1436 results about "Gas generator" patented technology

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

The invention provides a gas generator set fault detection method and device, equipment and a storage medium, and belongs to the technical field of gas power generation, and the method comprises the steps: obtaining target detection data collected by different types of sensors of a gas generator set, and calculating a correlation coefficient between the target detection data and a target parameter; adding the target detection data of which the correlation coefficient is greater than a set threshold value into a fusion candidate set, and calculating a target weight corresponding to each target detection data in the fusion candidate set; based on each piece of target detection data in the fusion candidate set and the target weight corresponding to each piece of target detection data, obtaining comprehensive detection data; performing feature extraction on the comprehensive detection data to obtain time domain features and frequency domain features corresponding to the comprehensive detection data; and determining the fault type of the fault of the gas generator set based on the time domain feature and the frequency domain feature. According to the gas generator set fault detection method and device, the equipment and the storage medium provided by the invention, the accuracy of fault detection can be improved.

A triple-flow turbine engine for an aircraft, this turbine engine having a longitudinal axis and including upstream suspension elements which are located in a first plane perpendicular to the axis and are connected or fixed to the gas generator of the turbine engine; downstream suspension elements which are located in a second plane perpendicular to the axis and are connected or fixed to the gas generator; and thrust-absorbing rods which include first ends which are connected or fixed to the gas generator and opposing second ends which are located in a third plane perpendicular to the axis, wherein the first, second and third planes are located at a cold compartment of the gas generator.

A gas generator includes an igniter, a partition member that axially partitions a space in the inside of a housing into a gas generating agent accommodation chamber and a filter chamber, and a gas generating agent and a coil spring accommodated in the gas generating agent accommodation chamber. The coil spring is interposed between the partition member and the gas generating agent and fixes the gas generating agent while it keeps the gas generating agent away from the partition member. V1 represents a volume of the gas generating agent accommodation chamber and V2 represents a volume of a non-filled space which is a space where the gas generating agent is not arranged in the inside of the gas generating agent accommodation chamber as a result of arrangement of the coil spring, where V1 and V2 satisfy a condition of 0.05≤V2 / V1≤0.32.

The invention discloses an ejection device, a control method of the ejection device and electric mobile equipment, and the ejection device comprises a guide structure which is connected to a body; the ejected body is contained in the guide structure and is connected to the body in a releasable manner through a fastener; the parachute is accommodated in the guide structure in a foldable manner and is connected with the ejected body; the gas generator is mounted on the outer wall of the guide structure; wherein the fastener releases the catapulted body when responding to ignition current to be broken, and the gas generator inflates the parachute when responding to the ignition current, so that the parachute is converted into an unfolded state from a folded state, and the catapulted body is driven to fall. The dangerous source or the unit needing to be protected serves as the ejected body to be ejected from the body, damage to the body caused by fire of the dangerous source is effectively reduced, the safety of passengers is greatly improved, and an efficient and practical safety solution is provided for various scenes related to flight safety and equipment protection.

The invention provides a control method and device of a mixed gas power generation system, equipment and a storage medium, and belongs to the technical field of new energy power generation. The method comprises the following steps: calculating the introduction rate of each target gas based on load operation data, the type of gas introduced into the gas generator set at present, the type of target gas introduced into the gas generator set after a first duration in a combustion stage and the proportion of the target gas, based on the introduction rate and the total heat per unit time of the exhaust gas output by the gas generator set after the second duration, the exhaust gas proportion used for heating each target gas is calculated, each target gas is heated based on the exhaust gas proportion, and the temperature value of the gas in the gas generator set is monitored in real time; and regulating and controlling the operation state of the mixed gas power generation system based on the temperature value. The proportion of gas input into the gas generator can be flexibly adjusted, and the energy utilization rate of the system is increased.

