7results about "Intermittent jet plants" patented technology

The application provides a knock engine, comprising: a knock power unit comprising at least two knock chambers and a transmission member, each knock chamber being provided with a reciprocating piston; one end of the transmission member being in transmission connection with a compressor, and the other end of the transmission member being connected with the pistons in the at least two knock chambers respectively, so that when the at least two knock chambers are ignited, the transmission member is driven to move through the pistons, and the compressor is driven to work; the compressor being in communication with the at least two knock chambers, and being used for providing compressed air to the at least two knock chambers. The reverse transmission energy of the knock chamber is directly utilized to drive the compressor through the piston-transmission shaft mechanism, so that the traditional turbine component is completely omitted. This fundamentally avoids the inherent contradiction that the turbine efficiency is low due to the difficulty in matching between the intermittent and non-steady-state work of the knock combustion chamber and the continuous and steady work of the turbine. The turbine is omitted, the engine structure is simplified, the manufacturing cost and the maintenance difficulty are reduced, and the working reliability of the engine is improved.

The application relates to the field of aerospace propulsion technology, and discloses a multi-mode cluster shock-absorbing pulse detonation engine with intelligent gap control; the engine comprises multiple explosion tube bodies in a concentric circle layout, a hydraulic sealing system, a fuel supply system, an electric arc igniter, an integrated thermal management system and an intelligent control system. The core lies in: the sealing reliability is ensured through intelligent dynamic gap control; a wide-range flight is adapted through multi-mode gas supply; precise ignition control is realized through multi-sensor fusion; waste heat is recycled and thrust gain is generated through integrated thermal management; and vibration and noise are inhibited through cluster detonation interference with a specific layout. The application has the dual-mode intelligent switching capability of high-frequency large thrust and low-frequency high efficiency, integrates health monitoring, and forms an advanced propulsion system solution scheme with high reliability, wide-range self-adaptation and low vibration.

The application discloses a supercritical water pulse detonation device for treating battery waste liquid, which comprises a pulse detonation chamber for oxidizing and decomposing organic pollutants by supercritical water, wherein each pulse emitter in the pulse detonation chamber is provided with a pulse emission tube, the pulse emission tube of each pulse emitter is connected to an energy-gathering ring, and a pulse detonation assembly is arranged in the pulse emitter. The application designs the supercritical water pulse detonation device for treating battery waste liquid, which can cause a violent oxidation reaction in the pulse detonation chamber, is an important component for realizing supercritical water oxidation treatment of battery waste liquid, significantly improves the degradation efficiency of organic pollutants in the battery waste liquid, reduces energy consumption, and has important environmental protection and engineering application values.

This invention discloses a subsonic ramjet engine based on counter-rotating rotary detonation flame stabilization ignition, belonging to the field of subsonic ramjet engine flame stabilization ignition technology. It includes an intake cooling channel, an integrated fuel supply device, and a symmetrical rotary detonation flame stabilization device. The intake cooling channel cools the engine wall temperature; the integrated fuel supply device achieves high system integration, low flow resistance loss, and lightweight and convenient design; the symmetrical rotary detonation flame stabilization device uses a counter-rotating jet to assist in creating a stable low-speed recirculation zone in the main combustion chamber, thereby achieving flame stabilization. Furthermore, the continuously operating rotary detonation generator acts as a pre-combustion tube, providing forced ignition to the main combustion chamber. This highly integrated invention effectively cools the combustion chamber wall temperature of the subsonic ramjet engine, improves combustion stability, and significantly increases the ignition success rate of the main combustion chamber, thus providing an effective technical approach for subsonic ramjet engines to operate within a wide range of conditions.

The application discloses a time sequence control rotating detonation engine system combined with a turbojet engine, which comprises a turbojet engine, a shell sleeved on the periphery of the tail nozzle of the turbojet engine, a cylindrical base coaxially arranged on the inner side of the shell, and a fan-shaped detonation tube. A cover driven by an electromagnetic push rod is arranged at the top end of each detonation tube. A sequential ignition control device is arranged, and a fuel supply unit of the sequential ignition control device comprises an oil pump, a fuel coil pipe coiled in the cylindrical base, a common rail ring outside the shell, and a plurality of fuel injectors. A control unit adopts a mechanical time sequence controller, and through rotating a moving contact on an outer rotor, the mechanical time sequence controller sequentially connects static contacts on an electrode distributor, synchronously triggers electromagnetic push rods and fuel injectors of corresponding detonation tubes, and realizes multi-tube sequential cycle detonation. The application recovers exhaust heat energy to preheat fuel through a coaxial integrated structure, supplies air by using an ejecting effect, replaces a complex electronic system with a simple and reliable mechanical control, and realizes efficient, compact, wide working condition adaptation and thrust enhancement.

The application discloses a valveless pulse jet engine quick starting device and method, which comprises a valveless pulse jet engine, an igniter, a blowing system and an oil supply system; after alcohol is filled in the alcohol tank and the engine starts, the igniter starts to work first, alcohol is pressed into the combustion chamber by fuel, the blowing system blows high-pressure air into the combustion chamber from the air inlet, and the blowing system and the igniter are closed in turn after a period of time, so that the engine can be started reliably. The method of the application can improve the starting reliability of the engine and greatly shorten the starting time of the engine by using alcohol combustion assisting preheating and high-pressure air blowing excitation.

The present application relates to the field of hypersonic aerodynamics and intelligent control technology, especially to a bulge assisted oblique detonation wave initiation intelligent control method based on a feedforward neural network, which is used for the design and control of high-performance propulsion systems such as scramjet engines and oblique detonation wave thrusters. Wave structure data under different bulge geometric parameters and inflow conditions are obtained through numerical simulation technology. Image processing technology is used to extract feature parameters, label wave structure types, and construct sample data sets. A multi-layer feedforward neural network is used to train the samples, and the optimal network structure is selected through cross-validation to establish a nonlinear mapping model between the bulge geometric parameters and the wave structure categories. The neural network is used to quickly identify and predict the wave structure under unknown conditions, and the probability distribution is output to evaluate the confidence. According to the wave structure category and the control rule library, the height, length, position or inclination angle of the bulge is adjusted to realize real-time intelligent control of the oblique detonation wave system.