194 results about "Turboprop" patented technology

A reversible hydraulic pump for setting the pitch of a propellor of a turboprop can include two barrels connected by a transmission shaft. The first and second barrels are connected to the transmission shaft via first and second clutch means so that, when the transmission shaft rotates in a first direction, only the first barrel is rotated by the transmission shaft, and so that, when the transmission shaft rotates in a second direction opposite to the first direction, only the second barrel is rotated by the transmission shaft.

The invention discloses a method for connecting a front shock absorber and a torque compensation device, the front shock absorber comprises a main mounting bracket, a through hole I and a through hole II are formed in the main mounting bracket, the central axis of the through hole I and the central axis of the through hole II are distributed in a crossed manner, one end of the through hole II is communicated with the through hole I, and the other end of the through hole II is communicated with the torque compensation device. A vertical third through hole is further formed in the main mounting support and located in the middle of the second through hole, and one end of the third through hole is communicated with the second through hole. The connecting method includes the steps that one end of a connecting rod with a ball bearing extends into the second through hole from the third through hole, and the other end of the connecting rod is connected with a torque compensation device. Then the bolt rod part of the bolt is inserted from the through hole II, penetrates through the inner ring of the ball bearing at one end of the connecting rod, is connected with the inner ring of the ball bearing in a matched manner and then extends into the through hole I, and then the nut is locked on the bolt rod part in the through hole I in the through hole I, so that the bolt is locked on the main mounting bracket; and the front side shock absorber and the torque compensation device are connected.

According to the turboshaft turboprop engine overall performance scheme design method meeting the multiple working conditions, an engine nonlinear equation set containing a plurality of design points is constructed through an aerodynamic thermal process equation and engine complete machine matching conditions, and cycle parameters of aerodynamic design points and working points and rotating speeds under other working conditions are iterated; the invention relates to a process and a method for enabling an engine to simultaneously meet the requirements of component matching, performance requirements and load limitation at a plurality of design points (20-30 points), namely a multi-design-point model modeling and performance matching method meeting multi-working-condition-point calculation. In the process of designing engine cycle parameters and control laws under a new working condition combination by adopting a multi-design-point model, whether physical rotating speeds, conversion rotating speeds and turbine front temperatures of residual working condition points exceed limits or not under the existing cycle parameters and control laws is checked in sequence; and in the process of replacing the original working condition in the multi-design-point model with the working condition if the working condition exceeds the limit, a three-item replacement principle method is adopted for the working condition points of the engine.

The invention discloses a movable frame device for a high-power turboprop engine test bed and the engine test bed. The movable frame device comprises a movable frame framework, a front mounting seat and a counterweight system. The movable frame framework is arranged below the static frame device and used for being connected with the static frame device through a plurality of spring pieces arranged on the periphery of the movable frame framework, and then the rack system used for measuring the thrust of the turboprop engine is formed. The front mounting seat is used for being connected with an engine mounting rack for mounting a turboprop engine in a fast mounting manner so as to mount and support the turboprop engine to be measured. And the counterweight system is used for balancing the total weight of the turboprop engine and the engine mounting frame, so that the gravity center of the rack system is positioned in the center defined by the plurality of spring pieces. According to the movable frame device, the air inlet flow field of the propeller is not influenced by the size of the frame of the movable frame device, so that the engine performance is not influenced, the test result is high in accuracy, the test is safe and reliable, and the installation position of the propeller does not interfere with the structure of the movable frame device.

The invention provides a turboprop engine lubricating oil pressure adjusting system and adjusting method.The adjusting system comprises a lubricating oil tank output end, a lubricating oil pump and a filtering assembly, an engine, the lubricating oil pump and the lubricating oil tank are sequentially communicated through pipelines, the lubricating oil pump is communicated with the filtering assembly through a first pipeline, and a second pipeline is additionally arranged in the middle of the first pipeline and communicated with the lubricating oil tank; and a flow limiting assembly is mounted on the second pipeline. According to the lubricating oil system and the adjusting method, the first outlet end of the lubricating oil pump is additionally provided with the lubricating oil bypass oil way entering the lubricating oil tank in a pipeline parallel connection mode, and the lubricating oil output by the lubricating oil pump is shunted through the lubricating oil bypass oil way, so that the lubricating oil pressure of the lubricating oil main oil way is changed; the electric adjusting valve is used for adjusting and controlling the flow of the lubricating oil in the second pipeline, so that the variable test requirements of the lubricating oil pressure of the engine are met, and the technical problems that the lubricating oil pressure in the lubricating oil system is difficult to adjust in real time in the test and the lubricating oil pressure is inaccurate are solved.

