A punch turbine generator

Abstract

This invention discloses a ramjet turbine generator suitable for ramjet engines. It includes a ramjet turbine assembly and a generator assembly, with the generator assembly connected to the ramjet turbine assembly. The rotating ramjet turbine assembly drives the generator assembly to generate electricity. The generator assembly has a cooling inlet and a cooling outlet, with the outlet end of the ramjet turbine assembly connected to the cooling inlet. Compared to existing technologies, the ramjet turbine generator provided by this invention introduces the air that drives the ramjet turbine assembly to rotate into the generator assembly for heat dissipation. The air after passing through the ramjet turbine assembly expands in volume and decreases in temperature compared to the air at the front end of the ramjet turbine assembly, thus better dissipating heat from the generator assembly. While meeting heat dissipation requirements, it effectively reduces the weight of the cooling components, thereby effectively reducing the overall weight of the generator, aligning with the development trend of lightweight and high-efficiency ramjet turbine generators.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and more specifically to a ramjet turbine generator. Background Technology

[0002] In the future, aircraft possessing long range (greater than 100 kilometers), supersonic speed (Mach number greater than 2), and ultra-low altitude (sea-skimming or ground-hugging flight) characteristics will have broad application prospects. Currently, when developing supersonic propulsion systems, countries primarily choose ramjet engines for air-breathing propulsion systems. This is because ramjet engines have more significant advantages compared to rocket engines, such as higher safety, flexibility, and economy. Furthermore, since ramjet engines do not require their own oxidizer like rocket engines, they are smaller and lighter, allowing the flight platform to carry more payload.

[0003] However, ramjet engines compress air using the forward motion of the engine and do not use a compressor with rotating blades. Since there is no rotating machinery in the primary power source of a ramjet engine, there is no possibility of extracting shaft work from the primary power source, and therefore, it is impossible to convert the energy of the gas into electrical energy without auxiliary power. To provide a sufficiently long-lasting and continuous power supply for the onboard equipment of such high-speed cruise aircraft (including radar, fuel pumps, servos, and temperature control systems), it is necessary to design and develop an onboard power generation system suitable for high-speed aircraft that can efficiently generate sufficient electrical energy.

[0004] Given that ramjet engines lack rotating machinery, current high-speed airborne power generation systems primarily utilize ramjet turbine technology. During generator operation, approximately 10% of the power is converted into heat. Due to the integrated design and limited system space, the generator's heat dissipation capacity is relatively low, leading to overheating and performance degradation. Therefore, to ensure safe generator operation, it is essential to enhance the generator's heat dissipation capacity without unduly increasing its weight. Summary of the Invention The purpose of this invention is to overcome the above-mentioned technical deficiencies and propose a ramjet turbine generator to solve the technical problem of insufficient heat dissipation capacity of generators suitable for ramjet engines in the prior art.

[0005] To achieve the above-mentioned technical objectives, the present invention adopts the following technical solution: This invention provides a ramjet turbine generator, suitable for ramjet engines, comprising a ramjet turbine assembly and a generator assembly. The generator assembly is connected to the ramjet turbine assembly, and the rotating ramjet turbine assembly can drive the generator assembly to generate electricity; The generator assembly includes a housing, a stator, and a rotor. The stator is fixedly disposed within the housing, and the rotor passes through the stator and is rotatably connected to the housing. One end of the rotor extends outside the housing and is fixedly connected to the ram turbine assembly, enabling it to rotate synchronously with the ram turbine assembly. The housing has multiple cooling air inlets and cooling air outlets. The multiple cooling air inlets are arranged circumferentially around the rotor, and the cooling air outlets are located on the side of the housing away from the ram turbine assembly. Cooling channels are formed inside the housing around the stator and rotor, and the cooling channels connect the cooling air inlets and cooling air outlets. The outlet of the ramjet turbine assembly is connected to the cooling inlet.

[0006] In some embodiments, the generator assembly further includes an air bearing, through which the rotor is rotatably connected to the housing.

[0007] In some embodiments, the air suspension bearing includes a radial dynamic pressure air bearing and a stop pressure air bearing. The rotor is located at both ends of the stator and is connected to the housing via the radial dynamic pressure air bearing. The end of the rotor away from the ramjet turbine assembly is also connected to the housing via the stop pressure air bearing.

[0008] In some embodiments, the ramjet generator further includes an air intake device, the outlet of which is connected to the ramjet turbine assembly for guiding air to the ramjet turbine assembly.

