Gas turbine engine birotary screw fan |
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IPC classes for russian patent Gas turbine engine birotary screw fan (RU 2439376):
         
 Turbo-machine containing cooling system of lower surface of impeller of centrifugal compressor / 2437000
Turbo-machine consists of unit of diffuser-rectifier (12) set at output of impeller (18) of centrifugal compressor (14) and supplying air into circular combustion chamber (10) and of device (36) of air supply for ventilation of turbine. The unit of the diffuser-rectifier consists of lower circular flange (30) with its lower end connected with devices for supply and together with lower surface (40) of the impeller restricting circular cavity (41) of circulation of air for ventilation withdrawn at an output of the compressor. Device withdrawing part of air volume (92) for ventilation of turbine and device for direction of withdrawn air (83) to radial internal part of lower surface of the impeller are installed on device (36) of supply. Air is circulated radially from inside outside along lower surface of the impeller and is mixed with air withdrawn at output (26) of the compressor for lowering air temperature in circular cavity (41).
 Power unit / 2425256
Water is supplied to system of shut off water from pressure part of first circuit to ensure normal operation of unit. Relief device 14 opens only at pressure drop occurring when it exceeds pressure drop with closed device 14 of shut down main circulation pump aggregate - MCPA - upon end of its running out while all rest MCPA of unit operate normally. Cooler 6 of a cooling and lubrication system of bearing 4 is positioned over the bearing thus ensuring stable circulation of water both due to natural convection sufficient for withdrawal of heat from the zone of bearing 4 at fixed shaft 1 and at cooling water with cooler 6 when water is withdrawn from the cooling and lubricant system of bearing 4 to the system of shut off water of the operating MCPA. Shut-off accessories 12 on the pipeline of leakage draining from the system of shut-off water operate only with shut down of the MCPA upon end of the latter running out and when water from the pressure section of the first circuit is not supplied to the system of shut-off water.
 Primary circulation pump unit / 2418197
Each bypass of medium stages 7, 8 of end face seal assy 5 incorporates shut-off vales 11, 13 arranged communicated with throttle vale 10, 12 to inhibit leaks from seal assembly 5 with the help of shut-off valves 17 on drainage pipeline. Aftercooler 15 of shut-off water is arranged above seal assy 5 to allow steady gravity feed of shut-off water from said aftercooler 15 into seal assy space on primary circulation pump shaft 1.
 Vane pump / 2412378
Vane pump with side supply of working fluid comprises shaft 3, passing through input header 2 with gap 4, blade impeller 5 and bearing 6, installed on shaft at both sides of gap 4, and holes 7 to supply cooling liquid to bearing, on shaft 3 along gap 4 there is helical pump 10 with input from side of bearing 6 and output towards blade impeller 5.
 Compressor air unit / 2410572
Invention refers to compressor air unit (1), namely for submerged operation. Stator (16) of electric motor (2) is connected to separate cooling device (40). Cooling device (40) has the possibility of natural circulation in it in operating conditions of cooling medium and it includes condenser (55) which at least by means of one supply line (53) and at least one drain line (54) is connected to cooled stator (16). Cooling device (40) has the possibility of cooling medium circulation between condenser (55), drain line (54), stator (16) and supply line (53).
 Gas turbine engine compressor / 2396471
Gas turbine engine compressor comprises rotor with vanes and stator with outer and inner casings jointed together by taper flange. Compressor has also blow-down chamber and perforated deflector. Note also that radial but of taper flange with inner casing is arranged between the inlet and outlet edges, first from the circular groove arranged between air intake chamber and compressor flow section. Flanged nozzle made in deflector is directed towards said vane. Note here that the angle between compressor flow section outer wall generatrix and stator front flange outer surface, nearby circular groove, makes α=40°…80°.
 Procedure for test calibration of working parametres of fan / 2384754
Invention refers to procedure of test calibration of working parametres of fan designed for smoke removal in installation for smoke elimination. The technical result is achieved in the procedure for test calibration of working parametres of the fan designed for smoke removal in the installation for smoke elimination by means of diagnosis process consisting in measuring temperature of fan bearings and of an electric engine actuating the fan; the process of diagnosis is actuated with the fan switched on for a limited in time run; further temperature mode changing in time is measured and processed.
 Deep-well electrically driven centrifugal pump unit / 2382237
Invention relates to oil production by deep-well electrically drive pumps and can be used for extracting oil with high content of mechanical impurities. Proposed unit comprises motor 3 cooled by pumped fluid and centrifugal pump 1 with intake screen. Said unit is accommodated inside casing 5 with circular gap. Valve assembly 6, carcass-wire filter 7 and accumulator 8 are consecutively attached to casing 5 from below. From above, said casing is attached to tubing string. Aforesaid carcass-wire filter 7 is made up of bearing rod, tubular carcass and filter shell. Note here that tubular carcass has lengthwise slots, tubular carcass outer surface being furnished with triangular thread. Filter shell is made from triangular-section wire with slots made between wire turns to expand inward the structure.