The invention relates to the technical field of aircraft power systems, and discloses a hybrid power management system suitable for a vertical take-off and landing aircraft and a control method. A lithium battery pack; a super capacitor; the power distribution module is electrically connected with the main turboprop engine, the lithium battery pack and the super capacitor and used for controlling energy flow among the main turboprop engine, the lithium battery pack and the super capacitor according to instructions. The control method comprises the steps that a staged power distribution strategy is executed according to judged flight stages such as vertical take-off and landing, horizontal cruise or emergency, instantaneous power is compensated through a super capacitor during vertical take-off and landing, and combined propulsion or energy recovery is decided according to key parameters such as the lift-drag ratio during horizontal cruise. According to the scheme, the vertical take-off and landing response and flight stability are improved, the endurance mileage is increased, and the intelligence and safety of the system are improved through self-adaptive control and redundancy design based on the ground digital twin model.

Propeller restraint kits for turboprop aircraft are provided which include at least one, and preferably a pair, of propeller restraint systems. Each propeller restraint system will preferably include an open-ended propeller restraint boot that may be formed of a flexible and durable fabric material which is sized and configured for placement over the tip of a propeller blade. A cowling attachment assembly is provided in the kit and is adapted to being attached to an aircraft cowling skin. A propeller boot tether strap of predetermined length interconnects the propeller restraint boot and the cowling attachment assembly. The cowling attachment assembly includes (i) a quick disconnect (QD) pin assembly connected to a terminal end of the propeller boot tether strap, and (ii) a pin receiver adapted to being positionally attached to an interior portion of the aircraft cowling skin.

The invention provides a method for detecting global temperature distribution of a nacelle loaded with a turboprop engine, and relates to the technical field of aeronautical engineering.The method comprises the steps that a first nacelle model is generated according to temperature distribution of the surface of the turboprop engine at different stages and the ventilation requirements of air intake and exhaust of the nacelle; extracting a fluid computational domain of the first nacelle model, and performing temperature field and airflow field analysis on the fluid computational domain to obtain a temperature distribution cloud picture and an airflow vector distribution picture of the first nacelle model; if the temperature distribution cloud picture and the airflow vector distribution picture both meet the preset requirements, aerodynamic configuration details and internal solid components of the first nacelle model are added, and a second nacelle model is generated; and performing fluid-structure interaction conjugate heat transfer analysis on the second nacelle model under different working conditions, optimizing the nacelle air intake and exhaust layout according to the result of the conjugate heat transfer analysis, and generating a target nacelle ventilation and heat dissipation scheme. The nacelle has the technical effect that the overall performance and reliability of the nacelle are improved.

The invention relates to the technical field of aero-engine speed reducer and transmission system tests, and discloses a transmission shaft loading device which comprises a force transmission assembly connected with the front end of a transmission shaft, and the front end of the transmission shaft is suitable for serving as a power input end; the radial loading assembly applies a radial load Fr in the z-axis direction to the transmission shaft through the force transmission assembly. The axial loading assembly applies an axial load Fx in the x-axis direction to the transmission shaft through the force transmission assembly; the radial loading assembly and the axial loading assembly apply a bending moment load My around the y-axis direction to the transmission shaft through the force transmission assembly. According to the technical scheme, the radial load, the axial load and the bending moment load borne by the transmission shaft can be effectively simulated. According to the transmission shaft loading device, the load states of a turboprop engine speed reducer and a tilting main speed reducer of a tilting rotorcraft transmission system in a horizontal working condition in actual work can be truly simulated, and when the speed reducer is subjected to a simulation operation test, the real performance of the speed reducer is obtained.

The invention discloses a lubricating oil system of an aviation turboprop engine. The lubricating oil system comprises a lubricating oil supercharging device, an oil-gas separation device, a lubricating oil return device, a lubricating oil filtering device, a lubricating oil monitoring device and a connecting guide pipe communicating all the devices. The lubricating oil supercharging device comprises a main lubricating oil pump, an auxiliary lubricating oil pump and a torque measuring pump; the oil-gas separation device comprises a ventilation oil tank, an air separator and an oil mist separator; the lubricating oil return device comprises a lubricating oil tank, a lubricating oil radiator, a middle and rear bearing oil well pump, a transmission box oil well pump and a direct-current electric lubricating oil pump; the lubricating oil filtering device comprises a lubricating oil filter and a middle-rear bearing oil return filter; the lubricating oil monitoring device comprises a temperature metal chip annunciator and a magnetic chip detection annunciator. Appropriate lubricating oil pressure and oil quantity are provided, lubrication and heat dissipation of friction surfaces of parts in an engine are improved, and the use reliability of the engine is improved.