[0009] In some embodiments, the ramjet generator further includes a flow regulating device disposed on the air intake device for regulating the airflow through the air intake device.

[0010] In some embodiments, the ramjet generator further includes a compressor, the air inlet of which is connected to the cooling outlet.

[0011] In some embodiments, the ramjet generator further includes an exhaust device connected to the outlet of the compressor.

[0012] Compared with the prior art, the ram turbine generator provided by the present invention introduces the air after driving the ram turbine assembly to rotate into the generator assembly for heat dissipation. The air after passing through the ram turbine assembly expands in volume and decreases in temperature compared with the air at the front end of the ram turbine assembly, which can better dissipate heat from the generator assembly. While meeting the heat dissipation requirements, it effectively reduces the weight of the cooling components, thereby effectively reducing the total weight of the generator, which is in line with the development trend of lightweight and high-efficiency ram turbine generators. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the structure of the ram turbine generator provided in an embodiment of the present invention; Figure 2 This is a partial structural schematic diagram of the ramjet turbine generator provided in an embodiment of the present invention. Detailed Implementation

[0014] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0015] To address the technical problem of insufficient heat dissipation capacity of generators suitable for ramjet engines, this invention provides a ramjet turbine generator that can achieve lightweight and high-efficiency ramjet turbine generators.

[0016] Please see Figure 1 and Figure 2 , Figure 1 This is a schematic diagram of the structure of the ram turbine generator provided in an embodiment of the present invention; Figure 2 This is a partial structural schematic diagram of the ramjet turbine generator provided in an embodiment of the present invention. The airflow path is indicated by arrows. This ramjet turbine generator is applicable to ramjet engines and includes a ramjet turbine assembly 1 and a generator assembly 2.

[0017] A ramjet engine is a relatively simple air-breathing jet engine that operates under demanding conditions. Its core principle lies in using the powerful ramjet generated by the aircraft's high-speed flight to compress air, eliminating the need for the complex compressor components found in traditional jet engines. After entering the engine, air is slowed and diffused through the intake duct, mixes with fuel, and burns. The resulting high-temperature exhaust gas is expelled at high speed from the exhaust nozzle, thus generating thrust. Because it cannot start from a standstill or at low speed, it must rely on other propulsion methods to reach supersonic speeds before it can operate efficiently. Therefore, it is primarily used in supersonic and hypersonic aircraft.

[0018] Generator assembly 2 is connected to ramjet turbine assembly 1. The rotating ramjet turbine assembly 1 can drive generator assembly 2 to generate electricity. In actual use, the aircraft is equipped with bleed air dampers. After receiving a working command, the bleed air dampers open, and ramjet air flows through the bleed air duct to the air intake end of ramjet turbine assembly 1, driving ramjet turbine assembly 1 to rotate and output shaft power to the coaxial generator assembly 2, driving generator assembly 2 to generate electricity.

[0019] The generator assembly 2 has a cooling air inlet 2a and a cooling air outlet 2b, and the outlet of the ram turbine assembly 1 is connected to the cooling air inlet 2a. If external air is directly guided into the generator assembly 2 for heat dissipation, due to the high speed of the aircraft, the air moving at high speed relative to the aircraft decelerates rapidly and is compressed, converting its enormous kinetic energy into internal energy, leading to a temperature increase and severely affecting the heat dissipation efficiency of the generator assembly 2. This invention connects the outlet of the ram turbine assembly 1 to the cooling air inlet 2a. The air passing through the ram turbine assembly 1 expands in volume and decreases in temperature before being guided into the generator assembly 2 for heat dissipation. The lower temperature of the air used for heat dissipation effectively improves the heat dissipation efficiency of the generator assembly 2. Furthermore, this heat dissipation method only requires the arrangement of ducts to guide airflow; these ducts can even utilize existing aircraft casings, shells, or other structural elements. Only minimal structural and weight additions are needed to meet the heat dissipation requirements. Compared to a separate cooling component, the solution of this application significantly reduces the weight of the generator, meeting the requirements of miniaturization and lightweight design.

[0020] In some embodiments, the generator assembly 2 includes a housing 21, a stator 22, and a rotor 23. The housing 21 has a cooling air inlet 2a and a cooling air outlet 2b. The stator 22 is fixedly disposed within the housing 21, and the rotor 23 passes through the stator 22 and is rotatably connected to the housing 21. One end of the rotor 23 extends outside the housing 21 and is fixedly connected to the ramjet turbine assembly 1. When the ramjet turbine assembly 1 rotates, it can drive the rotor 23 to rotate together to generate electricity.