 Compressor plant / 2370675
Proposed plant comprises compressor, heat exchanger, end refrigerator and air accumulator interconnected by the main and extra pipelines mounted at the pressure line. Aforesaid pipelines are furnished with valves electrically connected to control unit. Note here that compressor is connected, via suction line, with air filter representing a resonator with cover and tapered bottom. The bottom lower part accommodates a float-condenser. The housing upper part accommodates a tapered nozzle. The nozzle outlet is furnished with a screen. A bimetal baffle consisting of rigidly jointed plates is arranged behind the said outlet. Note here that the first plate is porous, while the second one is solid. Note also that aforesaid baffle is pivoted to the filter housing upper part to separate the housing into chambers communicating with aforesaid suction pipeline and tapered nozzle. The latter has its inner surface features curvilinear grooves running from the inlet to outlet, the curvature being directed clockwise. Mind that the baffle first plate features curvilinear grooves with pores the curvature of which is directed counter clockwise.
 Filtering fan with device for fast securing in place / 2349797
Invention is related to filtering fan in body with frame equipped by device for fast securing in place in the form of elastic plates, which prevents suction of dirty air. Filtering fan (100) has body (10) and frame (11), at that frame (11) is equipped with device for fast securing in place in the form of elastic plates (12). Frame (11) is arranged as uninterruptedly solid along perimeter, and plates (12) are molded to frame (11).
 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.
 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.
 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.
 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.
 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.
 Axial multi-stage compressor of a gas turbine engine / 2243418
The invention relates to compressors of gas turbine engines ground-based and airborne applications
 Multistage compressor of gas turbine engine / 2235913
The invention relates to compressors of gas turbine engines for aircraft and ground applications
 Multistage compressor of gas turbine engine / 2235912
The invention relates to compressors of gas turbine engines for aircraft and ground application
 Axial multistage compressor / 2180054
The invention relates to a compressor engineering, in particular to the design of multistage axial compressor
 The fan / 2174194
The invention relates to ventilyatorostroeniya and can be used as part of systems management products aviation and rocketry
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.
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FIELD: engines and pumps. SUBSTANCE: 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 EFFECT: higher reliability due to efficient cooling of rear suspension. 3 dwg
The invention relates to birotational windowingsystem located at the outlet of the gas turbine engine. Known birotational wincounter, the blades of which are placed on a rotating housings birotational turbine (SAUNO. Construction and design of aircraft gas turbine engines, Moscow, Mashinostroyeniye, 1981, str, RES.). The disadvantage of this design is its low reliability due to the increased temperature of the shanks of the propfan blades installed on the hot buildings birotational turbine. Closest to the claimed is birotational wincounter, the gas channel in the sleeve which is connected to the inlet gas path of the power turbine of a gas turbine engine (patent of great Britain No. 2186918, VS 11/38, F01D 7/00, 1987). A disadvantage of the known designs adopted for the prototype, is the low reliability due to high body temperature back support and force ring rear suspension. The technical problem solved by the invention is to improve reliability due to the effective cooling power ring rear suspension and chassis rear feet propfan. The invention consists in that in birotational windowancestor gas turbine engine containing power ring rear the suspension and the rear support with the installed rotor, according to the invention the power ring is connected to the front flange of the rear housing bearing, in which the connecting bolts are made The connection of the power rings of the rear axle with the front flange of the body back support allows you to reduce the temperature of the ring rear suspension by cooling the air entering the Run in the front flange of the rear housing bearing between the connecting bolts The implementation of the ribs between the channels of the front flange with aerodynamically streamlined profile reduces hydraulic losses of the cooling air flowing from the annular slit of the cavity along the inner surface of the outer casing back support, and improve the cooling efficiency. Figure 1 shows a longitudinal section birotational propfan turbine engine of the claimed design; figure 2 is an element I in figure 1 in an enlarged view; figure 3 presents the cross-section A-a in figure 2. Birotational wincounter gas turbine engine 1 includes a front 2 and rear 3 impellers, which is installed with the front 4 and rear 5 propfan blades, respectively. Sleeve 6 propfan 1 together with the impellers 2 and 3 installed in the rear bearing 7, which is made with a gas channel 8 is connected at the input gas duct 9 power turbine 10. In the gas channel 8 of the housing 7 is placed a power rack 11, and the front flange 12 of the outer wall 13 of the housing 7 by means of bolt connection 14 is docked with the power ring 15 rear suspension, which, in turn, is connected to the outer to what bosom 16 power turbine 10. To ensure an intense barrage of film cooling in the front flange 12 of the housing 7 between the bolts 17 bolted connection 14 is made To reduce the hydraulic resistance of the cooling ribs 23 between the channels 18 is made in the form of an aerodynamically streamlined profile 24. Does this device as follows. When working birotational propfan 1 cooling air 25 of the cavity 19 of high pressure Birotational wincounter gas turbine engine containing power ring rear suspension and rear supports, characterized in that the power ring is connected to the front flange of the rear housing bearing, in which the connecting bolts are made
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-shaped air channel connecting the air chamber is increased pressure on the external side of the housing with the gas channel of the rear feet, forming the output of the ring slit cavity, and edges between the air channels are made with aerodynamically streamlined profiles.