158 results about "Gas generator" patented technology

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.

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.

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.

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.

This invention relates to the field of waste heat utilization technology and discloses a waste heat recovery device and method for a gas generator set, including a flue gas box and a waste heat recovery assembly. The flue gas box is used to circulate high-temperature flue gas, which flows in a first direction within the flue gas box. The waste heat recovery assembly includes multiple water tanks and multiple heat-absorbing plates. The multiple water tanks are respectively arranged on both sides of the flue gas box along a second direction, which is orthogonal to the first direction. The multiple heat-absorbing plates are respectively arranged on both side walls of the flue gas box along the second direction, and are spaced and staggered along the first direction. The multiple heat-absorbing plates and the flue gas box together form an S-shaped flue, with the heat-absorbing plates penetrating the side walls of the flue gas box and extending into the water tanks. The high-temperature flue gas flows in the S-shaped flue, and the heat-absorbing plates absorb heat and transfer it to the water tanks. By forming an S-shaped flue with the heat-absorbing plates and the flue gas box, the contact heat exchange area between the flue gas and the heat-absorbing plates is increased, thereby improving the absorption efficiency of waste heat from the flue gas.

The present application relates to gas power generation technical field, specifically to a kind of gas power generation concentration self-adaptive voltage stabilizing device, applied to gas source is transported to the gas supply pipeline of gas generator set, including main regulating valve, it is set on the gas supply pipeline, movable valve core is arranged in the main regulating valve, for adjusting the gas supply flow of gas supply pipeline;Heat value sensing component, it is set in sampling pipe, the inlet end of the sampling pipe is communicated with gas supply pipeline, the outlet end of the sampling pipe is communicated with external environment, to form the gas flow in the sampling pipe through the surface of heat value sensing component.This application realizes the full mechanical type, self-adaptive regulation of gas flow, simplifies system structure, reduces cost, while realizing the automatic cleaning of heat bimetallic spiral belt, ensures the long-term use performance of heat bimetallic spiral belt, and hysteresis is small, can respond to the rapid fluctuation of gas concentration in time.

The invention relates to an assembly (1) comprising a turbine engine (2) of an aircraft, a hanger (40) for mounting the turbine engine on an element of the aircraft, and a system for suspending the turbine engine on the hanger, the turbine engine having a longitudinal axis (X) and comprising, in the gas flow direction from upstream to downstream: > a fan casing (11) centered on the longitudinal axis (X) and having a first axial end (12) upstream of a fan (10), and > a gas generator (16) configured to receive the air flow generated by the fan, the hanger (40) having a substantially elongated shape along the longitudinal axis (X) and being adapted to be attached to an element of the aircraft, characterized in that the suspension system comprises at least one intake force-bearing link (30, 30a, 30b), a first end (31, 31a, 31b) of the at least one intake force-bearing link being connected to an attachment point (11a, 11b) of the fan casing (11), the attachment point being located on the first axial end or on an upstream section of the fan casing, a second opposite end (32, 32a, 32b) of the at least one intake force-bearing link being connected to said hanger.

Instrument panel (10) of a motor vehicle, with a carrier (11) for a decorative material (12), wherein the carrier (11) extends in the transverse direction of the motor vehicle in the front area of ​​the same below a windscreen (14) between a driver area and a passenger area of ​​the motor vehicle, with a passenger-side front airbag module (15) which includes a gas generator (16) and an airbag (17), with a firing channel (18) for the airbag (17) of the passenger-side front airbag module (15), wherein the firing channel (18) is limited in the longitudinal direction of the motor vehicle by a transversely extending front wall (20) and a transversely extending rear wall (21), with an airbag flap (22) incorporated into the carrier (11), which opens along a transversely extending predetermined breaking point (23) as a result of a triggering of the passenger-side front airbag module (15) and folds open about at least a transversely extending pivot axis (24), wherein the predetermined breaking point (23) is positioned adjacent to the rear wall (21) of the firing channel (18) behind the same, with a cover element (26) associated with the rear wall (21) of the firing channel (18), which is attached to the rear wall (21) by a first section (26u) and which is not attached to the rear wall (21) by a second section (26o), wherein the second section (26o) of the cover element (26) associated with the rear wall (21) is dimensioned such that, in the event of the deployment of the airbag (17) of the passenger-side front airbag module (15) caused by the triggering of the passenger-side front airbag module (15), it covers a transversely extending, rearward fracture edge (27) of the predetermined breaking point (23) as seen in the longitudinal direction of the vehicle, with a further cover element (28) associated with the front wall (20) of the firing channel (18), which is attached to the front wall (20) with a first section (28u) and which is not attached to the front wall (20) with a second section (28o), wherein the second section (28o) of the further cover element (28) is dimensioned such that, in the event of the deployment of the airbag (17) of the passenger-side front airbag module (15) caused by the triggering of the passenger-side front airbag module (15), it covers a pivot axis (24) of the airbag flap (22) running in the area of ​​the front wall (20).

