Quantum modified energy storage microsphere working medium turbofan power system and laser explosion method

Abstract

The invention belongs to the technical field of power systems, and particularly relates to a quantum modified energy storage microsphere working medium turbofan power system and a laser explosion method. Aiming at the pain points of traditional turbofan power fuel oil pollution, low ignition precision and low energy efficiency, quantum modified bio-based solid microspheres with the intrinsic energy density being 7-8 MJ / kg and the diameter being 50 microns serve as a core working medium, and the quantum modified bio-based solid microspheres with the intrinsic energy density being 7-8 MJ / kg and the diameter being 50 microns are subjected to precise high-frequency impact through a 16-path independent VCSEL femtosecond pulse laser array (a VCSEL unit is 100 mW, a subunit is 1.35 W, 16 paths are 472 W, the frequency is 100 Hz, the electro-optical conversion efficiency is larger than or equal to 70%, the pulse width is 100-300 fs, the wavelength is 810 nm, and the focusing power density is 1 * 10 < 9 >-5 * 10 < 9 > W / cm < 2 >); the energy-releasing broken particles, atomized water drops and filtered air form a mixed working medium, and the intelligent control unit and the turbofan mechanism are combined to do work; the power is amplified by 22 times, 1% of the laser power causes a 13N / kW impulse coupling coefficient and 400-1200 s specific impulse, and the system is superior to a fuel oil power system. The technology is novel, low-power input is accumulated into high-power output, carbon emission is low, and the system is suitable for low-altitude economic traffic and high in popularization value.

Description

Technical Field

[0001] This invention relates to the fields of power system engineering, quantum-modified bio-based materials, and VCSEL femtosecond pulsed laser technology. Specifically, it relates to a quantum-modified energy storage microsphere working propellant turbofan power system and a laser detonation method. The VCSEL femtosecond pulsed laser array precisely detonates the microsphere working propellant, forming a three-phase working propellant system with injected atomized water droplets and compressed air, and possessing a synergistic expansion mechanism. This novel turbofan power system is suitable for medium- and long-range high-speed flying cars and low-altitude aircraft, as well as equipment manufacturing fields requiring low-carbon emissions and green power sources. Background Technology

[0002] Turbofan engines, as the mainstream power plant in the aviation field, are widely used in various aircraft such as mainline passenger planes and military fighter jets due to their core advantages of high thrust and low fuel consumption. Their core working principle involves compressing air through a fan and compressor, dividing it into inner and outer bypass ducts. The inner bypass duct air is burned in the combustion chamber, driving the turbine to rotate, which in turn drives the fan and compressor, ultimately generating thrust through high-speed airflow ejection. Currently, the research and development technology of mainstream turbofan engines is relatively mature, but two major technological bottlenecks remain: first, limited by the physical limits of traditional fuel-fired heat engine cycles, energy conversion efficiency is difficult to exceed 40%, limiting the potential for thrust improvement; second, reliance on fossil fuels as an energy source results in high carbon emissions, which does not align with the global trend of "carbon reduction and emission reduction" in the aviation industry, and the complex fuel storage and refueling systems restrict the aircraft's range and lightweight design. Furthermore, existing turbofan power systems all employ a single energy input mode, making them unable to adapt to the integrated requirements of new clean energy power sources, posing a significant challenge to technological upgrades. In addition, turbofan engines that use environmentally friendly fuels such as hydrogen fuel and biomass fuel have had many bottleneck problems in fuel manufacturing and application scenarios that have not been solved for nearly 60 years, which has also limited their mainstream application.

[0003] Since the advent of lasers in the 1960s, research institutions around the world have gradually explored related technologies, with laser propulsion being one of the important applications. In 1972, American scholars first proposed the concept of laser propulsion, laying the theoretical foundation for this technological field. After the 1990s, the United States, Germany, Russia, Japan, and other countries successively completed ground experiments on laser plasma propulsion, initially verifying the feasibility of converting laser energy into thrust. In recent years, Harbin Institute of Technology has developed underwater fiber laser-induced plasma detonation wave propulsion technology, as evidenced by the joint publication by Harbin Institute of Technology and Harbin Aircraft Industry Group on underwater… The academic paper on laser propulsion, "Performance Study of Short Microcavity Structure for Underwater Fiber Nanosecond Laser Propulsion," analyzes that by optimizing the laser focusing structure and plasma confinement method (forming directional detonation waves through dual-tube short microcavity technology), the impulse coupling coefficient of solid-state microspheres in underwater scenarios has been improved to 3.4 N / kW, achieving a preliminary exploration of laser propulsion for underwater equipment. However, this technology is mainly suitable for low-speed underwater navigation scenarios, and its directional control accuracy and energy conversion efficiency of plasma detonation waves still cannot meet the core requirements of "high speed, stability, and continuous thrust" for aero-engine turbofan propulsion systems, and it has not yet achieved integration and adaptation with turbofan propulsion structures.

[0004] Laser plasma physics propulsion technology is one of the important application styles of laser propulsion system technology. As pointed out in monographs such as "Laser Plasma Propulsion Technology", "Laser-Supported Detonation Wave", "Introduction to Air-breathing Pulsed Laser Propulsion", "Ablation Mode Laser Propulsion", and CN102230456B "Atmospheric Breathing Laser Engine Device" and application number 201110169276 "Method for Manufacturing Atmospheric Breathing Laser Engine Device", its core principle is to directly ablate the working medium (gas, liquid, solid or mixture) with a single high-power laser, so that it instantly forms a high-temperature and high-pressure plasma. The plasma expands rapidly to generate a detonation wave, which is then converted into thrust output to form the kinetic energy of the carrier. This technology breaks the energy limitation of traditional chemical propulsion and has significant advantages of high specific impulse and low pollution. However, it is still the traditional mode of "high-power power output requires high-power laser energy input", and the high-power input limits practical applications.

[0005] The working fluid, as the core carrier of energy transfer in a power system, directly determines the energy conversion efficiency of the power system. Existing laser propulsion systems mostly employ single-phase or dual-phase working fluids (gas, liquid, or gas-liquid dual-phase). As pointed out in the monograph "Performance of Atomized Water Droplet Laser Propulsion," the invention patent CN103291498B "A Laser Propulsion Device and Method Based on the Principle of Laser-Induced Water Droplet Breakdown" (specific impulse approximately 700s), and the master's thesis "Numerical Simulation and Experimental Exploration of Laser-Supported Detonation Waves in Gas-Liquid Two-Phase Working Fluids," single-phase gas working fluids have a large breakdown threshold and require high-performance lasers. Although they have a large specific impulse, their impulse coupling coefficient is small (achieving a specific impulse of approximately 100-700s, an impulse coupling coefficient of approximately 0.52N / kW, and an energy conversion efficiency of approximately 26%), resulting in problems such as low energy storage density, unstable phase transition processes, and large thrust output fluctuations. While the breakdown threshold of gas-liquid two-phase working fluids can be reduced by reasonably designing laser parameters and the liquid phase ratio, the energy density of gas-liquid two-phase working fluids differs significantly from that of fossil fuels, rendering them completely impractical.

[0006] If a solid working material is added to the liquid-gas two-phase working fluid to form a solid-liquid-gas three-phase synergistic working fluid system, the problem of low energy storage density in the liquid-gas two-phase working fluid can be solved. This is achieved by using quantum modification technology to endow the solid working fluid material with a certain intrinsic energy density, which can simultaneously improve the specific impulse and impulse coupling coefficient. As clearly pointed out on page 48, lines 24-26 of the monograph "Laser Plasma Propulsion Technology," the ideal working fluid material for laser propulsion should be a composite material with at least six advantages: high specific impulse, high coupling coefficient, easy storage, easy processing, low cost, and no pollution. The aforementioned composite material integrates the advantages of each of these materials. Preliminary explorations have been conducted in energy storage and combustion fields, but it has not yet been applied to turbofan propulsion systems, and there is a lack of three-phase working fluid formulation design and dynamic control technology for laser ablation scenarios. This invention relates to the comprehensive effect of the solid-liquid three-phase working fluid, the femtosecond pulse laser effect, and conventional parameters of laser propulsion; the laser-broken microsphere impulse coupling coefficient is 13 N / kW, and the specific impulse is 400–1200 s.

[0007] Traditional turbofan engines rely on the combustion of fossil fuels for power generation, resulting in technical drawbacks such as high carbon emissions, low energy conversion efficiency, and sluggish ignition system response, making them unable to meet the development needs of new energy power equipment. Existing electric ignition technologies for new power systems are mainly divided into two categories: electric spark ignition and plasma ignition, but both have shortcomings: electric spark ignition has an energy utilization rate of less than 30%, low ignition accuracy, and is easily affected by combustion chamber pressure; plasma ignition devices are large in size and have high energy consumption, making them difficult to adapt to miniaturized vehicle layouts.

[0008] Laser detonator technology, due to its non-contact triggering and precise energy control, has become an important direction for replacing traditional ignition methods. However, conventional continuous laser or nanosecond laser ignition still suffers from problems such as high energy threshold, poor focusing effect, and inability to accurately trigger the release of energy from energy storage materials. VCSEL (Vertical-Cavity Surface-Emitting Laser) femtosecond pulsed laser technology offers advantages such as electro-optical conversion efficiency >70%, narrow pulse width (200–500 fs), and high focusing power density (up to 1 × 10⁻⁶). 9 ~5×10 9 W / cm 2 With its core advantages such as fast response speed and low energy consumption, VCSEL offers a new solution to the aforementioned problems. It can precisely focus on tiny targets within femtosecond timeframes, achieving efficient fragmentation and high-frequency energy accumulation of quantum-modified energy storage microspheres. Furthermore, the power of a single laser is only 100W, making it easy to integrate into arrays. However, current VCSEL femtosecond pulsed laser technology is mostly applied in precision machining and biomedicine, and has not yet been integrated with quantum-modified energy storage solid-state microsphere materials and piston power systems. It lacks key technical solutions for automotive power scenarios, such as laser parameter matching and co-expansion of the working fluid, thus failing to fully realize the technological potential of low-energy laser triggering and high-efficiency energy release from solid-state working fluids.

[0009] Existing bio-based solid microsphere materials without quantum modification cannot be directly used as working fluids and lack the VCSEL femtosecond pulse laser precision fragmentation-high-frequency cumulative energy release technology. While VCSEL lasers offer advantages such as small size and controllable frequency, they have not yet been combined with quantum-modified solid microsphere working fluids to form a new power architecture of "laser fragmentation of microspheres - efficient energy release from micron-sized particles." Meanwhile, traditional gasoline vehicles suffer from limited fuel tank capacity, short range, and frequent maintenance, making it difficult to meet the demands of long-range travel. The low-altitude economy, as a key development area, urgently requires long-range, low-carbon, or even zero-carbon, low-cost power systems, which traditional power solutions are ill-suited for. Against this backdrop, developing a novel turbofan power system using 50μm quantum-modified bio-based solid microspheres as the working fluid material, achieving compatibility with traditional fuel-powered systems and adapting to medium- and long-range high-speed flying vehicle scenarios in the low-altitude economy, has become a key breakthrough for the industry.

[0010] Traditional electric igniters are fixed in their placement and number. If any ignition point fails, it can easily cause partial or even complete system failure. Furthermore, they cannot be expanded in capacity according to the power requirements of actual working conditions, resulting in significant deficiencies in adaptability and fault tolerance under complex working conditions. Moreover, if traditional single-channel lasers are used, they will be bulky, have an electro-optical conversion efficiency of only about 26%, and suffer from serious thermal management problems. In addition, high power inevitably requires high intrinsic energy density working fluid materials.

