471 results about "Gas generator" patented technology

The present application provides an oil-gas separation apparatus capable of implementing complete degassing and methods. The apparatus comprises: a piston cylinder and a degassing cylinder, a degassing solenoid valve being arranged between the degassing cylinder and the piston cylinder, one end of the degassing solenoid valve extending into the interior of the piston cylinder, and the other end thereof being in communication with the degassing cylinder; a variable speed diaphragm pump, an air intake end thereof being in communication with the atmosphere and an air discharge end thereof being in communication with the degassing cylinder for drawing ambient air, and used for cleaning a gas path of the oil-gas separation apparatus, and providing power for the degassing cylinder, thereby replacing a design involving a carrier gas cylinder or a gas generator; and a main control module. According to the present application, the piston cylinder, the degassing cylinder, the degassing solenoid valve, and the variable speed diaphragm pump are integrated and are uniformly controlled by the main control module, so that high-efficiency oil and gas separation is implemented. A unique degassing control method and a concentration calculation method are designed, so that fast and efficient degassing is implemented, nearly complete degassing is achieved without correcting a degassing rate, a mathematical model for inverse calculation of an oil sample concentration on the basis of a gas concentration is simplified, and concentration conversion is convenient.

The invention discloses a heating control method for an engine gas delivery pipeline of a marine gas generator set, which relates to the technical field of marine gas power systems, and comprises the following steps: collecting multi-dimensional environment state information of the gas delivery pipeline in real time, analyzing gas components and pressure fluctuation data, and calculating the temperature of the gas delivery pipeline; a theoretical dew point temperature and a potential paraffin precipitation temperature under real-time pressure are calculated by combining a fuel gas physical property database, a real-time heat exchange model is constructed by combining a pipeline outer wall temperature gradient and a cabin environment temperature, theoretical temperature attenuation curves of different positions of fuel gas in a pipeline are obtained, condensation and paraffin precipitation risk positions and degrees are predicted after comparison, and a real-time heat exchange model is established. And differential electric heat tracing control strategies of different sections of the pipeline are generated in combination with relative humidity data of the cabin. The method can adapt to the real-time physical property of gas and the heat exchange state of the pipeline section, and the heating control execution mode of the gas pipeline is optimized.

The utility model discloses a collection device for combustion products of an aero-engine fuel-rich gas generator, which adopts an asbestos fiber material, a zeolite molecular sieve, sandy soil and a filter screen for multiple filtration, and filters and collects solid-liquid components in outlet flue gas; and under the action of the water-cooling coil pipe, the residual outlet flue gas is cooled to a safe temperature, and the low-pressure gas tank is utilized to complete the collection of gas components. The collecting device disclosed by the utility model is stable in material performance, low in price, good in usability and service life, and capable of obtaining remarkable working and economic benefits.

A non-full-covering single flight vehicle helmet comprises a helmet body, goggles are arranged on the front portion of the helmet body, a temporal bone-occipital bone annular air cushion is arranged on the inner wall of the lower portion of the helmet body, a top bone-frontal bone cap-shaped air cushion is arranged on the inner wall of the upper portion of the helmet body, an inflatable neck support is arranged at the bottom of the helmet body, a gas generator is arranged on the back of the helmet body, and the inflatable neck support is connected with the gas generator through a pipeline. The inflatable neck support is contained in a net-shaped braid arranged along the edge of the bottom of the helmet, the upper portion of the net-shaped braid is connected to an interlayer between the helmet and the parietal bone-frontal bone cap-shaped air cushion, and the net-shaped braid is made of elastic materials. The temporal bone-occipital bone surrounding air cushion and the parietal bone-frontal bone cap-shaped air cushion are both non-trigger type air cushions, are provided with snap fasteners connected with the helmet, and are both of a multi-layer structure. According to the scheme, the non-triggering air cushion is integrated in the helmet, and the triggering type neck support air bag is arranged, so that a pilot is effectively protected.

