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45results about How to "Reduce blending loss" patented technology
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Blade hole type prewhirl nozzle for prewhirl cooling system
InactiveCN105114186AGuaranteed accelerationGuaranteed deflection performanceTurbine/propulsion engine coolingAviationEngineering
The invention discloses a blade hole type prewhirl nozzle for a prewhirl cooling system, and belongs to the field of application of aero-engine prewhirl cooling systems. The blade hole type prewhirl nozzle is characterized in that a blade pressure face and a blade suction face are adopted for forming inclined hole runners deflecting in the circumferential direction of a nozzle ring at equal intervals, deflecting molded faces of the nozzle runners are in a gradually-contracted shape, a minimum laryngeal area is achieved at an outlet of the prewhirl nozzle, the accelerating performance and the deflecting performance of the prewhirl nozzle are effectively guaranteed, and the flowing loss of a main flow is small. Blade type solid blocks are distributed between adjacent runners of the prewhirl nozzle, under the condition that the laryngeal area of the nozzle is definite, the ratio of the blade height to the pitch of the prewhirl nozzle can be flexibly adjusted by additionally arranging the blade type solid blocks, and the long and narrow performance of the sections of the runners is effectively improved, so that the secondary flow loss of the end walls in the runners is reduced, the flow coefficient and the prewhirl efficiency of the prewhirl nozzle are improved, and the system temperature drop effect is further improved.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Engine turbine disc cavity structure with pre-rotation nozzle and flow guiding disc
ActiveCN111441828AShorten speedLower the total temperatureBlade accessoriesLeakage preventionEngineeringConvection heat
The invention discloses an engine turbine disc cavity structure with a pre-rotation nozzle and a flow guiding disc. The engine turbine disc cavity structure comprises a turbine disc and further comprises the flow guiding disc and a pre-rotation nozzle ring which are arranged in front of the turbine disc. High-pressure low-temperature two-strand airflow is divided into two strands after entering apre-rotation airflow cavity through the pre-rotation nozzle ring. One strand of airflow passes through pre-rotation cool air receiving holes evenly distributed in the circumferential direction of theflow guiding disc and enters an axial ventilation hole in the bottom of a turbine disc mortise along a radial flow guiding plate on the rear side of the flow guiding disc. The other strand of airflowpasses through a sealed grid tooth ring on the flow guiding disc, and after the other strand of airflow is pre-rotated and pressurized through an inclined flow guiding plate above the front side of the flow guiding disc and is converged with cool air from cool air impact holes evenly distributed in the circumferential direction of the installing edge of a guiding device, the other strand of airflow enters a main runner through a turbine rotor and stator gap. By means of the engine turbine disc cavity structure, the relative total temperature of cool air can be reduced, convection heat exchangeof cool air and the turbine disc is enhanced, pre-rotation pressurizing is conducted on the wheel edge seal gas, the seal effect is improved, and seal gas and main flow mixing losses are reduced.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Turbine disk cavity sealing structure with bypass bleed air
InactiveCN110905606AIncrease air velocityIncrease the angleLeakage preventionMachines/enginesCold airEngineering
The invention relates to a turbine disk cavity sealing structure with bypass bleed air. The turbine disk cavity sealing structure with bypass bleed air comprises an inner support ring assembly and a front baffle assembly, wherein a bypass bleed air groove is formed in the inner support ring assembly, the bypass bleed air groove is a second flow path of a third path of cold air, and the cold air passing through the second flow path is mixed with the cold air of a first flow path at an inlet of a main flow path; the airflow speed and the pre-rotation angle of the sealed cold air outlet are increased, so that speed triangle difference with the main flow gas of a guide vane root outlet is reduced, the mixing of the sealed cold air and the main flow is reduced, the efficiency of the turbine isimproved, and a movable vane root is guaranteed to work in a design working condition.
Owner:AECC SICHUAN GAS TURBINE RES INST
Stator blade, compressor structure and compressor
InactiveCN107120315AReduce blending lossImprove aerodynamic efficiencyEngine manufacturePump componentsJet flowLow speed
The invention discloses a stator blade, a compressor structure and a compressor. The stator blade comprises a blade body in which an empty cavity is formed, wherein air supplementing holes are formed in the blade body. According to the stator blade, supplemented air is in a form of jet flow on a suction surface of the stator blade, so that a low-speed and low-energy area formed by the suction surface can be removed by means of blowing, and as a result, the loss due to air doping and mixing in air supplementing can be decreased, and the aerodynamic efficiency of a centrifugal compressor is improved.
