78 results about "Off design" patented technology

A method and system for performing continuous (real-time) physics based prognostics analysis as a function of actual engine usage and changing operating environment. A rule-based mission profile analysis is conducted to determine the mission variability which yields variability in the type of thermal-mechanical loads that an engine is subjected to during use. This is followed by combustor modeling to predict combustion liner temperatures and combustion nozzle plane temperature distributions as a function of engine usage which is followed by off-design engine modeling to determine the pitch-line temperatures in hot gas path components and thermodynamic modeling to compute the component temperature profiles of the components for different stages of the turbine. This is automatically followed by finite element(FE) based non-linear stress-strain analysis using an real-time FE solver and physics based damage accumulation, life consumption and residual life prediction analyses using microstructural modeling based damage and fracture analysis techniques.

The invention discloses a multi-disciplinary optimization design method for the airfoil profile of a wind turbine. According to performance requirements for blade enlargement and operating environment diversification of the wind turbine, aerodynamic performance, structure attributes and acoustic characteristics of the airfoil profile are optimized at the same time, various performance requirements of the airfoil profile are parameterized, a multi-disciplinary optimal objection function of the airfoil profile is established in combination with a weight coefficient method, and an optimization design system of the airfoil profile of the wind turbine is established in combination with an optimization algorithm. Numerical prediction indicates that multiple aspects of aerodynamic efficiency, off-design point performance, variable working condition stability and the structure of the novel airfoil profile designed according to the multi-disciplinary optimization design method for the airfoil profile of the wind turbine are promoted under the condition that the aerodynamic sound pressure level is not increased obviously, meanwhile, the working range of the airfoil profile is optimized, and the airfoil profile has low stalling characteristic parameters and performance stability parameters.

An aircraft thickness / camber control device mounts to the lower surface of a airfoil configuration, for example on a fuselage, and extends along a longitudinal axis. The device, when deployed, generates expansions ahead of compressions generated by off-design conditions, inlet spillage for example, and enables maintenance of a low boom signature. The device, when positioned at appropriate locations, may also be used as a drag reduction device. The thickness / camber control device comprises a structural member capable of coupling to the airfoil at a position forward of the concentrated source of added compression and a control element. The control element is coupled to the structural member and controls the structural member to adjust thickness / camber of the configuration to cancel the far-field effect of the extra compression or concentrated pressure source.

The invention discloses a full-automatic cooker, which mainly comprises a rice supply structure, a cleaning structure and a heating structure, and is characterized in that: the rice supply structure is arranged in the body of the device; the body is connected with the heating structure and a cover; the cover has a direct covering type structure or a cover-turning type structure; and the cleaning structure is arranged at the upper end of the cover or in a shell of a pot, and is provided with a lifting shaft cleaning structure or optionally provided with a spiral lifting cleaning structure or atelescopic cleaning structure. The full-automatic cooker also comprises heat preservation design, power-off design, time setting, rice quantity setting and water quantity setting, a local control panel singlechip is combined with an embedded system, a data instruction is connected to a display screen, the automatic control is carried out by a programmable logic controller (PLC), or the PLC forms a network communication interface, performs data transmission and the like, and a series of automatic cooking programs or remote control commands are executed. Through optimized combination, the structure is simplified, the manufacturing cost is low and the full-automatic cooker is suitable for industrial promotion.

The invention discloses a method for realizing state monitoring and fault diagnosis of a water turbine based on a chaos theory, in particular, relates to a method for operating state monitoring and fault diagnosis of the water turbine, can preferably master the characteristic of instability of an internal flowing field of the water turbine, and solves the problem of difficult diagnosis of cavitation fault of a traditional water turbine. The method uses the promotion of wavelet transform for denoising pressure pulsation signals, and uses a chaos dynamics method for analyzing chaos dynamics characteristics of the water turbine in off-design operation so as to judge the caviation degree in the operation of the water turbine and to predict possible faults. The method is applied to the operation state monitoring and the fault diagnosis of the water turbine.

