the same length and different diameters, wherein the section with the larger diameter is sequentially sleeved on the section with the smaller diameter, and the section with the smaller diameter can slide along the axial direction; Furthermore, a driving device is provided next to the air duct, and the driving device is the push-pull rod, one end of which is connected to the air duct section with the smallest diameter, and can push and pull the air duct to slide and retract along the axial direction; After the aircraft is flying normally, the auxiliary starting device stops working. At this time, retracting the air duct into the cabin can reduce flight resistance.
[0008] Furthermore, the power machine is an electric motor or an internal combustion engine.
[0009] After determining the power of the fan, the air supply device must match it with a power machine of the same power. The standard for choosing an electric motor or an internal combustion engine is the "power-to-weight ratio". If the matched electric motor is lighter, the electric motor is used; otherwise, the internal combustion engine is used.
[0010] Furthermore, the water nozzles are provided in plurality and are evenly arranged along the circumference of the front end of the shell, and are all connected and communicated with the water outlet end of the water pipe, and the working ends all extend into the shell.
[0011] Multiple water nozzles can make the sprayed water mist uniform.
[0012] Due to the adoption of the above technical solution, the present invention has the following beneficial effects: The ramjet engine of the present invention retains the original advantages of ramjet engines, but has further advantages due to the addition of a flame tube. 1. The flame is prevented from contacting the casing, and the flame cannot reach the flame tube either. This is because the air entering the casing enters the combustion chamber at high speed through the small holes in the flame tube, and the flame can only follow the airflow. Therefore, neither the casing nor the flame tube need to be made of expensive heat-resistant alloys. 2. The flame tube, like the afterburner, is resistant to extremely high temperatures. During cruise, the gas temperature is around 1500°C, which is fuel-efficient. When increased thrust is required during takeoff or combat, the throttle is increased to raise the gas temperature to over 2000°C. 3. The spark plug and fuel injector are installed in the leeward position at the front end of the flame tube, eliminating the need for a flame stabilizer. No flame stalling occurs even at high wind speeds, and only one spark plug and fuel injector are required, simplifying wiring and piping. 4. The longer cylinder increases the contact surface between air and fuel, enabling perfect mixing and full combustion of the fuel and air, thereby improving combustion efficiency. 5. The nearly conical shape of the flame tube reduces shock wave drag during supersonic flight. The wave drag of an oblique shock wave is less than that of a normal shock wave.
[0013] Second, the auxiliary starting device of this invention overcomes the drawback of ramjets being unable to start while stationary on the ground, making it suitable for use in aircraft engines, not just for target drones, missiles, and other disposable aircraft. Compared to components with similar functions in turbine engines (fan vs. compressor, engine vs. turbine), this device offers a significant cost difference. Furthermore, it offers the following advantages: 1. Located within the nacelle, the air duct is retractable, without increasing the windward area or flight resistance. 2. It can operate multiple ramjets (twin or triple engines) with a single auxiliary starting device, simply by multiplying the power of the engine and fan. 3. It operates only briefly during takeoff and when thrust is required, and is inactive after normal flight, rather than continuously operating from takeoff to landing.
[0014] Third, a key indicator of aircraft engine economic efficiency is fuel consumption. It takes about 1 millisecond for fuel to travel from the injector nozzle through the combustion chamber to the exhaust port. In such a short distance and time, it is difficult for the fuel to burn completely. Some fuel is ejected from the engine, resulting in a bright, long flame from the nozzle. This combustion has no effect on the engine. The more fuel ejected from the engine, the lower the combustion efficiency and the higher the fuel consumption (afterburners are the worst in this regard). The flame tube of this invention increases the contact surface between the fuel and the air, allowing the fuel to complete the combustion process within a longer tube, effectively reducing the oil content of the exhaust, improving combustion efficiency, and lowering fuel consumption.
[0015] Fourth, another important metric for measuring the economic efficiency of aircraft engines is thrust-to-weight ratio. While the overall weight advantage of this invention is not significant compared to turbine engines (a single-engine-to-multi-engine scenario is more pronounced), it does have a significant advantage in thrust: the working fluid in the latter consumes considerable energy to drive the turbine, which inevitably slows the jet velocity. In the former, the working fluid flows unimpeded, resulting in a high jet velocity and greater recoil thrust. The compressor and turbine of the latter are located within the engine, increasing the frontal area, while the fan and power unit of the former are located within the nacelle, maintaining this area. If the nozzle diameters of the two are the same, the former generates greater thrust, while the latter generates greater thrust offset by flight resistance.