Owner:GREE ELECTRIC APPLIANCE INC OF ZHUHAI
High pressure annular jet pump suitable for pumping pressure type supply system
The invention belongs to the technical field of aviation and space, and particularly relates to a high pressure annular jet pump suitable for a pumping pressure type supply system. The high pressure annular jet pump comprises an inlet section pipe, a mixing section pipe, a throat pipe, a diffusion section pipe and an outlet section pipe which are sequentially arranged in the flowing direction of main fluid. The high pressure annular jet pump is characterized by further comprising step section pipes which are sequentially arranged between the inlet section pipe and the mixing section pipe; each step section pipe comprises a convergence section pipe and a straight section pipe; each straight section pipe is provided with a spraying nozzle for providing high pressure fluid. The high pressure annular jet pump is compact in structure, light in weight, good in anti-cavitation performance and capable of meeting the requirement for normal work under the working conditions of high rotating speed and low inlet pressure.
Owner:NO 11 INST OF NO 6 ACADEMY OF CHINA AEROSPACE SCI & TECH
Unsteady standing vortex type treatment casing
The invention relates to a treatment casing applied to an axial-flow air compressor in the field of impeller machinery, in particular to an unsteady standing vortex type treatment casing, which can be used for improving the stability margin of the axial-flow air compressor without reducing efficiency. The unsteady standing vortex type treatment casing comprises an air jet groove, a bridge-type air flow channel and an air suction groove, wherein the air jet groove is arranged at the position of a suction surface of a blade, and the air suction groove is arranged at the position of a pressure surface of the blade. The treatment casing is designed to suppress leakage flow generated on the suction surface of a front edge of the blade, the air suction groove is exactly close to the pressure surface in the rear middle of the blade when the blade sweeps over, and the air jet groove is close to the suction surface of the front edge of the blade. Therefore, differential pressure is formed between the air suction groove and the air jet groove to drive fluids to spray from the downstream of the blade to the upstream of the blade, and the air jet groove is positioned close to the suction surface of the front edge of the blade and exactly aligned to a leakage vortex generating area of the blade, so that leakage flow can be suppressed, and further the stall margin of the air compressor is increased. Moreover, as an air jet direction is consistent with a main flow direction, mixing loss of an air jet area and a main flow area is decreased, the momentum of a boundary layer of the wall surface of the casing is increased, and positive effects are achieved for the efficiency of the air compressor.
Owner:BEIHANG UNIV
Turbine cooling cascade with vortex structure
InactiveCN101551120AReduce the spatial scaleReduce the impactContinuous combustion chamberCold airLeading edge
A turbine cooling cascade with a vortex structure relates to a turbine cooling cascade. The invention settles the problems of flowing loss, blending loss and easy burning of blade leading edge and end wall surface of blade leading edge caused by the existence of horse shoe vortex structure in the prior blade cascade. According to the blade (2) of the invention, a pressure surface (2-2) next to the blade leading edge (2-1), a suction surface (2-3) of blade (2) next to the blade leading edge (2-1) and the blade leading edge (1-1) of wall (1) are respectively provided with a plurality of elongated slots (3) which are distributed in row. One side wall of each elongated slot (3) is provided with a plurality of cold air injection openings (4). Furthermore the positions of cold air injection opening (4) are next to the base of elongated slot (3). The turbine cooling cascade with vortex structure according to the invention reduces the flowing loss at the inner part of flow passage, reduces the bigger blending loss of air currents with different flowing velocities, provides better thermal protection function for the end wall of blade and the blade surface, effectively protects the end wall adjacent with the blade leading edge and the high-temperature area on the surface of blade, and increases the usage factor of cold air.
