156 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 invention discloses a fault diagnosis system for an aviation turboshaft engine, and relates to the technical field of fault diagnosis. An acquisition module acquires horizontal, vertical and axial vibration signals; the processing module is used for generating real-time feature vectors by introducing dynamic short-time Fourier transform, variational mode decomposition and singular value decomposition of an unfixed-width Gaussian window; the incremental diagnosis module calculates the matching degree between a real-time feature vector or a prediction feature vector and a known class through a dynamic expansion network, selects to belong to the known class or triggers an expansion mechanism according to an adaptive resonance theory, constructs joint loss by using a Bayesian learning framework after expansion, and performs Gaussian process modeling; loss is determined through Bayesian optimization, and network parameters are updated; the prediction module generates a prediction feature vector when there is no fault; the maintenance module sends or stores a maintenance scheme according to needs, self-adaptive recognition of known classes and new fault classes is achieved, the state can be pre-judged in advance, the operation safety of the engine is effectively guaranteed, and the maintenance cost is reduced.

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.

An aviation turbine shaft engine over-rotation protection execution mechanism detection device comprises an oil way system and a control circuit, and the oil way system comprises an oil tank, a direct-current electric pump and a two-position three-way electromagnetic valve; a normally open loop of the electric pump and the electromagnetic valve and the oil tank form a circulating oil path through an oil pipe; a normally closed loop of the electromagnetic valve is connected with an oil inlet of the aviation turboshaft engine over-rotation protection execution mechanism test piece, and an oil outlet of the over-rotation protection execution mechanism test piece is connected with the oil tank through an oil pipe; the control circuit comprises a power switch, a detection switch and a two-position three-way electromagnetic valve; the power switch controls power supply of the direct-current electric pump, and the detection switch controls power supply of a control coil of the two-position three-way electromagnetic valve and a test piece of the aviation turbine shaft engine over-rotation protection executing mechanism. According to the utility model, an integrated box type design is adopted, the size is small, the structure is simple, an onboard direct current 27V power supply is used for supplying power, the external field use requirement of a helicopter can be met, and the working condition of an aviation turbine shaft engine over-rotation protection executing mechanism can be conveniently detected.

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 provides a modeling method and device for a turboshaft engine of a helicopter, and relates to the technical field of turboshaft engine simulation, and the method comprises the steps: sequentially solving the thermodynamic characteristics of all parts according to the position sequence of all parts in the turboshaft engine of the helicopter, and obtaining the modeling of the turboshaft engine. According to the method, the thermodynamic characteristics of all the components are solved in sequence according to the station sequence of all the components in the turboshaft engine, modeling of the turboshaft engine is achieved, it is guaranteed that the inlet parameter of each station is consistent with the outlet parameter of the previous station, and the problem that the matching performance between the parameters of all the stations is poor is solved.

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).

This application discloses a method, apparatus, equipment, and medium for calibrating the torque of an aero-gas turbine shaft engine based on a torque meter. The method includes the following steps: S1, engine steady-state performance testing: starting the engine to idle, then slowly increasing the engine to several takeoff torque states, recording the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state; S2, torque calibration: selecting N=2 takeoff torque states for the engine, the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter, and obtaining the calibration function relationship through linear fitting; S3, post-calibration check: calculating the calibrated torque values ​​of the power turbine shaft torque sensor at several takeoff torque states based on the calibration function relationship. If the differences between each calibrated torque value and the torque value corresponding to the torque meter all meet the requirements, then the torque calibration meets the requirements. This application improves the accuracy of engine torque calibration.

The invention relates to the technical field of turbofan engine fuel system control, in particular to a turbofan engine fuel pump current interference detection and extraction circuit and analysis device, the circuit comprises a voltage following module and a bidirectional threshold detection and extraction module; in the bidirectional threshold detection and extraction module, the positive input end of a first operational amplifier is grounded, the negative input end of the first operational amplifier is connected with the output end of a voltage following module, and the output end of the first operational amplifier is connected with the cathode of a first diode and the anode of a second diode. The anode of the first diode is respectively connected with the output end of the voltage following module and the negative input end of the second operational amplifier; the cathode of the second diode is respectively connected with the output end of the voltage following module and the positive input end of the second operational amplifier; and the output end of the second operational amplifier is connected with an external current interference analysis module. Therefore, through the hardware circuit, the detection and extraction effect of the interference current can be effectively improved.