The invention provides a landing and life-saving system adaptive to a non-fully-coated single aircraft. The landing and life-saving system comprises a helmet for wearing, a flying suit connected with the aircraft and used for wearing, and a plurality of mechanical feet mounted on the aircraft, the helmet comprises a shell and a non-trigger air cushion arranged in the shell, and a visual window is arranged on the front side of the shell; the flying suit comprises a vest, a back air bag installed on the back of the vest, a thoracico-abdominal air bag installed on the front portion of the vest and a gas generator connected with the air bags through pipelines, the gas generator is installed on the vest or the aircraft, and a trigger switch for inflating the air bags is arranged on the gas generator. The mechanical foot comprises a supporting rod, a rotating rod and a mounting block, the mounting block is connected to the aircraft, one end of the rotating rod is rotationally connected with the mounting block or the aircraft, one end of the supporting rod is rotationally connected with the other end of the rotating rod, and the other end of the supporting rod serves as a supporting foot. The system is used for assisting normal flight landing of a manned flight non-coated single aircraft, and realizes forced landing and lifesaving.

The invention relates to an assembly (1) comprising an aircraft turbine engine (2), a pylon (40) for mounting the turbine engine on an element of the aircraft, and a system for suspending the turbine engine from the pylon, the turbine engine having a longitudinal axis (X) and comprising, from upstream to downstream, in the gas flow direction: > a fan casing (11) centred on the longitudinal axis (X) and having a first axial end (12) located upstream of the fan (10); and > a gas generator (16) configured to receive an air flow generated by a fan, the pylon (40) being generally elongate along the longitudinal axis (X) and being able to be attached to the element of the aircraft, characterised in that the suspension system comprises at least one intake force uptake link (30, 30a, 30b), a first end (31, 31a, 31b) of which is connected to an attachment point (11a, 11b) of the fan casing (11) located on the first axial end or on an upstream portion of the fan casing, and a second, opposite end (32, 32a, 32b) of which is connected to the pylon.

The invention discloses an intelligent inspection system of a gas generator set, and particularly relates to the field of intelligent inspection, which comprises a multi-dimensional operation parameter real-time acquisition module, a data processing module, an equipment operation evaluation module, a dynamic adjustment module, a fault analysis module, a fault disposal and effect verification module and an equipment health trend prediction module. The multi-dimensional operation parameter real-time acquisition module is used for acquiring key operation parameters in real time in the operation process of the gas generator set by utilizing a multi-parameter sensor array; the data processing module is used for carrying out preprocessing and feature extraction on the collected key operation parameters; the equipment operation evaluation module is used for carrying out operation risk analysis according to the extracted equipment state characteristics and constructing a risk evaluation model; according to the method, comprehensive sensing of the running state of the gas generator set is achieved by deploying the multi-parameter sensor array, multiple dimension parameters are collected, deep feature extraction and analysis are carried out on each parameter, and the one-sidedness of traditional inspection is avoided.

The invention describes an airbag module (10), specifically a knee airbag module, comprising at least a module housing (12), an airbag, specifically a knee airbag, and an inflator (16), as well as a holding element (14), the holding element (14) including a seat (18) for the inflator (16) and enclosing the inflator (16) at least partly, in particular in a cage-like manner, the holding element (14) including securing elements (20) at least for securing the holding element (14) and the airbag to the module housing (12), the holding element (14) and / or the module housing (12) comprising a fixing element (24) for fixing the inflator (16) in the holding element (14). The invention further describes a method for replacing an inflator (16) of an airbag module (10).