Owner:HARBIN INST OF TECH
Gas turbine rim sealing structure and method
ActiveCN105971674ASignificant progressReduce usageLeakage preventionMachines/enginesProduct gasGas turbines
The invention relates to the technical field of gas turbines, in particular to a gas turbine rim sealing structure. The structure comprises a static vane connected to a static vane platform and a movable vane connected to a movable vane platform, wherein an airtight cool air channel is formed between the static vane platform and the movable vane platform, blowing holes are formed in the peripheral direction of the static vane platform and communicated with a static vane cooling channel, an outlet of each blow hole is located on the downstream side of the static vane platform and communicated with the airtight cool air channel, and the blow holes are used for guiding cooling air in the cooling channel out and making cooling air form an air curtain at the position of an outlet of the airtight cool air channel. The invention further relates to a rim sealing method. By the adoption of the method, cooling air in the static vane cooling channel can be guided out from the downstream side of the static vane platform, and the air curtain can be formed by cooling air at the position of the outlet of the airtight cool air channel. The air curtain can improve the airtight performance of the gas turbine rim sealing structure, reduce airtight cool air amount, reduce the influence of airtight cool air on aerodynamic efficiency of main current, and improve overall efficiency.
Owner:SHANGHAI ELECTRIC GAS TURBINE CO LTD
Centrifugal compressor diffusor structure with blades being integrated with case and hub
ActiveCN108386389AReduce blending lossReduce the maximum outer diameterPump componentsGas turbine plantsDistortionCentrifugal compressor
The invention discloses a centrifugal compressor diffusor structure with blades being integrated with a case and a hub. The centrifugal compressor diffusor structure with the blades being integrated with the case and the hub belongs to the technical field of middle-small aero-engine compressors, and is characterized in that a radial diffuser and an axial diffuser are connected into a whole, and aleading edge is designed into a sharp edge, so that the loss is reduced, and the outer diameter of each diffuser is reduced; and the blades are further integrated with the case of each diffuser and the hub, so that the distortion degrees of the blades of each diffuser are reduced, and the blades are convenient to design and process. The centrifugal compressor diffusor structure with the blades being integrated with the case and the hub provided by the invention can be directly applied to small aero-engines, the outer diameter of the engine can be reduced without increasing the processing costand reducing the compressor performance, and the thrust-weight ratio of the engine is improved.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Turbine disk cavity sealing structure with bypass gas entraining
InactiveCN109458229AReduce secondary flow lossImprove turbine efficiencyLeakage preventionMachines/enginesEngineeringHigh pressure
The invention belongs to the field of gas turbine engines, and relates to a turbine disk cavity sealing structure with bypass gas entraining. The turbine disk cavity sealing structure with bypass gasentraining comprises an inner support ring assembly provided with an inner support ring gas inlet hole, a front baffle plate assembly, a pre-rotation nozzle, a first gas passage for transferring a first path of cold gas output by the pre-rotation nozzle, a second gas passage for transferring a second path of cold gas output by the pre-rotation nozzle, and a third gas passage arranged between the inner support ring assembly and the front baffle plate assembly, wherein the third gas passage comprises a first sealing device arranged between the inner support ring assembly and the front baffle plate assembly, a sub gas passage and a bypass gas entraining passage; a third path of cold gas output by the pre-rotation nozzle flows into the sub gas passage and the bypass gas entraining passage through the first sealing device; and gas output by the third gas passage flows toward a high-pressure turbine movable blade.
Owner:AECC SICHUAN GAS TURBINE RES INST
Turbulent baffle heat transfer enhancing device with jet impingement function
InactiveCN101586477AAchieving closed loop requirementsUniform temperature distributionBlade accessoriesMachines/enginesTurbine bladeTrailing edge
The invention discloses a turbulent baffle heat transfer enhancing device with jet impingement function, and relates to the heat transfer technology. The heat transfer enhancing structure with impingement and turbulence functions utilizes a zigzag channel arranged along a blade expanding direction, controls the section surface of a circulation part by regulating a baffle structure in the channel to achieve the aim of enhancing heat transfer, and is suitable to be arranged on a trailing edge of a turbine blade of a gas turbine with narrow space and high heat load to form a closed cooling structure. The jet baffle turbulent structure of the invention has simple structure and high heat exchange capacity, can meet the cooling requirement of the trailing edge of the turbine blade of the gas turbine through high-efficiency impingement cooling function, and can effectively cool the high-temperature trailing edge of the turbine blade on the premise of closed cycle of a cooling medium, reduce mixing loss caused by cooling, and make the temperature on the trailing edge of the blade distributed more evenly compared with other open cooling structures applied to the trailing edge of the turbine blade.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Realizing method of axial slot casing with low mixing losses
ActiveCN105927589AImprove suction effectIncrease front jet velocityPump componentsPumpsFriction lossEngineering
The invention provides a realizing method of an axial slot casing with low mixing losses. First, the treatment range of a treatment slot in an axial direction and the axial length of the treatment slot are determined in the critical flow region range of a blade tip. After the radii of the front-end circle and the rear-end circle of the treatment slot are determined, the inner and outer common tangent arcs of the two circles are constructed, and an integral axial treatment slot consisting of four sections of arcs is obtained. In the invention, the flow field structure of the blade tip at a near stall point and the element geometrical characteristics of the blade tip are considered, the front-end jet velocity of the treatment slot is increased, mixing losses are reduced, and the pumping effect on the flow blockage of the blade tip is enhanced; and as the treatment slot consists of four sections of arcs, friction losses produced by fluid in the treatment slot are reduced.