[0011] In contrast, the laser ignition array structure of the quantum-modified bio-based solid microsphere working propellant turbofan power system described in this invention, with its technical advantages of ignition stabilization and omnidirectional capacity expansion, achieves precise and stable control of the laser ignition process, rapid replacement of faulty points, and flexible capacity expansion of the system through a coordinated layout of 4 radial cross-shaped layout / 8-12 axial ring layout working positions and 4 redundant expansion positions. Each working position is uniformly equipped with a VCSEL femtosecond pulse laser with a rated power of 150W and a working frequency of 100Hz. This effectively overcomes the limitations of traditional electric ignition. Overcoming the inherent technical limitations of traditional single-channel lasers, the VCSEL femtosecond pulsed laser detonator uses high-frequency impact on quantum-modified bio-based solid microspheres with low intrinsic energy density (7-8 MJ / kg) to amplify power by 22 times. This changes the traditional model where high-power output requires energy storage materials with "high intrinsic energy density" (such as diesel and gasoline, approximately 43-45 MJ / kg). By synchronously and at the same frequency injecting a large quantity of quantum-modified bio-based solid microspheres into the cylinder and accumulating high-frequency energy release, high-power continuous output can be guaranteed on a macroscopic scale.

[0012] The aforementioned VCSEL femtosecond pulsed laser, with its quantum state modulation characteristics, can achieve higher power density and more stable laser output. Compared with traditional lasers, its electro-optical conversion efficiency is significantly improved, its size and weight are significantly reduced, and its beam quality and controllability have significant advantages, providing core support for the performance upgrade of laser propulsion systems. Currently, vertical cavity laser arrays have achieved initial applications in quantum communication, precision measurement, and quantum gyroscopes, but their application in the field of aerospace propulsion is still in its infancy. On the one hand, due to the limitations of traditional laser propulsion system technologies, they cannot be adapted to the limited installation space and complex operating conditions of aircraft. On the other hand, there is no technology that can systematically integrate the high-efficiency electro-optical output characteristics of vertical cavity laser arrays with laser plasma power conversion and turbofan propulsion structures, resulting in the inability to effectively convert the high electro-optical conversion rate advantage of vertical cavity laser arrays into aerospace turbofan thrust.

[0013] Based on this, the present invention combines a VCSEL femtosecond pulsed laser array, a factory-prefabricated quantum-modified bio-based energy storage solid microsphere, and the aforementioned solid-liquid-gas three-phase working fluid synergistic expansion mechanism to construct a novel turbofan power system, breaking through the bottleneck of traditional power technology and achieving low energy consumption, multiple power amplification, and green low-carbon emission power output. Summary of the Invention

[0014] This invention provides a quantum-modified energy storage microsphere working fluid turbofan power system and a laser ignition method. The core of this system lies in constructing a cyclical, synergistic technology system of "quantum-modified energy storage microspheres and liquid-gas mixed three-phase working fluid material input - 12-16 femtosecond pulsed laser directional ignition - turbofan power enhancement output." The system comprises a series of laser igniter array modules, a laser-supported plasma power conversion module, a turbofan power enhancement output module, and a three-phase working fluid material storage and input module (air is drawn in and compressed, microfluidic water storage unit atomizes water droplets and injects, solid microsphere storage and supply unit microfluidic injection). The system comprises seven core components: a virtual and physical power supply module, a multi-dimensional energy recovery module, and an intelligent collaborative control module. These modules achieve dynamic linkage through the intelligent collaborative control module, deeply integrating the high electro-optical conversion efficiency of lasers, the excellent mass / heat transfer characteristics and efficient power conversion characteristics of laser-directed plasma detonation wave impacting the three-phase working fluid, the enhanced output characteristics of turbofan power, the efficient energy storage and scheduling characteristics of virtual and physical power storage, and the recycling characteristics of multi-dimensional energy recovery. This breakthrough overcomes the technical bottlenecks of traditional turbofan power and laser power, achieving low-energy consumption, stable and continuous power output with small energy accumulation and high power.

[0015] The laser detonator array module series comprises a cross-shaped array module and a ring-shaped array module. The cross-shaped array module (installed at the front of the detonation tube) includes 4 laser detonators, and the ring-shaped array module (installed at the front end of the detonation tube) includes m laser detonators. The cross-shaped and ring-shaped array modules are arranged separately at the front and rear, totaling 4+m laser detonators (m = 4 / 6 / 8 / 12 as needed, usually m < 24). Each laser detonator includes n 10W... The system includes VCSELs (electro-optical conversion efficiency 74-88%), optical focusing devices (shaping lenses and convex lenses), fiber optic focusing devices (tapered optical fibers), directional dual-tube short microcavities (diameter 20μm, wall thickness 2μm, length 100μm), heat managers, thermoelectric converters, etc.; each unit VCSEL in the n VCSEL laser array has a power of 10W, and n is chosen as needed to be 2 / 4 / 6 / 12 / 14 / 16, usually <20. In this invention, n=19, including 15 working positions and 4 backup redundant positions.

[0016] The VCSEL vertical-cavity laser array described is a semiconductor laser utilizing quantum well technology. In 2024, Professor Wang Jun's team from Sichuan University and Suzhou Changguang Huaxin Optoelectronics Co., Ltd. published an English paper titled "Multi-junction cascaded vertical-cavity surface-emitting laser with a high power conversion efficiency of 74%" in *Light: Science & Applications* (impact factor 19.4, ranked among the top 3 optics journals worldwide), indicating that simulation results showed that a 20-junction VCSEL could achieve an energy conversion efficiency of over 88% at room temperature. Experiments showed that, driven by nanosecond pulses, a 15-junction VCSEL could achieve an energy conversion efficiency of up to 74% at room temperature, with a corresponding differential quantum efficiency exceeding 1100% (one electron converts into 11 photons in 11 quantum wells). To the authors' knowledge, this is the most efficient VCSEL device to date. Simultaneously, this differential quantum efficiency is also a world record in the field of semiconductor lasers. These world-leading achievements are the key basis for the application of VCSEL lasers in this invention.

[0017] The combined rated output power of the cross-shaped array module and the ring array module of the laser detonator is 1.8kW to 2.4kW (typically chosen, but determined according to overall needs). Each laser detonator outputs a femtosecond pulse laser from the tapered fiber (with a much higher efficiency in working fluid dissociation and energy conversion than nanosecond pulse lasers), with a pulse width of 100–300 fs, a frequency of 100 Hz, a wavelength of 800–810 nm, and a power density of 8 × 10⁻⁶. 10 ~1×10 11 W / cm 2 The laser beam with the above wavelength and pulse width has a spot diameter of 50 μm (area approximately 1.96 × 10⁻⁶). -6 cm 2 Beam quality factor M 2 The power control unit can achieve continuous power adjustment from 0% to 100%, with a dual-tube short microcavity laser transmission efficiency of ≥99% and a directional accuracy of ≤±0.5°. The average power of each laser detonator is approximately 0.3–30 μW, and the peak power is approximately 3.75 × 10⁻⁶. 12-13W, simultaneously adaptable to the operational requirements of three working fluids. Each laser detonator in its laser detonator array module series is activated under the command of the intelligent collaborative control module. Power is supplied by the virtual and physical electric chamber energy supply module to generate a high-power-density femtosecond pulse laser (a composite laser beam from the n VCSEL unit laser arrays). The laser is focused by the shaping lens and convex lens, then converged by the tapered optical fiber, and then emitted as a directional plasma detonation wave through a dual-tube short microcavity. This wave precisely impacts the three-phase mixed working fluid, which is then powered by the laser-supported plasma power conversion module and the turbofan power enhancement output module. At the same time, the power control unit dynamically adjusts the laser output power according to the thrust requirements.

[0018] The synthesized laser beam from the n VCSEL laser arrays, after passing through a tapered fiber, enters a dual-tube short microcavity and emits a directional plasma detonation wave. This is far superior to the direct ablation of solid, liquid, and gaseous working fluids by the laser, improving the laser coupling efficiency. The tapered fiber can achieve efficient coupling with the short microcavity, meaning more laser energy can enter the microcavity and be effectively utilized, resulting in a relatively higher laser intensity emitted from the microcavity, which has a more significant effect when acting on mixed working fluids. It also enhances the localization of the optical field; after coupling the tapered fiber with the short microcavity, the optical field is highly localized, and the short microcavity has a high quality factor. The smaller mode volume allows the laser to form a strong local electric field within the cavity. When the laser is emitted from the microcavity, its energy concentration is higher, enabling it to interact more effectively with the working fluid when illuminating it. This can more efficiently excite the optical properties of atomized water droplets or trigger chemical reactions in the air working fluid. The laser mode can be optimized; the tapered fiber can screen and control the laser mode. When combined with the short microcavity, the output laser mode can be further optimized. The optimized laser mode has better beam quality and stability, enabling more precise achievement of the desired effect when illuminating droplets or air-mixed working fluids.

[0019] Drawing upon the monograph "Laser Plasma Propulsion Technology," the academic paper "Performance Study of Short Microcavity Structure for Underwater Fiber Optic Nanosecond Laser Propulsion," and the dissertation "Numerical Simulation and Experimental Exploration of Laser-Supported Detonation Waves in Gas-Liquid Two-Phase Working Fluids," it is found that using femtosecond pulsed lasers to irradiate multiphase composite working fluids results in a low gas-liquid two-phase breakdown threshold and a higher impulse coupling coefficient. In particular, by referencing the application of underwater fiber lasers passing through a "dual-tube short microcavity" for directional detonation wave ablation and breakdown of solid microspheres, the impulse coupling coefficient can be increased by 10. 3The magnitude and impulse coupling coefficient can reach 340 dyne / W (3.4 N / kW); the above-mentioned transfer from seawater to air, the laser supports the directional detonation wave of compressed air and atomized water droplets as a two-phase working medium through a dual-tube short microcavity to ablate and penetrate the solid microsphere, the overall estimated impulse coupling coefficient of the present invention is close to 3.4 N / kW; considering the drag reduction of the carrier by about 50% through multiple measures, its impulse coupling coefficient and specific impulse will increase by about 50% accordingly; the combination of solid microsphere + atomized water droplets + high-pressure air three-phase working medium with dual-tube short microcavity directional detonation technology can achieve a propulsion efficiency of >70% for photoelectric conversion to mechanical power; the total energy conversion efficiency of the system is about 52-62%, which is higher than the current energy conversion efficiency of gasoline turbofan aero engines of 35-50%, and its relative improvement is >23-48%.

[0020] The laser-supported plasma power conversion module comprises: a plasma generating cavity (within the space of the dual-tube short microcavity and the detonation tube described below), a detonation wave confinement device (the detonation tube described below), an energy conduction channel (the turbine, tail nozzle, and inner and outer bypass ducts described below), and a temperature monitoring unit. The plasma generating cavity is made of high-temperature resistant ceramic material, with an anti-oxidation coating on the inner wall. The detonation wave confinement device adopts an annular cylindrical structure. The energy conduction channel is connected to the turbofan power output module and the three-phase working fluid storage and control module. The cavity is equipped with a compressed air inlet and injection ports for atomized water droplets and solid microspheres as working fluid, as well as an outlet for the dual-tube short microcavity. After the three-phase working fluid, composed of compressed air, atomized water droplets, and solid microspheres, is injected into the plasma generating cavity, the laser emitted by its 12-16 laser detonators passes through the directional structure of the dual-tube short microcavity and ablates the liquid-gas mixture working fluid inside the cavity. Instantly, the impact coupling generates a high temperature (10℃). 4 ~10 5 K) High-pressure (10-100MPa) plasma clusters rapidly expand to generate directional detonation waves. These directional detonation waves impact the solid microspheres injected into the plasma generation cavity, causing them to release their inherent high-density chemical energy. Most of this energy is transferred to the turbofan power output module through the energy conduction channel and converted into thrust. A small portion of the energy is transferred to the working fluid storage and control module to drive the recycling of the working fluid.

