106 results about "Turboshaft" patented technology

The embodiment of the invention provides a digital simulation modeling method and device of a tandem type hybrid electric propulsion system, computer equipment and a medium, and relates to the technical field of simulation modeling, and the method comprises the following steps: constructing a turboshaft prime mover model, constructing a generator model, connecting the turboshaft prime mover model and the generator model in series to generate a generator set, the power generation groups are connected in parallel to construct a turbine power generation system; constructing a propulsion system; constructing a battery energy storage system; constructing a power transmission and distribution system, and respectively connecting the power transmission and distribution system with a turbine power generation system, a propulsion system and a battery energy storage system; and constructing a comprehensive control and energy management system, and outputting a digital simulation modeling result through a turbine power generation system, a power transmission and distribution system and a battery energy storage system. According to the scheme, a simulation modeling method based on multi-physics field coupling double-power-source dynamic response and energy flow regulation and control provides reliable modeling technical support for engineering application of a tandem type hybrid electric propulsion system.

The invention provides a generator and battery power distribution method and device based on model prediction control, and belongs to the technical field of power distribution. The method provided by the invention comprises the following steps: loading a preset dynamic model library; generating and calibrating a total load power prediction sequence based on the flight plan and the rotor aerodynamic power model; calling the dynamic model library to predict and control the rolling optimization to output the optimal power instruction sequence of the generator; in the rolling optimization execution process, bus voltage dynamic characteristics are monitored in real time, a graded response mechanism is started based on a turboshaft engine dynamic model when load sudden change occurs, and the power of a generator and the power of a battery are adjusted; in the load abrupt change response process, rolling optimization is executed again based on the adjusted power and the corresponding system state, meanwhile, feed-forward compensation is carried out on the bus voltage deviation, and the voltage is controlled to be within a stable interval set by rolling optimization by adjusting the power of the generator; and circularly executing until the flight task is finished, and determining the generator power and the battery power.

The utility model discloses a sleeve repair tool for a fuel manifold of a turboshaft engine, which comprises a support with the top end provided with a penetrating column with threads on the inner wall, and further comprises a threaded pressing rod with the top end provided with a pulling rod, and the threaded pressing rod is in threaded connection with the penetrating column through the threads on the outer wall; a semi-arc-shaped pressing plate is arranged at the bottom of the T-shaped sliding block, and the T-shaped sliding block is movably connected with the threaded pressing rod; a shape correcting arc plate is arranged on the positioning column opposite to the semi-arc pressing plate, and the positioning column is located at the middle section of the support; and the gland is connected to the positioning column through a bolt. According to the sleeve repairing tool for the turboshaft engine fuel main pipe, the problems that in the prior art, manual positioning is not accurate, and pipe wall cracks and internal threads are prone to being crushed to be scrapped due to repeated knocking are solved.

The invention discloses a hybrid power turboshaft engine and a working method, the engine comprises a core machine system and a fuel cell power supply system, and the core machine system comprises an air inlet channel, an air compressor, a main combustion chamber, a gas turbine and a power turbine; the fuel cell power supply system comprises a liquid ammonia storage tank, a fuel pump, a liquid ammonia decomposer, a pressure reducing valve, a heat exchanger and a proton exchange membrane fuel cell. According to the invention, a hybrid power form of combining a turbine power system and a fuel cell power system is adopted, so that the output power of the turboshaft engine is ensured, and meanwhile, the proton exchange membrane fuel cell provides electric energy for airborne electric equipment of the engine; the problems that the electric power requirement of an existing turboshaft engine is gradually improved, power of storage batteries such as lithium batteries is insufficient, and electric power is difficult to extract from a power turbine are solved. Meanwhile, the ammonia working medium serves as power generation fuel, the energy conversion efficiency of the aviation turboshaft engine is improved, and energy consumption is reduced.

The turboshaft engine comprises a speed reducer, a gas compressor, a combustor and an exhaust nozzle, the speed reducer and the combustor are both fixedly connected with the gas compressor, the input end of the combustor is connected with the output end of the gas compressor, and the exhaust nozzle is fixedly connected with the output end of the combustor. The speed reducer comprises a case, a transmission assembly and an auxiliary assembly are arranged on the inner wall, the transmission assembly is connected with the combustor, and the auxiliary assembly is connected with the gas compressor. And the output end of the lubricating assembly is communicated with the interior of the case. The turboshaft engine has the core advantages that a transmission assembly and an auxiliary assembly are integrated in the same case, the overall size is greatly reduced, and the compact installation requirement of the turboshaft engine is met; the case provides reliable protection for internal parts, and interference of the external environment on the transmission precision is reduced. By optimizing a power transmission path, the transmission assembly specially receives power transmission of the combustor, the auxiliary assembly concentrates on driving the gas compressor and related auxiliary parts, power distribution precision is achieved, and the power transmission stability of the whole machine is remarkably improved.