The invention discloses a high-power turboprop engine preassembling device and a test run method, which are used for preassembling a high-power turboprop engine, and the high-power turboprop engine comprises an engine main body, a propeller and a test structure, the preassembling device comprises a preassembling frame used for supporting, a height adjusting structure arranged on the preassembling frame and an installing frame used for being detachably connected with the height adjusting structure, the preassembling frame is used for being installed in a test preparation room so as to preassemble the installing frame and the high-power turboprop engine, and the height adjusting structure is used for adjusting the vertical height of the installing frame when the installing frame is preassembled. The mounting rack is used for mounting the engine main body in a cantilever manner and mounting the propeller and the test structure on the engine main body after being connected with the height adjusting structure, and then hoisting the engine main body into a test room after being separated from the height adjusting structure; the preassembling requirement of the high-power turboprop engine is met, rapid reloading and preassembling of the high-power turboprop engine are achieved, and the utilization rate of a test bed is increased.

The invention relates to the technical field of aero-engine vibration control, and discloses an on-line automatic balance system for a turboprop engine propeller rotor, which comprises a signal acquisition and analysis module, an automatic balance state monitoring and control module and an automatic balance actuator, the signal acquisition and analysis module is used for monitoring and acquiring an original vibration signal of the rotor system in real time to obtain vibration monitoring information, and transmitting the vibration monitoring information to the automatic balance state monitoring and control module; the automatic balance state monitoring and control module is used for receiving the vibration monitoring information and outputting a driving control instruction to the automatic balance actuator according to the vibration monitoring information; the driving control instruction comprises the moving direction and the stepping amount of the balancing weight; the automatic balance actuator comprises two balance weight discs, and the balance weight discs are used for moving according to the driving control instruction so as to carry out vibration suppression. According to the invention, the supporting stability and the assembling economy are improved.

The invention relates to the technical field of engine testing, and discloses a turboprop engine test bed simulation method, device and equipment and a storage medium, and the method comprises the steps: obtaining a turboprop engine test bed geometric model, and replacing a real propeller geometric model with an equivalent disc model in the turboprop engine test bed geometric model; performing parameter setting on the geometric model, wherein the parameter setting comprises setting the boundary condition of the equivalent disc in the geometric model as a fan boundary condition and setting the pressure jump parameter of a fan as a propeller pressure jump value; and performing flow field simulation of the turboprop engine test bed based on the geometric model of the turboprop engine test bed after parameter setting to obtain a propeller air flow simulation value. According to the method, a complex real propeller geometric model with a large number of grid nodes is omitted, computing resources are saved, the evaluation efficiency is improved, and therefore optimization iteration of turboprop engine test bed design is accelerated.

The invention relates to the field of unmanned aerial vehicles, and discloses a tilting type composite thrust system of a small fixed-wing aircraft, comprising: a physical bearing and power unit module comprising wings and six groups of tilting thrust units on the wings, each group of unit being composed of a turboprop engine and a variable pitch propeller and generating thrust; the thrust vector adjusting module comprises six sets of electric tilting joints and drives the tilting thrust unit to rotate so as to adjust the thrust direction. The state sensing and feedback module is provided with an angle sensor for monitoring the tilting angle in real time; the cooperation and synchronization control module comprises a synchronization controller which is connected with the angle sensor and the electric tilting joints and controls the six sets of electric tilting joints to be converted in batches according to the monitored angle. According to the invention, the integrated electric tilting joint is arranged, and the joint contains a main tilting shaft for wide-angle mode switching and an auxiliary fine tuning shaft for small-range active compensation, so that two adjusting mechanisms with different functions are integrated in a single structure.

The invention belongs to the technical field of structural vibration testing, and particularly relates to an actual measurement spectrum conversion method and system for a vibration acceleration power spectrum, which considers system response caused by the vibration acceleration power spectrum as excitation for conversion of the vibration acceleration power spectrum, is beneficial to make up for the defects of the existing conversion method, and improves the reliability of the vibration acceleration power spectrum. According to the method, the vibration acceleration power spectrum of the typical part in the flight process of the turboprop aircraft can be reasonably and effectively converted into the actual measurement spectrum, so that the vibration environment test is carried out on the airborne equipment, a result conforming to the reality can be obtained, and the design and improvement of the airborne equipment can be effectively guided.