The utility model discloses a bridge ship collision prevention active protection device which comprises a laser range finder, a control assembly, a main bridge pier, a main bridge bearing platform, a separation type ship collision prevention facility structure, a polyurethane foam rotary drum and a riverbed, the laser range finder and the control assembly are arranged on the upper portion of the main bridge pier, and the main bridge bearing platform is arranged at the bottom of the main bridge pier. A plurality of separated ship collision prevention facility structures are arranged on the periphery of the main bridge bearing platform on the main bridge piers, polyurethane foam rotating cylinders are arranged on the separated ship collision prevention facility structures, and the other ends, away from the polyurethane foam rotating cylinders, of the separated ship collision prevention facility structures are used for being buried in a riverbed to be fixed. When the distance between the ship and the main bridge pier is detected to be smaller than a certain range through the optical distance measuring instrument, the control assembly controls the gas generator to inflate the gas bag to generate buoyancy, the polyurethane foam rotating drum is pulled to the water surface through the buoyancy to make contact with the ship, and the situation that the ship collides with the main bridge pier and consequently the main bridge pier is damaged is prevented.

An assembly for an aircraft propulsion system (20) includes a propulsion module (24), a gas generator (26) and an anti-icing system (28). The propulsion module (24) includes an open propulsor rotor (30). The gas generator (26) is configured to drive rotation of the open propulsor rotor (30) and includes a flowpath (74), a compressor section (69), a combustor section (70), a turbine section (71) and an exhaust section (72). The flowpath (74) extends through the compressor section (69), the combustor section (70), the turbine section (71) and the exhaust section (72). The turbine section (71) is axially between the combustor section (70) and the open propulsor rotor (30) along the axis (22). The anti-icing system (28) is configured to bleed gas from the flowpath (74) in the exhaust section (72) to provide heated gas and to direct the heated gas to the propulsion module (24) to reduce or prevent ice accumulation on an exterior surface (50, 66, 108) of the propulsion module (24).

An assembly is provided for an aircraft propulsion system. This assembly includes a propulsion module, a gas generator and an anti-icing system. The propulsion module includes an open propulsor rotor. The gas generator is configured to drive rotation of the open propulsor rotor about an axis. The gas generator includes a flowpath, a compressor section, a combustor section, a turbine section and an exhaust section. The flowpath extends through the compressor section, the combustor section, the turbine section and the exhaust section. The turbine section is axially between the combustor section and the open propulsor rotor along the axis. The anti-icing system is configured to bleed gas from the flowpath in the exhaust section to provide heated gas. The anti-icing system is configured to direct the heated gas to the propulsion module to reduce or prevent ice accumulation on an exterior surface of the propulsion module.

A propulsion assembly for a hybrid aircraft including a first and a second engine each having a gas generator and a free turbine, a main rotor coupled to the free turbine of the first and second engines, the first engine including a first electric machine and a second electric machine of lower power than the first electric machine, one of the first or of the second electric machine being able to be coupled to the gas generator and to set the gas generator in rotation during a start phase of the engine, and being further able to be coupled to the free turbine in order to generate electrical energy after the start phase, the other of the first or of the second electric machine being coupled to the gas generator only.

In a gas generator, a plurality of gas discharge ports include a plurality of first gas discharge ports and one or a plurality of second gas discharge ports having an opening pressure higher than an opening pressure of the first gas discharge ports. An opening pressure of the first and second gas discharge ports are set, such that only the plurality of first gas discharge ports of the plurality of gas discharge ports are opened by the pressure of the gas when the igniter is actuated in a stand-alone state before the gas generator is incorporated into an airbag device, and among the plurality of gas discharge ports, the first gas discharge ports excluding some of the first gas discharge ports and at least some of the second gas discharge ports are opened by the pressure of the gas when the igniter is actuated in an assembled state.

A system for protecting a rider on his / her horse, including an airbag vest intended to be worn by the rider and including at least one inflatable sheath, a gas generator, a gas cartridge and an electronic unit connected to the gas generator and allowing triggering the inflation of the sheath, the system further includes a motion sensor intended to be installed on the horse, for example on the saddle, and configured to detect a fall of the horse, the motion sensor being connected to the electronic unit so as to trigger the inflation of the sheath in case of detection of a fall of the horse, so as to mitigate a potential crushing of the rider by the horse.