This disclosure relates to the technical field of gas anti-clogging equipment. One embodiment of this disclosure provides an anti-clogging device for a gas generator, including a gas generator body. An exhaust pipe is fixedly connected to the top right side of the gas generator body. This invention, through the arrangement of a rod, a round block, and a first spring, allows the operator to pull the round block, causing the other end of the rod to detach from the rectangular block, thus releasing the fixation between the rectangular block and the collection box. At this time, the first spring is in a stretched state, allowing the collection box to be quickly removed and its contents emptied. After emptying, the operator inserts the top of the rectangular block into the connecting block and releases the round block. Due to the restoring effect of the first spring, the other end of the rod is reinserted into the rectangular block, thereby fixing the collection box. This technical solution solves the problem of slow disassembly in related technologies.

The present application relates to a kind of vice driver screen assembly and car, including vice driver screen and pull structure;Vice driver screen is rotatably connected with vice driver panel, to make vice driver screen can be opened relative to vice driver panel, and can be covered on vice driver panel;Vice driver screen in cover state avoids airbag deployment path of vice driver airbag;Pull structure is connected with vice driver airbag, can drive vice driver screen to cover under the gas generated by the gas generator of vice driver airbag, When vice driver screen is in the state of opening, if serious accident occurs, the gas generator of vice driver airbag generates a large amount of gas for airbag inflation, while also driving vice driver screen to cover quickly by pull mechanism, airbag can normally be unfolded and will not impact vice driver screen, ensure the safety of personnel in vehicle.

To provide a gas generator with improved assembly strength of the holder and cup. [Solution] The gas generator 1 comprises a cup 40 and a holder 10 to which it is mounted coaxially. The cylindrical portion 41 of the cup 40 has a flange portion 43 extending outward from the open end. The axial end face of the holder 10 facing the cup 40 is provided with an annular groove portion 16 for receiving the flange portion 43 and an annular flange portion 17. The flange portion 43 includes a first surface 43a facing the bottom surface of the annular groove portion 16 and a second surface 43b located on the opposite side. The second surface 43b includes an inclined surface that slopes away from the first surface 43a as it moves from the radially outer side of the cylindrical portion 41 towards the inside. The entire portion included in the first surface 43a that overlaps with the inclined surface when viewed along the axial direction of the cylindrical portion 41 has a planar shape perpendicular to the axial direction of the cylindrical portion 41.

A self-unlocking, self-buffering, rotary-locking multi-section drag-reducing rod, relating to the field of spacecraft structures, includes an outer shell, an intermediate shell assembly, an inner shell, a gas generator, a self-unlocking component, and a chassis. The intermediate shell assembly is located inside the outer shell, and the inner shell is located inside the intermediate shell assembly. The intermediate shell assembly includes multiple shells nested sequentially. Any two adjacent shells form an outer shell and an inner shell. The top of the inner wall of the outer shell has a raised inner ring segment, and the inner ring segment has multiple rotating U-grooves arranged circumferentially. The outer wall of the inner shell is provided with cylindrical guide pins, which mate with the rotating U-grooves one by one. The chassis is fixedly connected to the bottom of the outer shell. The gas generator is connected to the middle of the chassis and extends into the inner shell. The self-unlocking component is located at the outlet of the gas generator so that the outlet of the gas generator opens after the self-unlocking component is unlocked. This invention solves the problems of large unlocking impact, large positioning impact, and excessive gap in the locking structure of existing multi-section deployable locking drag-reducing rod structures.