The invention relates to the technical field of unmanned aerial vehicles, and discloses an unmanned aerial vehicle with a modularized fuselage and a design method thereof.The two sides of the fuselage of the unmanned aerial vehicle are provided with wings, each wing is provided with an engine compartment, and the two sides of the fuselage are further symmetrically provided with empennage supporting assemblies; each empennage supporting assembly is provided with a vertical empennage, and a horizontal empennage is arranged between the two vertical empennages. The layout form of two turboprop engines, double tail booms and a high horizontal tail is adopted, and the requirement for fast loading and unloading goods on the ground of the unmanned transport plane is met; when the horizontal tail of the unmanned transport plane is designed, the aerodynamic characteristics of the wings and the axial position of the horizontal tail are considered, so that the installation height of the horizontal tail is reasonably determined, and it is ensured that a rear cargo hold door at the tail of the plane body leaves sufficient space for loading; the problem that the control efficiency of the horizontal tail elevator is reduced due to downwash airflow generated by the wings is avoided, and the stability and maneuverability of the unmanned transport plane during takeoff and landing are guaranteed.

The invention aims to provide a turboprop engine and a variable pitch device thereof. The variable pitch device comprises an outer shell, a piston, an adjusting piece, a locking piece and a flow path. The piston divides the interior of the outer shell into a first cavity and a second cavity, a third cavity is defined between the adjusting piece and the outer shell, and the locking piece is in transmission connection with the adjusting piece. When the fluid pressure in the second cavity is larger than a pressure threshold value, the adjusting piece is driven to move in the direction of compressing the elastic piece and can drive the locking piece to move to the first position, and when the fluid pressure in the second cavity is smaller than the pressure threshold value, the elastic piece can elastically reset and drive the adjusting piece to act. The adjusting piece drives the locking piece to move to the second position, the locking piece allows the piston to move at the first position, and the locking piece limits the piston to move at the second position. By means of the variable pitch device, the propeller fan can be prevented from moving towards the flat propeller at any pitch angle position.

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

A hybrid electric turboprop includes a propeller, a thermal engine, an electric motor, a gearbox, and an air inlet. The propeller is configured to rotate about a propeller axis and includes a plurality of blades extending radially outwardly from the propeller axis such that, as the propeller is rotated about the propeller axis, the plurality of blades define a substantially circular blade path area centered about the propeller axis and having a radius. The gearbox couples both the thermal engine and the electric motor to the propeller to enable each of the thermal engine and the electric motor to drive rotation of the propeller about the propeller axis. The air inlet defines an opening. A radial distance is defined from the propeller axis to a location within the opening. The radial distance is equal to or less than 60% of the radius.

Disclosed is an interconnection system (1) for an aircraft turbine engine, comprising a plate (2) that comprises rigid conduits (C) secured to the plate (2) and connecting at least two elements to one another and to at least one inlet and to at least one outlet, in order to allow oil to circulate.

The invention discloses a hydraulic torque compensation device, and belongs to the technical field of aviation equipment vibration isolation installation, the hydraulic torque compensation device comprises a left actuating cylinder, a right actuating cylinder and a hydraulic pipe, the left actuating cylinder and the right actuating cylinder respectively comprise an oil cylinder sleeve and an actuating rod, the oil cylinder sleeves and the actuating rods form hydraulic cavities, the hydraulic cavities of the left actuating cylinder and the right actuating cylinder are communicated through the hydraulic pipe, and the hydraulic pipe is connected with the left actuating cylinder and the right actuating cylinder. A rubber layer is arranged between the oil cylinder sleeve and the actuating rod, the rubber layer is fixedly connected with the oil cylinder sleeve and the actuating rod, the actuating rod is provided with a plug pin penetrating through the side face of the actuating rod, the plug pin is provided with a connecting lifting lug, plug pin holes are formed in the side wall of the oil cylinder sleeve and the rubber layer, and the two ends of the plug pin extend out of the plug pin holes. And the bolt can move along with the actuating rod. The invention is suitable for an aircraft turboprop engine, the service life of the aircraft turboprop engine is equivalent to that of the engine, and maintenance is not needed in the whole life cycle.

The invention discloses an aero-engine propeller stalling mechanism, a propeller mechanism and a stalling control method.According to the aero-engine propeller stalling mechanism, an actuating mechanism rotates, the actuating mechanism drives a lead screw to rotate, rotation of the lead screw is changed into axial displacement of a lead screw sleeve, and a brake disc on the lead screw sleeve is pressed to a movable face together; and then the propeller transmission shaft is locked through the working shaft, and locking of the propeller is completed. Under the condition of power failure, elastic force generated by compression of the first spring on the lead screw sleeve exerts acting force on the brake disc and the lead screw, self-locking of the lead screw and stalling of the propeller are completed, and the problems that blades of the propeller of the turboprop engine rotate after the engine stops and the like are solved.