[0021] Based on the above embodiment, a cooling channel is formed inside the housing 21, surrounding the stator 22 and the rotor 23, and the cooling channel is connected to the cooling air inlet 2a and the cooling air outlet 2b.

[0022] Based on the above embodiment, the housing 21 has multiple cooling air inlets 2a, which are arranged circumferentially around the rotor 23, and the cooling air outlet 2b is located on the side of the housing 21 away from the ramjet turbine assembly 1.

[0023] In a preferred embodiment, by providing a partition or other structure inside the housing 21, the flow direction of the low-temperature air is controlled, so that the low-temperature air follows the... Figure 2 In this manner, after entering the cooling inlet 2a, it first moves against the stator 22 towards the direction of the ramjet turbine assembly 1. Then, it moves around the stator 22, between the stator 22 and the rotor 23, towards the direction of the direction away from the ramjet turbine assembly 1, until it is discharged from the cooling outlet 2b.

[0024] This design allows for a larger contact area between the low-temperature air and the stator 22 and rotor 23, enabling the low-temperature air to fully absorb the heat generated by the stator 22 and rotor 23 and improve heat dissipation performance.

[0025] In some embodiments, the generator assembly 2 further includes an air suspension bearing 24, through which the rotor 23 is rotatably connected to the housing 21. The air suspension bearing 24 is a precision support component that utilizes a high-pressure air film to achieve non-mechanical contact. Its core principle is to form a stable air film between the shaft and the bearing through external air supply, completely "suspending" the rotor and fundamentally eliminating friction and wear between solids. Because the viscosity of gas (usually air) is much lower than that of liquid, it can achieve extremely high speeds, extremely low power consumption, and micron-level motion precision, and it operates without relying on lubricating oil, possessing clean and pollution-free characteristics. This type of bearing is mainly used in high-precision, high-speed equipment such as high-speed electric spindles, precision machine tools, turbomachinery, and gyroscopes in the aerospace field.

[0026] Since the rotor 23 rotates at tens of thousands of revolutions per minute, if traditional ball bearings were used, cooling and lubrication would be necessary to ensure continuous and reliable operation of the rotor 23. This additional cooling and lubrication system would increase the weight of the aircraft. However, by using air-bearing bearings 24, which utilize air lubrication, no additional cooling and lubrication assembly is required, effectively reducing the overall weight of the generator and bearing losses, thus meeting the development trend of lightweight and high-efficiency ramjet generators.

[0027] Based on the above embodiment, the air suspension bearing 24 includes a radial dynamic pressure air bearing 241 and a stop-thrust pressure air bearing 242. The rotor 23 is located at both ends of the stator 22 and is connected to the housing 21 via the radial dynamic pressure air bearing 241. The farthest end of the rotor 23 from the ramjet turbine assembly 1 is also connected to the housing 21 via the stop-thrust pressure air bearing 242.

[0028] The radial hydrodynamic air bearing 241 is a non-contact support element that utilizes the rotor's own rotation to "wedge" and compress gas, thereby generating a hydrodynamic effect. Its internal surface is typically machined with specially designed herringbone or helical grooves. When the rotor rotates at high speed, these micro-grooves draw surrounding air towards the wedge-shaped region, creating a rigid air film that stably suspends the journal within the bearing sleeve, eliminating the need for an external air source. Due to its compact structure, extremely high rotational speed, and minimal frictional loss, this type of bearing is widely used in rotating machinery such as high-speed electric spindles, air circulators, and micro gas turbines.

[0029] The thrust-type air bearing 242 is specifically designed to withstand axial loads. Its working principle is similar to that of the radial type, relying on the micro-groove structure on the relatively moving surfaces to generate a dynamic pressure air film during high-speed rotation. Typically, a grooved thrust disc mates with a stationary bearing surface. When the rotor rotates at high speed, gas is drawn into the wedge-shaped gap to form a high-pressure zone, thereby balancing the rotor's axial thrust and achieving non-contact operation. It can withstand large axial forces and features high precision and long service life, commonly found in critical equipment requiring axial positioning, such as aero engines, turboexpanders, and large high-speed compressors.