The invention relates to an early warning service management system based on remote expert service. In the system, sensors based on hybrid automatic repeat request (ARQ) technology collect the grouped data of a bridge; the machine to machine (M2M) technology is adopted to monitor the information between the intelligent sensor devices, the monitoring information is transmitted remotely in a wireless digital manner; a terminal collector performs bidirectional data transmission on the monitoring information through a terminal remote transport protocol and an intelligent network platform, the data collected by the terminal collector are compared with the stress simulation database information of the bridge design and off-design small probability state finite element computation structure established by an expert service system, the comparison result is used for evaluating and processing; early warning is performed according to the comparison and evaluation result of the condition and monitoring information of the bridge; and when the monitoring data are abnormal or the warning level is higher, the system automatically sends a message to an expert and the expert can give corresponding handling advices and measures timely, thus the timely and dynamic management of information can be realized.

A shunt pulsation trap for a screw compressor reduces gas pulsation, NVH and improves off-design efficiency without using a traditional serial pulsation dampener and a sliding valve. Generally, a screw compressor with the shunt pulsation trap has a pair of multi-helical-lobe rotors housed in a compressor chamber for propelling gas flow from a suction port to a discharge port of the compressor chamber with internal compression. The shunt pulsation trap comprises an inner casing as an integral part of the compressor chamber, and an outer casing oversized surrounding the inner casing, therein housed various gas pulsation dampening means or gas pulsation energy recovery means or gas pulsation containment means, at least one injection port (trap inlet) branching off from the compressor chamber into the pulsation trap chamber and a feedback region (trap outlet) communicating with the compressor outlet.

The invention relates to a stimuli-responsive composite material made from bacterial nano cellulose as well as a preparation method and application of the stimuli-responsive composite material. A bacterial nano cellulose base material in a hydrogel state is combined with polyelectrolyte macromolecules in an interpenetrating or semi-interpenetrating manner, and then is wholly or partially dehydrated to obtain the composite material. The composite material is high in rehydration and swelling capacities under the condition of a particular Ph, and keeps the characteristics of low swelling capacity and difficulty in rehydration under the condition of an off-design Ph value. The composite material has the characteristics of temperature response; the pore size of network of the composite material can be controlled, and the penetration rate of solute molecules can be controlled to release a drug in a control manner. Meanwhile, the composite material has the characteristics of high strength, high biocompatibility and the like of the bacterial nano cellulose, and can be applied to smart wound dressings, smart drug carriers, sensors, chemical valves and the like. The composite material has the advantages that the preparation process is simple, the cost is low, and a good application prospect is achieved.

This invention provides three-D shaping software, which can simulate the complete assembling process of transformer in screen, produce the three-D products model same with the real products in shape, reflect the fitting information of parts and make the designer modifying the design before production, which is operated in MDT three-D software platform and adapted to the power transformer equal to or lower than 110 kv type.

The invention provides a multifunctional manned lunar surface lander based on modular design, modularization and integral landing and take-off design modes are adopted, and repeated use and extensibleapplication are achieved. The lander comprises a living cabin, wherein the living cabin is in a multifunctional centralized manner, is located on the upper part of the lander and is used for establishing sealing connection with other aircrafts, providing life and working environments for an astronaut and supporting the astronaut in entering and exiting from the cabin; and the lander further comprises a landing cabin, the landing cabin is used for placing a propelling system, electronic equipment and a landing buffering mechanism so that a supporting platform and a buffer energy absorption support can be provided for landing and take-off, and the living cabin and the landing cabin are designed in a modular mode so that different tasks can be executed through the combination of different modules. The manned lunar surface lander is compact in structure and low in requirement for the transport capacity of a carrier rocket, can be used repeatedly, has a multi-task application expansion characteristic, and is beneficial for reducing the cost of the manned lunar-landing comprehensive task.