This utility model discloses a fixing structure for a gas generator, comprising: a semi-circular fixing shell detachably mounted on an airbag support; a limiting baffle is provided on the left end of the semi-circular fixing shell, and a limiting constriction is formed on its right end, which cooperates with a limiting groove formed on the surface of the gas generator's outer shell; and a limiting snap-fit ​​piece located inside the semi-circular fixing shell, the limiting snap-fit ​​piece having a snap-fit ​​groove for fixing the excitation end of the gas generator; during installation, the gas generator is installed into the semi-circular fixing shell, the left end face of its excitation end abuts against the inner surface of the limiting baffle, the limiting groove of which cooperates with the limiting constriction of the semi-circular fixing shell for limiting, and one end of the airbag deflation strap extends between the limiting baffle and the limiting snap-fit ​​piece and is tied to the excitation end of the gas generator. The fixing structure of this utility model is easy to install, has better reliability, lower cost, and stronger versatility.

The invention relates to a hydrazine arc thruster support in split design, and relates to the field of spacecraft supports, the hydrazine arc thruster support comprises a generator support and a thruster support, the generator support is fixedly connected with a fuel gas generator, the thruster support is fixedly connected with an arc thruster, and the generator support is made of an aluminum alloy material and is in heat conduction connection with a satellite mounting surface; the thruster bracket is made of a titanium alloy material and is in heat insulation connection with a satellite mounting surface; and one side of the generator bracket is fixedly connected with one end of the thruster bracket through a blocky bracket connecting piece. The electromagnetic valve has the advantage that the use temperature and the mounting surface temperature of the electromagnetic valve are effectively reduced.

The application provides an air bag device and a manufacturing method thereof, and relates to the technical field of air bags. The air bag device comprises a main cloth, a first reinforcing piece and a gas generator. The first reinforcing piece is laminated on the inner panel of the main cloth corresponding to the installation range of the gas generator. A first through hole for installing the gas generator is arranged on the main cloth in the installation range of the gas generator. A second through hole for the gas generator is arranged on the first reinforcing piece. The projection of the second through hole on the main cloth does not overlap with the position of the first through hole. At least a part of the second through hole is a slanting cut. Since the through holes are arranged in a staggered manner in the laminated cloth, after the air bag is folded, the cloth is staggered to cover the through holes, the air tightness of the air bag is improved, and the performance of the air bag system is optimized.

The utility model discloses a high purity gas generator relates to gas generator technical field, the high purity gas generator includes tank, the tank top exhaust pipe one end is provided with the pressure gauge, the pressure gauge one end is provided with the generation module, the lower end of tank is provided with the transportation subassembly, the transportation subassembly is provided with the pressure gauge one end. A protection assembly is arranged on one side of the transportation assembly, a stabilizing assembly is arranged at the lower end of the protection assembly and moves up and down along the transportation assembly, the transportation assembly comprises a transportation base, a limiting inserting groove is formed in the upper surface of the transportation base, and the edge of the bottom end of a tank is inserted into the limiting inserting groove. According to the scheme, the problems that in the transportation process of a tank body of an existing gas generator, the tank body easily shakes and falls off due to inertia, a limiting structure is installed, most of the limiting structures are arranged outside the tank body in a sleeving mode and fixed through bolts, time and labor are wasted during installation and disassembly, and consequently the tank body is inconvenient to install and disassemble are solved.

An ejection device (100) for a gas generator, the ejection device (100) for ejecting a combustion product, comprising: a detonator (101) with an ignition charge and an ignition area (102) designed to burn the ignition charge; a pyrotechnic device (121) arranged to be burned by burning the ignition charge; a cup (104) made of metal, wherein the cup (104) has a base (107) and a peripheral wall (105), wherein the bottom surface (107) is arranged opposite the ignition area (102), the peripheral wall (105) adjoins a peripheral edge of the bottom surface (107) and is arranged to surround the ignition area (102), wherein the cup (104) further comprises a receiving space (120) which is defined by the peripheral wall (105) and the floor area (107) is formed and receives the pyrotechnic agent (121), wherein the bottom surface (107) of the cup (104) contains a through-hole (108) through which the receiving chamber (120) and an exterior area of ​​the cup (104) are connected, wherein the through-hole (108) is formed by several peripheral through-hole edges (108a, 108b, 108c, 108d), and the adjacent peripheral through-hole edges (108a, 108b, 108c, 108d) are connected to each other at a predetermined connection point, the through-bore (108) contains a narrow part (115) in which the width of the through-bore (108), formed by each of parts of the two peripheral through-bore edges (108a, 108b, 108c, 108d) of the several peripheral through-bore edges (108a, 108b, 108c, 108d), gradually decreases with increasing distance from a center of the bottom surface (107) to the peripheral edge of the bottom surface (107), and the narrow part (115) is closer to the peripheral edge of the bottom surface (107) than a non-narrow part (125) formed by each of the other parts of the two peripheral through-bore edges (108a, 108b, 108c, 108d), and the narrow part (115) is a predetermined part in which stress due to the emission of the combustion product is concentrated, and the bottom surface (107) is designed to be split starting from the narrow part (115), and the peripheral wall (105) is designed to be split.