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.

A turboshaft engine transmission with a torque measurement system is provided. The turboshaft engine transmission includes a front housing, a rear housing, a mating flange axially interposed between the front and rear housings, the mating flange defining a sensing bolt hole, assembly bolts disposed to assemble the front and rear housings to the mating flange with a preload sufficient to maintain assembly during engine operational conditions and a sensing bolt installed in the sensing bolt hole to measure forces exerted on the mating flange by the front and rear housings.

A non-propulsive turbomachine (2) for an aircraft (M) fuel conditioning system (Q) comprising: a first compressor (21), a combustion chamber (23) supplied by a first airflow (A1) flowing in a general supply channel (30) connected to the first compressor (21), a second compressor (22) connected to the general supply channel (30) by a first sampling channel (31), so as to be supplied with a second airflow (A2) from the first compressor (21), and to a cabin air conditioning device (6), a single gas turbine (24) connected to both the first compressor (21) and the second compressor (22) by a single turbomachine shaft (25), a second sampling channel (33) connecting the general supply channel (30) and the cabin air conditioning device (6), and at least one sampling valve (4),mounted on the first sampling channel (31) and configured to allow or prevent the circulation of the second airflow (A2) in the sampling channel (31). Abstract figure: Figure 3,

The invention relates to an aircraft propulsion system (100), which comprises a turbine engine (102A, 102B) provided with a rotary portion (104A, 104B), a starter (122A, 122B), a freewheel clutch system (124A, 124B) and a control system (126) designed, when the turboshaft engine is operating at idling speed, to receive a standby request (Rv), and in response to the standby request (Rv), to turn off the turbine engine (102A, 102B). The control system (126) is designed, in response to the standby request (Rv), before the turbine engine is switched off, to control the starter so that the speed (ND) of the starter becomes non-zero, and after the turbine engine is switched off, to control the starter to maintain the non-zero speed (ND) of the starter during the decrease in the speed (NGG) of the rotary portion to the standby speed (NGGv).

HIGH-STABILITY, HIGH-AGILITY THREE-SAILING SURFACE AIRCRAFT The three-sail aircraft (1), (2), and (3) is equipped with movable flaps (6), (7), and (8) on each of the lifting surfaces. The flaps of the upstream lifting surface (6) are connected to the flaps of the main wing (7) by a rigid linkage with a deflection angle ratio of 50%. The forces on the downstream lifting surface (horizontal tail) (3) reverse between takeoff (negative lift) and cruise (positive lift). Stabilizing fins (5) are positioned at the rear of the fuselage in the lower section at an angle of 30° to the aircraft's centerline. A weighted control rod (22) located in the vertical tail (4) provides stabilization for the aircraft in the presence of severe turbulence.The propulsion system is located at the rear of the fuselage and consists of either a piston engine driving a multi-bladed propeller, one or two turboshaft engines driving a multi-bladed propeller or two contra-rotating propellers, a turbojet engine, or one or two electric motors driving a multi-bladed propeller or two contra-rotating propellers. This aircraft can be piloted either by a human pilot on board or by an electronic computer controlled from the ground or autonomously.

This utility model relates to a mobile testing system for ground testing of a turboshaft engine, belonging to the field of turboshaft engine technology, and solves the problem of the lack of mobility in existing whole-engine testing technologies. This utility model includes an experimental platform unit, a measurement and control unit, and a water circulation unit; the experimental platform unit, measurement and control unit, and water circulation unit are mounted on a mobile device; the experimental platform unit includes an engine testing platform and a dynamometer; the measurement and control unit includes a measurement and control device and a data acquisition device; the water circulation unit includes a circulating water cooling device, a cold water tank, and a hot water tank. This utility model enables ground testing and rapid transfer of a turboshaft engine.

Gas turbine engines and methods of their operation are provided. For example, a method of operating a gas turbine engine comprises selectively engaging and disengaging an engine clutch disposed between a low speed spool and a rotor assembly of the engine. Engagement or disengagement of the engine clutch is selected based on an operating condition of an aircraft comprising the engine. Further, an inter-spool clutch disposed between the low speed spool and a high speed spool of the engine transitions between engaged and disengaged, disengaging when the high speed spool reaches a speed greater than an operational speed of the low speed spool. Similarly, a gas turbine engine comprises an engine clutch configured to selectively position a low speed spool in operative communication with a rotor assembly and an inter-spool clutch configured to position the low speed spool in operative communication with a high speed spool.