This invention belongs to the field of aero-engine turboshaft technology and discloses an automatic monitoring method and system for the performance degradation of aero-engine turboshaft engines. The method includes: determining the number of monitoring states and the altitude range corresponding to each monitoring state; determining the converted power value for each monitoring state; determining the turboshaft engine power; determining the converted gas generator speed and converted turbine inlet temperature corresponding to the converted power value for each monitoring state; determining the variation trend of the converted gas generator speed and converted turbine inlet temperature with the number of sorties for each monitoring state, and characterizing the degradation trend of the turboshaft engine through these trends. This invention does not require baseline performance, can monitor the engine performance variation trend with the number of sorties, and can monitor the performance degradation of the engine over operating time, without adding extra maintenance workload.

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 application discloses a degradation state monitoring method, device, equipment and medium of a turboshaft engine. The degradation state monitoring method of the turboshaft engine overcomes the shortcomings of the existing degradation state sensing method of the turboshaft engine based on limited measurement parameters, introduces a degradation factor range linear solution method based on a degradation factor fingerprint theory on the basis of a traditional particle swarm optimization algorithm, provides a more accurate and reasonable particle optimization limit range for the particle swarm optimization algorithm under the condition that the available system input parameters are insufficient, can provide a specific optimization range corresponding to any sensor actual collection main performance parameter degradation situation combination, avoids the degradation factor optimization from falling into a local optimum in multiple possible optimization spaces due to the insufficient data complexity, and thus optimizes the degradation state monitoring of the turboshaft engine to accurately obtain the overall performance degradation trend of the engine.

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 short annular backflow combustion chamber comprises a combustion chamber outer layer, a combustion chamber inner layer is arranged on the inner side of the combustion chamber outer layer, one end of the combustion chamber outer layer is connected with one end of the combustion chamber inner layer through a connecting cover, and a combustion cavity is formed between the combustion chamber outer layer and the combustion chamber inner layer; a plurality of evaporation pipes are fixedly arranged on the connecting cover located in the combustion cavity, a plurality of oil nozzles are fixedly arranged on the connecting cover located on the outer side of the combustion cavity, the output ends of the oil nozzles are inserted into the evaporation pipes in a one-to-one correspondence mode, and an inner flow guide cover is arranged on the inner side of the other end of the inner layer of the combustion chamber. A semi-closed space is provided for combustion through the combustion cavity formed by the outer layer and the inner layer of the combustion chamber, and the evaporation pipe on the connecting cover is matched with the oil nozzle, so that fuel oil is primarily evaporated in the evaporation pipe and then mixed with air entering the combustion cavity, and the fuel oil atomization effect is greatly improved; the short-ring backflow cover can guide gas which is not fully combusted to flow back to the combustion area to participate in the reaction again, and energy waste is reduced.

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.

Device and method for adapting (1, 5) the operation of a turboshaft engine comprising a variable-geometry element (2), the position of which is dependent on at least one parameter (3), allowing detection of a servo failure of the variable-geometry element and adaptation of the operation of the turboshaft engine by servo-controlling said at least one parameter by setting a setpoint value (Vcons) determined on the basis of the current value (Pcour) of the position of the variable-geometry element so as to impose a particular engine speed.

The invention discloses a novel turboshaft engine double-rotor coaxial nested transmission structure which comprises a power turbine shaft, a power turbine disc is fixedly arranged at one end of the power turbine shaft, a spline shaft is arranged on the side wall of the other end of the power turbine shaft, and a gas compressor shaft is arranged on the power turbine shaft between the spline shaft and the power turbine disc in a sleeving mode. The gas compressor shaft is coaxial with the axis of the power turbine shaft, a fastening seat is arranged on the gas compressor shaft, a centrifugal impeller is sleeved on the gas compressor shaft on one side of the fastening seat, the centrifugal impeller is fixedly connected with the gas compressor shaft, a gas turbine blade is sleeved on one side of the centrifugal impeller, and the gas turbine blade is fixedly connected with the centrifugal impeller. A hold-down ring is arranged on one side of the gas turbine blade. The coaxial nesting design is adopted for the power turbine shaft and the gas compressor shaft, the radial size of the whole structure can be obviously reduced, a transmission system is more compact, and the turbine engine is matched with the limited installation space of a turboshaft engine; the power turbine disc is directly fixed to one end of the power turbine shaft, and power can be efficiently transmitted.

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.