Rotor shaft bearing of low-pressure compressor of turbojet engine (versions), casing of rotor shaft rear bearing, rotor shaft component, polyfunctional external tightening component of rotor shaft, connection component of rotor shaft, casing of bearing of rotor shaft rear bearing

FIELD: engines and pumps.

SUBSTANCE: group of inventions refers to the area of production and operation of gas turbine engines. The rotor shaft bearing of the low-pressure compressor is located in an intermediate casing of the engine and contains a ball bearing, which is performed thrust and radial, dividing the shaft bearing to stator and rotor parts. The stator part from its internal part is performed conjointly to the external ring of the ball bearing, and on its external perimeter, the stator part is secured in the intermediate casing of the engine and equipped with cover supports of labyrinth seals. The rotor part contains a trunnion of a drum-disk constituent of the rotor shaft detachably connected to a cylinder constituent of the rotor shaft, by means of which the rotor part is rested on the internal ring of the ball bearing, as well as contains the polyfunctional external tightening component in the form of a circular cylindrical nut and a connection component in the form of a hollow screw. The rotor and stator parts of the shaft bearing are in the oil medium common to them both.

EFFECT: group of inventions allows adapting the low-pressure compressor as a part of the engine to more sensitive mode of external air current supply, as well as to intense operation in stationary conditions of ground functioning.

20 cl, 7 dwg

 



 

Same patents:

FIELD: machine building.

SUBSTANCE: subsonic blade of axial turbine machine intended for radial installation on the specified machine, contains frond edge, rear edge and two aerodynamic surfaces. The aerodynamic surfaces are located at opposite sides and pass through the blade length, at that each connects the front edge with the rear edge. The blade front edge has S-shaped lateral profile. The most front part of the front edge is at height within 3-20% of blade length, and/or the most rear part of the rear edge is at height within range 85-97% of the blade height. The another invention of the group relates to the compressor of the axial turbine machine containing rotor with at least one stage of rotor blades and stator with at least one stage of stator blades, at that blades of at least one stage of rotor and stator are made as specified above. One more invention of the group relates to axial turbine machine containing the above compressor.

EFFECT: group of inventions increases the engine capacity by at least 1% in comparison with the optimised stage having blades with front edges of S-shape profile.

19 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: turbomachine compressor rotor consists of a disk which carries blades. The wall of the disk at its radial outer ring is made from several angular sectors each of which is limited between the first blade back and the pressure side of the second blade following the first blade in the circumferential direction. Each of the sectors comprises a bulge section being convex in the axial and circumferential directions. The tip of the bulge section is set radially outside in respect to the imaginary surface of rotation around a rotor disk axis passing through four points determined by the intersection of the wall respectively with the front edge of each of the first and second blade and the rear edge of each of the blades. The tip is distanced in the circumferential direction from the first blade back by 30-70% of the circumferential distance between the back and the pressure side of the blades measured at the tip level. The wall comprises also a recess section located upstream from the bulge section and being concave in the axial direction and in the circumferential direction and having a base being approximately point-like one. Other inventions of the group refer to the compressor including such a rotor and a turbomachine including such a compressor.

EFFECT: group of inventions allows for increasing the efficiency of turbomachine compressor rotor.

6 cl, 2 dwg

Gas turbine engine // 2553889

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine (1) comprises a fan (2) disk (13) and a tapered shaft (8) of a low pressure compressor (3) fixed by radial flanges (9) and (16) on a radial flange (11) of a common shaft (12) of the fan with fit bolts (19). The tapered shaft (8) of the low pressure compressor is mounted by the flange (9) on the external surface of the (12) fan (11) shaft (10) flange. The fan disk (13) is placed by the flange (16) on the internal surface (17) of the (12) fan (11) shaft (17) flange. The ratio of the thickness h of the radial flange of the fan disk in the location of the fit bolts to the thickness H of the radial flange of the fan shaft is within 0.8…1.2. The ratio of the thickness h1 of the radial flange of the tapered shaft of the low pressure compressor in the location of the fit bolts to the thickness H of the radial flange of the fan shaft is within 0.4…0.8.

EFFECT: due to avoidance of collapse of the fit bolts, avoidance of imbalance of the fan rotors and the low pressure compressor rotors during the gas-turbine engine operation its reliability is improved.

