35results about How to "Efficient blending" patented technology

A tumbling container is mounted for rotation with a curved screen fixedly mounted within the tumbling container. A multiple vane paddle is mounted to a shaft that is rotatably mounted to the tumbling container. The paddle vanes are formed with angular edges. As the tumbler rotates and the paddle rotates, powder is repeatedly dropped onto the screen to be sifted with the aid of the paddle. Rotating the tumbler further drops unsifted portions of the powder from the screen to mix with additional powder in the tumbler body. Thus, sifting and blending of powders is accomplished in one single operation. The invention utilizes an apparatus having a multiple section screen and a multiple section paddle to enable assembly through the openings in the tumbling container. The screen of a second embodiment has a cowl adjacent to each screen opening to optimize powder lump disintegration.

The invention belongs to the technical field of piezoelectric materials, and particularly relates to a polyvinylidene fluoride composite piezoelectric film and a preparation method and application thereof. The polyvinylidene fluoride composite piezoelectric film provided by the present invention includes polyvinylidene fluoride and Prussian blue analogs; the Prussian blue analogs are Co 3 [Co(CN) 6 ] 2 . The invention provides a polyvinylidene fluoride composite piezoelectric film, which solves the problem of insufficient piezoelectric performance of traditional PVDF materials, and has excellent piezoelectric performance and low cost. The experimental results show that the polyvinylidene fluoride composite piezoelectric film provided by the present invention has good flexibility, and compared with pure PVDF material, the remanent polarization is significantly increased, the polarization is more sufficient, and the ferroelectric performance is more excellent; Compared with pure PVDF material, the piezoelectric constant d 33 significantly increased, showing excellent piezoelectric properties.

The invention provides a combustion chamber adopting a swirl vane tail edge pre-film atomization mode. The combustion chamber comprises a combustion chamber flame tube, a center level oil and gas mixing assembly and a main combustion level oil and gas mixing assembly which is arranged at the front end of the combustion chamber flame tube and the periphery of the center level oil and gas mixing assembly. The main combustion level oil and gas mixing assembly comprises a main combustion level swirl channel, N wedge-shaped swirl vanes and M vane interior oil paths; the N wedge-shaped swirl vanes are slantly fixed to the interior of the main combustion level swirl channel, and the M vane interior oil paths are arranged in at least one part of wedge-shaped swirl vanes respectively; the front end of each vane interior oil path is connected with a main combustion level oil cavity, and the tail end of the each vane interior oil path extends to the tail edge of the corresponding wedge-shaped swirl vane; the M is smaller than or equal to the N. The swirl vanes are wedge-shaped; velocity gradients are formed at the tail edges of the swirl vanes; a fuel liquid film flowing out of the tail edges of the swirl vanes is rapidly shorn and atomized under the action of the velocity gradients; the oil and gas blending distance is short, and the flame length and the length of the flame tube are shortened.

The invention belongs to the technical field of gas turbines, and specifically relates to a multi-stage partitioned combustion structure for gas turbines, which includes a combustion chamber casing, a flame tube, a plurality of swirlers and flow dividers, and the swirlers are divided into on-duty swirlers, The flame transfer swirler, the first and the second main combustion swirlers, each swirler is provided with a first gas channel, and the first gas channel transports the gas used for premixed combustion; at the duty swirler A second gas channel is also provided, and the second gas channel transports the gas used for diffusion combustion; the installation angles of the swirler blades are different, and the swirling air flow fields generated by each swirler are relatively independent, so that each swirler The streamer participates in the combustion of independent zones. In this scheme, the multi-stage partition combustion technology uses four different cyclones combined with diverters to form a multi-stage partition organization combustion in the form of graded fuel supply, which meets the needs of all working conditions and ensures the combustion chamber ignition performance and combustion stability. , to achieve the demand for low emission of nitrogen oxides.

The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector, so as to solve the problem that in the current working process of the liquid oxygen methane injector, since both liquid oxygen and methane belong to liquid low-temperature propellants, the The structure of the DC shear nozzle or the impact injector will lead to the poor mixing effect of the propellant in the thrust chamber injector and the problem of insufficient combustion efficiency. A liquid oxygen methane thrust chamber injector includes a plurality of injection units, a midsole, and a top cover, a flow guide and an inner bottom that are coaxially arranged on the midsole in sequence; the plurality of injection units are fixed in the midsole. On the bottom, the deflector and the inner bottom; a liquid oxygen cavity is formed between the top cover, the middle bottom and multiple injection units, and a methane cavity is formed between the mid bottom, inner bottom and multiple injection units; multiple injection units All nozzles with indented chambers are used, and the nozzles include central area nozzles, main combustion area nozzles, and edge area nozzles.