This invention provides a multi-layer gradient composite sheath flame-retardant power cable, relating to the technical field of power cables. It includes, from the inside out, a conductor core unit, a filling layer, an inner reinforcing layer, and a multi-layer gradient composite sheath. Several groups of conductor core units are uniformly distributed along the circumference of the cable. Each conductor core unit includes a conductor core, the outer wall of which is covered with a conductor insulation layer. A fire-resistant carbon layer is coaxially arranged on the outer side of the conductor insulation layer. This invention achieves initial fire extinguishing by placing a fire-extinguishing medium capsule inside the conductor core unit and filling the cavity with fire-extinguishing medium. Combined with a thermoplastic sealing film and a gas generator, when the temperature reaches the melting temperature of the thermoplastic sealing film, the film melts, and the fire-extinguishing medium is released through an overflow hole, directly acting on the heated surface of the conductor insulation layer. Simultaneously, the gas generator decomposes upon heating, releasing nitrogen and carbon dioxide gases, which are released through an outlet pipe, forming a flame-retardant gas atmosphere.

The invention discloses a signal control circuit applied to a parachute opening controller, which is used for activating an action response component electrically connected to the parachute opening controller, the action response component comprises a steering engine and / or a gas generator, and the signal control circuit comprises a single chip microcomputer, a power supply module, a sensing module, an activation module and a heating module, the power supply module supplies power to the single-chip microcomputer, the sensing module, the activation module and the heating module. The activation module is electrically connected to the action response component; the single-chip microcomputer collects external environment information through the sensing module, and when the external environment information meets the parachute opening condition, the activation module is controlled to activate the action response component. Wherein the heating module comprises a heating circuit and a graphene flexible electrothermal film; and the heating circuit supplies power to the graphene flexible electrothermal film, so that the graphene flexible electrothermal film is electrified to heat. According to the signal control circuit applied to the parachute opening controller, a powerful guarantee is provided for safe operation of the parachute opening controller in an extreme environment through the heating module.

The invention relates to the technical field of aviation safety, in particular to a parachute type slow descent and tail end buffering emergency lifesaving system and method for an ultra-low-altitude aircraft. The system comprises an umbrella-shaped slow descent module, a tail end buffer module, a detection and control module and an emergency energy discarding module. When the detection and control module judges that the aircraft is out of control, the emergency energy discarding module is triggered to throw away the battery pack, meanwhile, the umbrella-shaped slow descent module is triggered to pop out of the canopy, and the canopy is rapidly inflated through high-pressure gas, so that the aircraft is stably and slowly descended; before touching the ground, the gas generator of the tail end buffering module enables the buffering air bag to expand rapidly, impact energy is absorbed through compression deformation and controllable pressure relief, and safe landing is achieved. The problem that traditional lifesaving equipment cannot effectively work in the ultra-low-altitude environment is solved, the system has the advantages of being rapid in response, high in reliability and good in buffering effect, and the safety of the ultra-low-altitude aircraft is remarkably improved.

