Magnetic thrust bearing, turbomachine and method

FIELD: machine engineering.

SUBSTANCE: thrust bearing includes the electromagnetic stator (22) with the stator surface (26) and the rotor disk (28) with the rotor surface (36), facing the stator surface (26). The rotor disc (28) contains the radially inner part, made of the first material and directly and exclusively connected to the radial outer part, made of the second material. The first material is the corrosion-resistant metal or the metal alloy, and the second material is the ferromagnetic metal or the metal alloy.

EFFECT: wear resistance increase.

14 cl, 8 dwg

 



 

Same patents:

FIELD: machine building.

SUBSTANCE: support of the turbomachine rotor containing ceramic bearing and bushing, is equipped with thrust weights. The internal ring of the ceramic bearing is installed on bushing. From one side of the internal ring of the ceramic bearing on the bushing a radial ring collar is made, it contacts with beating as per end faces, and from another side on the bushing along the circle the specified thrust weights are installed, besides, on the bushing surface the longitudinal cuts are made with beams created between them. Each of the longitudinal cuts passes from the radial ring collar and further over the seat surface of the bushing, then between the nearby thrust weights till bushing end.

EFFECT: simplified installation, dismounting of the internal ceramic ring of the bearing on the rotor, from the rotor keeping the required fit of the internal ceramic ring on the steel shaft, increased support reliability.

3 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: fixing structure for attachment of a guide blade to a frame or a casing of a fan of an aircraft engine. The guide blade is formed of composite material. The guide blade is intended to straighten an air flow. The fan casing is arranged outside the fan frame. The fixing structure includes the following: a mating surface, the first installation section, a supporting element, a supporting mating surface and the second installation section. The mating surface is formed in an end section of the guide blade. The first installation section is formed in the mating surface of the guide blade. The supporting element is made from metal as its component material, with that, the supporting element is connected in the form of an integral unit of the fan frame or the fan casing. The supporting mating surface is subject to conjugation with the mating surface of the guide blade and formed in the supporting element. The second installation section has a possibility of wedge-like adhesion to the first installation section of the guide blade and formed in the supporting mating surface of the supporting element. Rigidity and strength of conjugation is increased between the guide blade and the frame or the casing of the fan.

EFFECT: improved design.

9 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises rotor radial outer and inner stator parts with compressor air channel extending there between, circular clearance between rotor and radially inner stator part as well as discharge pipe. Rotor comprises fluid bearing rotor part while radially inner stator part comprises stator part. Circular clearance makes circular air channel communicated with compressor air channel. Cross-section of circular air channel decreases in airflow direction in first part and increases in second part. Discharge pipeline air inlet extending through second part of circular air channel is arranged axially between second part of circular air channel second part and fluid bearing. In operation of said engine, rotor is driven relative to radially outer and inner walls of stator part. Compressed air is forced via compressor air channel into circular air channel composed by the part of circular gap between rotor and radially inner stator part.

EFFECT: ruled out fluid ingress from bearing chamber into compressor air channel.

15 cl, 2 dwg

Jet turbine engine // 2554130

FIELD: engines and pumps.

SUBSTANCE: jet turbine engine comprises a fan (2) with an inlet bell mouth (3) on the runner (4) and an angular-contact thrust bearing (5) with labyrinth seals of an oil cavity (7), and also a low pressure compressor (8) and a high pressure compressor (9). From the front side of labyrinth seals the ring cavity of high pressure cooling air and a ring cavity of the high pressure heat air are located in series. The ring cavity of the cooling air at the outlet through the labyrinth seals is connected to the oil cavity, and at the inlet - through the pipes located in channels of the oil cavity support, an open header and a pipe in the oil cavity - with the peripheral cavity (17) of the air-gas channel (18) of the low pressure compressor (8) at its outlet (19). The ring cavity of the heat air is connected at the outlet with the air cavities (23) of the inlet bell mouth (3), and at the outlet - through the break of the open header and the pipe (25) in the oil cavity of the angular-contact thrust bearing of the fan - with the air-gas channel (26) at the outlet (27) of the high pressure compressor (9).