Owner:SHANGHAI JIAO TONG UNIV
Pressure expander blade, compressor structure and compressor
PendingCN107023516AReduce blending lossImprove aerodynamic efficiencyPump componentsPumpsEngineeringCentrifugal compressor
The invention discloses a pressure expander blade, a compressor structure and a compressor. The pressure expander blade comprises a blade body, and a cavity is formed in the blade body. Air supplementing holes are formed in the blade body. According to the pressure expander blade, the compressor structure and the compressor, jet flow can be formed on the suction surface of the pressure expander blade by means of air supplementing through the pressure expander blade of the hollow structure and the air supplementing holes in the back portion of the pressure expander blade so as to blow down a low-speed and low-energy area formed on the suction surface, airflow mixing losses caused by air supplementing are reduced, and therefore aerodynamic efficiency of the centrifugal compressor is improved, and the operation range of the compressor can be widened while the aerodynamic performance of compressor design points is improved.
Owner:GREE ELECTRIC APPLIANCES INC
Closed centripetal turbine cover-machine case cavity structure for restraining leakage losses
ActiveCN111441827AReduce leakageShorten speedBlade accessoriesMachines/enginesEngineeringPetrochemical
The invention relates to a closed centripetal turbine cover-machine case cavity structure for restraining leakage losses, and the closed centripetal turbine cover-machine case cavity structure is suitable for a compressed air energy storage system. An expansion runner, a seal structure and a leakage flow mixing restraining structure are sequentially arranged in a narrow and long cavity formed between a front wheel cover and a machine case. The circulation area of the expansion runner is gradually increased in the flowing direction. The leakage flow mixing restraining structure is a shielding sheet from a cavity outlet to a seal outlet. On the basis of leakage flow control through a conventional seal structure, the inlet leakage flow can be reduced through the cavity expansion runner, leakage flow and main flow mixing losses are further reduced through leakage flow mixing restraining, finally, the pneumatic efficiency and the acting capability of a turbine are improved, and the rate ofutilization of energy through the turbine is increased. The closed centripetal turbine cover-machine case cavity structure can be widely applied to aerospace, transportation, petrochemical engineering, energy power and other multiple fields besides compressed air energy storage and is particularly suitable for high-pressure radial-flow turbines.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Casing treatment device for reducing stalling and surging of air compressor
The invention provides a casing treatment device for reducing stalling and surging of an air compressor. The casing treatment device comprises a casing and a space ring. The casing comprises an air inlet shell and an impeller. An annular flow division groove is fixedly formed in the position, opposite to the side wall of the air inlet shell, of the front side of the front impeller edge of the impeller. The annular flow division groove is provided with an opening facing the interior of the air inlet shell. The space ring is in a barrel shape and is fixed to the inner side wall of the air inlet shell and located at the opening of the annular flow division groove. According to the casing treatment device for reducing stalling and surging of the air compressor, the space ring is adopted for automatically separating main flow and casing treatment inner flow, the casing treatment inner flow is guided to the impeller tip direction and the axial inflow direction, and therefore the mixing loss of the main flow and the casing treatment inner flow is reduced, and backflow or counterflow generated by the impeller tip area is suppressed more effectively; and therefore stalling and surging are reduced, and under the condition of large flow, the influence of the groove on the main flow is smaller than that in a conventional method, and the influence of the groove on efficiency can be reduced.
