Axial multistage compressor |
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IPC classes for russian patent Axial multistage compressor (RU 2180054):
 The fan / 2174194
The invention relates to ventilyatorostroeniya and can be used as part of systems management products aviation and rocketry
 Screw compressor / 2173406
The invention relates to devices for mixing, pumping and compression of gases, can be used as a portable source of compressed air for aircraft on-Board tool in workshops, garages, workshops
 Axial three-stage compressor / 2136974
The invention relates to a compressor engineering, in particular to multi-stage axial compressors and allows to increase the generated pressure and the efficiency of the compressor
 The axial compressor of a gas turbine engine / 2111385
The invention relates to the field of aircraft engine industry, namely the high pressure compressor turbojet engines, mainly with a large by-pass ratio
 Three-stage multistage compressor / 2097604
The invention relates to a compressor engineering, namely the multi-stage axial compressors
 Vertical pump / 2005919
 Compressor housing (versions) and compressor impeller blade / 2247867
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.
 Method of increasing efficiency of axial multi-stage compressor operation / 2359160
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.
 Birotary srew-type blower / 2367822
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.
 Birotary screw-type blower / 2367823
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.
 Impeller of axial fan / 2422681
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.
 Gas turbine engine birotary screw fan / 2439376
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
 "maxinio" standard technology of vehicle manufacturing and operation, no-run take-off and landing electric aircraft (versions), lifting device, turbo-rotary engine (versions), multistep compressor, fan cowling, turbo-rotary engine operation method and method of electric aircraft lifting force creation method / 2457153
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.
 Air bleed device, compressor stage with said device, compressor with said stage, and turbojet with said compressor / 2467209
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.
 Fan for local ventilation of wells / 2509894
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.
 Water injection system of axial multistage compressor / 2524594
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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(57) Abstract: The invention relates to a compressor engineering, in particular to the design of multistage axial compressor. The compressor contains impellers and guide vanes with a constant height angle of the output edges. The compressor has a first stage comprising 5-20% of the total number of stages (upstream compartment), middle and final stages that make up 15-20% and 60-80% (main group stages), the slope of the output edges of the guide vanes which are respectively equal to 90-100o, 65-70oand 60-65o. The root diameter of the cross section of the initial part of the first working vanes upstream compartment, the subsequent monotonic decrease of 10-15% large diameter root sections of the main group stages. The use of the invention improves the efficiency of the compressor by optimizing the shape of a flowing part in the meridional cross section of the upstream compartment. 1 Il. The invention relates to mechanical engineering and can be used in axial compressor machines. Known forms of flow of the axial-flow compressors in the meridional cross-section with increasing or postoenie", 1970, S. 207). Known flow part of an axial compressor with increasing root diameter section of the first (upstream) of the stages containing the impellers and guide vanes with a constant height angle output edges, including the first steps that make up 5-20% of the total number of stages (upstream compartment), middle and last stages, components and 15-20 60-80% (main group stages), and in which the angles of inclination of the output edges of the guide vanes are respectively equal to 90-100o(on the upstream compartment), and 60-65 65-70o- the main group of steps (patent 953271 RF, MKI F 04 D 19/02. Axial multi-stage compressor). These angles of inclination of the guide blades in the upstream compartment allow you to have TRANS - and supersonic flow around blades of this compartment and at a moderate load of these stages to ensure high efficiency axial compressor as a whole (Y. I. Zhuravlev, G. C. Proskuryakov. The number of uniform axial compressors for stationary gas turbines. Power plant engineering, 1984, 6, S. 10-13). The disadvantage of the considered design is that with increasing load levels upstream compartment (Y. I. Zhuravlev and d is 4), despite the headroom available on the possible slight increase of Mach numbers in relative motion (and, accordingly, increase of the outer diameter of the impeller), the coefficients of diffusivity are root sections reach the limit (and exceeding) values, which reduces the efficiency of these sections of rotor blades. The use of constant root diameter of the upstream section of the compartment, i.e. the increase in the first stage compared with the original version allows only partially reduce the coefficients of diffusivity are root sections. The objective of the invention is to optimize the shape of the flow part in the meridional cross-section upstream of the Bay. This technical result is achieved by an increase of 10-15% of the root diameter of the cross section of the initial part of the first stage as compared with the diameter of the root section of the main compartment under monotonic decrease of the diameter of the root sections upstream compartment from the marked to the constant diameter of the root section of the main group stages. The drawing shows a flow part multistage axial compressor. The proposed multistage axial compressor sod the wow section 3, plot with a constant root diameter section 4, the initial root diameter of the first stage 5, greater than the root diameter of the section 4 by 10-15%. With the passage of gas (air) through the preliminary group stages 1 compressor at the site root sections 3 with a marked increase in the diameter of the cross section of the initial part of the first stage 5 at the increased load upstream stages are supported permissible values of the coefficient of diffusivity are in this section of rotor blades. This design allows to increase the efficiency of root sections upstream compartment and efficiency multistage axial compressor as a whole. Axial multistage compressor containing impellers and guide vanes with a constant height angle output edges, including the first steps that make up 5-20% of the total number of stages (upstream compartment), middle and last stages, components and 15-20 60-80% (main group stages), the slope of the output edges of the guide vanes which are respectively equal to 90-100, and 60-65 65-70o, characterized in that the diameter of the root sections at the initial part of the first working blades producl the Oia main group stages.
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