[0021] The turbofan power enhancement output module comprises: a compressor (fan and low- and high-pressure compressors), a turbine, an inner duct, an outer bypass duct, and a thrust monitoring unit. The fan adopts a wide-chord hollow blade structure, the compressor adopts an axial-centrifugal combined structure, the turbine and compressor are manufactured using an integrated forging process, and the inner and outer bypass ducts adopt a streamlined design to optimize airflow characteristics. The compressor outlet is connected to the air inlet of the plasma generation chamber. The fan rotates to draw in outside air, which is compressed to a high pressure (0.5–1.0 MPa) by the compressor and then delivered to the plasma generation chamber as the gaseous component of the three-phase working fluid. The laser-supported plasma detonation wave is transmitted to the turbofan power output module, driving the turbine to rotate at high speed, which in turn drives the fan and compressor to operate continuously. The airflow in the outer bypass duct is compressed by the fan and directly injected to generate thrust. The airflow in the inner duct mixes with the high-temperature, high-pressure gas generated by the detonation wave and is then injected at high speed through the turbine and tail nozzle to generate thrust. The thrust monitoring unit collects thrust data in real time and feeds it back to the intelligent collaborative control module to dynamically adjust the working status of each module to ensure stable thrust output.

[0022] The three-phase working fluid storage and control module has a working fluid material composition of a solid-liquid-gas three-phase synergistic energetic working fluid system consisting of "high-energy solid microspheres + atomized water droplets + compressed air". The solid microspheres are designed with a two-layer core-shell structure. Both the composite shell material and the mixed inner core material are bio-based energy storage materials. The selected shell-core material is environmentally friendly, highly safe, medium-energy, and highly adaptable. The core diameter is 35μm, the sphere diameter is 50μm, and the outer shell thickness is 15μm (it can be precisely controlled to break upon impact, and the fragment particle size is >10μm). The intrinsic energy density of the solid microsphere working fluid material after quantum modification reaches 7-8MJ / kg.

[0023] The atomized water droplets have a particle size of 5–20 μm. The inhaled air is compressed into a high-pressure, high-temperature axial airflow. The mass ratio of the solid-liquid-gas working fluid is 1:0.6:23, the percentage is 6%:4%:90%, and the energy contribution rate is 90%:4%:6%. The solid microspheres are the core energy source, with a total energy contribution rate of approximately 99%, providing microsphere materials with medium energy density (7–8 MJ / kg, thermal efficiency 40–48%, and chemical energy to thrust efficiency 70–77%). The atomized water droplets act as a buffer for temperature control and serve as a raw material for hydrogen production. Their vaporization expansion physical energy can improve energy conversion efficiency (with a total energy contribution rate of approximately 4%). The compressed air is an oxidant and energy carrier, providing oxygen (oxygen concentration 21–40%) to support combustion within the microsphere core. The combined energy density released after coupling laser energy with the three-phase working fluid is approximately 80–120% (secondary decomposition of bio-based energetic materials).

[0024] The three-phase working fluids flow into or are injected into the plasma generating chamber (annular detonation tube), while compressed air flows in directly. Atomized water droplets are injected using an ultrasonic atomizer, and solid microspheres are precisely delivered and injected via a delivery pump. A three-phase working fluid component monitoring unit is configured, and the solid and liquid two-phase working fluid storage unit adopts a double-layer insulation structure. The solid microspheres, atomized water droplets, and compressed air are controlled by an intelligent collaborative module to flow into and inject into the plasma generating chamber, forming a mixed three-phase working fluid system. After the three-phase working fluid is continuously injected into the plasma generating chamber, its flow rate is dynamically adjusted (50-200 L / h) according to the laser power and thrust requirements. The component monitoring unit monitors the working fluid mixing ratio in real time and feeds it back to the intelligent collaborative control module to ensure the stability of the working fluid composition. The frequency of the femtosecond pulse laser is matched with the flow rate to ensure that each batch of solid microspheres can be precisely ablated and penetrated by the laser-supported directional plasma detonation wave. Its airflow is controlled by the compressor speed and guide vane angle (reference parameters), and its microsphere supply rate is adjusted according to flight conditions (from 70% of cruise to 150% of takeoff reference value). The atomized water droplet flow rate and the solid microsphere flow rate maintain a fixed ratio of 1:0.6, forming a "atomized water droplet-solid microsphere" synergistic supply system.

[0025] The virtual and physical power supply module comprises a physical power storage unit, a virtual power storage unit, an energy conversion device, and an intelligent scheduling unit. The physical power storage unit includes a power battery (continuous power supply), a supercapacitor (instantaneous power / recovered energy), a flywheel energy storage device (stable medium-to-high frequency power), and a hybrid battery. The power battery (continuous power supply to support range) is an all-solid-state battery pack (energy density ≥ 400Wh / kg) or a metal-air battery (energy density ≥ 700Wh / kg). The supercapacitor is miniaturized (instantaneous power compensation and energy recovery), and the flywheel energy storage device is also miniaturized (dynamic power balance for stability). The hybrid battery is based on isotope batteries. For example, the batteries in BV100 and subsequent products (to compensate for the problems of easy power loss / short lifespan of batteries); the virtual energy storage compartment is an equivalent negative physical energy storage compartment that saves / retains / generates electricity, which can offset the weight requirement of the power battery in the physical energy storage compartment. The virtual energy storage compartment can include the following components: all power-saving, power-retaining, and electricity-generating methods used in its power system and carrier, such as carrier laser plasma drag reduction, carrier energy-saving design, temperature control of composite phase change materials in the carrier space, carrier friction and vibration electricity generation, temperature control of composite phase change materials in the power battery, supercapacitor energy recovery, laser thermoelectric power generation, external bypass duct power efficiency enhancement, and hub motor energy recovery, etc. The above-mentioned virtual energy storage compartments can offset 50% of the weight requirement of solid-state power batteries. The above adopts a distributed energy storage scheduling unit. The energy conversion device includes a rectifier, inverter, and bidirectional DC-DC converter. Its intelligent scheduling unit realizes dynamic scheduling and optimized configuration of energy to avoid energy waste; the energy conversion device realizes the conversion of electrical energy between AC and DC to match the power supply requirements of each module. The use of a virtual and real battery compartment in the embodiments of the present invention means a 50% reduction in the weight requirement of the power battery.

[0026] The multi-dimensional energy recovery and circulation module comprises: an exhaust gas energy recovery device, a braking energy recovery device, and a working fluid waste heat recovery device. The exhaust gas energy recovery device is installed at the turbofan tail nozzle and adopts a waste heat boiler structure. The braking energy recovery device is connected to the turbine shaft and has a built-in electromagnetic induction generator. The working fluid waste heat recovery device is connected in series with the three-phase working fluid circulation pipeline and adopts a plate heat exchanger structure. The exhaust gas energy recovery device captures the waste heat of the exhaust gas from the tail nozzle and converts it into heat energy, which is transferred to the three-phase working fluid storage and control module to preheat the working fluid and reduce phase change energy consumption. When the turbofan decelerates or stops, the braking energy recovery device drives the generator through the turbine shaft to generate electricity, converting mechanical energy into electrical energy and storing it in the physical electric chamber. The working fluid waste heat recovery device recovers the waste heat from the plasma generation chamber and the working fluid circulation pipeline and transfers it to the newly injected working fluid through the heat exchanger, realizing working fluid preheating and energy reuse. The recovered energy is allocated and reintroduced into the physical electric chamber by the intelligent collaborative control module, forming a closed-loop cycle of "energy output-recovery-reuse", further improving the system's energy utilization rate.

[0027] The intelligent collaborative control module comprises a main controller, a sensor group, and a communication module. The main controller uses a high-performance FPGA chip. The sensor group includes thrust sensors, temperature sensors, pressure sensors, electrical quantity sensors, and working fluid composition sensors. The communication module uses a CAN bus communication method. Its core functions include: real-time acquisition of operating parameters (thrust, temperature, pressure, electrical quantity, working fluid composition, etc.) from each module via the sensor group; data processing and analysis by the main controller using an improved PID algorithm; and outputting control commands to each module. It dynamically adjusts the quantum laser output power, the orientation angle of the dual-tube short microcavity, the inflow and injection flow rates of the three-phase working fluid, the detonation wave constraint strength, and the turbofan speed to achieve coordinated and optimized operation of each module. It also has a fault diagnosis function; when a module malfunctions, it quickly switches operating modes to ensure safe and stable system operation.

[0028] The following are further optimizations and improvements to the above-mentioned invention's technical solution.

[0029] This invention improves the traditional fossil fuel turbofan power system architecture by adapting it to a laser detonation method. The system generally consists of a compressor section (including an intake fan), a detonation chamber (modified from the original combustion chamber, with the original internal annular flame tube replaced by an annular detonation tube), a turbine section, and a tailpipe section. The aforementioned laser detonator system is configured in the detonation chamber section, specifically in the front section and end face of the detonation tube. The material and structure of the flame tube are improved to adapt to VCSEL femtosecond pulse laser detonation, thus accommodating the impact of the laser-supported plasma detonation wave on the three-phase working fluid.

[0030] At the front section of the detonation tube, there is one cross-shaped VCSEL femtosecond pulse laser detonator in the radial direction and one circular VCSEL in the axial direction, along with two separate arrays. The cross-shaped array has four laser detonator modules (fixed at the 12 o'clock, 3 o'clock, 6 o'clock, and 9 o'clock positions from the outer wall of the detonation chamber to the outer wall of the detonation tube; each laser detonator radially passes through the shell of the detonation chamber and the front section of the detonation tube, emitting a laser-supported directional plasma detonation wave into the detonation tube; a circular array of m solid microsphere injection nozzles is also arranged radially thereon; two circular arrays are evenly arranged on the axial end face: one array is a VCSEL femtosecond pulse laser detonator module (fixed at various points in a 360°÷m angle on the end face of the detonation chamber; each laser detonator axially passes through the end face of the detonation chamber, emitting a laser-supported directional plasma detonation wave into the detonation tube); the other array arranged axially is an array of N atomized water droplet injection nozzles.

[0031] Therefore, the laser turbofan power structure described in this invention is a spatial arrangement of four arrays: a cross, a circle, and a double ring. A cross-shaped laser detonator array and a solid-state microsphere nozzle circle array are radially arranged at the front section of the detonation tube. An annular laser detonator array and an annular atomizing water droplet nozzle array are axially arranged on the end face of the detonation tube. This constitutes the overall architecture of this invention: a cross-shaped laser detonator array / a circle array of m solid-state microsphere nozzles is installed radially at the front section of the turbofan engine detonation chamber and detonation tube, plus an annular array of m laser detonators / N annular arrays of N atomizing water droplet nozzles installed axially on the end face.

[0032] The solid-liquid two-phase working fluid storage unit with the above-mentioned double-layer heat insulation structure is equipped with a pulse signal transmitter (first and second pulse signal transmitters); in addition, it is also equipped with a pulse signal transmitter (third and fourth pulse signal transmitters) for the above-mentioned cross-shaped and ring-shaped laser detonator arrays; the first pulse signal generator is connected to the second pulse signal generator that controls the preheating microfluidic atomized water droplet storage unit; the third pulse signal generator that controls the ring array laser is connected to the fourth pulse signal generator that controls the microfluidic solid microsphere storage unit, thereby precisely controlling the laser detonator to ablate and impact the solid-liquid-gas mixed working fluid material.

[0033] A quantum-modified energy storage microsphere working propellant turbofan power system and laser ignition method, comprising the following steps:

[0034] (1) Power input: The power of the virtual and real power chambers is input to its laser detonator array module and the following 4 pulse signal generators respectively. The 4+m laser detonators, 1 preheating microfluidic atomized water droplet injection unit, and 1 microfluidic solid microsphere injection unit work together under the intelligent control of the 1st, 2nd, 3rd, and 4th pulse signal generators.