Owner:CHINA NORTH ENGINE INST TIANJIN
Solar heating system based on dissipation-reduction optimization and control system of solar heating system
ActiveCN107477644AIncrease guarantee rateImprove economyLighting and heating apparatusSpace heating and ventilation detailsControl systemEngineering
The invention provides a solar heating system based on dissipation-reduction optimization and a control system of the solar heating system. The solar heating system comprises a solar heat collector, a heat storing water tank, an indoor heat dissipater, a heat collecting circulating pump, a heat supply circulating pump, connecting pipelines, connecting valves, a digital temperature sensor, a flowmeter, a frequency converter and a controller. According to the solar heating system based on dissipation-reduction optimization and the control system of the solar heating system, optimized design is conducted on the integrated form, an operation mode and a control method of the links of solar heat collecting, heat storing, heat supplementing and heat supplying from the perspective of energy dissipation, and the common problems that the solar heating system conducts reverse heat transferring through the heat collector, control targets of supply and storage of the heat collecting volume cannot be coordinated, the heat of the heating side is transmitted reversely to the water tank, the control target of heat supply of the water tank cannot be coordinated, simultaneous operation of heat supplementing and heat storing cannot be achieved, and heat storing is ineffective in application of solar opto-thermal heating are solved. Meanwhile, the solar heating system based on dissipation-reduction optimization and the control system of the solar heating system can maximally utilize the passive heat storage characteristic of a building, the requirement for heat storing volume is reduced effectively, and the mixing loss in the heat storing water tank is effectively reduced.
Owner:TSINGHUA UNIV +1
Prismatic cavity blade tip for controlling leakage flow of movable blade tip of turbine
InactiveCN108412556AShorten speedIncrease flow resistanceBlade accessoriesMachines/enginesTurbine bladeFront edge
The invention provides a prismatic cavity blade tip for controlling leakage flow of a movable blade tip of a turbine. At the blade tip of a movable blade of the turbine, a plurality of prismatic cavities are formed from the front edge to the tail edge of the movable blade of the turbine; and the ratio of the maximal depth h of the prismatic cavities to the height H of the movable blade of the turbine is 0.5%-4%. According to the prismatic cavity blade tip for controlling the leakage flow of the movable blade tip of the turbine provided by the invention, a part of leaking fluid which enters a clearance enters the prismatic cavities to form vortex in a rolling way; at one hand, the dynamic energy of the fluid in the clearance is dissipated; on the other hand, a jet flow stop effect is achieved on the fluid in the clearance above the cavities; and thus the aim of controlling the leakage flow of the blade tip of the turbine is realized; the leakage amount of the blade tip of the turbine isreduced; the size and strength of leakage vortex of the blade tip are reduced; leakage related loss of the turbine is reduced; the efficiency of the turbine is improved; and furthermore the prismaticcavity structure can reduce the weight of the blade of the turbine.
Owner:HARBIN INST OF TECH
Novel axial flow turbine suitable for pulse pressure charging
InactiveCN105464711AImprove efficiencyReduce blending lossInternal combustion piston enginesStatorsStatorEngineering
The invention provides a novel axial flow turbine suitable for pulse pressure charging. The novel axial flow turbine comprises a volute, stators, a rotor, a rotating shaft, a seal ring and a bearing. A gas inlet is formed in the front end of the volute, and a pressure expander is arranged at the rear end of the volute. An exhaust port is fixedly formed in the upper end of the pressure expander. The stators are each in an annular shape and located on the inner wall of the gas inlet of the volute. The front end of the rotating shaft is in an arc shape and located on the portion, close to the rear side, between the stators. The rear end of the rotating shaft is fixed to the rear side wall of the volute through the bearing. The rotor is fixed to the portion, close to the front end, on the rotating shaft. The front end of the pressure expander is located on the rear side of the rear side wall of the rotor. According to the novel axial flow turbine suitable for pulse pressure charging, work of the stators and work of the rotor are closer to the quasi-steady state, and therefore the efficiency of the rotor is improved; and in addition, flowing at the outlet of the rotor is uniform in the circumferential direction, and the mixing loss generated on the downstream part of the rotor due to circumferential-direction ununiformity is also reduced to some extent.
