781results about How to "Reduce flow loss" patented technology

A product that includes a compressor, a housing and a vibration isolation mount located between the compressor and the housing. The compressor includes an impeller, a first inlet located upstream of the impeller, a first outlet located downstream of the impeller, a second inlet located downstream of the first outlet, and a second outlet located downstream of the second inlet. During operation, fluid enters the compressor via the first inlet and exits the compressor via the first outlet. The mount creates a restriction between the compressor and the housing that causes fluid exiting the first outlet to re-enter the compressor via the second inlet.

The invention discloses a multichannel plasma area igniting burner. The igniting burner comprises a plasma power supply, a nozzle, an air inlet fish nozzle, a tangential air hole, an air pipe, a hollow insulator, a high-voltage electrode, an insulation piece, a low-voltage electrode, a housing, a swirl chamber, air vents, barrier mediums, a low-speed area, center jet flow and a flame stabilization chamber. Fuel oil is atomized by the use of a splash plate disposed inside the air inlet pipe, mixed gas composed of high-speed rotation air-flow and direct current jet flow is disposed inside the igniting burner, and the two flows cool the igniting burner. The space between the high-voltage electrode and the low-voltage electrode is filled with the inflammable mixed gas flowing at a low speed, so that multi-point discharge and ignition can be carried out in a low-speed mixed gas area inside the igniting burner; and an on-duty high-temperature combustion thermonuclear area and the flame stabilization chamber have ignition source and flame stabilization functions and form a miniature high-speed combustion chamber, so that the combustion chamber can efficiently and reliably ignite and keep flames stable under poor conditions such as high-speed, low-temperature, low-pressure, coal firing and the like.

A turbine engine component, such as a turbine blade, has an airfoil portion, a plurality of cooling passages within the airfoil portion with each of the cooling passages having an inlet for a cooling fluid. Each inlet has a flared bellmouth inlet portion. The turbine engine component may further have a dirt funnel at the tip of the airfoil portion, a platform with at least one beveled edge, and an undercut trailing edge slot.

The invention discloses a bypass type double-throat passive vectoring sprayer nozzle, comprising a sprayer nozzle main body, wherein the inner flow channel of the sprayer nozzle main body comprises front contraction sections of the throats, a bypass convex block, a first throat, a second throat front part expanded contraction section, throat reentrant cavities and a second throat; the front contraction sections of the throats are provided with bypass channels close to the first throat, wherein the inlets of the bypass channels are arranged facing the fluid entrance of the inner flow channel of the nozzle main body while the outlets of the bypass channels are arranged on the first throat. Therefore, the bypass channels are arranged in the double-throat nozzle to change the flow structure in the double-throat nozzle to further make the outflow of the nozzle achieve deviation, that is, producing and maintaining vector deflection. In addition, when the bypass type double-throat passive vectoring sprayer nozzle produces a thrust vector, a little flow loss is caused. The bypass type double-throat passive vectoring sprayer nozzle also has a simple structure, and does not influence performances of the nozzle when the nozzle works normally without vector deflections.

The invention discloses a double-layer-wall heat insulation screen used for an afterburner. Cooling protection is formed for the wall surface of the afterburner by using an inner convection cooling mode and a gas side air film cooling mode. The double-layer-wall heat insulation screen comprises a gas side gas film hole plate, a cool air side impacting plate and a trapezoidal reinforcing frame. The gas side air film hole plate serves as the inner wall of a cylinder body of the afterburner, the inner side of the gas side air film hole plate is provided with a main gas duct of the afterburner, the cool air side impacting plate and an outer wall surface form a cool air duct, and the trapezoidal reinforcing frame is arranged between the impacting plate and the air film hole plate. The double-layer-wall heat insulation screen is formed by the impacting plate, the air film hole plate and the trapezoidal reinforcing frame. Cooling air is made to form an air film on the gas side inner wall of the heat insulation screen, and heat load and gas flow losses are reduced. In addition, composite cooling is formed through inner convection cooling and outer air film cooling of a double-layer wall, incoming heat is brought away through convection heat exchange, and the cool air utilization rate is increased. Reduction is achieved after reflection, the effect of vibration prevention is achieved, the service life of the afterburner is prolonged, and the reliability of the afterburner is enhanced.

The invention relates to a sweeping and twisting type three-dimensional blade diffuser. According to the structure, the front edges of blades are designed into a sweeping shape, the sweeping angle ranges from -45 degrees to 45 degrees, and the blades are suitable for incoming flow and are twisted to be expanded into different air flow angles. The main blade is designed into a three-dimensional integral structure from an inlet to an outlet in the axial direction. The flow-dividing blades are arranged on the rear section in a main blade channel. The sweeping and twisting type three-dimensional blade diffuser has the advantages that interaction of shock waves and a boundary layer is relieved, so that flow in the diffuser is modified; blade surface air flow separation and load loss which are caused by a relative large positive/negative attack angle in part of the blades in the high portion are eliminated, flow loss is reduced, and therefore a stator part diffuser of a centrifugal/oblique flow gas compressor can reach the higher efficiency and the larger pressure ratio. The strength of the shock waves is changed and the shock waves are even eliminated and influence caused by interaction of the shock waves and the boundary layer is relieved; flow loss caused by the overlarge positive attack angle or the overlarge negative attack angle is avoided, the expansion capacity and the operation range of the diffuser are improved, and therefore the improvement in the performance of the whole-level gas compressor is assisted.