[0035] (2) Laser detonation: Its 4+m laser detonators emit femtosecond pulse lasers, which are directed and focused into the detonation tube below after passing through a dual-tube short microcavity. The lasers instantly ablate and penetrate the solid-liquid three-phase working medium inside the detonation tube, thereby generating plasma detonation waves and reverse thrust to drive the carrier. Because the femtosecond pulse laser has an extremely short pulse duration, it can complete the ablation and penetration before the working medium diffuses, thus avoiding energy waste.

[0036] (3) Circulation and replenishment: At the same time, the working medium of air is drawn in and the working medium of solid microspheres and atomized water droplets is injected for replenishment and circulation, and the solid particles of solid microspheres are recovered with the exhaust gas; after the high temperature working medium is discharged from the tail nozzle, a low pressure zone is formed in the engine, and the external air is drawn in and mixed with the newly injected water droplets and solid microsphere working medium, in preparation for the next femtosecond pulse laser ablation and breakdown, thus completing the above cycle.

[0037] By repeating steps (1)-(3) at a certain frequency, a continuous laser-powered propulsion process can be achieved, providing continuous thrust and take-off force to the platform that provides power support; the frequency of repeating the steps must be less than 100Hz so that the two consecutive operation steps and reactions do not affect each other.

[0038] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0039] (1) Significantly improves electro-optical conversion efficiency. Compared with traditional laser power technology, this invention uses VCSEL vertical cavity laser array technology to improve the electro-optical conversion efficiency from the traditional 26% to 74-88%.

[0040] (2) Significantly reduces laser thermal management. Compared with traditional single-path laser power technology, the present invention uses 12 to 16 independent VCSEL laser detonators in two arrays of "cross-shaped / ring-shaped" to reduce laser thermal management by more than 90%.

[0041] (3) Significantly improves power amplification factor. Compared with traditional laser power technology, high-power mechanical output requires high-power laser input. This invention realizes the conversion of low-power laser input into 22 times high-power mechanical output, and simultaneously improves impulse coupling coefficient and specific impulse.

[0042] (4) Adaptation to existing turbofan power architecture. Based on the existing turbofan engine architecture, this invention directly uses the outer bypass duct architecture and adapts and improves the inner duct combustion chamber / flame tube into a detonation chamber / detonation tube, reducing the laser power requirement, power battery weight requirement, and R&D cost.

[0043] (5) Improved practical feasibility. Compared with simply using a power battery as the power source, the virtual and real battery compartment method of the present invention reduces the power battery weight requirement by 50% and the laser power requirement by 50% (the outer bypass duct contributes 50% of the power), thus increasing the practical feasibility of the present invention. Attached Figure Description

[0044] The main components in the schematic diagram are positioned as follows: viewed from the front of the engine towards the rear, they are divided into left, right, top, and bottom. The specific structure of this application is given in the following figures and embodiments:

[0045] Figure 1 This is a schematic diagram of a laser turbofan power system according to the present invention.

[0046] Figure 2 for Figure 1 A schematic diagram from point A to eye level: m laser detonators and N atomized water droplet injection nozzles form two annular arrays on the end face of the detonation tube; 4 laser detonators form a cross-shaped array at the front of the detonation tube; and m solid microsphere injection nozzles form a circular array at the front of the detonation tube.

[0047] Figure 3 for Figure 2 The diagram shows one of the laser detonators, viewed from point B upwards, which consists of n VCSEL unit lasers and their n total reflection end faces.

[0048] Figure 4 This is a side view of one of the laser detonators, which consists of n VCSEL unit lasers, optical devices (shaping lenses and convex lenses), a focused beam, and tapered optical fibers, dual-tube short microcavities, a heat manager, a thermoelectric converter, etc. (not shown in the figure).

[0049] Figure 5 This diagram illustrates the process of injecting solid microspheres from a microfluidic solid microsphere injection unit into a detonation tube, and the emission of n laser beams from an array of n vertical cavity lasers within a laser detonator. After being focused by a shaping lens and a convex lens, the laser beams are first converged through a tapered optical fiber and then enter a dual-tube short microcavity. This ablates and breaks down the liquid-gas dual-phase working fluid material within the cavity, resulting in a laser-supported directional plasma detonation wave that impacts the precisely injected solid microsphere and generates a force.

[0050] In the picture: SO is the working fluid material for the inhaled air. S1 is the intake compression section, which includes the intake duct, fan, high-pressure compressor, and low-pressure compressor. S2 is the annular detonation chamber section, including the inner and outer walls of the detonation chamber and the inner and outer walls of the detonation tube. Its front section is equipped with N atomizing water droplet nozzles connected to the microfluidic atomizing water droplet injection unit and equipped with vortex generators, and 4 laser detonators. S3 refers to turbines (including high-pressure turbines and low-pressure turbines). S4 is a tailpipe with a tail jet recovery device (either a conventional tailpipe or a vectoring nozzle). S5 is a fluid that is a mixture of solid microspheres, atomized water mist, and compressed gas working fluid that is ejected backward by detonation impact. S6 is the rotor shaft. S7 is the working fluid from the microfluidic atomizing water droplet unit. S8 is a microfluidic atomizing water droplet unit and includes first and second pulse signal generators. S201 is the outer wall of the detonation tube. S202 is the inner wall of the detonation tube. S203 is the outer wall of the detonation chamber. S204 is the interior wall of the detonation chamber. S205-1-N consists of N microfluidic atomizing water droplet injection unit nozzles that make up the 205 water droplet nozzle array. S206-1 / 2 / 3 / 4 are four laser detonators that form the cross-shaped array of the S206 laser detonator. S206-ZL-F is a top view of the n total reflection end faces of a laser detonator. S206-ZL-C is a side-view laser detonator. S206-ZT is a type of shaping lens and a convex lens. S206-J represents a focused laser beam and a tapered optical fiber (not shown), and a dual-tube short microcavity (not shown). S207-1-m refers to the m microfluidic solid microsphere injection unit nozzles that constitute the 207 solid microsphere nozzle array. S208-1--m refers to the m laser detonators that make up the circular array of S208 laser detonators. S9 is the solid microsphere working fluid from the microfluidic solid microsphere injection unit. S10 is a microfluidic solid-state microsphere injection unit and includes a third and a fourth pulse signal transmitter. S11 is a focused laser beam from a laser detonator that is incident directly into a tapered optical fiber. S12 represents a laser-supported liquid-gas two-phase plasma detonation wave within a dual-tube short microcavity connected to a tapered optical fiber. S12 also represents the tapered optical fiber, the dual-tube short microcavity, and the directional plasma detonation wave within the cavity. S13 represents the direction of motion of a microfluidic solid microsphere injection nozzle injecting solid microspheres into the detonation tube. S14 is a solid microsphere that has been injected into the detonation tube. S15 represents the direction of the thrust generated by the backward ejection of solid particles after a solid microsphere is ablated and penetrated by a directional plasma detonation wave. S16 is a solid microsphere that is about to be injected from the microsphere nozzle into the flame tube. S17 is a solid microsphere to be injected into a solid microsphere nozzle.

[0051] For the sake of simplicity, in Figure 1 The outer bypass duct and compressed air inlet are not shown in the drawing. Detailed Implementation

[0052] The preferred embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be understood that these descriptions are intended to illustrate the basic principles and main features of the present invention, and not to limit the present invention; this application is not limited to the following six specific embodiments, and specific implementation methods can be determined according to the technical solutions of this application and the actual situation.

[0053] Example 1

[0054] like Figure 1 , Figure 2As shown, a laser turbofan power system includes an intake compression section (S1), a detonation chamber (S2), a turbine (S3), an exhaust nozzle (S4), and a turboshaft (S6). The detonation chamber S2 is composed of an outer wall (S203) and an inner wall (S204). The annular detonation tube inside S2 is mainly composed of an outer wall (S201), an inner wall (S202), and an end face. The front ends of S201 and S202 are sealed to form an "end face" and enclose an "annular cavity," supporting the installation of a laser detonator array and ensuring the coupling of laser energy and three-phase working material within the cavity. The system is designed for use in conjunction with other components. The S206 laser detonator is mounted in a cross-shaped array at the front of the detonation tube; the S208 laser detonator is mounted in a ring-shaped array at the end face of the detonation tube; the S205 atomizing water droplet nozzles are mounted in a ring-shaped array at the end face of the detonation tube; the S207 solid-state microsphere nozzles are mounted in a circumferential array at the front of the detonation tube; the S8 is a microfluidic atomizing water droplet injection unit equipped with the first and second pulse signal generators; and the S10 is a microfluidic solid-state microsphere injection unit equipped with the third and fourth pulse signal transmitters.

[0055] The overall layout of the detonation chamber S2 follows the traditional turbofan engine combustion chamber installation position, replacing the original combustion chamber structure. The inlet of the detonation chamber S2 is connected to the compressor outlet flange (the flange specifications are consistent with the original engine), and the outlet is seamlessly connected to the turbine guide vane assembly to ensure smooth airflow transition. The outer diameter and length of the detonation chamber S2 match the original combustion chamber, without requiring modification to the engine casing structure. S201 and S202 are adapted for detonation impact, and their material is GH4169 high-temperature alloy forgings (tensile strength ≥1400MPa, temperature resistance ≥1100℃). The inner wall is sprayed with a double-layer protective coating - the bottom layer is a NiCrAlY bonding layer (thickness 0.1mm), and the surface layer is a YSZ ceramic coating (thickness 0.3mm, hardness ≥1200HV), with an impact strength ≥200MPa, adapted to working fluid detonation impact (impact pressure 12~15MPa) and high-temperature environment.

[0056] The detonation tube features four laser detonators arranged radially and uniformly in an S206 array at its front section, and m laser detonators arranged axially and uniformly in an S208 array at its end face. The dual-tube short microcavities are fixed to the inner wall of the detonation tube (with uniform spacing) by high-temperature resistant supports to ensure uniform distribution of detonation energy. Multiple sets of working fluid inlet holes (1.2mm diameter) are opened on the side wall of the detonation tube, connecting to microfluidic solid-liquid working fluid supply pipes. Reinforcing bushings are welded around the holes to prevent deformation of the hole walls due to detonation impact. An annular guide section (10° expansion angle) is provided at the rear of the detonation tube to guide the mixed fluid after detonation smoothly into the turbine S3. The tapered fiber optic transmission assembly requires each laser detonator to be equipped with one high-power quartz tapered fiber. The fiber is wrapped with an alloy protective tube and passes through a pre-drilled hole in the engine casing to connect to the detonation chamber S2. The fiber output end is coaxially aligned with the dual-tube short microcavity S12. Its dual-tube short microcavity has an outer tube made of quartz and an inner tube made of alloy. The inner wall of the inner tube is coated with a food-grade ceramic coating. The top of the microcavity is connected to a tapered optical fiber, the side wall has two inlets connected to solid and liquid working fluid pipelines, and the bottom end is directly connected to the inner cavity of the detonation tube to achieve instantaneous detonation of the working fluid.

[0057] The three-phase working fluid supply system is adapted to the airflow from the detonation chamber S2 and the original machine S1. Its solid working fluid supply is implemented by the microfluidic solid microsphere precision injection unit S10, using bio-based solid microspheres with 100% biocompatibility. The pre-fabricated solid microsphere working fluid is stored in its unit container S10. During operation, the solid microspheres S9 are injected from the working fluid inlet of the detonation chamber S2 through a piezoelectric pusher and high-temperature resistant polytetrafluoroethylene pipe into the m microsphere nozzles of the S207 array.