[0030] In some embodiments, the ramjet generator further includes an air intake device 3, which connects to the aforementioned bleed air damper and the ramjet turbine assembly 1, for guiding ramjet air to the ramjet turbine assembly 1. The air intake device 3 is a channel structure for guiding the movement of ramjet air; it can be a separate duct or a duct formed together with the aircraft casing. This application does not limit the specific structural form of the air intake device 3, as long as it can achieve the function of guiding ramjet air to the ramjet turbine assembly 1.

[0031] Based on the above embodiments, the ramjet turbine generator also includes a flow regulating device 4, which is disposed on the air intake device 3 to regulate the airflow through the air intake device 3. The flow regulating device 4 can be a valve structure, a baffle structure, or other structures. This application does not limit the specific structural form of the flow regulating device 4, as long as the flow regulating device 4 can regulate the air intake of the ramjet turbine assembly 1 to ensure that the generator assembly 2 can stably provide the rated power required by each electrical appliance in the system under different operating conditions.

[0032] In some embodiments, the ramjet generator further includes a compressor 5, the inlet of which is connected to a cooling outlet 2b for drawing air from the generator assembly 2. The compressor 5 is a component that uses high-speed rotating blades to perform work on the gas to increase its pressure. Compressors can be broadly classified into centrifugal and axial-flow types; those combining characteristics of both are called hybrid compressors. A centrifugal compressor consists of a guide vane, impeller, diffuser, etc. Air enters the compressor through the inlet duct, is guided by the guide vane rotating with the impeller, and then enters the impeller. Under the action of the high-speed rotating impeller, the air is thrown from the center of the impeller to the outer edge by centrifugal force, and the pressure gradually increases. The air flowing out of the impeller enters the diffuser, where its velocity decreases, and its pressure increases again, finally flowing out of the compressor through the outlet pipe. An axial-flow compressor consists of a rotor and a stator. A single stage consists of a row of rotor blades and a row of stator blades. The pressure ratio of a single stage is very small; to obtain a higher pressure ratio, a multi-stage structure is generally used. As air is pressurized in the compressor, its density and temperature increase step by step.

[0033] As the air volume expands, its temperature and pressure decrease due to the ram turbine assembly 1, and its flow velocity slows down, the airflow through the generator assembly 2 experiences greater resistance, especially given the winding and tortuous cooling channels within the generator assembly 2. By installing a compressor 5 to draw air from within the generator assembly 2, the airflow velocity is increased, thereby enhancing the heat dissipation capacity of the generator assembly 2.

[0034] Based on the above embodiments, the ramjet turbine generator also includes an exhaust device 6, which is connected to the outlet of the compressor 5. The exhaust device 6 is a channel structure for guiding gas out, and can be a separate pipe or a pipe formed together with the aircraft casing. This application does not limit the specific structural form of the exhaust device 6, as long as it can achieve the function of guiding gas out. Furthermore, the cross-sectional area of ​​the exhaust device 6 must be larger than the cross-sectional area of ​​the intake device 3 to meet the exhaust requirements.

[0035] To better understand this invention, the following is combined with... Figures 1 to 2 The technical solution of the present invention will be described in detail below: exist Figure 1 In the image, we can clearly see the overall layout of the ramjet generator. The intake device 3 is connected to the bleed air damper. When the aircraft receives a working command, the bleed air damper opens, and the ramjet air enters the ramjet turbine assembly 1 along the intake device 3. The design of the intake device 3 fully considers aerodynamic principles; its smooth inner wall effectively reduces airflow resistance, ensuring that the ramjet air smoothly reaches the ramjet turbine assembly 1.

[0036] The flow regulating device 4 is installed on the air intake device 3. When the aircraft is in different flight conditions, the flow regulating device 4 will precisely adjust the airflow entering the ramjet turbine assembly 1 according to actual needs. For example, when the power consumption increases, the flow regulating device 4 will appropriately increase the air intake in order to allow the generator assembly 2 to output more power; while when the power consumption decreases, it will reduce the air intake in order to save energy and ensure that the generator assembly 2 stably outputs the rated power.

[0037] The ramjet turbine assembly 1 begins to rotate at high speed under the impingement of ram air, and the shaft work generated by its rotation is transmitted to the generator assembly 2 through its connection with the rotor 23. The housing 21 in the generator assembly 2 serves to protect and support the stator 22 and the rotor 23, and is also an important channel for the flow of cooling air. Multiple cooling air inlets 2a are evenly arranged around the rotor 23, allowing low-temperature air to enter the cooling channels within the housing 21 uniformly.