EFFECT: improvement of the engine reliability due to anti-icing heating of the fan bell mouth and improvement of efficiency of labyrinth seal of the oil cavity of the angular-contact thrust bearing of the fan.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: two-rotor gas-turbine engine contains low and high pressure rotors installed with a possibility of rotation in a fixed case. The low pressure rotor contains a compressor and a turbine connected with the low pressure shaft supported by the forward support bearing, and also by the first back and additional back support bearings. The first back support bearing and the additional back support bearing are supported by an exhaust case of the fixed case. The high pressure rotor is installed on forward and back support bearings of the high pressure rotor. The back support bearing of the high pressure rotor is the intershaft support bearing containing the inner race rigidly fixed to the high pressure turbine rotor, and the outer race, rigidly fixed to the low pressure shaft.

EFFECT: invention allows to decrease radial gaps on the ends of rotor blades under the load resulted from aircraft manoeuvring.

7 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: group of inventions relates to gas-turbine engine building industry and can be used in designs of supports of gas-turbine engines of aviation and ground application with a ceramic bearing. A rotary machine support includes ceramic rolling bearing (1), the outer race (2) of which is installed in metal housing (3), and inner race (4) is installed on metal rotor (5). As per the first version of design, external mounting surface (6) of race (2) and mating mounting surface (7) of housing (3) are conical. On the side of the end face, race (2) is additionally provided with annular element (8) with end flange (9) that is made as an integral part of race (2), and housing (3) on the side of the end face is additionally provided with annular element (10) with end flange (11) that is made as an integral part of housing (3); besides, flanges (9, 11) are mechanically attached to each other. As per the second version of design, internal mounting surface (14) of race (4) and mating mounting surface (15) of rotor (5) are conical. On the side of the end face, race (4) is additionally provided with annular element (16) with end flange (17) that is made as an integral part of race (4), and rotor (5) on the side of the end face is additionally provided with annular element (18) with end flange (19) that is made as an integral part of rotor (5); besides, flanges (17, 19) are mechanically attached to each other. It should be not that it is possible to implement both versions in one device.

EFFECT: providing serviceability of a ceramic bearing in a support due to maintaining mounting of external and internal races of the bearing in the housing and on the shaft in a wide temperature range during operation.

6 cl, 1 dwg

FIELD: machine building.

SUBSTANCE: turbomachine rotor support contains casing, at least one its section is made symmetrically relatively to the support axis, and bearing installed on shaft, its external cage is rigidly connected with casing. At casing section or sections as least two rows of radial slots are made, creating beams between them, they are inclined relatively to longitudinal axis of the support. Inclination angles of each adjacent rows of beams are made opposite as per direction relatively to the longitudinal axis of the support.

EFFECT: invention reduces weight and rigidity of the support without increasing of its axial dimension and number of parts.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine assembly including external structure to cover its moving parts and jacket comprising bearing consists of bearing thrust part and support part. External structure and jacket are coupled by said thrust part. The latter can be secured at external structure to make the stop for thrust part. Thrust part comprises engine gas channel and coupling parts to secure said channel at engine external structure and at said jacket. One of said coupling parts is flexible for radial displacement of said channel. Note here that amplitude of radial displacement is limited by thrust part shit against the stop to support part. Support part comprises rear extension extending in lengthwise direction towards exit beyond said channel lengthwise extension to make the ring for gas turbine engine turbine disc. Another invention of proposed set covers gas turbine engine with above described structural carcass.

EFFECT: longer life of bearing support assembly.

5 cl, 4 dwg

Expanding turbine // 2550123

FIELD: machine building.

SUBSTANCE: expanding turbine consists of: a casing with an inlet hole and an outlet hole for working fluid medium, at least one stator (3) mounted inside the casing, at least one rotor (2) mounted inside the casing and able of rotation around the respective rotation axis (X-X), a branch pipe (4) enclosed in the casing, a mechanical unit (5) installed inside the branch pipe (4). The mechanical unit (5) comprises a bush (7) and a shaft (6) installed so that to rotate inside the bush (7). The shaft (6) is coupled to the rotor (2) with the possibility of rotation, and the whole mechanical unit (5) can be taken as a solid unit out of the branch pipe (4) on the side opposite the said rotor (2). The rotor can move along the axial direction (X-X) between the first configuration when the mechanical unit (5) is set inside the branch pipe (4) and the rotor (2) is distanced from the branch pipe (4) so that the working fluid medium can rotate it, and the second configuration when the mechanical unit (5) is taken out of the branch pipe (4) and the rotor (2) is pressed to the branch pipe (4) providing for static seal (18, 19).