The invention discloses a self-adaptive automobile safety air bag module which comprises an air bag shell, an air bag assembly and an air generator are installed in the air bag shell through a supporting ring assembly, and a bottom cover is fixedly arranged on the bottom face of the air bag shell through bolts of the supporting ring assembly. The air bag is provided with an adjusting exhaust port and connected with a tying rope, and one end of the tying rope is tied to the adjusting exhaust port and used for controlling opening and closing of the adjusting exhaust port. A fixing seat is clamped on the bottom surface of the air bag shell and located on one side of the center hole, a cavity with an opening in the upper end is formed in the fixing seat, a pin puller is clamped in the cavity, and the other end of the tether penetrates through the opening in the bottom surface of the air bag shell and the opening in the upper end of the cavity and is arranged on a pin shaft of the pin puller in a sleeving mode to be used for controlling release of the tether. Therefore, opening and closing of the exhaust port are controlled and adjusted. The air bag has the beneficial effects that the exhaust flow of the air bag can be adjusted, and the protection requirements of passengers with different collision strengths and different body types can be met.

The application provides a piling device, which comprises a water hammer bin, a pressure generating assembly and a gas generator replacing device, the pressure generating assembly comprises a pressure chamber, a gas guide structure and a gas generator, the gas guide structure is fixed to the side wall of the pressure chamber and communicates with the pressure chamber, the gas generator comprises a plurality of components for loading gas generating agent, the gas generator replacing device comprises a gas generating agent conveyor and a mechanical arm, wherein the gas generating agent conveyor is used for conveying the components loaded with the gas generating agent from one side close to the workboat end to one side close to the mechanical arm, and conveying the components in a second use state from one side close to the mechanical arm to one side close to the workboat end, and the mechanical arm is used for fixedly connecting the components in a first use state with the gas guide structure, and transferring the components in the second use state from the gas guide structure to the gas generating agent conveyor; the piling device provided by the application can realize automatic installation or dismounting of the gas generator.

The invention discloses a dynamic measurement system for the ablation rate of a thermal protection material of an aircraft under high-temperature fuel gas. The dynamic measurement system comprises a sample placement unit, a fuel gas generation unit, laser displacement equipment and a data acquisition and processing system, the sample placement unit is used for placing a thermal protection material sample piece, the fuel gas generation unit comprises a fuel gas generator, and a flame nozzle of the fuel gas generator is used for being aligned with the surface of the thermal protection material sample piece; the laser displacement equipment dynamically captures displacement change signals of surface retreating of the thermal protection material sample piece under the action of the fuel gas generator; and the data acquisition and processing system calculates the dynamic ablation rate of the thermal protection material under the high-temperature fuel gas according to the displacement change signal. The laser displacement equipment is matched with a data acquisition system to finish dynamic acquisition of the retreat amount and calculation of the dynamic ablation rate, a dynamic measurement system is established, and the problems that the ablation rate of the thermal protection material cannot dynamically respond to changes and the accuracy of an ablation model prediction result is low when traditional static measurement is adopted at present are solved.

An airbag for a vehicle, comprising: a main cavity air bag (6), which is used for coming into contact with the positions of the head, neck, and chest of a front-seat passenger when being inflated; a support structure, which is used for supporting the main cavity air bag (6) once the main cavity air bag (6) has been inflated; and a gas generator (11), which is mounted in a ceiling (4) of the vehicle and is communicated with the main cavity air bag (6) for inflating the main cavity air bag (6).

The application discloses a gas generator water supply system and a water supply method, and relates to the technical field of spacecrafts, wherein the gas generator water supply system comprises a water tank, a variable frequency water pump, a water supply main pipeline, a main valve, a plurality of branch pipelines and a plurality of gas generators. The inlet of the variable frequency water pump is connected with the water tank, the outlet of the variable frequency water pump is connected with the water supply main pipeline, the water supply main pipeline is connected with a backflow pipeline, the backflow pipeline is provided with a backflow cut-off valve and a backflow regulating valve, the outlet end of the backflow pipeline is communicated with the water tank, the main valve is arranged on the water supply main pipeline and located downstream of the connection position with the backflow pipeline, the outlet of the main valve is connected with the plurality of branch pipelines, and the plurality of branch pipelines are used for connecting the plurality of gas generators arranged in parallel. The gas generator water supply system and the water supply method can ensure that water flow can be quickly supplied, and can avoid the problem that irreversible damage is caused to the water pump and the pipeline system by the great water hammer generated when the valve of the gas generator is opened and closed.

A multi-flow turbine engine for an aircraft, the turbine engine having a gas generator with geometrical characteristics allowing it to have at its periphery a cold compartment larger than its hot compartment.