2 dwg

Gas turbine engine // 2536655

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine (1) comprises a body of drives (2) with a compressor (4) arranged downstream along the air flow (3) with front straightening (8) and working (9) titanium blades along the flow. On the front tail (12) of the compressor shaft (13) there is a geared wheel (14) for driving of units. On the geared wheel there is a thrust radial end (16) arranged as directed to the body of the drives (2), and on the body of drives there is a support radial surface (17) that responds to the end (16). The ratio of the minimum axial distance H between the inlet edge of the front working blade and outlet edge of the guide blade of the compressor to the axial distance h between the thrust end of the geared wheel and the support surface of the body of drives is within 1.1…3.

EFFECT: by exclusion of failures of compressor titanium blades in case of damage of its radial and thrust bearing, gas turbine engine reliability increases.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to propeller hub, particularly, to that for gas turbine engine with blower not covered by cowl. This hub comprises polygonal ring 134 composed of, in fact, radial cylindrical grooves 136 distributed about central axis of said ring 134 to accommodate said blades. Gas turbine engine turbine rotor 134 and retainer clip secured at said ring so that said ring is not engaged with said rotor 143. Said hub comprises extra multiple safety retainers 144 engaged with rotor 143. Note here that every said safety retainer has at least one thrust surface 145 located opposite outer surface 146 of said ring 134 spaced radially therefrom.

EFFECT: higher safety owing to catching of broken hub fragments.

7 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: invention relates to a compressor rotating blade (10) for axial flow compressors with preferably stationary gas turbines. To minimise losses in a radial clearance a centreline (32) of located on the top of the airfoil side (30) of the airfoil (12) of the compressor rotating blade (10) have at least two bending (36, 38) points. Due to two bending points (36, 38) for the suction side circuit (42) at the section covering 35-50 % of length of the chord of the section profile (D) of the suction side circuit which is concave, and for the pressure side circuit (40) the section (E) of the pressure side circuit, which is convex.

EFFECT: due to the geometry the possibility of vortex generation in the clearance, resulting in smaller losses, with the purpose of increase of general efficiency fitted with these compressor rotating blades (10) of the axial compressor.

17 cl, 10 dwg, 1 tbl

FIELD: machine building.

SUBSTANCE: circulating forced and ventilation air compressor including a compressor housing and a rotor, differing by the fact that rotor consists of a bladed wheel; bladed wheel consists of a shaft hub, a disk of bladed wheel and moving blades; bladed wheel is connected to the disk of the bladed wheel by means of shanks of moving blades, and is formed by summation of multiple tiers of bodies of moving blades; the air channel is made between two adjacent bodies of moving blades and has an air channel inlet and an air channel outlet.

EFFECT: providing circulating forced and ventilation air compressor having a simpler design, low material consumption, low weight and low friction losses; as a result, circulating forced and ventilation air compressor has higher efficiency and lower energy consumption, as well as wider application area, and is convenient at transportation, installation and maintenance.

9 cl, 16 dwg

FIELD: machine building.

SUBSTANCE: guide blade or rotating blade includes aerodynamic surface (1) with shaped sections (3, 5, 15A-15E) having span, bending line and front edge (7), on which bending line encloses with axial direction of the compressor an angle of blade front edge. On rear edge the bending line encloses with axial direction (A) of compressor an angle of rear edge. Shaped sections (3, 5, 15A-15E) of blade aerodynamic surface are located one above another on front edge (7) along straight line passing in radial direction (R) of compressor from compressor hub to compressor housing. Angles of front edge of shaped sections of aerodynamic surface vary along the span and more for shaped sections of aerodynamic surface near the hub and near the wall than for shaped sections of aerodynamic surface in the middle of the span.

EFFECT: reduction of spatial losses and increase in stability margin at adequate strength margin.

18 cl, 7 dwg

Axial-blow fan // 2484310

FIELD: machine building.

SUBSTANCE: axial-blow fan impeller comprises hub, bushing, discs to couple said bushing with said hub, vanes with butts and attachments of said butts to said vanes. Vane butt has collar while vane attachment is equipped with barrel with inner annular groove and lock ring whereto pressed is the vane butt collar. Note here that said barrel is fixed in discs groves while lock ring is fixed in said barrel groove.

EFFECT: lower metal intensity and moment of inertia.

3 dwg

Turbomachine wheel // 2477800

FIELD: engines and pumps.