[0058] The atomized water droplet working medium supply is implemented by the microfluidic atomized water droplet injection unit S8, using food-grade deionized water (GB5749 standard, 0.2μm ultrafiltration filtration). The treated and preheated water working medium is stored in S8. During operation, the water working medium S7 is connected through the reserved interface of the engine's original fuel line, without the need for additional external pipes or modification to adapt to the structure of the atomized water droplet injection unit. The atomized water droplet water storage unit container → high-pressure microfluidic pump → ceramic-based MEMS atomizing chip → atomized water droplets → heat-resistant silicone tube, is sent into the N nozzles of the water droplet nozzle array S205 through the water droplet working medium inlet hole of the detonation tube.

[0059] The gaseous working fluid supply reuses the original compressor. High-pressure air (pressure ≥ 0.6 MPa, filtration accuracy ≤ 2 μm) is divided into two paths, flowing into the inner and outer bypass ducts respectively. The main airflow entering the inner duct passes through the original combustion chamber inlet guide ring → detonation chamber S2 detonation tube inner cavity, serving as the detonation carrier and energy transfer medium (accounting for 75-85% of the total air entering the inner duct). The other branch entering the inner duct provides cooling air source for the microfluidic system and laser cooling system, working in conjunction with the original cooling circuit. The outer bypass duct process adapts and retains the original engine architecture, optimizing airflow coordination. The original outer bypass duct is retained, completely adopting the traditional turbofan engine outer bypass duct structure (the bypass ratio is determined according to the scenario requirements), including the outer bypass casing, rectifier blades, and outlet guide device, without any changes to size or layout.

[0060] like Figure 1 , Figure 2 As shown, when the laser turbofan power system is started, the fan in S1 begins to rotate, drawing in the air working fluid S0 into S1. After initial compression by the fan in S1, a portion of the air enters its outer bypass duct and flows directly backward through it, mixing with the fluid discharged from its inner duct in the tail nozzle S4 to form S5. Another portion of the air enters the inner duct and is further compressed by the low-pressure and high-pressure two-stage compressors in S1, providing high-temperature and high-pressure compressed air to its annular detonation chamber S2. It first enters the diffuser of the combustion chamber S2, where the airflow velocity decreases and the pressure increases. Then, a portion of the compressed air (determined by the bypass ratio) enters the annular cavity of the detonation tube from the microfluidic cyclone separator at the end face of the detonation tube formed by S201 and S202, forming a liquid-gas two-phase mixed working fluid. The microfluidic cyclone separator causes the airflow to rotate, forming a stable liquid-gas two-phase mixed working fluid.

[0061] like Figure 1 , Figure 2 As shown, another portion of the compressed air flowing out of the diffuser in the detonation chamber S2 enters the detonation tube through openings on the outer wall S201 and inner wall S202 of the detonation tube. The distribution and size of these openings are carefully designed so that the compressed air enters the detonation tube at a specific flow rate and direction, cools the detonation tube, prevents it from being damaged by high temperature, mixes with the detonation wave in the detonation zone, reduces the temperature of the combustion gas to a temperature that the turbine S3 can withstand, and makes the temperature field at the outlet of the detonation chamber uniform.

[0062] like Figure 1 , Figure 2As shown, in S8 of the power system, the first and second pulse signal generators generate control signals, simultaneously activating S206 and S205. The four laser detonators in S206 each emit femtosecond pulse lasers, and the N atomizing water droplet nozzles in S205 inject atomized water droplets into the detonation tube that has already received compressed air. In S10, the third and fourth pulse signal generators also simultaneously generate control signals, simultaneously activating S208 and S207. The m laser detonators in S208 each emit femtosecond pulse lasers, and the m solid-state microsphere nozzles in S207 inject solid-state microspheres into the detonation tube that has already received compressed air and atomized water droplets.

[0063] like Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 As shown, the four laser detonators of S206 each contain an array of n vertical cavity lasers S206-ZL=F. The n laser beams emitted are focused by the shaping lens and convex lens S206-ZT of each laser detonator to form a laser beam S206-J. This beam then enters a dual-tube short microcavity S12 connected by a structurally integrated tapered optical fiber. After passing through the tapered optical fiber, S206-J forms S11, which then ablates and breaks down the gas-liquid two-phase working fluid in the short microcavity S12, forming a directional plasma detonation wave S12. This wave then propagates into the detonation tube, further impacting the solid-gas-liquid three-phase working fluid in the detonation tube.

[0064] The m laser detonators of S208 each contain an array of n vertical cavity lasers S208-ZL-F (same as S206-ZL-F). The n laser beams emitted are focused by the shaping lens and convex lens S208-ZT (same as S206-ZL-F) of each laser detonator to form a laser beam S208-J (same as S206-J). The beam then enters a dual-tube short microcavity S12 connected by a structurally integrated tapered optical fiber. After passing through the tapered optical fiber, S208-J forms S11, which then ablates and breaks down the gas-liquid two-phase working fluid in the short microcavity S12. The directional plasma detonation wave S12 emitted by S208-1-m then propagates into the detonation tube, precisely impacting the solid microspheres S14 that are injected into the detonation tube and shattering them into solid particles larger than 10 micrometers.

[0065] The airflow optimization involves the mixed fluid (high-temperature, high-pressure multiphase fluid) at the outlet of detonation chamber S2 being efficiently mixed with the cold air from the bypass duct in the mixing chamber (original engine exhaust mixing chamber) of the tail nozzle S4 after the turbine S3 performs work. The cold air from the bypass duct lowers the temperature of the mixed fluid, preventing it from being overheated when passing through the tail nozzle. Simultaneously, the entrainment effect of the bypass airflow increases the velocity of the mixed fluid, enhancing thrust output. Inside the detonation chamber, a complex solid-liquid-gas three-phase mixture of detonation wave and shock wave is formed. Under the action of pressure difference, the fluid flows through turbine S3 and drives compressor S1 to rotate continuously via axle S6. This causes the airflow from the bypass duct to be ejected at high speed backward and mixed with the fluid flowing through turbine S3 in the tail nozzle S4. The mixture is then ejected backward to form a high-speed fluid S5 and a reaction force S15 with the impulse kinetic energy of the reaction force, driving the carrier's movement. The air flowing in the bypass duct, mixed with the fluid discharged from the turbine S3, enters the exhaust mixing chamber, where it is mixed with the cold air in the bypass duct to cool down and increase speed. Then it enters the tail nozzle and is accelerated to be ejected (exit flow velocity ≥ Mach number 1.4) of the mixed fluid S5, generating the main thrust. A portion of the fluid (12-18%) flows back to the front end of the compressor through the bypass to help increase the intake pressure.

[0066] The described workflow conforms to the working cycle of a traditional turbofan engine. During the engine start-up phase: the original intake fan in S1 starts, and S0 is initially compressed by the electric fan and then divided into two paths. One path enters the bypass duct, and the other path enters the already started original compressor S1. The air after being deeply compressed by the high-pressure compressor S1 is also divided into two paths. The main stream enters the detonation chamber S2, and the branch stream is used for cooling. The microfluidic solid-liquid working fluid supply system starts, and solid microspheres and atomized water droplets are injected into the flame tubes S201 and S202 in proportion. The laser module is preheated, and the water cooling system works synchronously with the original engine cooling circuit. During its detonation power phase: each laser detonator in the S206 and S208 arrays is activated synchronously. The laser is guided through optical devices and tapered optical fibers into a dual-tube short microcavity, ablating and penetrating the liquid-gas two-phase working medium within the cavity, forming a directional plasma detonation wave. This wave is then directionally transmitted into the detonation tube, impacting the solid-liquid-gas three-phase working medium. When the impact energy acts on the mixture of water droplets, air, and solid microspheres, the high energy density of the shock wave rapidly heats and ionizes the surrounding medium, forming plasma and triggering the detonation wave. The initial detonation wave impacts the water droplets and solid microspheres, causing the water droplets to break up and atomize, and the solid microspheres may be shattered or accelerated. Simultaneously, it interacts with... The air is fully mixed; in this process, the energy of the detonation wave is transferred to the mixture, giving it the kinetic energy of high-speed motion and forming a high-speed airflow; this high-speed airflow has high energy and can drive the turbine S3 to rotate, and then eject the high-speed mixed fluid S5 from the tail nozzle S4, thereby forming a reaction force to realize energy conversion and power output; its three-phase working fluid high-energy mixed fluid enters the turbine S3 through the detonation tube guide section, driving the turbine S3 to rotate, and driving the compressor S1 to rotate through the wheel shaft S6, driving the intake fan in S1 to continuously draw in air S0, thereby achieving continuous air supply, matching the original engine's "Brayton" cycle.

[0067] The particulate recovery system is compatible with the bypass duct. The three-stage particulate recovery system is integrated within the exhaust nozzle S4 (without occupying bypass duct space). It consists of a first-stage negative pressure recovery port (nozzle contraction section), a second-stage cyclone separator (nozzle expansion section), and a third-stage electrostatic interceptor (nozzle outlet). The recovery process does not affect the airflow in the bypass duct. The recovery pipeline is arranged along the inner side of the engine casing, isolating it from the bypass duct airflow to prevent particulates from entering the bypass duct. Its solid particulate integrated recovery subsystem, installed within the exhaust nozzle S4, captures solid particulates throughout the entire process with a recovery efficiency of 100%. All solid particulates with a diameter >10μm are monitored throughout the process.

[0068] The intelligent collaborative control module receives the start command and coordinates with the battery management system of its virtual and physical battery module and the engine control system. The power battery precisely outputs start-up power to drive the compressor to rotate and power the laser detonator. It monitors the engine speed and three-phase working fluid mixing ratio in real time and dynamically adjusts the power supply to ensure rapid and stable engine start-up. After successful start-up, it automatically switches to collaborative working mode. The intelligent collaborative control module identifies take-off and landing, and high thrust requirements for low-altitude endurance in real time, dynamically allocating power through algorithms: the power battery and engine generator work together to supply power, supplementing instantaneous high energy consumption; it synchronously regulates the thermal management circuit, directing waste heat from the battery into the engine air duct to increase thrust, balancing power output and energy utilization. Its intelligent energy manager determines the engine's efficient operating range based on flight parameters and battery state of charge, using the generator as the primary power source and automatically replenishing the power battery; it optimizes charging and discharging strategies in real time to maintain the battery's optimal state while avoiding inefficient engine operation, achieving optimal energy consumption. The intelligent collaborative control module continuously collects battery temperature, voltage, and engine thermal parameters, and dynamically adjusts charging and discharging power and heat dissipation path; through the waste heat recovery algorithm, it accurately matches heat exchange efficiency, ensuring safe heat dissipation of the battery and maximizing the use of waste heat to improve engine aerodynamic performance, forming an energy closed loop.

[0069] The intelligent collaborative control module works in conjunction with the original engine ECU (single control unit). A dedicated control unit is added to the central control system, compatible with the original engine ECU, integrating the following functions: laser detonator module S206 and S208 control, microfluidic propellant ratio adjustment, detonation chamber pressure / temperature monitoring, and particulate recovery control, with a response time ≤3ms. Key monitoring features include a miniature pressure sensor and temperature sensor inside the detonation chamber S2; pressure sensors at the inlet and outlet of the outer bypass duct to monitor the airflow coordination status in real time; in case of abnormalities, the original engine ECU is prioritized to trigger a load reduction or shutdown procedure. During the load adjustment phase, the central control system dynamically adjusts the laser power, microfluidic propellant ratio, and detonation chamber electrode voltage according to the thrust requirements transmitted by the original engine ECU, achieving an adjustable thrust range of 0.8 to 1.8 times that of the original engine, adapting to different operating conditions such as vertical takeoff and landing, takeoff and stop, low-altitude cruise, and ground endurance.

