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Water injection system of axial multistage compressor Water injection system of an axial multistage compressor, having tubes and outlet channels, further comprises a fairing, in this case the fairing is located in the area of the front edge of each guide blade of the axial multistage compressor with a possibility to form a slot-type channel. Each tube is positioned in a longitudinal cavity formed in the area of the front edge of the indicated blade, and has holes made by the blade height to provide a uniform vapour flow by the section of an air flow, and outlet channels are made at the front edge of each indicated blade, in this case the slot-type channel, and the outlet channels are designed in each guide blade of the axial multistage compressor with a possibility to provide a nonseparated water flow and air flow. In addition, each tube has a heat-protective material. |
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Fan for local ventilation of wells Fan includes two basic modules of the first and the second stages adjacent to each other by a connection box-type insert so that each module includes a housing, an electric motor, an impeller installed immediately on the electric motor shaft. Impellers of the first and the second stages are made as per a counter-rotation scheme as all-welded impellers with non-rotational double plate blades of S-shape with a variable along the impeller radius by a geometry calculated by means of a single vortex method as jointly operating without any directing vanes based on minimum acoustic power (noise) of the fan, maximum efficiency, pressure and capacity. |
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Proposed device comprises moving wheel with moving vanes and stationary wheel with fixed vanes. It comprises also moving wheel manifold for collection of airflow sucked off moving vanes and stationary wheel manifold to collect airflow forced onto fixed vanes. Moving wheel manifold is located on compressor stage casing outer edge, opposite the moving wheel. Stationary wheel manifold is located above moving wheel manifold. |
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Set of invention relates to aircraft engineering. In the first version, no-run take-off and landing electric aircraft contains fuselage (1) with pillars (3) and helical fan in cowlings (2), lifting planes and chassis. Turbo-rotary engines (4) have generator units of the first and the second screws connected by electric circuit with electric motors (12,13) of the first (23) and the second (28) screw respectively of screw fan (11) installed on the front upper pillar (10). In the second version, no-run take-off and landing electric aircraft contains fuselage with upper and lateral pillars with fork at the end. In the fork of front upper pillar (10), turbo-rotary engine (4) with generator units having rotors on shafts of screw fan screws is installed, and in forks of front lateral pillars (48), electric motors (50) driven fans (49) are installed. Invention also covers lifting device, turbo-rotary engine, multistep compressor, fan cowling, turbo-rotary engine operation method and lifting force creation method. |
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Gas turbine engine birotary screw fan Birotary screw fan comprises structural ring of rear suspension and rear bearing housing. Note here that said structural ring is jointed with rear bearing housing flange wherein -like air channels are made to communicate higher-pressure air chamber located outside of said housing with rear veering gas chamber. Said gas channels form annular slotted chamber while ribs between air channels feature aerodynamically streamlined profiles. |
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Holes are made in the hub located at an angle of 90 degrees to its axis as per the number of blades; pin is fixed in each hole; slot for arrangement and turn of the base is made in each pin; each rotation axis is installed in the holes made in pin on opposite sides of the slot and passes through the slot; springs are made in the form of torsion springs arranged on axes of bases; at that, one free end of each spring is connected to the pin, and the other end is connected to the base, and edges of pins protruding to outer surface of hub are made in the form of cylindrical surface coaxial to hub, the diameter of which is equal to outer diameter of the hub. |
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Invention relates to aircraft engine production, particularly to blowers of aircraft gas turbine engines. Proposed screw-type blower comprises 1st and 2nd turbine wheels arranged one behind the other and furnished with vanes running in disks relative to radial axes. Front edges of the 1st turbine wheel vanes feature a departure from radial rotational axis increasing from the hub to periphery to create the vane sweep forward. 2nd turbine wheel vane front edges feature a departure from radial rotational axis decreasing from the hub to periphery to create the vane sweep forward. Birotary stew-type blower can be cowled. |
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Invention relates to aircraft engine production, particularly to aircraft gas turbine engine blowers. Proposed birotary blower consists of two consecutive impellers running in opposite directions. To produce required profiles of both impellers, necessary distributions of blades angles are corrected by algebraic summation of their designed angles. Birotary screw-type blower can be cowled. |
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Method of increasing efficiency of axial multi-stage compressor operation Invention relates to compressor production and can be used in, for example, gas turbine plants incorporating axial multi-stage compressors. The proposed method comprises injecting water into, at least, two compression stages that allows maximum increase in efficiency of the axial multi-stage compressor along with minimum water flow rate. The above effect is provided for by a mathematical expression to calculate the compressor efficiency that allows for steam content and steam enthalpy in air behind the compressor, and to calculate the optimum amount of water injected into the compressor stages required for the said increase at preliminary stages of compressor operation. |
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Compressor housing (versions) and compressor impeller blade Proposed housing of compressor includes axially convex inner surface located around row of impeller blades with radial clearance between surface and blades. Edges at tip of blades add to housing contour, thus reducing losses on ends at blade tips and blocking of flow. |
Another patent 2551224.