The invention belongs to the technical field of condenser monitoring, and particularly discloses a condenser dirt degree online monitoring method. The method includes the steps that a steam turbine off-design performance model is built, condenser steam parameters are obtained according to the steam turbine off-design performance model, and the overall heat exchange thermal resistance of a condenser is obtained through calculation according to the steam parameters of the condenser; the cooling pipe water side convection heat transfer thermal resistance of the condenser, the heat conduction thermal resistance of the wall of a cooling pipe and the steam side condensation heat transfer coefficient of the condenser are calculated, the steam side condensation heat transfer coefficient is modified, and the steam side condensation heat transfer thermal resistance is obtained; the dirt thermal resistance of the condenser is solved according to the overall heat transfer thermal resistance of thecondenser, the cooling pipe water side convection heat transfer thermal resistance, the heat conduction thermal resistance of the wall of the cooling pipe and the steam side condensation heat transfer thermal resistance, the dirt thermal resistance represents the water side cleanliness of the condenser, and then dirt degree online monitoring of the condenser is achieved. By means of the method, dirt degree real-time online monitoring of the condenser can be achieved, and the method has the advantages of being stable, accurate and tolerant to faults.

The invention relates to a CAE (Computer Aided Engineering) analysis based product structure optimization method and system. The CAE analysis based product structure optimization method comprises step 1, establishing a finite element mesh model of a product structure before optimization through an application module which is arranged in a computer system and receiving material parameters of the structure; step 2, receiving boundary conditions and loads of the modal analysis under the static analysis and of constraint condition, wherein the boundary conditions and loads are defined based on the working conditions under two working states, loading the finite element mesh model and obtaining a response result through calculation; step 3, establishing a design space and an off-design space according to the response result; step 4, receiving topology optimization parameters which are defined according to the design space, the off-design space, structural loads and the response result, establishing a topology optimization model, completing the optimization analysis and obtaining an optimization result; step 5, reestablishing the finite element mesh model according to the optimization result, performing loading in the way as same as that in the step 2 and obtaining a response result of the product structure after optimization through calculation. According to the CAE analysis based product structure optimization method and system, the performance requirements are met and meanwhile the lightweight design is implemented.

A unique process cycle and apparatus design separates the consumer (cryogenic) load return flow from most of the recycle return flow of a refrigerator and / or liquefier process cycle. The refrigerator and / or liquefier process recycle return flow is recompressed by a multi-stage compressor set and the consumer load return flow is recompressed by an independent consumer load compressor set that maintains a desirable constant suction pressure using a consumer load bypass control valve and the consumer load return pressure control valve that controls the consumer load compressor's suction pressure. The discharge pressure of this consumer load compressor is thereby allowed to float at the intermediate pressure in between the first and second stage recycle compressor sets. Utilizing the unique gas management valve regulation, the unique process cycle and apparatus design in which the consumer load return flow is separate from the recycle return flow, the pressure ratios of each recycle compressor stage and all main pressures associated with the recycle return flow are allowed to vary naturally, thus providing a naturally regulated and balanced floating pressure process cycle that maintains optimal efficiency at design and off-design process cycle capacity and conditions automatically.

A thermal power plant thermoelectric decoupling system comprises two steam turbines, two condensers or two air cooling islands corresponding to the two steam turbines, a dead steam extraction system and a dead steam recovery and heat supply system. Dead steam is extracted through the dead steam extraction system and conveyed to the dead steam recovery and heat supply system through a pipeline. Thedead steam recovery and heat supply system is connected with a heat supply pipe network and comprises a first dead steam condenser, a second dead steam condenser, a steam increase machine and a steamincrease machine condenser. Dead steam of the steam turbines is recovered for heat supply, the discharge steam amount during heat supply consumption is reduced, thus, main steam flow is reduced, thepower of a high-pressure cylinder and an intermediate-pressure cylinder is lowered, and large thermoelectric decoupling is achieved; cold end losses can be reduced, and energy conservation and emission reduction are achieved; the self-balancing function is achieved, the off-design condition performance is excellent, and the adaptability is high; the steam turbine loads are adjusted rapidly; and the complementarity with thermoelectric decoupling technologies of other types is good, and the combined operation effect is better.

