34 results about "Nozzle geometry" patented technology

Systems and methods are provided in which individual elements of a thin patterned film are deposited by two or more nozzles having different geometries. The different nozzle geometries may include one or more of different throttle diameters, different exhaust diameters, different cross-sectional shapes, different bore angles, different wall angles, different exhaust distances from the substrate, and different leading edges relative to the direction of movement of the nozzles or the substrate. Methods may include steps of ejecting a carrier gas and a material from a plurality of nozzles and depositing the material on the substrate in a plurality of laterally spaced elements, each of the elements deposited by a separate nozzle group. At least one of the nozzles in a group of nozzles depositing an element may be configured to deposit the material on the substrate in a width that is smaller than the width of the element.

An inducer that includes a profiled throat. In some embodiments, the inducer includes a conical shape upstream of the profiled throat with a relatively large circular inlet that narrows to the profiled throat and, downstream of the profiled throat, a downstream section that broadens from the profiled throat. The profiled throat may include an approximate convergent-divergent nozzle geometry.

Exemplary vanes for a turbocharger having variable nozzle geometries are disclosed. In one aspect, each of the vanes includes two axial surfaces that are on opposite sides of the vane. The opposite axial surfaces include two corresponding chambers. These chambers are partially exposed to each other through an aperture. Such an aperture allows for some degree of equalization of the pressures in the chambers and, thereby, reduces the axial load exerted by a vane, for example, on the unison ring. In another aspect, each of the vanes includes two opposite airfoil surfaces. At least one of the airfoil surfaces includes a notch that allows a chamber in the nozzle to be pressurized by the exhaust gas. The pressure in the chamber creates a counteracting force that reduces the axial load exerted by a vane.

The invention relates to a multi-fuel-loop used for premixing synthetic gas / NG DLN in nozzle. Concretely, a fuel / air premixer used for a burner in a combustion system of a gas turbine comprises an air inlet (1 and 6), a fixed nozzle geometry structure (4) and a annular mixing channel (3). The fuel / air premixer mixes fuel and air in the annular mixing channel to inject the mixture in a burner reaction area (5). A plurality of fuel sources (21 and 22) are connected with the fixed nozzle geometry structure, and cooperate with the fixed nozzle geometry structure to realize various fuel flow changes such as fuel type change, fuel doping change, volume flow change and pressure ratio change.

A variable geometry turbine (VGT) for turbochargers incorporates a turbine nozzle having a plurality of vanes, each vane having an airfoil with an inner disc and an outer disc. A first nozzle plate incorporates pockets to receive the inner discs with the inner discs substantially flush with a nozzle surface on the first nozzle plate. A second nozzle plate has pockets to receive the outer discs with outer discs substantially flush with a second nozzle surface. An integral actuation system rotates the plurality of vanes for variation of the nozzle geometry.

The present invention is a simulation calculation method based on FLUENT to simulate the distribution of hard phase particle matrix surface, belongs to the field of numerical simulation calculation, and comprises the following steps: S1: establish the geometric model of cold spraying Raoult nozzle, S2: divide the grid and divide the grid Import FLUENT, S3: select the solver and solution method, S4: select the basic equation to be solved, S5: specify the physical properties of the material particles, S6: specify the boundary conditions, S7: initialize the flow field, start iterative solution, S8: gas phase convergence Then add discrete phase particles, S9: insert UDF program into DPM, S10: post-processing of calculation results, S11: repeat the above steps as needed; the present invention adopts discrete phase numerical simulation method, by comparing the change law of cold spray gas phase velocity and particle motion Trajectories, accurately complete the distribution of particles sprayed to the substrate surface, and provide a theoretical basis for solving the distribution uniformity and deposition of cold spray particles on the substrate.

The invention provides a variable turbine. The variable turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a movable nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway. A substantially annular rib is provided either on the face of the nozzle ring (such that the minimum width of the inlet passageway is defined between the rib and a the facing wall of the housing) or on the facing wall of the housing (such that the minimum width of the inlet passageway is defined between the rib and the nozzle ring).

A filter assembly (1), which separates particles and liquid droplets from the airflow (W) passing through the cooker extraction hood, comprises two dished shells (11, 12). These are detachably connected. One shell (12) carries a spacer (18). The sheet-metal construction of the shells includes filter openings. These are located in the side walls of each shell, which are bent-up from the base (9). Openings in adjacent shells are mutually-offset. At least some of the openings are round holes. Around their edges, nozzle geometries are formed. These formations are integral with the shells. The shells are coated (e.g. with PTFE) and their overall shape is blunt-pyramidal.

The invention relates to a method for real-time calculation and prediction of jet flow noise of a turbofan engine based on a proxy model. ;Construct the finite element model of turbofan engine jet flow field, simulate the orthogonal test and obtain noise samples; use the noise sample data to solve the proxy model; use the atmospheric conditions, flight speed and nozzle geometry to correct the noise model, and finally get the A real-time model of jet noise with certain accuracy. The invention solves the problems that the traditional computational fluid dynamics method has a huge amount of calculation, cannot cover the noise conditions in the entire flight process, and cannot meet the real-time simulation requirements in the numerical calculation process of the jet flow noise of the aero-engine. basis for control.