Owner:CHINA NORTH ENGINE INST TIANJIN
Distributed parameterized impeller self-circulation treatment casing
ActiveCN112539184AIncrease stall marginReduce efficiency lossPump componentsRadial flow pumpsImpellerInlet channel
The invention discloses a distributed parameterized impeller self-circulation treatment casing which is composed of a casing body, an air inlet channel, impeller blades, a front channel, a rear channel and air entraining bridge circuits; the air entraining bridge circuits are fixed to the outer side of an impeller casing, and air flows back in the bridge circuits through the front channel and therear channel connected to a channel front edge of the impeller casing; and the front channel and the rear channel of the impeller self-circulation treatment casing are located at the positions with different axial chord lengths away from an impeller inlet respectively, an inner wall face two-dimensional molded line is formed by fitting and optimizing a structured curve so as to ensure that jet flow is close to the wall face as much as possible, and the outer wall face molded line is a controllable contraction molded line, so that the effects of guiding and accelerating airflow are achieved. The impeller self-circulation treatment casing utilizes the airflow pressure difference in rotor channels corresponding to the self-circulation front channel and the self-circulation rear channel to perform air exhaust and air injection. According to the treatment casing structure, the blocking margin and the stall margin of the centrifugal impeller can be improved, the purpose of reducing the efficiency loss is achieved, and the impeller can operate and work at a larger margin.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Compressor air supplementing structure and compressor
PendingCN107165869AReduce blending lossImprove aerodynamic efficiencyPump componentsPumpsPhysicsRefrigerant
The invention discloses a compressor air supplementing structure and a compressor. The compressor air supplementing structure comprises a first diffuser, a first volute and a backflow device; the output end of the first diffuser is connected with the input end of the backflow device through the first volute, and the first volute is provided with an air supplementing opening. According to the compressor air supplementing structure, volute air supplementing is adopted as the air supplementing manner, and air supplementing refrigerants enter the compressor through an inlet of the first volute, flow in the circumferential direction of the first volute, and meanwhile enter a main flow zone through an inlet of the backflow device continuously. As the air supplementing refrigerants flow in the circumferential direction, and the air supplementing refrigerants have a high rotating speed which is the same as the main flow speed, mixing losses of supplemented air and main flow can be effectively reduced, and the aerodynamic efficiency of the centrifugal compressor is further improved.
Owner:GREE ELECTRIC APPLIANCES INC
Turbine device with seal leakage flow guiding function
ActiveCN103883362AEliminate lossIncrease flow resistanceLeakage preventionMachines/enginesTurbine bladeLeakage flow
The invention provides a turbine device with a seal leakage flow guiding function. The turbine device comprises a turbine case and N turbine blade stages. The inner surface of the turbine case is provided with N blade working sections, and each blade working section comprises a static blade outer ring wall, a movable blade outer ring wall and an integral shroud sealing cavity front and back transition section. Each turbine blade stage comprises a static blade, a movable blade and a flow guiding ring, wherein the top of the movable blade is provided with an integral shroud, and labyrinths are arranged on the integral shroud, the flow guiding ring is in a circular ring shape and located on the downstream side of the movable blade, the tail ends of rear transition sections of the turbine blade stages extend toward the connecting positions of the integral shrouds and the labyrinths on the movable blades, and the edges of the inner sides are close to the turbine integral shrouds and the labyrinths but do not make contact with the turbine integral shrouds and the labyrinths. The flow guiding rings guide seal leakage flows to flow, close to the solid surface, inside a cavity formed by the inner wall of the turbine case, the labyrinths and the flow guiding rings, it is avoided that part of fluid of blade lattice main flows invades into an outlet cavity, so that entrainment losses are caused, and mixing losses of the seal leakage flows and the blade lattice main flows are reduced.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Aero-engine rim sealing structure
InactiveCN112922681AReduce fuel consumptionIncrease flow resistanceLeakage preventionMachines/enginesCold airEngineering
The invention provides an aero-engine rim sealing structure. The aero-engine rim sealing structure comprises: a guide blade; a rotor blade; and a front rim sealing structure installed on the guide blade and a rear rim sealing structure installed on the rotor blade, wherein the front rim sealing structure is provided with a first backward protrusion and a second backward protrusion which extend in the direction of a main airflow runner, the first backward protrusion and the second backward protrusion form a first groove, a flow deflector is arranged on the upper wall of the first groove, the rear rim sealing structure is provided with a first forward protrusion extending in the direction opposite to the direction of the main airflow channel, and at least part of the first forward protrusion extends into the first groove. On one hand, the flow resistance of hot fuel gas flowing to a gap can be increased in the operation process of the engine, so that the sealing effect is improved, on the other hand, the mixing loss of the fuel gas and cold air can be reduced, the cold air acts on a turbine, the acting efficiency of the fuel gas is improved, the turbine efficiency is improved, and the oil consumption rate of the engine is reduced.