The invention provides a shipbuilding man-machine engineering simulation evaluation method and a system. The method comprises that S1. the product data, tool data, building resource data, virtual human data and technological requirements which the shipbuilding technology relates to are input, and a environment of shipbuilding man-machine engineering simulation evaluation is established; S2.according to the input technological requirements, the processes of shipbuilding technology is simulated and the critical technological processes of shipbuilding are screened out; S3.the critical technological processes of shipbuilding screened out is performed the virtual human operation simulation; S4.the virtual operation of the virtual human is performed a man-machine engineering evaluation and a result of man-machine engineering evaluation is acquired; and S5.judging if the result of man-machine engineering evaluation reaches the standard, if the result reaches the standard, the result of shipbuilding man-machine engineering simulation which the result of man-machine engineering evaluation that reaches the standard corresponds to are output, if the result does not reach the standard, go back to the step 2. The shipbuilding man-machine engineering simulation evaluation method has the advantages of achieving man-machine engineering simulation and analysis and evaluation for the shipbuilding technology at design stage and avoiding the design mistake.

The invention relates to a method for determining mineral aggregate gradation range based on gradation variability of raw materials, which obtains average sieve curves and corresponding coefficients of fluctuation through sieve tests on various grades of raw material large sample amounts, and determines the fluctuation range of sieve classification, target resultant gradation and the use ratio ofvarious grades of raw materials, thereby determining the fluctuation range of various grades of raw materials. Values of throughput rate off design gradation of certain sieve pores in an upper fluctuation line and a lower fluctuation line are large because of the influence of the variability of raw materials, so that the complexity of material gradation is reflected. No matter an average value resultant gradation curve or the gradation fluctuant upper and lower fluctuation lines are adopted, the pavement performance can meet the relevant requirements, therefore, the control of raw material gradation is required to be enhanced during practical works, so as to ensure that the gradation is close to the average value resultant gradation curve to the greatest extent and does not exceed the upper and lower fluctuation lines, so that good pavement performance can be guaranteed.

A method for predicting fluid temperature distribution of a vertical single U-shaped buried pipe of a ground source heat pump under variable operating conditions belongs to that field of ground sourceheat pump, and is used for calculating fluid temperature distribution in U-shaped pipe under variable heat flux or variable inlet fluid temperature operating conditions. Firstly, a single U-shaped buried pipe is simplified to an equivalent pipe based on the equivalent pipe diameter method, and a one-dimensional radial heat transfer numerical model including fluid, equivalent pipe, backfill and soil is established, and the heat transfer equation is discretely solved to calculate the average temperature of the fluid in the single U-shaped buried pipe. The results show that the average temperature of the fluid in the U-shaped buried pipe is higher than that in the single U-shaped pipe. Then, based on the quasi-three-dimensional heat transfer model in the borehole, the relationship between the inlet fluid temperature and the average wall temperature of the borehole with respect to the average fluid temperature and heat flux is established, and the fluid temperature distribution in the U-tube under the conditions of variable heat flux or variable inlet fluid temperature is calculated. This method has the advantages of less computation, high precision and strong generality.

The invention discloses a high-orbit satellite comprehensive electronic computer system and a control method. A fault-tolerant SRAM module is adopted to locally save and restore important data, the storage space of the important data is expanded to 512 KB from 2KB, and the storage cycle is shortened to 4 seconds from 60 seconds. By means of the high-orbit satellite comprehensive electronic computer system and the control method, the spaceborne computer system power supply design is optimized, and by adding an independent fault-tolerant power source, the problem that a CPU system and a fault-tolerant machine switching circuit are supplied with the same power source is solved. By the adoption of the idea of machine switching fault-tolerant circuit one-way design and independent switch-on andswitch-off design, the hidden safety hazards of the design which causes frequent machine switching between a host and a standby unit are avoided. Multi-clock input control logic is adopted, and any path of a CPU minimum system crystal oscillator, a temperature-compensation crystal oscillator, and a precise clock source can be adopted by a spaceborne computer system to achieve time management. A Spacewire bus node module is designed, interconnection of the spaceborne computer system and the satellite Spacewire bus network is achieved, two independent full duplex data interfaces are provided, and the maximum rate of the bus interfaces reaches 200 Mbps.