[0070] Example 1 achieves the following beneficial effects (1) Advantages of efficient coupling of multiple energy sources: The energy conversion of a traditional turbofan engine has four links (chemical fuel - combustion heat energy - turbine kinetic energy - internal and external bypass mechanical energy - jet gas flow energy), while the energy conversion links of the aforementioned laser turbofan power system increase to six: battery power energy - laser light energy - short microcavity directional detonation wave energy - high working fluid internal energy release detonation fluid energy - turbine kinetic energy - internal and external bypass mechanical energy - jet gas flow energy; among these, the battery chemical energy, capacitor electrostatic energy, and flywheel mechanical energy of the battery are combined and synergistically transferred to the laser; its laser turbofan power system Lighter weight is achieved, whereas fuel-powered turbofan engines require complex fuel supply and exhaust systems, resulting in bulky structures and a large size inherent to high power output. Laser turbofan power systems do not emit harmful gases and do not require regular fuel system maintenance or oil changes. Their working fluid detonation is cleaner and free from complex mechanical wear. Starting with "low-energy triggering," the aforementioned laser turbofan power system breaks through the bottlenecks of traditional turbofan engines, which are characterized by "fuel dependence, low efficiency, and bulky size." In particular, when combined with an external bypass duct and a collaborative power supply system, it achieves numerous combined advantages in terms of lightweight design, high efficiency, and adaptability to various operating conditions. (2) Advantage of double energy superposition: Traditional laser energy transfer directly ablates and breaks down the working medium, while in this invention, the laser beam first passes through a "dual-tube short microcavity" and then indirectly ablates and breaks down the working medium. That is, the laser beam is first confined to the tapered optical fiber and the dual-tube short microcavity, ablates and breaks down the gas-liquid two-phase working medium within the short cavity, and forms a laser-supported directional plasma detonation wave within the short microcavity. This wave is then transmitted to the detonation tube and then directionally impacts the solid-liquid-gas three-phase working medium. This results in double energy transfer, with energy transfer occurring "within the microcavity" and "within the detonation tube," which improves the laser energy transfer efficiency of this invention by approximately 10% compared to the traditional method. 3 Order of magnitude. Advantages of directional energy transfer: The laser does not directly impact the working medium, but supports the generation of directional plasma detonation waves to impact the working medium. Its detonation energy utilization rate is much higher than that of ordinary ablation, which is the core of improving thrust efficiency. "Indirect" directional detonation avoids energy scattering, allowing more laser energy to be converted into directional thrust. This advantage of directional energy transfer enables the thrust efficiency (the efficiency of converting the energy of the laser superimposed on the working medium into the kinetic energy of the carrier) of this invention to reach more than 70%. (2) Advantages of microfluidic precision delivery: It overturns the cumbersome technology mode of traditional large water tank / storage and supply tank for delivery and injection. It uses microfluidic technology to realize the micro-volume, precise and controllable delivery and injection of solid microspheres and atomized water droplets. The volume is reduced by more than 90%, the delivery and injection accuracy and timing are precise and controllable without waste, and the flexibility is more suitable for small batch and high frequency precise delivery. The efficiency and stability are significantly improved without excessive redundancy in working fluid storage.

[0071] Example 2

[0072] This invention refers to the "vertical takeoff and landing flying car" as a "helicopter," and uses the helicopter as the carrier in this embodiment. This carrier has an integrated power system, comprising two different types of power systems. One is a "four-engine power system" (for ease of calculation, this example considers it as a single, integrated laser turbofan power system, such as...). Figure 1 As shown, it mainly consists of S1, S2, S3, and S4. Another system is a "four-hub reversible permanent magnet motor and blade power generation system" (its hub is equipped with ≥3 360° wind-chasing blades. This set of blades converts wind energy from 360° into mechanical energy of blade rotation, which is then converted into electrical energy by the hub reversible permanent magnet motor to charge the solid-state power battery on the carrier. It accounts for 40% of the energy source for low-altitude flight, contributes about 40% to the reduction of the weight requirement of the solid-state power battery, reduces the redundant hub power weight, and increases the effective payload of the carrier).

[0073] Its integrated power system enables the vehicle to have both low-altitude flight and ground-based air-ground functions. Its low-altitude flight functions include vertical take-off, vertical landing, low-altitude hovering, and low-altitude level flight continuation. Its ground-based functions include ground "short-distance transport", "short-distance continuation", and "connection to the helicopter pad". The helicopter pad is a "vertical take-off and landing mini airport" for helicopters.

[0074] Its "four-engine power system" consists of four "low-power laser turbofan power systems", two of which are located at the front of the vehicle and two at the rear. The four-engine laser turbofan power system supports various low-altitude flight conditions, including vertical ascent, low-altitude hovering, low-altitude long-range endurance, and vertical descent (applicant number: 202521493568.1, publication number: 2025071700761990).

[0075] Its four-wheel hub electromagnetic motor system includes four radial hub motors integrated with its four wheels and multiple 360° wind-chasing blades that can generate electricity. When assisting the helicopter in low-altitude navigation, it mainly supports the helicopter's movement under various ground conditions after landing. When the helicopter lands vertically on the ground, its four laser turbofan power systems stop working and simultaneously activate the four hub permanent magnet motor systems to carry out short-distance transport, short-distance extension, and connection to the helicopter pad.

[0076] The helicopter is generally composed of two main modules: a skateboard chassis module and a body module (see application number: 202521816097.3, document number: 2025082601339070). The helicopter uses a virtual and physical power bay to simultaneously power its chassis and body. The virtual and physical power bay, the four-engine power system, and the four-wheel hub motor system are structurally integrated with the skateboard chassis. When estimating power requirements, the four sets of low-power laser turbofan power systems are simplified to one set of medium-low power laser turbofan power systems, and the four sets of low-power radial hub motors are simplified to one set of medium-low power radial hub motors. Under the management of its intelligent collaborative control system, the four-engine power system and the four-wheel hub motor system operate as a single unit.

[0077] The core basic parameters of the helicopter described in this embodiment. (1) Vehicle curb weight: 2000kg, corresponding gravity G=mg=2000×9.8=19600N. (2) Energy storage system configuration: solid-state battery + micro supercapacitor + micro flywheel (cooperative power supply / energy recovery, transient power sharing efficiency 22%, gravitational potential energy recovery efficiency 75%, total energy conversion loss ≤5%). (3) Power system architecture: 4 laser-powered turbofan engines (with vector nozzles, responsible for the full thrust of vertical take-off and landing + the main thrust of air cruise) + 4 hub reversible permanent magnet motors (with 360° wind-chasing blades, responsible for the auxiliary thrust of air cruise and the full thrust of ground operation, and not involved in vertical take-off and landing). (4) Drag reduction configuration: The air resistance is reduced by 50% in all scenarios (the carrier is equipped with a vertical cavity laser array plasma drag reduction device, the carrier streamlined design and other drag reduction measures), which are suitable for high-speed air cruising and high-speed ground driving. (5) Core battery indicators: Energy density 700Wh / kg (based on Huawei’s official announcement on December 1, 2025 that sulfide solid-state batteries will break through 900Wh / kg in 2027), supporting high-rate discharge (matching transient power requirements).

[0078] The vertical lifting parameters in this embodiment (core: turbofan vector nozzle provides lift independently, hub motor is off) (1) Lifting speed: 1.2m / s (uniform lifting speed to ensure stability). (2) Lifting height: 300m per cycle, 6 cycles in total (3 ascents + 3 descents, covering take-off and landing needs in multiple scenarios). (3) Power logic: When ascending, the turbofan thrust offsets the vehicle's weight + 10% redundancy (to resist airflow disturbance), and when descending, the turbofan outputs a small thrust in the opposite direction to control the speed, and the energy storage system recovers gravitational potential energy. (4) The vertical lift thrust is about 2200 kg (100% output of turbofan vector nozzle), which needs to completely overcome gravity and leave redundancy. (5) The vertical descent thrust is about 200 kg, and only reverse speed control is needed. There is no need to overcome gravity (turbofan vector nozzle reverse output). (6) The total power of vertical ascent (turbofan driven) is approximately 307kW. (7) The total energy consumption of the three upward turbofans is about 6kWh (requiring battery replenishment). (8) Vertical descent energy recovery: flywheel + supercapacitor recovers approximately 20kW. (9) The total energy recovered from the three descents is approximately 4 kWh. (10) The net battery power consumption in vertical lifting mode is about 2kWh (only for energy replenishment, no large power output). (11) Turbofan engine: It operates throughout the entire process, outputting large thrust in the upward direction and small thrust in the downward direction. (12) Hub electromagnetic motor: It stops during the entire process and does not participate in lift supply and energy recovery. (13) Solid-state batteries replenish the energy consumption of the turbofan during ascent; supercapacitors and flywheels recover energy during descent, eliminating the need for solid-state batteries to output peak power.

[0079] The main parameters of this embodiment are as follows: low-altitude flight range of 1000 kilometers (turbofan + hub motor work together to provide horizontal thrust). (1) Flight altitude: 300m low altitude (air density ρ≈1.145kg / m³) 3 (Slightly below ground level to reduce wind resistance loss). (2) Average flight speed: 450km / h = 125m / s (high-speed cruise requirement). (3) Range: 1000km, corresponding flight time = 1000km ÷ 450km / h ≈ 2.22h. (4) Power logic: Turbofan drives the thrust output, hub motors assist in sharing the load, and energy storage system optimizes battery power demand. (5) Total air resistance: 2238N (approximately 228kgf). (6) Thrust matching principle: Horizontal thrust = total air resistance (to ensure uniform cruising speed), turbofan accounts for 60% and hub motor accounts for 40%. (7) Turbofan output thrust: F_turbofan = 2238N × 60% = 1342.8N (≈137kgf) (8) Total output thrust of 4 hub motors: Total motor thrust = 2238N × 40% = 895.2N (≈91.3kgf) (9) Output thrust of a single hub motor: 895.2N ÷ 4 = 223.8N (≈22.8kgf, low thrust load, suitable for superconducting motor characteristics) (10) Total power required for cruising in the air (total power required to overcome air resistance): approximately 330kW (11) Turbofan engine power: 330kW × 60% = 198kW (12) After energy storage synergy optimization, the motor power is approximately 96kW (averaged across four turbofan engines, each requiring 24kW of power). (13) The total battery power consumption during in-flight cruise is approximately 230 kWh. (14) The vector nozzle of the turbofan engine switches to horizontal mode, outputting 60% of the horizontal thrust to dominate the cruise power. (15) Four hub permanent magnet motors work synchronously, with a total output of approximately 103kW of power, providing an additional 40% of the horizontal thrust. (16) Its solid-state battery provides continuous power to the motor / supercapacitor compensates for peak transient power of the motor / flywheel energy storage battery recovers energy.

[0080] The main parameters of this embodiment are based on the condition of cumulative ground operation of more than 100km (turbofan shutdown). (1) Average driving speed: 180km / h = 50m / s (high-speed driving requirements on the ground). (2) Range: 100km or more, corresponding driving time = 100km ÷ 180km / h ≈ 0.56h. (3) Road surface: hard surface (rolling resistance coefficient f≈0.013, low friction loss). (4) Power logic: Only the total ground resistance needs to be overcome, the hub motor drives the wheel alone, and the energy storage system optimizes power and recovers braking energy. (5) Air resistance (after drag reduction of 50%) is approximately 532N. (6) Ground resistance is approximately 255 N. (7) The total output thrust of the four hub motors is approximately 787 N. (8) Output thrust of a single hub motor: 786.4N ÷ 4 = 196.6N (≈19.9kgf, low thrust load). (9) Total power after energy storage synergy optimization: approximately 37kW (supercapacitor assists in acceleration transient power, reduces peak output of solid-state battery, and recovers braking energy). (10) Optimized power of single hub motor: 37kW÷4=9.25kW (low power load, superconducting motor efficiency reaches over 98%). (11) Total battery power consumption under ground operation conditions: approximately 20.7 kWh. (12) Turbofan engine: The engine is shut down throughout the entire process, with no power output and energy consumption. (13) Hub permanent magnet motor: 4 units work synchronously, with a total output of 37kW power, and each unit is responsible for ground drive. (14) Energy storage system: Solid-state batteries provide continuous power to the motor, supercapacitors compensate for transient power during acceleration, and recover energy during braking to further reduce battery power consumption.