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 gas generator frequent starting system without a starting motor and an implementation method, and belongs to the technical field of generator control. The gas generator frequent starting system comprises a charging and discharging circuit, a charging control circuit and a discharging control circuit; the storage battery is connected with an inverter and a plurality of super capacitors through a normally open contact of the relay, each super capacitor is connected with a coil of a solid-state relay, the storage battery is further connected with a rectification voltage stabilizer, the inverter and the rectification voltage stabilizer are connected with a coil of a gas generator, the coil of the gas generator is further connected with a coil KMC-0 of an 8 # relay, and the coil KMC-0 of the 8 # relay is connected with the storage battery. A starting mode of directly driving a generator coil is adopted, an external starting motor is not needed, and therefore the problems that a conventional starter slips, cannot be separated and is abraded are solved.

Driver safety module (10) of a vehicle equipped with a vehicle steering wheel (110) movable between a driving position and a retracted or stowed position, the driver safety module (10) comprising:- a safety airbag (20), inflatable and comprising at least one front portion (21), arranged to deploy from a rest position to a protection position,- a gas generator (30) arranged to inflate the safety airbag (20), characterized in that the driver safety module (10) comprises an adaptive device arranged to adjust an inflation volume of the front portion (21) as a function of the driving position or the retracted or stowed position of the vehicle steering wheel (110). Figure for abstract: Fig. 1

The utility model discloses a perfluorohexanone fire extinguishing device used in a battery box, which comprises an outer shell and an inner shell arranged in the outer shell, a perfluorohexanone fire extinguishing agent is arranged in the outer shell, a gas generating agent is arranged in the inner shell, one end of the outer shell is provided with a nozzle end cover, the gas generating agent is in contact with an electric ignition head, and the electric ignition head is in contact with the nozzle end cover. The electric ignition head is connected with the output end of the piezoelectric ceramic through a starting line, an impact piece is arranged on one side of the piezoelectric ceramic and connected with one end of a fusible metal rod through a pull rod, a spring is arranged between the impact piece and the end of the inner shell, and the other end of the fusible metal rod is connected with a fixing part on the surface of the battery box. According to the perfluorohexanone fire extinguishing device, the structure that the fusible metal rod, the impact piece, the piezoelectric ceramic and other parts are matched is designed, so that the problem of starting failure caused by the fact that a traditional thermosensitive wire is prone to aging and failure in a complex environment in a battery is effectively solved, and the starting efficiency and the starting success rate of the perfluorohexanone fire extinguishing device are greatly improved.

An airbag device includes a gas generator including an ignition device, a gas generating agent and a housing and provided with a gas discharge port, a shielding member covering an outside of the housing and moving to a shielding position located in a discharge direction of a combustion gas from the gas discharge port and a non-shielding position not located in the discharge direction of the combustion gas from the gas discharge port, an elastic member disposed between the housing and the shielding member and configured to energize the shielding member to position the shielding member at the shielding position or the non-shielding position in accordance with a magnitude of an external force received by the shielding member, and an airbag bag body disposed in communication with the inside of the housing through the gas discharge port of the gas generator, and accommodating the shielding member and the elastic member.

The invention discloses a multi-energy complementary micro-grid coordination control method, and relates to the technical field of micro-grid coordination control, and the method comprises the steps: obtaining the voltage, current, operation power, active power and circuit parameters of a gas generator, a diesel generator and a photovoltaic power generation system, and constructing a micro-grid link topological graph; load fluctuation is automatically shared according to a preset frequency-power and voltage-reactive Droop curve in the micro-grid of the gas generator and the diesel generator; when the bus frequency deviates from the nominal value, each power generation device increases or decreases the output according to a preset proportion; according to the method, the shortest path is calculated based on the power transmission loss, the current-carrying capacity and the voltage drop on the weighted topological graph, and the first power transmission path is dynamically verified and adjusted, so that rapid switching and reconstruction during a fault are realized; the monitoring and path recalculation mechanism can effectively improve the safety and reliability of the micro-grid, and reduce the risk of power supply interruption caused by abnormal lines or equipment.