This invention discloses a passenger-side airbag assembly and a vehicle dashboard, relating to the field of vehicle airbag technology. It includes an integrated injection-molded housing, on which a gas generator and an airbag assembly are mounted. The gas generator is connected to a grounding terminal via a grounding harness. The outer mounting surface of the housing has horizontally and vertically distributed support ribs, with a retaining wall on the inner side of each rib. The retaining wall has a notch, and a slot is provided near the notch on each support rib. The slot and notch are used to restrict the rotation of the grounding terminal during assembly. This invention solves the problem of grounding terminal rotation without requiring additional tooling for positioning, ensuring effective grounding of the "generator housing" metal of the PAB assembly.

The utility model discloses a fire extinguishing system of an AGV (Automatic Guided Vehicle) with an air bag cover, which is characterized in that a parking garage comprises parking spaces, a fire extinguishing system and an automobile, the fire extinguishing system comprises a fire early warning system and the AGV, the AGV comprises an AGV body, a fire extinguishing device, the air bag cover and a high-pressure gas generating device, and the fire extinguishing device comprises a fire extinguishing medium. The air bag car cover comprises a contraction body and an expansion body. When the fire hazard early warning system detects that an automobile in a certain parking space becomes a dangerous automobile with a fire hazard or a fire hazard, information is immediately sent to the AGV fire fighting truck, the AGV fire fighting truck immediately runs to a set position beside the dangerous automobile, the high-pressure gas generating device is started to work, and the high-pressure gas generating device is started. After being inflated, the contraction body pops up and is unfolded to form an expansion body for covering a dangerous automobile, and the fire extinguishing device extinguishes fire through a fire extinguishing medium; for a fire hazard in the parking garage, the parking garage has the three advantages of quick response, accurate positioning and covering for fire extinguishment.

The invention relates to a vehicle occupant protection system (10), comprising an airbag module (12), an inflation hose (14) and an external gas generator (16) which is spaced apart from the airbag module (12) and which is fluidically connected to an airbag (18) of the airbag module (12) via the inflation hose (14). The bladder (18) has a chamber and a bladder wall (20) defining the chamber. In this case, the inflation hose (14) extends through an opening (30) in the airbag wall (20) into the chamber of the airbag (18).

The invention relates to a propulsion system (1) which is capable of generating a modular thrust, the propulsion system (1) comprising a body (10) which encloses a combustion chamber (8) in communication with at least one nozzle or propulsion valve (6) situated outside the body (10), the body (10) further enclosing a solid-fuel gas generator (9) which is configured to generate gases in the combustion chamber (8), wherein the gas generator (9) comprises a plurality of unit modules (5) which can be ignited independently by at least one combustion triggering device (40) and are separated from one another by a thermal insulator (30), the unit modules (5) being housed inside the body (10) and these unit modules (5) extending along the axis (A) while being distributed around the axis (A).

The application discloses a non-explosive seismic source device and a shock method for seismic exploration, relates to the technical fields of seismic exploration and blasting, and comprises a blasting cylinder, a top cover and a pipe plug, the pipe plug is arranged in the blasting cylinder, one end of the blasting cylinder is sealed, the other end is connected with the top cover through threads, and a gas-stopping pad, a sponge column and a gas generator are sequentially arranged in the blasting cylinder. The non-explosive seismic source device and the shock method for seismic exploration have the advantages of simple structure, easy material acquisition, no influence of the use environment, no harmful gas generation, no need of approval procedures, no need of a blasting operation certificate for an operator, easy operation after simple training, good coupling between the device and a stratum, use in complex terrain areas, use in water areas such as lakes and oceans, and high safety and good operability compared with a gas explosion seismic source.