[0081] Without considering the energy release from the microspheres by the femtosecond pulsed laser ignition, the turbofan power system requires a laser power of 24kW; when considering the energy release from the microspheres, the laser power input only needs to be 0.24kW. Specifically, the 16 lasers and each laser is emitted by 15 VCSEL lasers combined, and each VCSEL laser only needs a rated power of 100mW.

[0082] Example 3

[0083] This embodiment discloses a laser detonator and power adaptation scheme for a quantum-modified energy storage microsphere working fluid turbofan power system. The mechanical output power of the turbofan power system is 24kW, and the laser detonation input power accounts for 1% of the total system input power. The laser detonator component adopts a commercially available mass-produced 100mW VCSEL laser, which is adapted to the operating conditions of the turbofan power system, taking into account power output stability, operating condition adaptability, and redundancy fault tolerance, and provides stable detonation energy for the quantum-modified energy storage microsphere working fluid used in the turbofan power system. The specific structure and parameters are as follows.

[0084] Overall configuration of laser detonator module The laser detonator modules S206 and S208 are the core energy detonation units of the turbofan power system. The whole system includes 16 parallel laser branches. Each laser branch is connected in series with a beam emitting unit and a power amplification unit. The laser output from the beam emitting unit is amplified by the power amplification unit and then fed into the quantum modified energy storage microsphere working fluid module of the turbofan power system to provide energy support for the turbofan power output. like Figure 3 As shown, each beam emitting unit of the S206-ZL-F is equipped with 15 main working beam groups and 4 backup beam groups. The main working beam groups have 15 built-in VCSEL laser devices, and the backup beam groups have 4 built-in VCSEL laser devices. A single beam emitting unit integrates a total of 19 VCSEL devices. The VCSEL devices are commercially available mature mass-produced specifications, with a single beam rated output power of 100mW, an electro-optical conversion efficiency of ≥70%, an output beam with a circular spot, a beam divergence angle of 10°-20°, a wavelength drift of ≤±0.5nm and a power fluctuation of ≤±3% under high temperature conditions of 85℃, and a mean time between failures of ≥100,000 hours, which can stably adapt to the long-term continuous operation requirements of turbofan power systems. The core conversion parameters of the 206 / 208 laser detonator link are calibrated as follows: the energy conversion rate of the 15 laser beams in the single main working beam group is 90%, the power amplification unit of each laser branch is fixed to achieve a power gain of 22 times, and the energy input conversion rate of the quantum modified energy storage microsphere working fluid after the 16 parallel laser branches are combined is 70%; the total input power of the laser end is configured to 1kW, with more than 50% power redundancy reserved to ensure the stable power output of the turbofan power system under extreme conditions.

[0085] Single-channel laser branch power link parameters (1) The rated output power of a single-beam VCSEL device is 100mW (0.1W). Based on a 70% electro-optical conversion efficiency, the driving power consumption of a single-beam VCSEL device before electro-optical conversion is 100mW÷70%≈142.86mW, which meets the design requirements for low-power excitation of the turbofan power system. (2) After the power of the single main working beam group is superimposed by 15 VCSEL devices and converted by 90% beam combining conversion rate, the output power after beam combining is 15×0.1WX90%=1.35W; (3) After the power of the single-path backup beam group is superimposed by 4 VCSEL devices and converted by 90% beam combining conversion rate, the output power after beam combining is 4×0.1W×90%=0.36W; (4) After the single main working beam group is amplified by 22 times, the output power is 1.35W×22=29.7W; after the backup beam group is amplified by 22 times, the output power is 0.36W×22=7.92W; the independent output power of the main working position of the single laser branch is 29.7W, and the total output power of the single beam group when both the main and backup beam groups are fully activated is 37.62W. The single power fault tolerance rate is increased by 26.67%, which can cope with single or multiple VCSEL device failure scenarios and avoid the loss of single power affecting the overall operation of the turbofan power system. (5) Power adaptability: The single-path laser branch required to output power of the 24kW mechanical output of the turbofan power system is 23.81W, and the output power of the single-path main working beam group after amplification is 29.7W. The power redundancy is sufficient and can stably meet the single-path laser excitation energy requirements.

[0086] Total power adaptation calculation of the 16 laser branches of the laser detonators S206 and S208. (1) When the 16 laser branches of the laser detonators S206 and S208 are independently output, the total output power is 16×29.7W=475.2W. This power is the actual total input power of the laser end, which is lower than the configuration limit of 1kW. The power redundancy space is sufficient to support the normal operation of the turbofan power system. (2) The total output power of the 16 laser branches of the laser detonators S206 and S208, after being input into the quantum-modified energy storage microsphere working medium with a 70% energy conversion rate, is 475.2W × 70% = 332.64W. (3) Overall system power matching: The effective input power requirement for laser ignition corresponding to the 24kW mechanical output of the turbofan power system is 24kW×1%=240W. In this embodiment, the effective laser ignition power reaches 332.64W, with a redundancy rate of about 38.6%. If the turbofan power system is under high load extreme conditions, the full power output of the 16 laser branches of the laser igniters S206 and S208 is activated, with a total output power of 16×37.62W=601.92W. The corresponding effective ignition power input to the microsphere working fluid is 421.344W, which can stably support the 24kW mechanical output of the system. If the laser end is fully equipped with a total input power of 1kW, the corresponding effective power of the working fluid excitation can reach 700W, with a redundancy rate of over 191.7%, which fully covers the 50% redundancy design requirement of the system and adapts to the power requirements of the turbofan power system under different operating conditions.

[0087] Component operating condition adaptation guarantee (1) Beam characteristics adaptation: The VCSEL device outputs a circular beam, which, combined with a fast axis collimation structure, can ensure that the beam combining efficiency of 15 main working beams is maintained at 90%, which is suitable for the energy input requirements of the power amplifier unit. At the same time, it simplifies the optical link integration structure and is suitable for the compact layout requirements of the turbofan power system. (2) Thermal management adaptation: VCSEL devices adopt multi-junction specifications, with an electro-optical conversion efficiency of up to 74% and controllable power consumption. With the help of micro heat sinks and pulse drive mode (duty cycle ≤10%), the risk of thermal saturation during continuous operation of a single tube can be avoided, and it is suitable for the local high temperature conditions during the operation of turbofan power systems. (3) Reliability Adaptation: The VCSEL device is selected with industrial-grade specifications and can withstand slight vibration interference during the operation of the turbofan power system. It is equipped with overcurrent and overtemperature protection circuits and a fast replacement function of 4 backup beam groups to ensure continuous and stable output of the laser excitation component. (4) Supply compatibility: The 100mW VCSEL devices used are mature mass-produced products, with stable supply from leading domestic and foreign manufacturers. The yield rate is over 92%, and the cost of bulk purchase is controllable, which can meet the subsequent mass production support needs of turbofan power systems.

[0088] Under the precise control of the pulse signal generators in S8 and S10, the S8 microfluidic atomizing water droplet unit injects the S7 water working material into the 12 atomizing water droplet nozzles of the S205 array, which then injects it into the detonation tube cavity at the appropriate time. The injected atomized water droplets mix with compressed air in the annular cavity of the detonation tube. The Si0 microfluidic solid microsphere unit injects the material into the 12 solid microsphere nozzles of the S207 array, which then injects it into the detonation tube cavity at the appropriate time, resulting in a mixture of solid microspheres, atomized water droplets, and compressed air as the working material. The compressed air compressed by S1 flows into the annular cavity of its detonation tube. The 12 nozzles of the S205 array and the 12 nozzles of the S207 array inject atomized water droplets and solid microspheres into the annular cavity of its detonation tube at the appropriate time, ensuring no dead zones.

[0089] The directional plasma detonation wave emitted by each laser detonator directly impacts the water droplets, causing them to undergo elastic deformation (deformation of 40-50%) and absorb approximately 12% of the detonation wave energy. This weakens the impact of the detonation wave on the combustion chamber wall (reducing the peak wall pressure by 25%) and prevents the microsphere core from breaking down to below 10μm due to excessive instantaneous pressure. Some water droplets are rapidly pre-vaporized under the local high temperature of the detonation wave (approximately 35% converts into water vapor), while the remaining water droplets shrink to a size of 3-8μm and remain liquid. The pre-vaporized water vapor can directly provide water molecules as raw material for the hydrogen production reaction in the core.

[0090] The aforementioned three-phase synergistic combustion generates high-temperature, high-pressure gas (temperature 1700–2000 K, pressure 2.5–3.5 MPa), which flows backward along the flow path of its power system, completing the final conversion of energy into thrust: the gas first impacts the blades of turbine S3, driving turbine S3 to rotate at a high speed of 12000–28000 r / min, converting the thermal and pressure energy of the gas into the rotational mechanical energy of turbine S3; turbine S3 drives the compressor and fan in front-end S1 to rotate through drive shaft S6, and the compressor in S1 continuously draws in... Outside air (S0) is compressed to maintain the compressed air supply in detonation chamber S2; the fan in S1 drives a large amount of bypass airflow, generating more than 50% of the engine's total thrust; the combustion gas after passing through turbine S3 still retains a certain amount of energy and continues to expand and accelerate through tailpipe S4, increasing the flow velocity to supersonic speed (1300~1900m / s), and is ejected backward to generate reverse thrust, which is superimposed with the bypass thrust to form the engine's total thrust S5; ceramic fragments and trace amounts of inert particles in the combustion gas are discharged with the exhaust gas, which are non-toxic and harmless, meeting green environmental protection requirements.

[0091] When the helicopter has an impulse of 2238N and an input power of 100kW, the corresponding effective output thrust is 1300N. Therefore, the laser penetration microsphere impulse coupling coefficient is 13N / kW, and the laser specific impulse is 400-1200s.

[0092] Without considering the energy release of microspheres, the power battery needs to weigh 480kg; with the energy release of microspheres considered, the power battery needs to weigh 2kg.