SUBSTANCE: wheel of a turbomachine, such as an aircraft jet turbine engine, includes at least one rotary disc that carries blades, and at least one ring made from composite material with a metal matrix. The ring is installed on the disc to take centrifugal forces during operation. It includes at least one ring-shaped flange formed with sectors. Sectors are located end-to-end and each of them includes a ring-shaped radial internal part and radial external part. Radial internal part is put on side surface of the disc; radial external part is borne against the ring to provide axial retention of the latter on the disc. The wheel also includes radial retention means of flange sectors on the disc. The other object of this invention is a turbomachine containing the above described wheel.

EFFECT: invention allows facilitating the flange installation at the rotary disc periphery and decreasing the stress in the ring.

13 cl, 8 dwg

FIELD: machine building.

SUBSTANCE: straight-toothed cylindrical engagement between rotors of the movable parts of the turbine machine contains two toothed rims. Each toothed rim is located at end of the movable part and is in engagement with another toothed rim providing free passage for air between throats of the surrounding parts, and ends of the surrounding parts of teeth. The toothed rim of at least one movable part continues in radial direction relatively to another toothed rim to form external or internal extension of the toothed rim against the element surrounded by the movable part or surrounding the movable part installed on another toothed rim. To protect the air passage in joint between the rotors of the movable parts one end of the joint is continued in radial direction relatively to the another end to form the external or internal expansion. The expansion is made against the element surrounded by the movable part or surrounding the movable part installed at another end of the joint. This invention of the group relates to the rotor line of the turbine machine containing multiple specified above straight-toothed cylindrical engagements between the rotors of compressors and turbines.

EFFECT: group of inventions excludes closing of air passage in joint between rotors of the turbine machine.

9 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: turbine of a double-circuit gas turbine engine includes turbines of high and low pressures with supports of turbine rotors. Inside the rotor of the low pressure turbine there is an air cavity of high pressure connected at the inlet to the air cavity of the first nozzle block of the low pressure turbine, and at the outlet via the rear labyrinth seal - with a flow path of the low pressure turbine. The air cavity of high pressure is limited at the inner side - by the first and second labyrinth seals. Seals separate the air cavity of high pressure from the air cavity of low pressure. The air cavity of low pressure is divided into front and rear cavities. The front cavity is arranged between the high pressure turbine support and a cone flange of the low pressure turbine shaft. The rear cavity is located between the cone flange of the low pressure turbine shaft and low pressure turbine support. The first and second labyrinth seals are located relative to each other in such a manner that the ratio of the minimum diameter along sealing combs of the first labyrinth seal to the minimum diameter along sealing combs of the second labyrinth seal makes 1.2…2.0.

EFFECT: invention makes it possible to increase reliability and efficiency of a turbine.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rotors of high-temperature turbomachines of gas turbine engines of aviation and ground use. In a rotor (1) of a high-temperature turbomachine between the first (7) and second (8) and the last but one (9) and the last (10) along gas flow (11) sealing combs in a rim (6) of an intermediate disc 5 there are radial channels (13) and (14), connecting an air disc-to-disc cavity (4) with a gas cavity (12) of the turbine. Radial walls (15) and (16) of channels (13) and (14) are made flat, and walls (17) and (18) that connect them are made cylindrical. The ratio of the length L of the channel in circumferential direction to the radius R of the cylindrical wall of the channel is within 2…6.

EFFECT: by exclusion of contamination of inner surface of an intermediate disc and reduced concentration of stresses in a disc rim, high-temperature turbomachine rotor reliability increases.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: low-pressure turbine comprises vanned discs engaged with turbine shaft via bevelled claw. Vanned discs and bevelled claw comprise circular flanges with ledges composed of alternating solid and hollow parts at inner and outer periphery, respectively. Solid parts have passages for fasteners. Every solid part is engaged with periphery of the disc or bevelled claw by asymmetric concaved recesses. Other inventions of the set relates to low-pressure turbine disc and bevelled claw and gas turbine engine with such turbine.

EFFECT: longer life of disc flanges and bevelled claw.

7 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: insert (10) and the method of adjustment of steam balance through-hole (54) in a wheel (52) of steam turbine rotor are proposed. The insert (10) includes a housing (12) with have longitudinal axle (14) and oppositely located first and second ends (16, 18). Insert flange (20) is oriented in radial direction from the second end (18) of the housing (12). The exterior surface (22) is located along the housing (12) periphery between the named first end (16) and the flange (20). The first bore (24), made in the body (12), forms the first opening (28) in the first end (16), while the named first channel (24) and exterior surface (22) of the housing (12) together confine among themselves the wall (32), capable of being plastically deformed in a radially outward direction. The second bore (26), made in the housing (12), communicates with the named first bore (24) and has a smaller cross-section, than the first bore (24). The installation method entails the installation of the insert (10) in the through-hole (54) and expansion of the wall (32) to clamp the axial thickness of the wheel (52) between the flange (20) and expanded wall (32) of the insert (10).