The application discloses a kind of transformer oil chromatographic monitoring device pressure maintaining leak detection system and equipment, it is related to leak detection device technical field, wherein, pressure maintaining leak detection system includes power module, detection module and three control modules;Detection module includes carrier gas generator, first detection component, second detection component and third detection component;First detection component includes first detection pipeline, first pressure sensor and first electric valve group, and first pressure sensor is arranged on first detection pipeline for detecting the pressure in gas path module;Second detection component includes second detection pipeline, second pressure sensor and second electric valve group, and second pressure sensor is arranged on chromatographic detection module for detecting the pressure in chromatographic detection module;Third detection component includes third pressure sensor and bipolar pump, and third pressure sensor is arranged on degassing module for detecting the pressure of degassing module.The leak detection efficiency of the application is higher.

The application discloses a safety air bag and a steering wheel. In the application, the safety air bag comprises a main air bag, the main air bag comprises a first sheet layer and a second sheet layer, and a first cavity is formed by a relative joint seam; a gas passage is formed on the second sheet layer; a support air bag is jointed with the second sheet layer, and the support air bag has a second cavity which is communicated with the gas passage; a gas guide structure has a guide sheet layer and a pair of gas blocking sheet layers; the guide sheet layer covers the second sheet layer to form a guide channel, and the gas passage is located in the area covered by the guide sheet layer; the gas blocking sheet layers are jointed with the second sheet layer and extend into the support air bag; the pair of gas blocking sheet layers are alternately and staggeredly arranged; a gas generator passes gas into the support air bag through the guide channel; the main air bag and the support air bag are changed from a storage state to an inflation state when the gas generator is inflated, and the support air bag is supported on an instrument desk from the gap in the inflation state. Compared with the prior art, the safety air bag can be stably supported after being unfolded, and the loss risk of the driver is reduced.

This application relates to the field of high-altitude protective clothing technology, specifically disclosing a wearable high-altitude fall protection airbag device, including: a safety suit, an airbag assembly embedded in the safety suit, a gas generator connected to the air circuit of the airbag assembly, a sensor group for collecting human motion data, and a microcontroller electrically connected to the gas generator and the sensor group respectively; the airbag assembly includes multiple double-layer combined airbags, each double-layer combined airbag including an inner airbag and an outer airbag covering the inner airbag; the inner airbag is a sealed airbag, and the outer airbag is a venting airbag equipped with a dynamic pressure relief valve; the device also includes an airbag internal pressure sensor disposed inside the double-layer combined airbag, and the airbag internal pressure sensor is electrically connected to the microcontroller; the present invention proposes an inner and outer double-layer structure and a dynamic pressure relief valve, which improves the overall safety protection effect by connecting the initial deceleration of the dynamic pressure relief of the outer venting airbag with the rigid support at the end of the inner sealed airbag.

An assembly (20) composed of an elongate gas generator (10) and a clasp-shaped diffuser (22), the gas generator having an outer housing (14) with outflow openings (18) distributed in the peripheral direction (U), which define an outflow area (16) and an outflow direction, the diffuser (22) surrounding the outflow area (16), in which assembly the diffuser (22) has a central receiving opening (24) into which the outer housing (14) projects, so that the diffuser (22) surrounds an axial section of the outer housing (14) including the outflow area (16) in the peripheral sense. At least one abutment face (34) and at least one gas guide face (30) are provided on the inner side of the diffuser (22) which defines the receiving opening (24), wherein the abutment face (34) directly abuts the outer housing (14) of the gas generator (10) and the gas guide face (30) is spaced apart from the outer housing (14) in the radial direction to form at least one collection chamber (32) into which the gas flowing out of the outflow area (16) flows. The collection chamber (32) opens into at least one outlet opening (36) through which the gas exits the diffuser (22) in an outlet direction (RD) transverse to the outflow direction from the gas generator (10).