The invention provides a high-reliability multiblade cold / hot air flow mixed spoiler which comprises an outer ring and a spoiling component, wherein the outer ring can be connected with the inner wall of the pipeline through screws, and the spoiling component is arranged on the inner wall of the outer ring; the spoiling component comprises a plurality of flat blades and a spacing ring, and the blades are uniformly distributed in the circumferential direction; one end of each blade is welded on the inner wall of the outer ring and forms a certain included angle with the approach flow direction, and the other end of each blade is a free end and extends towards the central axis of the outer ring to form a center hole; the free end of each blade is provided with a spacing hole of which the cross-sectional shape is greater than that of the spacing ring; and the spacing ring orderly penetrates through the spacing hole of each blade. The invention overcomes the defect that the air flow temperature field uniformity of the existing high-flow high-temperature simulated ground equipment can not satisfy the requirements, provides a static mixed mode of multiblade spoiling and variable cross-section pipelines, and has the advantages of high flow, high temperature difference and high reliability.

A square Venturi mixer with a push-pull structure, including a mainstream fluid inflow pipeline, a mainstream fluid constriction section, a mainstream fluid throat pipeline, a mainstream fluid diffusion section, and a mainstream fluid outflow pipeline, which are connected in sequence and arranged on the upper end of the mainstream fluid throat pipeline And the side inlet fluid inlet pipeline connected with it, the mainstream fluid inlet pipeline, the mainstream fluid throat pipeline, the mainstream fluid outflow pipeline and the inlet fluid inlet pipeline are all square pipelines, and the mainstream fluid constriction section and the mainstream fluid diffusion section are quadrangular pyramid-like structures; The mainstream fluid inflow pipe, the mainstream fluid constriction section, the mainstream fluid throat pipe, the mainstream fluid diffusion section and the mainstream fluid outflow pipe all include an upper part and a lower part, with grooves on the vertical wall surface of the upper part, and grooves on the vertical wall surface of the lower part. With ribs adapted to the shape of the groove; the invention is applicable to a wider range of flow ratios of mainstream fluid and introduced fluid, and effectively improves the mixing efficiency of continuous phase fluid and dispersed phase fluid.

A premixing and pre-evaporation combustor for a main combustion stage using radial film formation consists of a diffuser, an outer combustor case, an inner combustor case, a pre-combustion stage, the main-combustion stage, a flame barrel outer wall and a flame barrel inner wall, wherein the flame of the pre-combustion stage is stabilized by a low-speed return flow zone formed by cyclone generated when a pre-combustion stage cyclone assembly enters the combustor; after being sprayed out by a plurality of tangential spraying openings of a main combustion stage nozzle, fuel oil of the main combustion stage spreads in a fuel oil film formation region and realizes connection, so that a peripheral continuous oil film is formed; the cyclone of an upstream cyclone ring of the main combustion stage nozzle and the cyclone of a downstream cyclone ring of the main combustion stage nozzle secondarily atomize the fuel oil, the fuel oil is brought to a premixing and pre-evaporation section to evaporate and is mixed with air, and uniform oil-gas mixtures are formed at an outlet of the premixing and pre-evaporation section, are jetted into a flame barrel, are ignited by the flame of the pre-combustion stage and then are combusted. The premixing and pre-evaporation combustor is simple in structure; and pollutant discharge can be effectively reduced while a normal working state of an aerial engine is guaranteed.

The invention discloses a radial rim sealing structure with damping holes and flow guide blades. The radial rim sealing structure is characterized in that the radial rim sealing structure is arranged in a gas turbine rotor-stator cavity or a gas turbine rotor-rotor cavity and comprises an outer tooth and a radial inner tooth which are matched; a plurality of damping holes are evenly formed in the upper end face of an inner tooth body of the radial inner tooth in the circumferential direction, and a plurality of flow guide blades are evenly arranged on the radial end face of the inner tooth body of the radial inner tooth in the circumferential direction; furthermore, the damping holes are in a cellular shape and are evenly distributed in a sealing tooth face in the circumferential direction; the flow guide blade are arranged on the end face of the sealing radial inner tooth with equal arcs, and the blades are provided with gradually-shrunk channels. The rim sealing structure can effectively lower the high-temperature gas invading degree and improve the sealing performance of rim sealing, and therefore the overheat failure of a turbine disc is avoided, the use amount of low-temperature cooling air flow introduced from the position of an air compressor can also be reduced, and the efficiency of a unit can be improved.

The invention discloses a dual-stage axial cyclone with a concave cavity for enhancing the mixing of oil and gas, comprising a primary cyclone and a secondary cyclone, wherein the first cyclone and the secondary cyclone A venturi is arranged between the two cyclones, a sleeve is arranged on the secondary cyclone, the primary cyclone is sleeved on the central nozzle, and also includes: a mixed flow part, and the mixed flow part is arranged on the sleeve At the end of the combustion chamber, the mixing part is used to fully mix the oil and gas in the combustion chamber again; the cooling part is arranged on the sleeve, and the cooling part is used to transport the cooling gas and swirl the combustion chamber. The vortex core precession (PVC) flow instability commonly exists in the flow field of the dual-stage axial swirler, which will cause combustion instability and reduce the flame stability of the combustion chamber, which is not conducive to the flame. stable effect.