[0016] Fifth, failure rate, maintenance cost, and service life are also important indicators for measuring the economic efficiency of aircraft engines. The failure rate is related to the accident rate. Aircraft crashes are often caused by engine failure. The ramjet engine of the present invention has no rotating parts and is not exposed to high-temperature combustion gases, resulting in a low failure rate and safety and reliability. Turbine engines have nearly 30,000 parts, and maintenance costs account for a large proportion of the aircraft's operating cost. The present invention has an extremely simple structure and minimal maintenance costs. A friendly operating environment leads to a long service life. The present invention's environmentally friendly operating environment and the short operating time of the auxiliary starting device extend the service life of the aircraft based on actual operating time. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] Figure 1 It is a structural schematic diagram of the present invention.
[0018] Figure 2 It is a structural schematic diagram of the trumpet-shaped housing of the present invention.
[0019] In the accompanying drawings, the technical features represented by the reference numerals are as follows: 1-shell; 2-nozzle; 3-flame tube; 4-spark plug; 5-fuel injector; 6-fan; 7-power machine; 8-air duct; 9-push-pull rod; 10-water nozzle; 11-water pipe; 12-water pump; 13-water tank. DETAILED DESCRIPTION
[0020] The principles and features of the present invention are described below. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.
[0021] The present invention refers to Figure 1-2 .
[0022] The present invention provides an aero-engine, comprising a ramjet engine and an auxiliary starting device; The ramjet engine includes a shell 1, a nozzle 2, a flame tube 3, a spark plug 4 and a fuel injector 5; the shell 1 is a straight cylinder or a trumpet-shaped cylinder; the nozzle 2 is a straight cylinder or an expanded double-layer cylinder, with a gap between the inner layer and the outer layer, the front end of the inner layer is connected to the rear end of the shell 1, and the rear end of the inner layer is connected to the rear end of the outer layer; the flame tube 3 is a truncated cone-shaped cylinder, the large end of the flame tube 3 is connected to the rear end of the shell 1 and the front end of the inner layer of the nozzle 2, the small end of the flame tube 3 is closed and fixed with the spark plug 4 and the fuel injector 5, the working ends of the spark plug 4 and the working ends of the fuel injector 5 both extend into the flame tube 3; a plurality of small holes are distributed on the side wall of the flame tube 3 along the circumferential and axial directions, the small holes are connected to the interior of the flame tube 3 and the inlet end of the shell 1, and the total area of the small holes is larger than the cross-sectional area of the shell 1; the spark plug 4 is connected to the electrical control device; the fuel injector 5 is connected to the fuel supply system; The auxiliary starting device includes an air supply device and a water supply device; The air supply device includes a power machine 7, a fan 6 and an air duct 8; the output shaft of the power machine 7 is drivingly connected to the input shaft of the fan 6; one end of the air duct 8 is connected to the air outlet of the fan 6, and the open end of the air duct 8 is bent toward the inlet end of the housing 1; The water supply device includes a water tank 13, a water pump 12, a water pipe 11 and a water nozzle 10; the water outlet of the water tank 13 is connected and communicated with the water inlet of the water pump 12; the water outlet of the water pump 12 is connected and communicated with one end of the water pipe 11; the other end of the water pipe 11 is connected and communicated with the interface of the water nozzle 10; the water nozzle 10 is arranged on the side wall of the inlet end of the shell 1, and the working end extends into the shell 1.
[0023] On the basis of the above technical solution, the present invention also makes the following improvements: Furthermore, a plurality of small holes are distributed on the inner side wall of the nozzle 2 in the circumferential direction and the axial direction.
[0024] According to the principles of fluid mechanics, when the gas passes through the nozzle 2 at high speed, an air suction effect will occur, sucking the air outside the small hole into the nozzle 2. This not only increases the jet volume, but also forms a protective layer between the nozzle 2 and the flame, protecting the nozzle 2 from high-temperature erosion.
[0025] Furthermore, the air duct 8 is composed of several sections of pipes of the same length and different diameters, wherein the section with the larger diameter is sequentially sleeved on the section with the smaller diameter, and the section with the smaller diameter can slide in the axial direction; Furthermore, a driving device is provided next to the air duct 8, which is the push-pull rod 9. One end of the push-pull rod 9 is connected to the air duct 8 with the smallest diameter, and the air duct 8 can be pushed and pulled to slide and retract along the axial direction. After the aircraft is in normal flight, the auxiliary starting device stops working. At this time, retracting the air duct 8 into the cabin can reduce flight resistance.
[0026] Furthermore, the power machine 7 is an electric motor or an internal combustion engine.
[0027] After determining the power of the fan 6, the air supply device must match it with a power machine 7 of the same power. The standard for selecting an electric motor or an internal combustion engine as the power machine 7 is the "power-to-weight ratio". If the matched electric motor is lighter, the electric motor is used; otherwise, the internal combustion engine is used.