FIELD: rocket science.SUBSTANCE: invention concerns the design of a ramjet engine. The ramjet engine body is a structure consisting of several layers, including: an internal heat-protection layer made of a composite material based on a thread frame of heat-resistant fibers impregnated with an elastic polymer binder, a power body based on a high-temperature polymer composite material and an external heat-protection layer made of a composite material based on an elastic polymer binder and a finely dispersed mineral filler. Thanks to the use of layers of external and internal thermal protection, it becomes possible to use a polymer composite material for the power casing.EFFECT: reducing the labor intensity of manufacturing and weight of the product and increased energy-mass perfection of the propulsion system.1 cl, 2 dwg

The application belongs to the technical field of aviation second power system, and discloses an airplane emergency power gas generating system and method based on water enhancement technology, wherein the system adopts fuel oil and high-pressure gas cylinder gas supply to combust in a gas generator, high-temperature and high-pressure gas is generated as the emergency power of the airplane; when the fuel oil and air are mixed and combusted in the gas generator, water is sprayed in the gas generator, water is used as the combustion coolant, and the compressed air amount used by the gas generator after combustion to generate unit gas is reduced. The aviation kerosene and high-pressure air are used as the fuel and oxidant, the fuel system has the advantage of good compatibility with the airplane, the compressed air amount used by the gas generator to generate unit gas is greatly reduced, the working time of the gas generator system is prolonged, the expensive catalyst is not used, and the problems of short service life of the gas generator system and high price of the catalyst of the traditional emergency power system are avoided.

A gas generator comprising: - a gas chamber (10) with a first orifice (21) having a first passage surface, - a main cover (51) closing the first orifice (21), - pressurized gases stored in the gas chamber (10), - a pyrotechnic chamber (30) arranged within the gas chamber (10), - an ignition device (40), characterized in that the gas generator comprises at least one partition wall (33) of the gas chamber (10) with at least one second orifice (22) having a second passage surface smaller than the first passage surface, and in that the pyrotechnic chamber (30) is arranged between the partition wall (33) and the first orifice (21). Figure for the abbreviation: Fig. 1

The invention discloses a high-flux gas transmittance detection device and method. The high-flux gas transmittance detection device comprises a detection cavity, a gas generator, a gas mixer, an integrated intelligent main body, a temperature and humidity control system and a screw cover, the detection cavity is a cylindrical cavity, one end of the detection cavity is provided with a spiral thread, one end of the detection cavity is in threaded connection with the spiral cover through the spiral thread, the spiral cover is used for installing and fixing a sample film at one end of the detection cavity, a piston is arranged in the detection cavity, and the piston is connected with the detection cavity. Scale marks and a final position line are engraved on the outer wall of the detection cavity, the scale marks facilitate measurement of the moving distance of the piston, and the maximum volume of the detection cavity is achieved when the piston is pushed to the position of the final position line. According to the invention, the gas permeability of the packaging film can be conveniently detected.

An aircraft turbine engine (10) comprises: - a gas generator (12), - a fan (14), and - an electric machine (70), the stator (70b) of which is connected to a power electronics circuit (78) by at least one electrically conductive rod (80) extending substantially radially with respect to the axis within an IGV (52a) forming a component of a vane angular segment (G2), the rod (80) being configured to be disassembled and removed from the turbine engine by disassembling and removing the segment.

The application discloses a turbo-shaft engine ground bench performance debugging method based on turbine guide vane area, comprising the following steps: obtaining different gas turbine guide vane areas A GT and power turbine guide vane areas A PT under the condition of same gas generator physical rotating speed t4.5 , corresponding gas temperature change data ΔT, power change data ΔP, and forming gas temperature change and power change tables respectively; obtaining different A GT and A PT under the condition of same take-off power g , corresponding specific fuel consumption change data Δsfc and rotating speed change data Δn, and forming specific fuel consumption change table and rotating speed change table respectively; obtaining A GT and A PT corresponding to the change data which simultaneously satisfy the related constraint conditions from the two-dimensional linear interpolation of each table, and taking A GT and A PT as candidate A GT and A PT ; and finding A GT and A PT with the minimum adjustment amount for performance debugging. The application can improve the debugging efficiency and reduce the debugging cost.

To provide an activated gas generation device that can treat more efficiently, and a method thereof.SOLUTION: An activated gas generation device comprises a plasma generation unit 1 that applies discharge to raw material gas, a plasma control unit 2 that controls the plasma generation unit, a raw material gas heating unit 5 that sets the temperature of the raw material gas to a temperature higher than ordinary temperature, a raw material gas control unit 6 for adjusting the heating temperature in the raw material gas heating unit, and an activated gas ejection unit 3 that ejects the activated gas generated in the plasma generation unit.SELECTED DRAWING: Figure 1