The invention discloses a cooling and lubricating system for a nested transmission shaft of a turboshaft engine, the transmission shaft comprises a transmission core shaft, a transmission sleeve shaft is sleeved outside the transmission core shaft, and an oil return channel is reserved between the transmission core shaft and the transmission sleeve shaft; a cooling lubricator is arranged in the combustor, one end of an oil return channel is communicated with the cooling lubricator, the other end of the oil return channel is communicated with the speed reducer, a pump set and a lubricating oil tank are fixedly arranged on the speed reducer, the lubricating oil tank is communicated with the speed reducer, the driving input end of the pump set is connected with the transmission shaft, and the oil suction end of the pump set is communicated with the lubricating oil tank. The oil outlet end of the pump set is communicated with the cooling lubricator, and a negative pressure pipe is further arranged between the speed reducer and the exhaust nozzle. The nested transmission shaft cooling and lubricating system has the beneficial effects of being compact in structure, efficient in cooling and lubricating, good in power collaboration and convenient and fast to maintain.

The invention discloses a turboshaft engine ignition frequency design method and system based on the hot start characteristic, and the method comprises the steps: determining the upper and lower limits of a reliable ignition rotation speed interval based on the real test data of a turboshaft engine, and determining the minimum ignition frequency through combining the hot start characteristic of the turboshaft engine; according to the method, the starting requirement is strict, the minimum ignition frequency corresponding to the turboshaft engines of different models can be accurately designed, the starting performance and requirements of the turboshaft engines of different models can be better met, and the starting success rate of the turboshaft engines is greatly increased.

This invention discloses a method, system, equipment, and medium for monitoring the operating status of a turboshaft engine. The method converts the gas generator speed and turbine inlet temperature into output torque, calculates the remaining torque for different flight conditions, and displays it on a helicopter. This reduces the parameters the pilot needs to monitor, simplifying the flight status assessment process. Furthermore, the pilot can intuitively understand how much power the engine can still produce, providing accurate reference for subsequent flight operations. In addition, by first fitting a mapping relationship based on a large amount of bench test data and then correcting the mapping relationship using output torque installation loss, a mapping relationship under actual engine installation flight conditions is obtained, which more closely reflects the actual flight conditions and ensures the accuracy of the mapping relationship. Moreover, bench testing is less costly and complex than installation testing, which helps reduce testing complexity and cost.

The present application relates to the technical fields of turbofan engine fuel system control, in particular to a kind of turbofan engine fuel pump current interference detection extraction circuit and analysis device, the circuit includes voltage follower module and bidirectional threshold detection extraction module;In bidirectional threshold detection extraction module, the positive input end of first operational amplifier is grounded, and the negative input end is connected to the output end of voltage follower module, and the output end of first operational amplifier is respectively connected to the cathode of first diode and the anode of second diode;The anode of first diode is respectively connected to the output end of voltage follower module and the negative input end of second operational amplifier;The cathode of second diode is respectively connected to the output end of voltage follower module and the positive input end of second operational amplifier;The output end of second operational amplifier is connected to the current interference analysis module outside.Such, by hardware circuit, the detection extraction effect of interference current can be effectively improved.

The present application relates to a kind of turbo-shaft engine gas storage system and method, belong to turbo-shaft engine field, including engine body, air storage structure, controller, still including bleed air valve seat, bleed air pipe, air collector, the bleed air valve seat is located on the compressor casing of engine body, the bleed air valve seat is close to the diffuser outlet of engine body, one end of the bleed air pipe is located on bleed air valve seat, the other end of the bleed air pipe is communicated with air collector, the air collector is communicated with air storage structure, the air storage structure is communicated with the air inlet of engine body, air pipe is equipped on the air collector.The high-pressure gas in the engine body and atmospheric air are collected by the air collector, and are pressurized and stored by air storage structure, not only realize self-circulation system, but also improve engine starting difficulty and make up take-off power, reduce the dependence on ground device auxiliary.

The invention relates to the technical field of fault diagnosis, and discloses a turboshaft turboprop engine main bearing fault sample generation method and device, and the method comprises the steps: obtaining a standard fault sample of a main bearing; generating a standard grey-scale map of the standard fault sample; training a fault sample generation model based on the standard grey-scale map and the standard fault label to obtain a target generator; obtaining a target fault label; and adopting a target generator to generate a plurality of target fault samples corresponding to the target fault tag. According to the invention, the standard fault sample carrying the label of the main bearing is obtained, the standard fault sample is converted into the grey-scale map, and the model is trained based on the grey-scale map and the fault label, so that the model learns the grey-scale map distribution characteristics of different fault categories. The target generator is adopted to generate the fault sample of the specified fault category, the physical authenticity of the fault is reserved through a semi-physical generation method, and effective expansion of the training data set is realized, so that the accuracy and generalization ability of main bearing fault diagnosis are improved.