Owner:AECC SHENYANG ENGINE RES INST
Steam supplementing chamber structure of steam turbine cylinder
ActiveCN112832875AReduce intermixingReduce blendingMachines/enginesEngine componentsEngineeringMechanics
The invention discloses a steam supplementing chamber structure of a steam turbine cylinder, and belongs to the technical field of steam turbines. The steam supplementing chamber structure of the steam turbine cylinder comprises an annular main steam flow channel formed between the cylinder and a rotor; a mixing ring cavity is formed in the cylinder in the circumferential direction of the cylinder; the outer side of the mixing ring cavity communicates with a steam supplementing channel; the inner side of the mixing ring cavity communicates with the main steam flow channel through a flow guide ring cavity; the flow guide ring cavity inclines towards the main steam flow flowing direction of the main steam flow channel; a plurality of flow guide partition plates are arranged in the flow guide ring cavity in the circumferential direction of the flow guide ring cavity; and the flow guide ring cavity is divided into a plurality of sub-cavities by the plurality of flow guide partition plates. According to the invention, the mixing degree and the mixing loss of the supplemented steam and the main steam flow can be reduced, and the influence of the supplemented steam on the stability of the rotor can be reduced.
Owner:DONGFANG TURBINE CO LTD
Cooling structure of top contra-rotating vortex of high temperature turbine moving blade
InactiveCN106988790AWell mixedImprove heat transfer effectBlade accessoriesMachines/enginesCold airTurbine blade
The invention discloses a cooling structure of a top contra-rotating vortex of a high temperature turbine moving blade, and belongs to the field of turbine heat transmission. The cooling structure of the top contra-rotating vortex of the high temperature turbine moving blade comprises a turbine tenon, a turbine blade body, a turbine blade front edge, a turbine blade top cover, a turbine blade tail edge, a serpentine channel and a contra-rotating vortex generator; the turbine tenon is connected with the tail of the turbine blade body into a whole; the top of the turbine blade body is closed through the turbine blade top cover; a cold air hole is formed in the turbine blade top cover; the serpentine channel is formed in the turbine blade body and is located at the chord-length middle part of a turbine blade; an air outlet channel of the serpentine channel communicates with the cold air hole; and the contra-rotating vortex generator is fixedly arranged on the internal surface of the turbine blade top cover and corresponds to the serpentine channel. The cooling structure is used for cooling the high temperature turbine moving blade, and has the characteristics that heat transfer is enhanced through forming the contra-rotating vortex and increasing a heat transfer area, and the increasing of the flow resistance is inhibited effectively.
Owner:HARBIN INST OF TECH
Static scroll plate assembly, scroll compressor and refrigeration equipment
PendingCN111963425AReduced intensity of pressure pulsationsReduce blending lossCompressorRotary piston pumpsEngineeringRefrigeration plant
The invention provides a static scroll plate assembly, a scroll compressor and refrigeration equipment. The static scroll plate assembly comprises a plate body, an enthalpy increasing channel and an enthalpy spraying channel, wherein the plate body is provided with a compression channel; the enthalpy increasing channel is arranged on the plate body, and the enthalpy increasing channel is used forcommunicating with an enthalpy increasing pipeline of the scroll compressor; and the enthalpy spraying channel is arranged on the bottom wall of the plate body, the enthalpy spraying channel communicates with the compression channel and the enthalpy increasing channel, the enthalpy spraying channel comprises a flow blocking part, and the flow blocking part is used for preventing gas in the compression channel from flowing back to the enthalpy increasing channel. The gas in the compression channel is prevented from flowing back to the enthalpy increasing channel through the flow blocking part,and spreading of the gas flow flowing back to the enthalpy increasing pipeline from the compression channel can be effectively attenuated, so that the pressure pulsation intensity in the enthalpy increasing pipeline is weakened, the technical effect of reducing the pressure pulsation level in the enthalpy increasing pipeline is achieved, and the problems that the joint between the enthalpy increasing pipeline and a shell of the scroll compressor is broken and a valve plate is broken due to the fact that the refrigerant gas in an enthalpy increasing pipeline generates strong pulsation in the prior art are solved.