The invention discloses an energy storage battery scheduling strategy for normal drilling operation of oil and gas drilling, belongs to the technical field of storage and charging, and mainly solves the problems of unbalanced charging and discharging of an energy storage battery and unreasonable starting time of a gas power generator due to cooperative energy supply of the gas power generator and the energy storage battery under the working condition of normal drilling operation of oil and gas drilling. The scheduling strategy combines the operation state of the winch, the estimated discharge capacity of the energy storage battery and the estimated chargeable capacity of the energy storage battery, dynamically adjusts the starting number of the gas generators, controls the continuous discharge capacity of the energy storage battery, not only improves the gas-electricity conversion efficiency of the gas generators, but also guarantees the charge and discharge balance of the energy storage battery. And cooperative energy supply safety of the gas generator and the energy storage battery in normal drilling operation of oil and gas drilling is ensured.

Device for drying material for an asphalt mixing plant, the device (2, 3) comprising a rotary kiln (9) which can be driven to rotate about a rotational axis (19) and in which the material is dried, the rotary kiln (9) having a material inlet (10) and a material outlet (11), b. a heating unit coupled to the rotary kiln (9) for supplying heat to the rotary kiln (9), the heating unit being designed with a burner (12) having i. a burner housing (27) having a longitudinal axis (26), ii. an air line (16) arranged on the burner housing (27) for supplying air, wherein the air line (16) is arranged axially to the longitudinal axis (26) on the burner housing (27), iii. an air blower (29) arranged in the air line (16, 28), iv. a burner head (41) arranged on the burner housing (27) for generating a burner flame (13), v. a hydrogen gas line (14) connected to the burner (12) for supplying hydrogen gas into the burner (12), wherein a hydrogen gas nozzle (31) for discharging the hydrogen gas is connected to the hydrogen gas line (14), characterized in that c. the burner (12) is designed to be operated either exclusively by means of hydrogen gas or by means of hydrogen gas and secondary fuel, d. the burner (12) has a swirling element (35) for swirling the air in the burner (12) relative to the longitudinal axis (26), e. the swirling element (35) comprises a flow guide element in the burner housing (27), wherein the flow guide element is arranged immovably in the burner housing (27), f. the flow guide element is arranged concentrically to the longitudinal axis (26) and is designed as a baffle plate having a plurality of blades (53, 54) arranged in a circle with respect to the longitudinal axis (26) and oriented at an inclination, g. the heating unit comprises a hot gas generator (24) connected to the burner (12) which is connected to the rotary kiln (9) by means of a hot gas line (25).

The invention belongs to the technical field of calibration of gas detection equipment, provides a calibration device which can detect a zero gas generator without manually replacing a gas cylinder and can control a gas path only through a software end, and particularly relates to an intelligent mobile zero gas generator calibration device and a use method. The device consists of a standard gas fixing device, a gas distribution control device, a moving device, a software control system and a Fourier infrared analyzer. An adjustable fixing frame of the standard gas fixing device can be matched with standard gas cylinders of different specifications, the gas distribution control device is controlled by a software control system to achieve fast switching of gas paths and accurately control gas pressure and flow, the standard gas cylinders are fixed and connected with equipment in the using process, then detection items are selected through software, and the software controls switching of the gas paths and parameter adjustment. And parameters can be checked in real time during detection. Manual frequent bottle replacement is not needed, the detection efficiency is high, the result is accurate and reliable, the operation interface is concise and visual, and the method is suitable for zero gas generator calibration at different places.