1. The name of the design product: the shell of turboshaft engine. 2. The use of the design product: the design product is mainly used as the shell of turboshaft engine. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: the perspective view 1. 5. The bottom view of the design product is not common view, and the bottom view is omitted.

This application provides a modeling method and system for a baseline model of a turboshaft engine, relating to the field of turboshaft engine simulation technology, and particularly to a modeling method for a baseline model of a turboshaft engine. The method includes: constructing a component-level model of the turboshaft engine based on the working principles of its various components, and solving the equilibrium equations for each component to obtain a general mathematical model of the turboshaft engine; selecting measured parameters from the measured data of the turboshaft engine, and establishing a set of constraint equations based on these parameters; and solving the equilibrium equations and constraint equations to obtain the baseline model of the turboshaft engine. This application can complete the construction of a baseline model of a turboshaft engine even with limited measured data and insufficient modeling conditions, and solves the accuracy problem caused by inconsistencies between characteristic diagrams, design point parameters, and the simulation object. The model accuracy meets the requirements of engineering applications.

The invention discloses an engine starting control method and device for thermal bending correction, equipment and a medium. The method comprises the steps that the acceleration of a rotor of a fuel gas generator at the third starting stage of the aviation turboshaft engine is jointly corrected through an atmospheric pressure correction coefficient, an atmospheric temperature correction coefficient and Tt45 afterheat correction coefficients under different highest hot starting Tt45 afterheat; in the third starting stage of the aviation turboshaft engine, the corrected acceleration of the rotor of the fuel gas generator is given, the engine is only driven by a turbine, the engine operates according to the given corrected acceleration of the rotor of the fuel gas generator, and fuel oil is supplied in a closed-loop mode according to the given corrected acceleration of the rotor of the fuel gas generator; and the rotating speed of the gas generator is increased according to the given corrected acceleration of the rotor of the gas generator. According to the method, the acceleration of the third starting stage of the turboshaft engine is corrected through the Tt45 afterheat, the hot starting time is adaptively prolonged, the surging and scraping abrasion probability caused by hot bending is reduced, and the attendance rate is increased.

The application discloses an aero-engine hot-end component full-life-cycle management method and system, and belongs to the technical field of aero-engines.The system constructs a full-life-cycle closed loop system of material gene optimization-precision forming process-service health monitoring-life prediction and active repair, can realize service life improvement of more than 200% of the aero-engine hot-end component, and improves the production yield rate from the conventional 60% in the industry to more than 90%.The application fills the core short board of short life, poor reliability and low yield rate of the aero-engine hot-end component in China, breaks through the core technical bottleneck of the "industrial crown pearl" of the aero-engine, and is 100% domestically produced and controllable in material and process, and can be widely applied to scenes such as army armed helicopter turboshaft engines, military unmanned aircraft turbojet / turbofan engines and the like.

The invention discloses a self-preheating starting system for a turboshaft engine under an extremely cold condition and a use control method. The self-preheating starting system comprises a fuel tank, a lubricating oil tank, a lubricating oil inlet loop connected with the lubricating oil tank, an electricity storage device, an engine core engine, a starting auxiliary combustion device and a control system. The starting auxiliary combustion device is used for introducing part of fuel oil from the fuel tank, introducing part of air under driving of the electricity storage device to be pressurized to form high-pressure gas, and enabling the high-pressure gas and the fuel oil to be combusted to generate high-temperature fuel gas. The lubricating oil inlet loop is connected to the output side of the starting auxiliary combustion device so that high-temperature fuel gas can preheat lubricating oil in the lubricating oil inlet loop, and the output end of the lubricating oil inlet loop is further connected into multiple bearing cavities of the engine core machine so that the preheated lubricating oil can enter the multiple bearing cavities of the engine core machine to be lubricated. According to the system, fuel of an engine is used as energy, and lubricating oil and a core engine of the engine are accurately and rapidly preheated through a set of built-in efficient combustion heating system.