Owner:GUANGDONG MEIZHI COMPRESSOR
Design for transonic axial fan blade angular seam casing treatment structure
The invention discloses a design for a transonic axial fan blade angular seam casing treatment structure, and belongs to the technical field of turbo machinery. According to the design for the transonic axial fan blade angular seam casing treatment structure, a plurality of narrow seams are formed in a fan casing in the axial direction and are uniformly distributed in the circumferential direction to form an axial seam casing treatment structure, and the width of the axial seam casing treatment structure covers the whole axial chord length of blade tips; and opening surfaces of the axial seam casing treatment structure rotate by a certain angle in the direction of the blade installation angle so as to form the blade angular seam casing treatment structure. The design for the transonic axial fan blade angular seam casing treatment structure has the advantages that the air-entraining direction and the air-jetting direction of the blade angular seam casing treatment structure are matched with the air flow direction in channels of the blade tips, and therefore the air-entraining amount and the air-jetting amount can be increased, and the mixing loss of the air flow can be reduced; and the stability extension capability of the blade angular seam casing treatment can be enhanced, and the blade angular seam casing treatment structure further improves the comprehensive stall margin and meanwhile reduces the efficiency loss.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Corrugated turbulent flow plane cooling device and application
InactiveCN114776470AReduce deliveryReduce thrust lossEfficient propulsion technologiesJet propulsion plantsCold airCold side
The invention discloses a corrugated turbulent flow plane cooling device and application, and belongs to the field of aero-engines. Comprising a cold side corrugated plate, a hot side flat plate and hollow turbulent flow columns, the cold side corrugated plate is located on one side of a cold air channel, and the hot side flat plate is located on one side of a high-temperature fuel gas channel; a hill-shaped middle channel with the sectional area changing periodically is formed between the cold side corrugated plate and the hot side flat plate. A plurality of hollow turbulent flow columns are arranged between the cold side corrugated plate and the hot side flat plate to form a middle channel containing the hollow turbulent flow columns, and the cold air channel is communicated with the high-temperature fuel gas channel through hollow holes in the hollow turbulent flow columns; the hollow turbulent flow columns are connected with wave troughs of the hot side flat plate and the cold side corrugated plate; and a gas film protection layer is formed on the hot-side flat plate by utilizing outflow of a trough high-pressure area of the cold-side corrugated plate. According to the invention, the amount of cold air near the wall surface of the spray pipe is reduced, and the thrust loss of the engine caused by cold air mixing is reduced under the condition of achieving higher cooling efficiency.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
Gas turbine rim sealing structure and method
ActiveCN105971674BReduce usageLow intrusionLeakage preventionMachines/enginesEngineeringGas turbines
Owner:SHANGHAI ELECTRIC GAS TURBINE CO LTD
Turbine device with sealing leakage flow diversion function
ActiveCN103883362BEliminate lossIncrease flow resistanceLeakage preventionMachines/enginesTurbine bladeLeakage flow
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Double-wall cooling device and application
InactiveCN114812257AGuaranteed outflowReduce cooling air volumeContinuous combustion chamberEfficient propulsion technologiesCold airCold side
The invention discloses a double-wall cooling device and application, and belongs to the field of aero-engines. Comprising a cold side flat plate, a hot side corrugated plate and hollow turbulent flow columns, the cold side flat plate is located on one side of a cold air channel, the hot side corrugated plate is located on one side of a high-temperature fuel gas channel, and an inverted hill-shaped middle channel with the sectional area changing periodically is formed between two layers of wall plates; a plurality of hollow turbulent flow columns are arranged between the cold side flat plate and the hot side corrugated plate, the cold air channel is communicated with the high-temperature fuel gas channel, and the connecting positions of the hollow turbulent flow columns and the hot side corrugated plate are located on the wave crests of the hot side corrugated plate. Hollow column turbulent flow cooling and external air film cooling are combined, the purpose of high cooling efficiency is achieved by using less cold air, meanwhile, the internal thermal stress of the structure is reduced, and the flow resistance of the structure is reduced. And meanwhile, the defect that a traditional corrugated plate cold air channel is large in flow resistance is overcome, and the problem that outflow cannot be achieved due to insufficient cold air total pressure of a downstream heat screen and a spray pipe heat screen is effectively solved.
Owner:NORTHWESTERN POLYTECHNICAL UNIV
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