EFFECT: significant simplification of design and faster maintenance because turbine disassembly operations can be carried out without the turbine casing being emptied.

9 cl, 2 dwg

FIELD: machine building.

SUBSTANCE: invention relates to the hydrodynamic bearings, in particular for heavy rotors in power units. The hydrodynamic segmental bearing contains several pads (131) distributed over the circle around the rotor of the large steam turbine. Each pad (131) is installed on the platform separating the pad from the cylindrical separator, which in its turn is connected with the floor of the room where the turbine is installed. The contact area between at least one of several pads (131) and platform on which at least one of several pads is installed (131) is made such that to include at least two zones with different curvature to increase stiffness of the contact area in case of the relative movement between the pad (131) and platform. At least one of several pads (131) has in the contact zone between the pad (131) and platform the first radius of curvature (R1) beyond the centre of the contact zone, and second radius of curvature (R2) in centre of the contact zone, at that the second radius (R2) exceeds the first radius of curvature (R1) by 5-10 times.

EFFECT: change of bearing rigidity, and hence increased stability of the bearing and its support structure.

10 cl, 6 dwg

FIELD: mechanical engineering; turbomachine building.

SUBSTANCE: invention relates to design of thrust-damper supports of rotors of turbomachines. Proposed support of turbomachine rotor contains bearing and shell secured on outer race and connected with stator member by means of split bushing and forming damping space between stator member and shell. Shell and stator member are provided with end face steps from side opposite to split bushing. Said steps engage with each other and with splines made behind. Moreover, shell is furnished with axial displacement limiter.

EFFECT: prevention of breakage of support and other members of turbomachine in operation, improved reliability of turbomachine.

2 dwg

Thrust bearing // 2287697

FIELD: mechanical engineering.

SUBSTANCE: thrust bearing comprises rotor with thrust comb, stator, thrust blocks interposed between the comb and stator, and balls interposed between the thrust blocks and thrust face of the stator and locked against shift in the peripheral direction. Several balls are set in the grooves made in the thrust blocks from the side of the stator and bear on the other balls mounted in the grooves in the thrust face of the stator .

EFFECT: enhanced reliability.

1 cl, 3 dwg

FIELD: mechanical engineering.

SUBSTANCE: proposed turbomachine in form of turbine or compressor has rotor and stator. Rotor consists of first part made in form of one disk and second part consisting of shaft connected with disk and stretched lengthwise perpendicular to disk, and two bearings fitted on shaft at a distance from each other. Disk of first part of rotor contains blades to direct flow of gas arranged over circumference. First bearing is located closer to disk than second one, and its housing has outer diameter greater than outer diameter of all other members arranged on rotor shaft between first bearing and free end of shaft. Stator of turbomachine has housing with first part arranged close to disk of rotor and installed on -place and secured from side of free end of rotor shaft. Turbomachine is assembled as follows: two bearings and other members of rotor are fitted on rotor shaft of turbomachine. Then rotor is subjected to balancing. After balancing, first part of stator housing is fitted on rotor shaft near disk, shifting it axially relative to rotor shaft from side of free end of rotor shaft in direction of rotor disk.

EFFECT: provision of high accuracy of rotor balancing after assembly.

16 cl, 3 dwg

FIELD: mechanical engineering.

SUBSTANCE: device comprises sealing spacers and clutch interposed between the spacers. The clutch is conical and bears on the transverse link of the outer shaft line for permitting access to the mounting nut of the front end through the space between the shaft lines, which allows the nut be screwed out and the outer shaft line to be dismounted.

EFFECT: simplified mounting.

3 cl, 4 dwg

FIELD: power engineering.