[0038] The air suspension bearing 24 plays a crucial role in the efficient operation of the generator assembly 2. The radial dynamic pressure air bearing 241 and the anti-push pressure air bearing 242 work together to provide stable support for the high-speed rotating rotor 23. The radial dynamic pressure air bearing 241 uses the rotation of the rotor 23 itself to generate a dynamic pressure air film, which stably suspends the rotor 23 in the bearing sleeve, greatly reducing friction loss; the anti-push pressure air bearing 242 effectively bears the axial load of the rotor 23, ensuring the axial stability of the rotor 23 when rotating at high speed.

[0039] After passing through the ramjet turbine assembly 1, the air cools and expands, entering the cooling inlet 2a of the generator assembly 2 from the outlet of the ramjet turbine assembly 1. Within the cooling channels inside the housing 21, the low-temperature air flows along a pre-designed path. It first moves close to the stator 22 towards the ramjet turbine assembly 1, fully absorbing the heat generated by the stator 22; then it bypasses the stator 22, moving between the stator 22 and the rotor 23 towards the distance from the ramjet turbine assembly 1, continuing to absorb the heat generated by the stator 22 and rotor 23, and finally exits from the cooling outlet 2b.

[0040] The air inlet of compressor 5 is connected to the cooling outlet 2b, which acts like a powerful "suction pump". As the air velocity slows down after passing through generator assembly 2 and there is a certain resistance in the cooling channel, compressor 5 performs work on the air through high-speed rotating blades, increasing the air velocity and pressure, and quickly extracting the air from generator assembly 2, further improving the heat dissipation capacity of generator assembly 2.

[0041] Finally, the air, pressurized by compressor 5, is discharged through exhaust device 6. The cross-sectional area of ​​exhaust device 6 is larger than that of intake device 3. This is to ensure that the air can be discharged smoothly, avoid pressure buildup inside the generator, and ensure the stable operation of the entire ramjet turbine generator system.

[0042] Through the coordinated operation of the above components, the ramjet turbine generator of the present invention achieves efficient power generation and heat dissipation functions, while meeting the development trend of lightweight and high efficiency, and providing reliable power support for supersonic and hypersonic aircraft. The specific embodiments of the present invention described above do not constitute a limitation on the scope of protection of the present invention. Any other corresponding changes and modifications made in accordance with the technical concept of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A ramjet turbine generator, suitable for ramjet engines, characterized in that, include Stamped turbine assembly; A generator assembly connected to the ramjet turbine assembly, wherein the rotating ramjet turbine assembly can drive the generator assembly to generate electricity; The generator assembly includes a housing, a stator, and a rotor. The stator is fixedly disposed within the housing, and the rotor passes through the stator and is rotatably connected to the housing. One end of the rotor extends outside the housing and is fixedly connected to the ram turbine assembly, enabling it to rotate synchronously with the ram turbine assembly. The housing has multiple cooling air inlets and cooling air outlets. The multiple cooling air inlets are arranged circumferentially around the rotor, and the cooling air outlets are located on the side of the housing away from the ram turbine assembly. Cooling channels are formed inside the housing around the stator and rotor, and the cooling channels connect the cooling air inlets and cooling air outlets. The outlet of the ramjet turbine assembly is connected to the cooling inlet.

2. The ramjet turbine generator according to claim 1, characterized in that, The generator assembly also includes an air bearing, through which the rotor is rotatably connected to the housing.

3. The ramjet turbine generator according to claim 2, characterized in that, The air suspension bearing includes a radial dynamic pressure air bearing and a stop-thrust pressure air bearing. The rotor is located at both ends of the stator and is connected to the housing through the radial dynamic pressure air bearings. The end of the rotor away from the ramjet turbine assembly is also connected to the housing through the stop-thrust pressure air bearing.

4. The ramjet turbine generator according to claim 1, characterized in that, The ramjet generator also includes an air intake device, the outlet of which is connected to the ramjet turbine assembly to guide air to the ramjet turbine assembly.

5. The ramjet turbine generator according to claim 4, characterized in that, The ramjet turbine generator also includes a flow regulating device, which is disposed on the air intake device to regulate the air flow through the air intake device.

6. The ramjet turbine generator according to claim 1, characterized in that, The ramjet turbine generator also includes a compressor, the air inlet of which is connected to the cooling outlet.

7. The ramjet turbine generator according to claim 6, characterized in that, The ramjet turbine generator also includes an exhaust device connected to the outlet of the compressor.

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