A blower having a divergence guide portion to reduce flow loss and discharge noise and an air conditioner having the same are provided. The blower includes a scroll casing, suction holes provided at opposite positions of the scroll casing, a discharge hole provided at a top position of the scroll casing, a centrifugal fan received in the scroll casing, and a divergence guide portion gently diverging air to the discharge hole after passing through the centrifugal fan to diffuse the air to both sides of the discharge hole.

The invention provides a flame stabilizer for an after-combustion chamber of a gas turbine engine. In the device, which is characterized in that turbine rear frames are integrated, a radial flame stabilizer and a center cone in the prior art are omitted, and the an upstream concave structure and the a jet injection gas flow are used for forming a vortex system to form a necessary backflow region for flame stabilization, thereby reducing the amount of parts, shortening the total length of the combustion chamber, lightening the structural weight, reducing the resistance loss, and enabling the thrust-weight ratio of the engine to have great expansion lifting space.

The invention discloses a supercritical carbon dioxide centrifugal compressor and radial-inward-flow turbine coaxial structure. A supercritical carbon dioxide working medium sequentially flows through a centrifugal compressor to improve pressure and a heat source to improve temperature, and finally after output work in a radial-inward-flow turbine, the supercritical carbon dioxide working medium enters a cooler to be cooled and circulates to enter the centrifugal compressor again. A start motor drives the coaxial structure to start working through one gearbox, the coaxial structure is formed by the radial-inward-flow turbine and the centrifugal compressor through a rotor shaft, the centrifugal compressor is driven by one part of output work of the radial-inward-flow turbine, and the other part of output work of the radial-inward-flow turbine is output into a generator through the other gearbox. Radial bearings are arranged at the shaft ends of the two sides of the coaxial structure, a thrust bearing is arranged in the middle of the coaxial structure, and the type adapting to the corresponding rotary shaft rotating speed can be selected. Furthermore, the form of supercritical carbon dioxide dry gas seals is adopted in sealing parts. The supercritical carbon dioxide centrifugal compressor and radial-inward-flow turbine coaxial structure has the prominent beneficial effects of being simple and compact in structure, high in pneumatic efficiency, low in manufacturing cost and the like and has wide market prospects.

The invention discloses a W-shaped rib channel cooling structure suitable for a turbine blade backside cooling cavity and belongs to the field of turbomachinery design. The structure comprises a blade backside cooling cavity, inclined diversion fins, linear diversion fins and flow blocking fins; a plurality of rows of inclined diversion fins on the inner wall of the blade backside cooling cavity are distributed in a W-shaped manner; the linear diversion fins are arranged in a space between the last row of inclined diversion fins and blade tailing edge split seam; and a W-shaped cooling channel is formed by a space defined by the inclined diversion fins, linear diversion fins and the inner wall of the blade backside cooling cavity. According to the W-shaped rib channel cooling structure, the W-shaped rib channel cooling structure is arranged in the blade backside cooling cavity, the rib channel has diversion and acceleration effects on an inner fluid, and simultaneously the blades are reinforced with the arrangement of W-shaped fins. Besides, the structure is simple and reasonable in design, and is suitable for the internal cooling system of turbine blades of a gas turbine.

The invention provides a flame stabilizing device and method of an afterburner for a gas turbine engine. In the device, the original turbine rear frame supporting plate is replaced with the supporting plate with the cavities; and the device is characterized in that: the section of the supporting plate is in the shape of a wing with a suddenly expanded trailing edge and is provided with the cavities. The aim of stabilizing flame is fulfilled through a low-speed backflow region formed by flowing gas flow through the cavities of the supporting plate and the suddenly expanded part of the trailing edge. The invention provides the turbine rear frame supporting plate (2) of the afterburner for the gas turbine engine; the afterburner comprises a case (12), a turbine rear frame inner wall (1) and a plurality of turbine rear frame supporting plates (2), wherein the turbine rear frame supporting plates (2) are connected with the case (12) and the turbine rear frame inner wall (1); and the turbine rear frame supporting plate (2) is characterized by being provided with the cavities (9).

A portable blower unit (1) includes a housing (2). A device for guiding the blower unit (1) over the ground (6) can be fixed to the housing (2) in order to facilitate a multi-use of the blower unit (1).