SUBSTANCE: invention can be used for power generation and for direct drive of mechanisms, for instance, pumps, used in irrigation. Proposed device has closed gas-liquid circuit for circulation of working medium including turbine to remove energy from working medium with rotor on sliding supports, main line to take off working medium from closed circuit for lubricating sliding supports, and main line to return medium after sliding supports into closed circuit. Take off of working medium is carried out on section where working medium is in liquid phase. Sliding support contains built-in labyrinth screw pump. Said labyrinth screw pump receives at input working medium as lubricating liquid and its forces said liquid through clearance between friction surfaces of sliding support of labyrinth screw pump. Turbine in closed gas-liquid circuit uses labyrinth screw seal as end seal, and to provide operation of the latter, in has device to control passage section of return main line of sliding support of labyrinth screw pump.

EFFECT: dispensing with self-contained lubrication system with oil pump, oil tank and other members from turbine system, simplified design, reduced cost of construction.

2 cl, 2 dwg

FIELD: mechanical engineering; aircraft industry.

SUBSTANCE: invention relates to gas-turbine engines of aircraft and ground application. Proposed turbocompressor of gas-turbine engine is provided with rear support with bearing arranged under combustion chamber. In shaft of turbocompressor and in adjoining to shaft parts, such as labyrinths and flanges, holes are made. Air intake holes are located before bearing and cooling air outlet holes, after bearing. Intake holes are connected with outlet holes through bypass holes. Invention improved reliability and economy of engine owing to reduction of losses in duct by excluding special air supply main line through gas-air duct between compressor and combustion chamber.

EFFECT: improved reliability and economy of engine owing to reduction of losses in duct.

3 cl, 2 dwg

Gas-turbine engine // 2300652

FIELD: mechanical engineering; gas-turbine engines.

SUBSTANCE: proposed gas-turbine engine has drum rotor with blades of compressor and turbine its inner surface. Supports of rotor are made in form of sliding bearings whose working spaces are arranged between outer surface of rotor and inner surface of housing enclosing the rotor. Cryogenic liquid or gas is used as bearing lubricant. Outer surface of rotor is made of material whose strength increases under action of cryogenic lubricant.

EFFECT: increased capacity of compressor and thrust of engine owing to increased strength of drum rotor.

2 dwg

FIELD: mechanical engineering; rotary machines.

SUBSTANCE: invention relates to design of variable pliability resilient supports of rotary machines. Proposed resilient-damping support of turbomachine contains bearing, stator member and shell secured on outer race of bearing and connected with stator member by means of split bushing and thus forming damping space with stator member. Stator member and shell are provided with steps and are installed relative to each other for engagement by their conical mounting surfaces. Split bushing is provided with slots tilted relative to longitudinal axis of support. Invention makes it possible to change pliability of support by changing axial load directly in process of operation of rotary machine, thus changing amplitude frequency characteristic of rotor and providing constant operation of rotor at nocritical speeds.

EFFECT: reduced vibrations of rotary machine and axial dimensions of support.

FIELD: mechanical engineering.

SUBSTANCE: device comprises thrust block (6), bottom levers (2), top levers(1), unmovable members (4). Rollers (3) are interposed between the top (1) and bottom (2) levers. Bottom levers (2) bear on unmovable member (4) through spherical bearings (5). Top levers (1) bears on unmovable member (4) through rollers (3) and bottom levers (2). Thrust block (6) bears on top levers (1) through spherical bearings.

EFFECT: improved design.

1 dwg

FIELD: machine building.

SUBSTANCE: invention is related to the field of aviation engine engineering. Support device of bearings is intended for holding of rotary shaft (10) of aviation engine installed in bearings (20, 50), which are connected to structure (16) of engine stator with the help of bearing supports (22, 52). At that support device comprises the first bearing (20) retained by support of the first bearing (22), and the second bearing (50) retained by support of the second bearing (52). Support of the second bearing (52) elements (24, 40), which act parallel and at the same time join the second bearing (50) with design (16) of engine stator. Two elements (24, 40) represent different degrees of rigidity and define rigid element (40) and flexible element (24). Rigid element (40) realises connection between the second bearing (50) and structure (16) of engine stator with the help of safety means. Support of the first bearing (22) ends with flange (34), which is fixed in structure (16) of engine stator with the help of safety elements (36).

EFFECT: creation of support device of bearing for rotary shaft of aviation engine, which comprises rigid path of forces transfer and flexible path of forces transfer, which are compatible with possible displacements of this rotary shaft after its disconnection, and which is quite convenient and easy to use.

14 cl, 5 dwg

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