[0028] Furthermore, the water nozzles 10 are provided in plurality and are evenly arranged along the circumference of the front end of the shell 1 , and are all connected to and communicated with the water outlet end of the water pipe 11 , and the working ends of the water nozzles 10 extend into the shell 1 .
[0029] The multiple water spray nozzles 10 can make the sprayed water mist uniform.
[0030] During implementation, the push-pull rod 9 is first used to extend the air duct 8 from the cabin to the front of the shell 1. The aircraft enters the ready-to-fly state, and the auxiliary starting device is turned on. The power machine 7 drives the fan 6 to generate a high-speed airflow that is ejected from the air duct 8 into the shell 1. The high-speed airflow generates an air suction effect, which reduces the air pressure in front of the shell 1 and is sucked into the shell 1. The airflow entering the shell 1 is like the airflow generated by the air in front of the aircraft flying at high speed, with a large wind speed, wind pressure and air volume (the greater the power of the fan 6, the greater the wind speed, wind pressure and air volume generated). At this time, the fuel injector 5 sprays atomized fuel which mixes with air, ignites and burns to produce high-temperature and high-pressure gas. At the same time, the water nozzle 10 also sprays water mist which vaporizes at high temperature to produce a large amount of steam. The gas and steam combine into one airflow, which is ejected from the nozzle 2 at a speed several times greater than that of the airflow entering the shell 1 (assuming that the airflow speed entering the shell 1 is 50 m / s, the volume of the air will increase by more than 7 times when the temperature rises from room temperature to 2000℃. With the support of steam, it is estimated that the jet speed can reach more than 400 m / s). The aircraft then accelerates on the runway under the action of recoil thrust.
[0031] As the aircraft's speed gradually increases, the ram pressure effect gradually becomes apparent. More air enters the housing 1 from the front, increasing the airflow velocity, the engine jet volume and jet velocity, and the recoil thrust. This not only increases the aircraft's speed but also its acceleration, helping the aircraft to rapidly increase its flight speed. After the aircraft takes off, the auxiliary starting device continues to operate. Once the aircraft can fly normally using the ram pressure effect, the auxiliary starting device can be deactivated (water pump 12 is shut off only after the water tank 13 is empty to reduce the aircraft's weight). Finally, the push-pull rod 9 is used to retract the air duct 8 into the cabin.
[0032] The water supply system significantly increases the engine's jet volume and velocity, thus providing greater thrust for takeoff. While it's possible to eliminate the water supply system and have the air supply system perform the auxiliary starting task alone, this would require a significant increase in power and weight, potentially exceeding the weight of the water supply system (without water).
[0033] If an aircraft's flight speed is too low (≤ Mach 0.5) and it is unable to utilize the ramjet effect to fly normally, the following three measures can be taken to accelerate the aircraft: 1. Increase the throttle to increase the engine's gas temperature; 2. Restart the auxiliary starting device to increase the engine's jet volume; 3. Lower the aircraft's flight altitude to reduce the aircraft's potential energy and increase its kinetic energy.
[0034] The shell 1 has two shapes: straight cylinder and trumpet shape. The straight cylinder has a small frontal area, small flight resistance, and better high-speed performance, and is suitable for aircraft with supersonic cruising speed; the trumpet shape has a large frontal area, poor high-speed performance, but better low-speed performance. It can also generate a large air volume and static pressure when flying at a lower speed, and is suitable for aircraft with subsonic cruising speed.
[0035] Since the total area of the small holes on the flame tube 3 is larger than the cross-sectional area of the shell 1, no pressure difference will occur inside and outside the flame tube 3.
[0036] In the description of the present invention, it should be understood that if there appear descriptive terms indicating orientation, direction or positional relationship, such as: "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., the orientation or positional relationship indicated in this specification is based on the orientation or positional relationship shown in the accompanying drawings, which is only for the convenience of understanding the present invention and simplifying the description, and does not indicate or imply that the part, element or whole referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.
[0037] In addition, if there are order description terms, such as "first", "second", etc., their purpose in this specification is to facilitate understanding or simplify the description. For example, in order to distinguish multiple technical features with the same type or function, but they have to be mentioned separately, this specification may use prefix or suffix order description terms to distinguish them. Therefore, it cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" can explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "multiple" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.
[0038] In the present invention, if terms describing the relative functional relationship of structures are used, such as "install", "connect", "connect", "fix", etc., they should be understood in a broad sense unless otherwise clearly specified and limited. For example, "install", "connect", "connect", etc. can be fixed connections, detachable connections, or integrated; can be directly connected, or indirectly connected through an intermediate medium, can be internal communication between two elements, or an interactive relationship between two elements; "fix" can be fixed to form an integral body, or can be detachably fixed through fasteners; can be directly fixed, or can be fixed through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above-mentioned descriptive terms in the present invention can be understood according to the specific circumstances, the context, the coherence of the preceding and following texts, etc.