[0093] Example 3 achieves the following beneficial effects (1) Significantly reducing the weight requirement of the power battery, achieving system lightweight optimization. The power system uses quantum-modified bio-based environmentally friendly energy storage solid microspheres as the core energy supply source, bearing 99% of the total system input energy, with only 1% of the energy demand covered by the laser detonation end; the laser detonation end adopts a femtosecond pulse mode VCSEL device, which operates stably at a frequency of 100Hz. Through the continuous and orderly accumulation of microscopic small energy, it achieves macroscopic high-efficiency large energy output, accurately adapting to the energy excitation requirements of the energy storage solid microspheres. After comprehensive energy reduction under all operating conditions, the net energy consumption of the laser end is only about 0.61kWh. With a solid battery with an energy density of 400Wh / kg, the basic power supply requires only 1.52kg of battery, and the battery weight is only about 1.98kg under high redundancy configuration. Compared with the traditional turbofan power system that relies on hundreds of kilograms of power batteries to bear the core energy supply, the power battery usage of the system is reduced by orders of magnitude, reducing the dependence on power batteries from the root, significantly optimizing the overall weight of the system, and improving the lightweight adaptability of the power system. (2) Significantly improves the environmental performance of the system throughout its entire life cycle, meeting the needs of green development. On the one hand, the core energy carrier is made of bio-based environmentally friendly materials, and its intrinsic energy density is greatly improved after quantum modification. There are no harmful pollutant emissions or heavy metal pollution risks in the entire process of its preparation, energy storage and energy release. It can also achieve efficient energy recycling and has outstanding advantages in resource utilization. On the other hand, the system requires very little power battery, avoiding the water and soil pollution caused by the excessive mining and purification of rare metals and chemical raw materials in the traditional power battery production stage, the resource waste caused by frequent replacement in the use stage, and the continuous environmental damage caused by improper disposal of heavy metals and electrolytes in the scrapping stage. This significantly reduces the environmental risks related to the entire life cycle of the power battery. At the same time, the high-efficiency energy conversion characteristics of the femtosecond pulse VCSEL at the laser excitation end further reduce energy loss, help improve the environmental benefits of the system, and achieve clean energy supply throughout the entire process. (3) Ensure stable and efficient energy output of the system and improve adaptability to operating conditions. The 100Hz femtosecond pulse VCSEL at the laser detonator end achieves macroscopic stable energy output through the accumulation of microscopic small energy. It can accurately and efficiently excite the stored energy of quantum-modified energy storage solid microspheres. With the beam configuration of 15 main and 4 backup laser branches in each of the 16 laser branches, the fault tolerance and stability of laser detonation are improved. The energy density and release efficiency of the core energy storage microsphere after quantum modification are adapted to the system operating conditions. Combined with the 50% comprehensive energy saving brought by the synergy of supercapacitors, flywheel energy storage and drag reduction design, the system can stably adapt to the operating requirements of multiple operating conditions such as ground driving, multiple vertical lifts and drops, and low-altitude high-speed cruise, while taking into account the high efficiency and stability of energy output.

Claims

1. A quantum-modified energy storage microsphere working fluid turbofan power system, characterized in that, It includes seven core components: laser detonator array module series, laser-supported plasma power conversion module, turbofan power enhancement output module, three-phase working fluid material storage and input module (air is drawn in and compressed, microfluidic water storage unit atomizes water droplets and injects water, solid microsphere storage and supply unit microfluidic injection), virtual and real electric chamber power supply module, multi-dimensional energy recovery module, and intelligent collaborative control module. The laser detonator module is equipped with 12-16 VCSEL femtosecond pulse laser emitting units. These units consist of four fixed channels arranged in a cross shape and eight to twelve channels arranged in a ring. The four cross-shaped channels are located at the front of the detonation tube, while the eight to twelve ring-shaped channels are located at the end face of the combustion tube. The VCSEL femtosecond pulse lasers penetrate quantum-modified energy storage microspheres with a 100Hz pulse frequency, achieving macroscopic high-power output through the accumulation of small energy released from the microscopic microspheres, resulting in a power amplification of 22 times. The system utilizes laser... A composite energy drive mode with 1% energy content and 99% microsphere energy release achieves a laser impulse coupling coefficient of 13 N / kW and a specific impulse exceeding 400–1200 s. The laser-supported plasma power conversion module converts the plasma energy generated by laser ignition into mechanical power. The virtual and physical electric chamber power supply module provides stable energy to each module, and the multi-dimensional energy recovery module recovers residual energy during system operation. The intelligent collaborative control module is electrically connected to all the aforementioned modules to achieve real-time dynamic linkage control of each module.

2. A laser detonation method based on the turbofan power system of claim 1, characterized in that, Includes the following steps: (1) A laser ignition assembly adapted to a turbofan power system, characterized in that the turbofan power system uses quantum-modified bio-based environmentally friendly energy storage solid microspheres as the core energy supply source, the core energy supply source accounts for 99% of the total input energy of the system, and the laser ignition input power accounts for 1% of the total input power of the turbofan power system; the laser ignition assembly includes 16 parallel laser branches, each of which is connected in series with a beam emitting unit and a power amplification unit; the beam emitting unit is configured with a main working beam group and a backup beam group, the main working beam group includes 15 VCSEL lasers, and the backup beam group includes 4 VCSEL lasers. The VCSEL operates in femtosecond pulse mode at a frequency of 100Hz, achieving macroscopic high-power output through continuous accumulation of microscopic small energy. The rated output power of the VCSEL unit is 100mW, with an electro-optical conversion efficiency ≥70%. The power amplification unit has a power gain of 22 times, and the VCSEL laser beam combining efficiency of the main working beam group is 90%. After the 16 laser branches are combined, the breakdown energy conversion rate to the quantum-modified bio-based energy storage microspheres is 70%. The quantum-modified bio-based energy storage microspheres are prepared using bio-based environmentally friendly materials, and their intrinsic energy density is increased to 7–8 MJ / kg after quantum modification treatment. (2) The laser detonation component adapted to the turbofan power system according to claim 2 is characterized in that the output beam of the single VCSEL is a circular spot with a beam divergence angle of 10°-20°, wavelength drift ≤ ±0.5nm under 85℃ conditions, power fluctuation ≤ ±3%, and continuous working average fault-free time ≥ 100,000 hours. (3) The laser detonation assembly adapted to the turbofan power system according to claim 2, characterized in that, in a single laser branch, the output power of the main working beam group after beam combining is 1.35W, and the output power after being amplified by the power amplification unit is 29.7W; the output power of the backup beam group after beam combining is 0.36W, and the output power after being amplified by the power amplification unit is 7.92W; (4) The laser detonation component adapted to the turbofan power system according to claim 2 is characterized in that the independent output power of the main working position of a single laser branch is 29.7W, the total output power of a single branch is 37.62W when the main and backup beam groups are fully activated, the single-path power fault tolerance rate is increased by 26.67%, and the laser detonation output stability is guaranteed. (5) The laser detonation component adapted to the turbofan power system according to claim 2 is characterized in that when the main working position of the 16 laser branches outputs independently, the total output power is 475.2W, and the effective detonation power input to the quantum modified bio-based environmentally friendly energy storage solid microsphere is 332.64W, which meets the 240W effective laser input power requirement of the 24kW mechanical output of the turbofan power system, and the power redundancy rate is ≥38.6%. (6) The laser detonation component adapted to the turbofan power system according to claim 2, characterized in that the total input power of the laser end of the laser detonation component is configured to be 1kW, and the effective detonation power of the quantum modified bio-based environmentally friendly energy storage solid microspheres can reach 700W when the 16 laser branches are fully equipped with output, with a power redundancy rate of over 191.7%, meeting the system's redundancy design requirement of more than 50%. (7) The laser detonation component adapted to the turbofan power system according to claim 2 is characterized in that the VCSEL adopts a multi-junction specification, the electro-optical conversion efficiency can reach up to 74%, and is equipped with a micro heat sink and a pulse drive module, the pulse drive duty cycle is ≤10%, and it is adapted to the femtosecond pulse 100Hz working frequency requirement. (8) The laser detonation component adapted to the turbofan power system according to claim 2, characterized in that the VCSEL is equipped with a fast axis collimation structure to ensure that the efficiency of the main working beam combination is stably maintained at 90%, adapting to the compact layout requirements of the turbofan power system, and adapting to the macroscopic high-efficiency energy output requirements of microscopic small energy accumulation. (9) The laser detonation component adapted to the turbofan power system according to claim 2, characterized in that the laser detonation component is equipped with an overcurrent protection circuit and an overtemperature protection circuit, and with the backup beam group filling function, realizes stable output of laser detonation power, and ensures the excitation stability of quantum modified bio-based environmentally friendly energy storage solid microspheres. (10) The laser detonation assembly adapted to a turbofan power system according to claim 2, characterized in that the laser detonation end is powered by a solid-state battery with an energy density of 400Wh / kg, and achieves a 50% comprehensive energy reduction through the synergy of supercapacitor, flywheel energy storage and drag reduction design under all operating conditions. The net energy consumption of the laser end under all operating conditions is about 0.61kWh, corresponding to a basic solid-state battery weight of only about 1.52kg, and the battery weight does not exceed 1.98kg under high redundancy configuration: (11) A turbofan power system, characterized in that it includes a laser detonation component as described in any one of claims 2(1) to 2(10), and further includes a quantum-modified bio-based energy storage solid microsphere working fluid working module, wherein the laser energy output by the laser detonation component is input to the quantum-modified bio-based energy storage solid microsphere working fluid working module to provide energy support for the mechanical power output of the turbofan power system; the turbofan power system is adaptable to ground driving, multi-cycle vertical lifting and lowering, low-altitude high-speed cruising and multi-condition operation, and is equipped with a supercapacitor, flywheel energy storage and drag reduction structure to achieve a 50% comprehensive energy saving.

3. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-2, characterized in that, The quantum-modified energy storage microspheres have a particle size of 50 μm, are coated with a quantum energy level modulation coating with a thickness of 8 μm, and have a microsphere packing density of 1.8 g / cm³. 3 .

4. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-3, characterized in that, The four VCSEL femtosecond pulse laser emitting units arranged in a cross shape and the eight to twelve VCSEL femtosecond pulse laser emitting units arranged in a ring shape have a pulse frequency of 100 Hz. Each laser beam is amplified 22 times after microscopic energy accumulation, with a pulse width of 100–300 fs, a wavelength of 800–810 nm, and a power density of 8 × 10⁻⁶. 10 ~1×10 11 W / cm 2 The focused spot diameter is 50μm; under this configuration, the impulse coupling coefficient of the single laser drive reaches 13N / kW and the specific impulse is 400~1200s.

5. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-4, characterized in that, The triggering method of the VCSEL femtosecond pulse laser emitting unit is grouped timing triggering, with four cross-shaped channels forming a group and eight to twelve ring-shaped channels forming two to three groups, with a triggering interval of 20μs between groups.

6. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-5, characterized in that, The air compression inflow unit is a centrifugal compressor with a compression ratio of 8:1, an inlet flow rate of 1.2 kg / s, and a compressed air temperature of 180°C.

7. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-6, characterized in that, The microfluidic water storage and atomizing injection unit has a water storage capacity of 5L, an atomizing nozzle orifice diameter of 5μm, an atomized water droplet size of 3-5μm, an injection flow rate of 0.1L / min, and an operating pressure of 0.8MPa.

8. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-7, characterized in that, The quantum-modified energy storage microsphere storage and microfluidic injection unit is equipped with a precision metering pump, with a microsphere delivery rate of 0.2 g / s, a delivery pressure of 0.8 MPa, and a microfluidic nozzle orifice diameter of 0.2 mm.

9. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-8, characterized in that, The laser-supported plasma power conversion module adopts an integrated detonation chamber-turbine structure. The detonation chamber has an inner diameter of 120 mm, an operating pressure of 3.5 MPa, an operating temperature of 2200 °C, a plasma energy conversion efficiency of ≥45%, and a turbine speed of 45000 r / min.

10. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-9, characterized in that, The turbofan power enhancement output module has a fan diameter of 350mm, 12 blades, and the blades are made of carbon fiber composite material. The turbine-fan transmission ratio is 1:5, the power output efficiency is ≥80%, and the rated thrust is 12000N.

11. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-10, characterized in that, The virtual and physical power supply module reduces energy consumption by 50% in the virtual power storage unit, thereby reducing the weight of the physical power storage unit by 50%.

12. The quantum-modified energy storage microsphere working fluid turbofan power system according to claims 1-11, characterized in that, The multi-dimensional energy recovery module includes a waste heat recovery unit for exhaust gas from a finned heat exchanger and a turbine waste power recovery unit for an auxiliary generator. The waste heat recovery unit recovers exhaust gas at a temperature of 350°C with a waste heat recovery efficiency of 30%. The turbine waste power recovery unit recovers power of 25kW, and the overall energy recovery efficiency of the system is ≥32%.

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