The utility model discloses a pull rod formula water control valve and gas generator relates to the field of falling into water rescue, and pull rod formula water control valve includes pull rod mechanism, still includes water -sensitive positioning mechanism, pull rod mechanism includes pull rod body, and the lower extreme of pull rod body is provided with the plug, and the spring is provided with the outer cover of pull rod body, water -sensitive positioning mechanism is used for compression spring, when water -sensitive positioning mechanism dissolves after meeting water, and pull rod body is under the action of spring and is resisted and closes the water inlet hole. It is suitable for the field of falling into water rescue (for example unmanned plane falls into water rescue).

This invention relates to a gas generator circulating liquid rocket engine split-flow drive system and method. The drive system includes a gas generator, a fuel pump, a fuel pump turbine, an oxidizer pump, an oxidizer pump turbine, and a thrust chamber. The fuel pump turbine is coaxially and fixedly connected to the fuel pump, and the oxidizer pump turbine is coaxially and fixedly connected to the oxidizer pump. The gas generator is connected to both the fuel pump turbine and the oxidizer pump turbine via pipelines. The fuel pump is connected to a first fuel pipeline and a second fuel pipeline. The first fuel pipeline is connected to and communicates with one of the gas generator and the thrust chamber, and the second fuel pipeline is connected to and communicates with the other of the thrust chamber and the gas generator. The oxidizer pump is connected to a first oxidizer pipeline and a second oxidizer pipeline. The first oxidizer pipeline is connected to and communicates with one of the gas generator and the thrust chamber, and the second oxidizer pipeline is connected to and communicates with the other of the thrust chamber and the gas generator.

This application relates to the field of gas generator set technology and discloses a wear detection and analysis system for gas generator set components, aiming to solve the problems of delayed response and noise masking in generator set wear monitoring. The system includes: an in-situ sensing component composed of high-temperature resistant ultrasonic and eddy current sensors; a signal conditioning module integrating bandpass filtering; a high-speed data acquisition matrix based on FPGA; and a distributed analysis engine. The system utilizes crankshaft position trigger signals to achieve phase alignment and employs an evaluation method based on energy center of gravity drift. By adopting the above technical solution, this application can achieve full-time domain perception and microscopic quantitative measurement of component wear, significantly improving the accuracy, robustness, and specificity of early fault identification under complex operating conditions.

Method for starting an aeronautical free turbine and single-spool gas generator turbomachine of a twin-engine aircraft including two independent electrical networks each comprising a 28V battery selectively powering a starter-generator, in which, to ensure, under the control of a turbomachine regulation computer, the startup of the turbomachine first at a voltage of 28V by putting the two batteries in parallel and then at a voltage of 56V by putting them in series while avoiding too rapid acceleration of the gas generator, the serialization of the two batteries is ordered only once the combustion chamber of the gas generator is ignited and the speed of the gas generator is greater than a predetermined speed threshold N1 for ensuring, through this serialization, a positive acceleration margin at the point of maximum drag of the gas generator.

Curtain airbag for a vehicle, featuring: a main chamber (200) installed between a roof liner (H) and a vehicle body (C) and designed to unfold downwards into an interior space of the vehicle; a diffuser (100) provided at an inlet section of the main chamber (200) connected to a gas generator and configured with a first outlet (120) and a second outlet (140) receiving gas from the gas generator, the diffuser (100) including a connected section (130) configured to partially or completely close the first outlet, and the diffuser (100) configured to increase the amount of gas supplied to the main chamber (200) when the connected section (130) is opened by an internal pressure of the diffuser (100); and an additional chamber (300) connected to the second outlet (140) of the diffuser (100) to receive gas from the diffuser (100), wherein the additional chamber (300) is configured to be inflated between the headliner (H) and the vehicle body (C) and to separate the headliner (H) from the vehicle body (C), wherein a one-way outlet section (150) is provided at the second outlet (140) of the diffuser (100); a feed opening (155) of the additional chamber (300) is formed on the one-way outlet opening section (150); and a closure band (157) is formed along an edge of the supply opening (155) of the additional chamber (300) so that the closure band (157) is pulled to close the one-way outflow opening section (150).