Aerofoil accessories are provided, configured for selective attachment to a wing element, the wing element having an outer facing aerofoil surface and being based on at least one datum aerofoil section. Each accessory provides a modified geometric profile to a datum profile of the at least one aerofoil section when attached to the wing element. The accessories are each configured for having a substantially fixed geometric profile with respect to the at least one datum aerofoil section at least whenever said wing element is airborne with the respective accessory attached to the wing element. The modified geometric profile is such as to provide said wing element with the accessory attached thereto with a desired change in performance relative to a datum performance provided by the wing element absent the accessory. A kit is also provided for enhancing performance of a wing element in off-design conditions. A method is also provided for enhancing performance of a wing element in adverse conditions.

An aircraft thickness / camber control device mounts to the lower surface of a airfoil configuration, for example on a fuselage, and extends along a longitudinal axis. The device, when deployed, generates expansions ahead of compressions generated by off-design conditions, inlet spillage for example, and enables maintenance of a low boom signature. The device, when positioned at appropriate locations, may also be used as a drag reduction device. The thickness / camber control device comprises a structural member capable of coupling to the airfoil at a position forward of the concentrated source of added compression and a control element. The control element is coupled to the structural member and controls the structural member to adjust thickness / camber of the configuration to cancel the far-field effect of the extra compression or concentrated pressure source.

Change in swirl of gas turbine exhaust gases at off-design conditions is a key driver of exhaust diffuser inefficiency that adversely impact the gas turbine performance. Conventional ways to control swirl such as blowing, suction, and vortex generation are undesirable since they require parasitic power, are complex to design, and dilute the exhaust gas energy. To address such short comings, shape memory devices are incorporated into struts of an exhaust diffuser of a gas turbine. The shape memory devices change shape in accordance with heat, which can be applied through memory device heaters. By controlling the memory device heaters, the heat applied to the shape memory devices can be controlled. The shapes of the struts can be altered through altering the shapes of the memory device in consideration of load conditions to increase the efficiency.

A shunt pulsation trap for a cyclic positive displacement (PD) compressor reduces gas pulsation, NVH and improves off-design efficiency without using a traditional serial pulsation dampener and a variable geometry. Generally, a shunt pulsation trap for a cyclic PD compressor is configured to trap and attenuate gas pulsations before discharge and comprises a housing structure having a flow suction port, a flow discharge port, a compressor cavity and a pulsation trap chamber adjacent to the PD compressor cavity, therein housed various pulsation dampening means or pulsation energy recovery means or pulsation containment means, at least one injection port (trap inlet) branching off from the PD compressor cavity into the pulsation trap chamber and a feedback region (trap outlet) communicating with the PD compressor outlet. The associated principles, methods and embodiments are disclosed.

The invention belongs to the technical field of aerodynamics, and discloses an active vortex generator based on electromagnetic excitation. The active vortex generator based on electromagnetic excitation comprises a vibrating reed, a frame structure, a permanent magnet and an electromagnetic exciter, wherein the vibrating reed, the frame structure, the permanent magnet and the electromagnetic exciter are sequentially arranged in a wing of an aircraft or a leading-edge cavity of the aircraft from top to bottom. When the active vortex generator is arranged in the wing of the aircraft, a groove structure which is matched with the vibrating reed in cross-section shape is arranged on the skin of the aircraft, the vibrating reed is embedded into the groove structure, and when the vibrating reed is buried inside the skin of the aircraft, the upper surface of the vibrating reed and the horizontal plane of the skin of the aircraft are kept consistent. According to the active vortex generator based on electromagnetic excitation, active adjustment of flow control is achieved, the parasitic drag and adverse influence of the active vortex generator under the off-design working conditions are reduced, and the purposes of optimal drag reduction and optimal noise reduction are achieved.

A shunt pulsation trap for a screw compressor reduces gas pulsation and NVH, and improves off-design efficiency, without using a traditional serial pulsation dampener and a sliding valve. A screw compressor has a pair of multi-helical-lobe rotors that are housed in a compressor chamber that propel gas flow from a suction port to a discharge port of the compressor chamber. The shunt pulsation trap includes an inner casing as an integral part of the compressor chamber, and an outer casing oversized and surrounding the inner casing. The shunt pulsation trap houses at least one gas pulsation dampening device, and includes at least one injection port (trap inlet) branching off from the compressor chamber into the pulsation trap chamber and a feedback region (trap outlet) communicating with the compressor outlet.