The invention discloses a high-strength micro-expansion prestress anchoring grouting material and a preparation method thereof. The material is prepared from a gelatinization component, a fine aggregate component, an expansion component, an active doped material, a water reducing component, a crack resistant component and a regulation component in a certain weight proportion. The preparation method specifically comprises the following steps: A, adding the gelatinization component, the expansion component, the active doped material, the crack resistant component and the water reducing component in a ball-mill in a designed mass ratio for commonly mixing and grinding, so as to obtain a even powder material; B, at room temperature and normal pressure, grinding until the Blaine specific surface of the material is not less than 350m<2>/kg; and C, evenly mixing and stirring the obtained in the step B with quartz sand prepared in a proportion at the room temperature and the normal pressure so as to obtain the grouting material. The method is practicable and is convenient for operation; the grouting material has high early strength and micro-expansion, thereby effectively compensating the hydration shrinkage of a cement-based material, obviously improving the adhesive strength of an anchor rod and a periphery base, effectively protecting the anchor rod from being corroded and prolonging the service of the anchor rod.

The invention provides a dual-machine regenerative steam extraction steam thermodynamic system. In the system, the intermediate stage of a high pressure cylinder of a main steam turbine is provided with a high pressure steam extraction opening, the high pressure steam extraction opening is respectively connected with a steam inlet of a small steam turbine and one high pressure heater with the highest steam inlet parameter in a plurality of high pressure heaters through high pressure steam extraction pipelines, the intermediate stage of the small steam turbine is provided with a plurality of regenerative steam extraction openings which are connected with the rest high pressure heaters except the high pressure heater with the highest steam inlet parameter through regenerative steam extraction pipelines, and a steam exhaust port of the small steam turbine is connected with a deaerator through a steam exhaust pipeline of the small steam turbine. According to the system disclosed by the invention, a high-temperature preposed steam cooler can be omitted, and the feed-water temperature of a boiler is reduced, which helps to improve the efficiency of the boiler and reduce the heat consumption of a machine set; and flow loss can be effectively reduced, the circulation efficiency is improved, and the cost of equipment is reduced.

The invention provides a multi-wing centrifugal fan. The multi-wing centrifugal fan comprises a spiral case, an impeller and a motor, wherein the motor is fixed on the spiral case; the impeller is arranged on a rotating shaft of the motor and is placed in the spiral case; the spiral case is provided with an air inlet channel and an air outlet channel; a blade guiding device is arranged in the air inlet channel of the spiral case and comprises guiding blades and a hub; the guiding blades are annularly distributed on the periphery of the hub and are inclined; and the inclined direction of the guiding blades is the same with the rotation direction of the impeller. Because the blade guider is arranged in the air inlet channel of the spiral case, before air flow flows through the guiding blades of the blade guider from the air inlet channel and enters a cavity of the impeller, the guiding blades rotate in advance, the rotation direction of the guiding blades is the same with that of the impeller, the air inlet attract angle of an inlet of the impeller can be reduced, so that the flowing loss of the inlet of the impeller is reduced, and the air volume of the fan is increased.

The present invention relates to an ultrasonic blade and a design method applied to aeroengine fans or aerocompressor rotors, pertaining to the art of impeller mechanical technology. The blade is characterized in that the small part of the blade on the front edge is S-shape and the large rear at the rear is flat and the thickness of the blade gradually increased from front to back; the ultrasonic air current flows into a grid formed by the blade, produces an expansion wave in the entrance of the grid, consequently forms an oblique shock wave in the transition from the S-shaped suction surface of the blade to the flat section intersected with the front edge of the adjacent blade, then produces a reflection shock wave and reproduces a local shock wave near the exit of the grid. The design method of the blade includes the following process: the front part is confirmed to be S-shaped and the rear part is divided by a straight medial camber line; the thickness distribution of the blade, which gradually increases from front to back, is confirmed; the surface mold of the blade is confirmed according to the medial camber line and the thickness distribution of the blade. The blade provided by the present invention can effectively reduce the flowing loss, increase the rim power of the rotor and improve the overall pressure ratio.

The invention relates to a module type multifunctional pulse conversion turbocharging system and belongs to the technical field of internal combustion engine. The module type multifunctional pulse conversion turbocharging system comprises a cylinder, an exhaust branch pipe, an exhaust pipe section, a turbine and a guide plate. The guide plate is inserted into the exhaust pipe section from a connecting part between the exhaust branch pipe and the exhaust pipe section, and gradually extends along the flowing direction of exhaust air till the guide plate is parallel to the axial line of the exhaust pipe section; the exhaust pipe section is divided into an upstream section of the exhaust pipe section, a lower downstream section of the exhaust pipe section and an extending section of the exhaust branch pipe; and the sectional area of the upstream section of the exhaust pipe section is gradually reduced. High-speed air current can be formed in an outlet of the upstream section of the exhaust pipe section; and a low-pressure region is formed in an outlet of the extending section of the exhaust branch pipe in order that scavenging is favored instead of being interfered. The air current of the outlet of the extending section of the exhaust branch pipe is basically parallel to the axial line of the exhaust pipe section, thereby producing no interference of air current. The module type multifunctional pulse conversion turbocharging system has the advantages that the module type multifunctional pulse conversion turbocharging system has simple structure, less occupation and convenient disassembly and assembly, reduces maintenance time and expense and is suitable for large-power four-stroke diesel engines with 4 to 20 cylinders and diversified supercharging degrees..