[0039] In the present invention, if descriptive terms with ancillary or connecting meaning appear, for example, a first feature being "on" or "below" a second feature, these should not be construed in a limiting sense unless otherwise expressly specified or limited. For example, "on" or "below" may refer to direct contact between the first and second features, or indirect contact between the first and second features through an intermediary. Persons of ordinary skill in the art will understand the specific meanings of these descriptive terms in the present invention based on the specific circumstances, context, and coherence of the preceding and following texts.
[0040] Furthermore, when a first feature is “above,” “above,” or “above” a second feature, it may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. When a first feature is “below,” “below,” or “below” a second feature, it may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.
[0041] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in a suitable manner in any one or more embodiments or examples. In addition, those skilled in the art may combine and combine the different embodiments, examples and features of different embodiments and examples described in this specification, unless there is any contradiction, and these combinations or combinations should all fall within the scope of the present invention.
[0042] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are illustrative and are not to be construed as limiting the present invention. Changes, modifications, substitutions and variations of the above embodiments made by persons of ordinary skill in the art within the scope of information available through public channels and in combination with the technical inspiration provided by the present application documents are still within the scope of protection of the present application.
Claims
1. An aircraft engine, characterized in that: Includes ramjet engine and auxiliary starting device; The ramjet engine comprises a housing (1), a nozzle (2), a flame tube (3), a spark plug (4) and a fuel injector (5); the housing (1) is a straight or trumpet-shaped cylinder; the nozzle (2) is a straight or expanded double-layer cylinder, with a gap between the inner layer and the outer layer, the front end of the inner layer is connected to the rear end of the housing (1), and the rear end of the inner layer is connected to the rear end of the outer layer; the flame tube (3) is a truncated cone-shaped cylinder, the large end of the flame tube (3) is connected to the rear end of the housing (1) and the front end of the inner layer of the nozzle (2). The small end of the flame tube (3) is closed and fixed with the spark plug (4) and the fuel injector (5), and the working end of the spark plug (4) and the working end of the fuel injector (5) both extend into the flame tube (3); a plurality of small holes are distributed on the side wall of the flame tube (3) in the circumferential direction and the axial direction, and the small holes are connected to the interior of the flame tube (3) and the inlet end of the shell (1), and the total area of the small holes is larger than the cross-sectional area of the shell (1); the spark plug (4) is connected to the electrical control device; the fuel injector (5) is connected to the fuel supply system; The auxiliary starting device includes an air supply device and a water supply device; The air supply device comprises a power machine (7), a fan (6) and an air duct (8); the output shaft of the power machine (7) is drivingly connected to the input shaft of the fan (6); one end of the air duct (8) is connected to the air outlet of the fan (6), and the open end of the air duct (8) is bent toward the inlet end of the housing (1); The water supply device comprises a water tank (13), a water pump (12), a water pipe (11) and a water nozzle (10); the water outlet of the water tank (13) is connected to and communicated with the water inlet of the water pump (12); the water outlet of the water pump (12) is connected to and communicated with one end of the water pipe (11); the other end of the water pipe (11) is connected to and communicated with the interface of the water nozzle (10); the water nozzle (10) is arranged on the side wall of the inlet end of the shell (1), and the working end extends into the shell (1).
2. The aircraft engine according to claim 1, characterized in that: The inner side wall of the nozzle (2) is provided with a plurality of small holes distributed in the circumferential direction and the axial direction.
3. The aircraft engine according to claim 1, characterized in that: The air duct (8) is composed of several sections of pipes with the same length and different diameters, wherein the section with the larger diameter is sequentially placed on the section with the smaller diameter, and the section with the smaller diameter can slide in the axial direction.
4. The aircraft engine according to claim 1, characterized in that: A driving device is also provided beside the air duct (8), and the driving device is the push-pull rod (9). One end of the push-pull rod (9) is connected to a section of the air duct (8) with the smallest diameter, and can push and pull the air duct (8) to slide and retract along the axial direction.
5. The aircraft engine according to claim 1, characterized in that: The power machine (7) is an electric motor or an internal combustion engine.
6. The aircraft engine according to claim 1, characterized in that: The water spray nozzles (10) are provided in plurality and are evenly arranged along the circumference of the front end of the shell (1). The nozzles are all connected to and communicate with the water outlet end of the water pipe (11), and the working ends of the nozzles extend into the shell (1).