The invention relates to a propeller blade or airfoil (10) for a turboprop engine, made of a composite material and comprising a matrix-densified fibrous reinforcement, the propeller blade or airfoil comprising, in a longitudinal direction (DL), a root (12) and an aerodynamic profile (11). The fibrous reinforcement comprises a fibrous preform (200) in the form of a three-dimensional woven body having a root preform portion (121) in the root (12) and an aerodynamic profile portion (211) in the aerodynamic profile (11), the root preform portion (212) and the aerodynamic profile preform portion (211) being joined to each other by three-dimensional weaving. The root preform portion (212) includes two woven skin layers (2121, 2122) wound about the insert (130).

The invention relates to the technical field of aero-engine overall performance and control, in particular to an acceleration rule design method based on a turboprop engine acceleration performance calculation model. According to the method, in the process of solving a performance calculation model of the turboprop engine, fuel flow iterative solving is carried out for limiting parameter errors, a pitch angle optimization method is matched, and implementation steps and a design process of turboprop engine acceleration law design are achieved. The calculation amount generated by frequently calling a turboprop engine performance calculation model is reduced, and the design efficiency of the turboprop engine acceleration law is remarkably improved. Meanwhile, by optimizing the pitch angle, it is ensured that the turboprop engine keeps safe and stable operation in the acceleration process, and the maximum performance potential of the turboprop engine is fully exerted.

This application discloses a turboprop engine dual-rod timing coordinated control and disturbance-free switching system and method. The system includes: a power rod and a status rod; two absolute encoders for converting the angle input of the dual rods into encoder signals and transmitting them to a programmable logic controller (PLC); an FPGA module for receiving and converting control signals from the PLC into RVDT signals, which are then sent to the EEC and PEC, respectively; a host computer for presetting loading test lines, monitoring test data in real time, displaying test status and alarm information, and communicating with the PLC to write loading test line data to the PLC; a sensor group for collecting relevant engine parameters in real time; and a PLC for communicating with the absolute encoder, FPGA module, host computer, and sensor group, respectively. This application overcomes the risks of interference during mode switching, timing coordination issues, sudden changes in electrical signals, and response delays of abnormal protection mechanisms.

The application belongs to the field of aviation medium-sized aircraft design, and relates to a large-angle glide performance calculation method of a fixed-wing turboprop aircraft. The method comprises the following steps: determining the combination characteristics of the power device of the turboprop aircraft according to the characteristics of the turboprop engine and the propeller; increasing the resistance and reducing the lift by using the double-open state of the spoiler, so as to realize large-angle glide; and obtaining the required large-angle glide performance of the aircraft by modeling and adjusting calculation.

The invention belongs to the field of flight performance design, and relates to a method for calculating the air-slip performance of a fixed-wing turboprop aircraft. The method comprises the steps that according to the characteristics of a turbine engine and a propeller, the combined characteristics of a propeller aircraft power device are determined, the influence of feathering of the propeller on the aerodynamic characteristics of an aircraft is considered, and the needed aircraft air-slip performance is obtained through modeling and adjustment calculation according to aerodynamic characteristic parameters and weight characteristic parameters of the aircraft.

To solve the challenge to make a single gas turbine engine function as both a turboprop and a turbofan, because, for an aircraft capable of vertical take-off and landing, a turboprop engine is used to enable horizontal flight with good fuel efficiency, and a turbofan engine, which can generate large thrust during vertical take-off and landing, is used for vertical take-off and landing.SOLUTION: A vertical take-off / landing gas turbine engine of the present invention can be configured as a turbofan engine capable of generating large thrust during vertical take-off and landing by opening and closing two valves relative to each other, and as a fuel-efficient turboprop engine during horizontal flight.SELECTED DRAWING: Figure 3

An aircraft engine, has: a core having a compressor, a combustor, and a turbine disposed in serial flow communication, the turbine in driving engagement with a propeller; a nacelle extending around the core, the nacelle having a nacelle intake upstream of the core and a nacelle exhaust downstream of the core, the nacelle intake configured for receiving air from an environment outside the nacelle, the nacelle intake fluidly connected to the compressor for feeding air thereto, the nacelle exhaust configured to discharge combustion gases from the turbine into the environment outside the nacelle; and a blocking member movable between an open position in which the core is fluidly connected to the environment via both the nacelle intake and the nacelle exhaust, and a closed position in which the blocking member hinders fluid communication between the core and the environment via one of the nacelle intake and the nacelle exhaust.