This utility model relates to the field of satellite propulsion equipment technology, and specifically provides an integrated gas-fuel hybrid propulsion system, including an integrated tank, gas generator, gas container, and thruster. The tank contains a flexible metal diaphragm, with one side forming a gas chamber and the other a liquid chamber. The gas chamber has a gas inlet, and the liquid chamber has a liquid inlet. The liquid inlet's output pipe is connected to the gas generator, the gas generator's output pipe is connected to the gas container, and the gas container's output pipe is connected to the thruster. This utility model solves the problems of low specific impulse in cold gas propulsion systems, heavy thruster mass and large envelope size in monocomponent chemical propulsion systems, and the difficulty in achieving low thrust output in bicomponent chemical propulsion systems, thus meeting the application requirements of satellites.

The application discloses a kind of oilfield associated gas VOC emission SOFC collaborative processing control method and system.Method includes: collecting initial purification gas state data;Based on electrical load demand, through distribution model output shunt instruction, control intelligent shunt valve and gas shunt to gas generator set and reforming equipment;According to VOCs component, calculate carbon molar flow to adjust reforming steam quantity, prevent carbon deposition and output hydrogen-rich fuel gas for SOFC power generation;When load fluctuation occurs, generator set power is adjusted first, and SOFC constant power output is maintained;Calculate the predicted temperature of mixed tail gas, if lower than the ignition temperature of purification bed, then increase SOFC cathode air intake to heat up.The application realizes the adaptive coordinated operation of power generation system, and takes into account power supply reliability, gas economy and efficient and clean treatment of tail gas.

The invention relates, among other things, to a pyrotechnic current separator (1) with a gas generator (70), a separating piston (90) movable in a firing channel (80) and an electrical conductor (50) which penetrates the firing channel (80) in the initial state before the gas generator (70) is triggered and is interrupted by the separating piston (90) after the gas generator (70) is triggered.According to the invention, a section of the firing channel (80) facing the gas generator (70) is formed by a guide tube (100) which guides the separating piston (90) towards the conductor (50) after ignition of the gas generator (70), the guide tube (100) is arranged in a hole (110) of a housing part (10) and the inner cross-section of the hole (110) is at least partially larger than the outer cross-section of the guide tube (100) and a gap (SP) is present between the hole (110) and the guide tube (100) before the gas generator (70) is triggered, which allows the guide tube (100) to expand radially outwards after the gas generator (70) is triggered by the gas pressure of the gas generator (70).

Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.

The utility model discloses a kind of beet secondary cleaning machine, and the equipment relates to beet cleaning equipment technical field;Including primary cleaning tank, gas generator, exhaust pipe, screw conveyor, conveying groove, secondary cleaning tank, cleaning roller, flush top cover, spray head, spray pipe;The side of the primary cleaning tank is equipped with gas generator;Gas generator is connected with exhaust pipe, and exhaust pipe is led into primary cleaning tank;The discharge port is communicated with the feed end of the conveying groove arranged obliquely;Screw conveyor is equipped in the conveying groove;More than one cleaning roller is arranged in the inside of the secondary cleaning tank;Spray head is fixedly arranged below the flush top cover;Through the equipment, beet is secondary cleaned, and after preliminary silt primary cleaning filtration in sink, it is then entered secondary stage cleaning, and secondary stage cleaning is mainly through physical friction plus flush combined mode, to ensure cleaning effect, while reaching the effect of cleaning equipment itself, ensure that equipment long-time stable operation.

A gas generator comprising: - a main gas chamber (10) having a side wall, - gas (20) stored under pressure in the main gas chamber (10), - a pyrotechnic chamber (30) arranged in the main gas chamber (10), - propellant (40) arranged in the pyrotechnic chamber (30) and exposed to the gas (20) stored under pressure, - a pyrotechnic igniter (51) attached to the side wall of the main gas chamber (10) and intended to trigger combustion of the propellant (40), characterized in that the gas generator comprises a sealing element, such as a casing (60), separate from the pyrotechnic igniter (51) and arranged between the pyrotechnic igniter (51) and the gas (20) stored under pressure. Figure for the abbreviation: Fig. 1