The invention provides a turbine shaft over-rotation protection device and method and an aero-engine, the turbine shaft over-rotation protection device comprises a protection bearing, the protection bearing is used for supporting a turbine shaft, the protection bearing comprises an outer ring, an inner ring and a roller structure arranged on the inner ring, the inner circumferential surface of the outer ring is a surface with radial height change, the inner circumferential surface comprises a first inner circumferential surface and a second inner circumferential surface, and the first inner circumferential surface and the second inner circumferential surface are arranged on the outer ring. The second inner circumferential surface is closer to one side of the turbine shaft than the first inner circumferential surface, and the outer ring is connected with a supporting conical wall; the roller structure is arranged to be not in contact with the outer ring when the turbine shaft works, the second inner circumferential face is located in the first direction of the first inner circumferential face, and the first direction is consistent with the moving direction of the shaft at the supporting position of the protective bearing after the shaft is broken, so that the second inner circumferential face makes contact with the roller structure to form a temporary supporting structure after the shaft is broken. According to the device, the protective bearing is additionally arranged, so that the low-pressure turbine shaft can be kept on the axis to continuously rotate after being fractured, and uncontained destructive faults are effectively avoided.

The invention relates to a disc-shaped manned aircraft with multiple bundled turbofan engines, which is mainly characterized in that a cockpit is taken as a center, the multiple turbofan engines are uniformly bundled and fixedly mounted around a main body bracket and the cockpit, and respective lift fans are driven to generate upward lift force; the bottom of the main body support is provided with a turbine shaft engine transmission turbine fan, the whole body is provided with a disc-shaped anti-collision net and a disc-shaped wind collection disc, the appearance of the whole body is in a flying saucer shape, the pneumatic layout of an existing saucer-shaped aircraft is improved, a flight control device is optimized, and the flight safety is improved; the flying saucer is reasonable in structural design, easy to manufacture, low in cost and safe and reliable to use, has novelty and creativity, and shows the basic structure of a modern flying saucer and the development direction of a future flying saucer.

The application discloses a kind of OEI state control requirements and cabin indicating method of turboshaft engine, first, the mathematical model of turboshaft engine component level is established, then based on the control of the steady-state process of turboshaft engine to incremental PID algorithm and steady-state PID control method, ensure that the steady-state process of turboshaft engine under OEI state can smoothly run, in addition, the steady-state control method and OEI state control requirement of turboshaft engine under OEI state are combined, the dynamic process of turboshaft engine is controlled by the method that total distance feedforward control is combined with feedback control, ensure that turboshaft engine can smoothly run when entering OEI state, and according to engine operating state, cabin indicating requirement is formulated;The application fills the vacancy problem of current domestic turboshaft engine OEI state control law, is suitable for the control law and cabin indicating design of a variety of models turboshaft engine under OEI state, has positive promoting effect for subsequent engine health management, sensor fault diagnosis etc.

The disc-shaped manned aircraft is mainly formed by combining a plurality of turbine shaft engine devices and a turbine fan engine, each turbine shaft engine drives a propeller blade fan and a turbine fan of the turbine shaft engine and is provided with an anti-collision net and a disc-shaped wind collecting disc, and the appearance of the disc-shaped manned aircraft integrally forms a flying saucer shape; according to the saucer-shaped aircraft, the aerodynamic layout of an existing saucer-shaped aircraft is improved, a flight control device is optimized, and the flight safety is improved; the flying saucer is reasonable in structural design, easy to manufacture, low in cost and safe and reliable to use, has novelty and creativity, and shows the basic structure of the Chinese type flying saucer and the development direction of the flying saucer in the future.

The aircraft propulsion system comprises: - a turboshaft engine; - a starter; - a freewheel clutch system; - a control system designed to, with the turboshaft engine at idle: - receive a standby request (Rv); and - in response to the standby request (Rv), shut down the turboshaft engine. The control system is designed to, in response to the standby request (Rv): - before the turboshaft engine shuts down, command the starter so that the starter speed (ND) becomes non-zero; and - after shutdown, command the starter to maintain the starter speed (ND) non-zero while the gas generator speed (NGG) decreases to the standby speed (NGGv). Figure for the abbreviation: Fig. 3

The application belongs to the technical field of aero turboshaft engine control system, and proposes an engine control system and method, wherein the oil path switching electromagnetic valve of the engine control system is electrically connected with the electronic controller, and the output end of the oil path switching electromagnetic valve is electrically connected with the oil path switching module; the outlet of the fuel metering device and the outlet of the single-point flow fuel supply module are communicated with the inlet of the oil path switching module, and the fuel metering device and the single-point flow fuel supply module are switched through the oil path switching module; the single-point flow fuel supply module is added, so that when the control system loses the control function due to power failure, strong electromagnetic interference or other serious faults, the oil path switching module outputs the fixed flow of the single-point flow fuel supply module to ensure that the engine does not stop, and when the fault disappears, the normal control is automatically restored, the safety is improved, the single-point flow fuel supply module has simple structure and low cost, and is suitable for wide promotion.