The utility model relates to a dog neck ring inflatable behavior stopper which comprises a first neck ring and a second neck ring, the first neck ring and the second neck ring are rotatably connected through a rotating shaft, and the first neck ring and the second neck ring integrally form a circular ring shape. Through the inflatable design, when a pet dog attacks, the action of the pet dog is quickly limited, and other people are prevented from being hurt; the air bag can wrap the head of the dog, shield the sight of the dog and limit the mouth of the dog through inflation expansion, so that the attack behavior of the dog is effectively stopped, and through cooperation of the remote controller and the gas generator, a stopping mechanism can be rapidly started when the pet dog attacks; a gas generating agent in the gas generator is heated and decomposed to generate gas, rapid inflation is achieved to achieve rapid expansion, behaviors of the pet dog are stopped in time, and the device has the advantages of being rapid, effective, high in safety, easy to operate, capable of being repeatedly used, high in comfort, reasonable in structure, convenient to carry, convenient to charge, high in cruising ability and the like.

The invention belongs to the related technical field of pressure tests, and particularly discloses a gas inlet pipeline test device for a gas generator, which comprises a first base and a second base, a round frame is fixedly mounted on one side of the upper end surface of the first base, an annular pipe is embedded in the round frame, and a connecting rod is mounted at one end in the annular pipe through an arranged telescopic mechanism. The outer side of the connecting rod is externally connected with a ring rod through an inner chuck fixedly connected in a sleeving mode, a sealing rotating ring is arranged on the outer wall of one side of the round frame, a test air inlet pipe movably penetrates through the sealing rotating ring in a penetrating mode, and a particle feeding simulation mechanism is arranged at the end, away from the sealing rotating ring, of the test air inlet pipe. By simulating multi-field coupling environments such as pressure fluctuation, particle scouring and mechanical vibration under real working conditions, the problem that data deviation is large due to the fact that complex working conditions cannot be reproduced in a traditional test is solved, and precise detection and full-life-cycle evaluation of the performance such as wear resistance, pressure resistance and blockage resistance of the pipeline are achieved.

A turboshaft engine for an air-craft including a gas generator including a compressor, a combustion chamber and an expansion turbine; a power turbine rotating a power take-off by a reduction gear; a heat exchanger including a first circuit and a second circuit. The compressor includes a first shaft rotated by a second shaft of the expansion turbine by a trans-mission mechanism, the transmission mechanism and the reduc-tion gear forming part of a gearbox which is arranged axially at a front end of the turboshaft engine, such that the compressor is arranged axially between the gearbox and the power turbine.

This invention provides a method for modeling the starting performance of a marine gas turbine. First, a gas turbine aero-thermodynamic performance calculation model is established using C++, and a heat transfer model, temperature sensor model, and control law model for the gas turbine's high-temperature components are established using the M language. Then, based on test data from the gas turbine startup process, the method analyzes how the pressure ratio and efficiency of typical gas turbine components change with the physical speed of the gas generator during startup. The corresponding low-speed characteristics of the gas turbine's rotating components are generated and corrected, enabling high-precision, real-time simulation of the gas turbine's starting performance. This method considers the heat exchange between the high-temperature fuel gas and the ambient atmosphere and the gas turbine itself, improving the accuracy of the gas turbine startup performance simulation. The method can provide a simulation testing tool for the design and optimization of gas turbine startup control laws.

The invention discloses a high-flow gas generator suitable for chemical vapor deposition equipment and a supply method, and belongs to the technical field of gas semiconductor manufacturing. The butterfly valve is adopted to replace a traditional flow meter to supply flow, the defects of large resistance and small flow caused by the flow meter are overcome, further, the generator integrates vibration and heating device, using temperature and vibration coupling control, and closed-loop control of pressure is matched, so that the large-flow gas generator can be constantly at the target air pressure, and the flow rate is increased. The stable flow of gas can be supplied; furthermore, the air pressure, namely the flow, can rapidly reach the target flow through closed-loop control of the air pressure and a mature PID algorithm, high-precision control is achieved, and unification of the flow, the precision and the stability is achieved through the scheme.