EFFECT: simple installation of the insert is achieved, which can be executed by one employee without modifying of the wheel, the risk of strain of adjoining wheels is eliminated during the installation.

7 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed rotor comprises discs jointed by thread joints arranged their mid part in rotor lengthwise axis. Peripheral circular section of one disc on its inner side is furnished with ledges and lengthwise slits alternating therewith and arranged in disc circle. Peripheral circular section of the other disc in contact with the former is provided with lugs with ledges and lengthwise slits alternating therewith on its outer size in quantity equal to that of disc lengthwise slits. End surfaces of said ledges are tapered. Lugs are extended over disc circle beyond said contact surface to allow engagement between ledges of one disc with conical surface of the other disc ledges.

EFFECT: higher reliability of gas turbine engine rotor.

2 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine rotor comprises working wheel discs connected by the surfaces of locating ring elements with cylindrical radial through bores made therein with retaining elements. Extended section is made on the part of every said bore on inner surfaces of locating ring elements, on the side of their outer surface. Retaining elements are composed of sleeves with internal thread arranged at extended sections and pints with appropriate outer thread locked at said bores by expansion. Working wheel discs are interconnected at their mid part along rotor lengthwise axis.

EFFECT: higher reliability, manufacturability and reparability.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: radial ring flange of turbine rotor or stator element comprises alternating ledges and recesses with bottom areas made at inner or outer peripheral part. Ledges have bores for fastening bolts. Recessed part bottom area to prevent inadequate joint at said inner or outer peripheral part is arranged radially inside or outside with respect to circle centred at flange centre and tangent inside or outside relative to ledge bores. Both parts with recesses arranged on their both sides feature concave bottom located radially inside or outside relative to, in fact flat bottoms of other recessed parts. Other inventions of this set relate to low-pressure turbine including abode described flange and to gas turbine engine with such turbine.

EFFECT: higher reliability of ring flange.

9 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to multistage gas turbines for aircraft engines and surface power generation plants. Proposed gas turbine comprises rotor wheels interconnected by flanges with axial studs. Coupling shaft is arranged at inner side of wheel hubs. First turbine rotor wheel is locked at in coupling shaft input extension by radial rib in radial and axial directions. Radial rib is arranged between wheels, right between rotor tightening nut and adjusting ring.

EFFECT: decreased overall dimensions, higher reliability.

2 dwg

FIELD: machine building.

SUBSTANCE: radial ring flange on its outer or inner periphery comprises alternating projections with holes for fastening tightening bolts and hollows as well as tools to prevent faulty angle joint by preventing bolts from entering a hollow. The tools to prevent faulty angle joint are formed by the bottom of at least one hollow of the inner or, respectively, outer periphery with its radius in relation to the turbomachine axis being less or, respectively, greater than the radius of the circle externally or, respectively, internally tangent to the holes for the bolts to pass through the projections. The other invention of the group relates to the connection of gas-turbine engine elements comprising the above said flange fixed by the bolts with ring clamps. The bolts are placed between the clamps' holes and in the flange projections' holes; the bottom of smaller or, respectively, greater radius is placed between the two flange projections and two projections of at least one of the clamps. One more invention of the group refers to a gas-turbine engine comprising the above connection.

EFFECT: invention eliminates risk of faulty ring flange installation.

8 cl, 6 dwg

FIELD: process engineering.

SUBSTANCE: invention relates to continuous thermal hydrolysis of sludge including biological material. This method comprises continuous feed of biological material to tubular reactor feed zone to increase the pressure and to maintain temperature equal to 100-200°C without boiling of biological material. Steam is fed to reactor steam feed zone to increase temperature to 100-200°C. Pressure inside reactor is maintained for preset time of 0-5 hours. Water is fed into rector cooling zone to down the temperature to below 100°C and biological material is fed to discharge zone. Proposed device comprises tubular reactor with inlet for feeding sludge therein at inlet zone, inlet to feed steam into reactor steam inlet zone, inlet to feed cooling water to reactor cooling zone, and used sludge outlet.

EFFECT: sludge cooling by water with heat exchanger, higher efficiency.

18 cl, 3 dwg

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