Turbopump unit

FIELD: engines and pumps.

SUBSTANCE: invention relates to turbomachinery, particularly to high-rpm high-pressure rotary pumps to be used in turbopump units of liquid-propellant rocket engines. Turbopump unit consists of the turbine and pump working wheels of which are fitted on common shaft running in bearings, and seals separating the cavity of one of bearings from pump and turbine. Said cavity is connected with working wheel outlet cavity via shaped channels, their inlet is arranged at acute angle to working fluid peripheral speed.

EFFECT: reliable operation in liquid-propellant rocket engine, higher efficiency.

7 cl, 2 dwg

 

The invention relates to the field of Turbomachinery, namely high-speed high-pressure centrifugal pumps, and can be used in the field of rocketry, turbopump units (TNA) liquid propellant rocket engines (LPRE).

In TNA engines with afterburning gas pressure in the cavity of the turbine substantially above the pressure in the cavity of the discharge openings of the pump impeller, which requires the supply in the cavity between the pump and the turbine of the fluid pressure exceeds the pressure in the adjacent cavity of the turbine. Breakthrough high-pressure gas from the cavity of the turbine into the cavity of the pump causes damage to and loss of the operational condition of the bearings due to their insufficient cooling, and hit the gas in the liquid end of the pump leads to cavitation breakdown. This is the reason for the abort liquid-propellant rocket engine. Thus, in the development and operation of LRE special attention should be paid to the division of the cavities of the pump and turbine TNA, whose main task is the elimination of the possibility of breakthrough of gas from the turbine to the pump with a minimum reduction efficiency TNA, that is, to ensure minimum leakage of working fluid from the pump cavity into the cavity of the turbine.

Known turbopump unit containing a pump, a turbine seal separating the pump and the turbine, the bearing pump bearing, bearing turbine bearing. (A. Dmitrenko, I., Ivanov, A. C., Kravchenko, A. G., Molotov Century. And., Savin A. A., Glebov Century A. Development turbopump assemblies for modern oxygen-kerosene engines with afterburning oxidizing gas // international scientific journal "Space". No. 1-2, 2012. - S. 42-49, Fig.1, 3; Ivanov, A. C., Belousov A. I., A. Dmitrenko, I. Turbopump units oxygen-hydrogen rocket engine. Voronezh: VPO Vilnius Gediminas technical University, 2011. 283, Fig.162 (page 188) prototype.)

This turbopump Assembly with respect to the liquid rocket engine has the following disadvantages.

The selection of fluid from the pump leads to a significant reduction of the efficiency of the pump and the design of such a complex selection. If the pressure difference between the cavities of the pump and turbine of more than 30%of the fluid is performed after the pump impeller through the holes in the enclosure parallel to the axis of the pump. However, such a selection may not provide reliable separation of startup, shutdown and regulatory regimes.

The task of the invention is to remedy these disadvantages.

The technical effect is achieved by the turbopump Assembly consisting of the turbine and pump impellers mounted on the same shaft supported on bearings, seals, separating Polo is to be one of the bearings from the pump and the turbine, the bearing is connected to the cavity exit of the impeller using a profiled channel, the entrance to which is at an acute angle to the circumferential speed of the working fluid. At the entrance to the profiled channels can be performed o-ring manifold. After profiled channels can be performed by-pass holes or channels. At the entrance to the profiled channels can be performed o-ring manifold, and after a profiled channel - bypass holes or channels. After profiled channels can be performed by-pass holes or channels, and between the profiled channels and overflow holes - ring header. At the entrance to the profiled channels can be performed o-ring manifold, after the profiled channel - bypass holes or channels, and between the profiled channels and overflow holes - ring header.

Offer turbopump Assembly of liquid-propellant rocket engine shown in Fig.1; Fig.2 - section a-a in Fig.1, where 1 is the turbine; 2 - pump; 3 - turbine wheel; 4 - impeller pump; 5 - shaft; 6, 7 - bearing; 8 - the bearing; 9 - seal between the bearing and the turbine; 10 - seal between the bearing and the pump; 11 - cavity exit of the impeller of the pump; 12 - profiled channels; 13 - entrance angle profilirovannyj channel; 14 is a circumferential speed of the working fluid; 15 - overflow drain; 16, 17 - ring header.

Turbopump Assembly (Fig.1) consists of turbine 1 and pump 2, the impeller of the turbine 3, the pump impeller 4, a shaft 5, bearings 6, 7, the seal between the pump and the turbine. The sealing system consists of a seal 9, which separates the bearing from turbine, the bearing cavity 8, the seal 10 between the bearing and the pump. The bearing 8 is connected to the cavity exit of the impeller of the pump 11 through a shaped channels 12. At the entrance to the profiled channels can be performed annular manifold 16. After profiled channels can be made of the overflow drain 15 or channels. After profiled channels 12 can be made of the overflow drain 15 or channels, and between the profiled channels and overflow holes - ring manifold 17.

When working turbopump turbine unit 1 causes the rotation of the pump 2, while the turbine wheel 3 and the pump impeller 4 rotates with the same angular velocity as installed on the same shaft 5, supported on bearings 6, 7. The fluid from the cavity to the exit of the impeller of the pump 11 through a profiled channel 12 enters the cavity of the bearing 8, is limited by seals of the turbine 9 and the pump 10. The entrance angle of the liquid at about lirovannye channels 13 is located at an acute angle to the circumferential speed of the working fluid 14. This ensures reliable separation of the cavities of the pump and the turbine, as the choice of the angle of the inlet 13 and the profile of the channels 12 can be achieved using not only the static component of the pressure behind the impeller of the pump, but also partly convert the dynamic pressure into static pressure, which is especially important for transient operation modes; and through the use of seals is minimal impact of the leaks on the efficiency of the unit. To provide a more uniform supply of liquid to the profiled channels on the water in them can be made annular manifold 16. For a more convenient supply of fluid to the bearing after profiled channels 12 or collector ring 16 can be made of the overflow drain 15 or channels, and between the profiled channels and the bypass holes for flow equalization - ring manifold 17. To provide a more uniform supply of liquid to the bearing after the bypass channels can be made manifold with overflow holes or channels.

Thus, in the turbopump unit ensures reliable separation of the pump and turbine modes of operation at a high efficiency unit that provides reliability TNA in the composition of the liquid rocket engine.

1. Turbopump Assembly, sustasis turbine and pump, impellers mounted on the same shaft supported on bearings, seals separating the cavity of one of the bearings from the pump and the turbine, characterized in that the bearing is connected to the cavity exit of the impeller using a profiled channel, the entrance to which is at an acute angle to the circumferential speed of the working fluid.

2. Turbopump Assembly under item 1, characterized in that the inlet shaped channels made ring header.

3. Turbopump Assembly under item 1, characterized in that after the profiled channels are bypass holes or channels.

4. Turbopump Assembly under item 1, characterized in that at the entrance to the profiled channels are ring collector, and after profiled channels are bypass holes or channels.

5. Turbopump Assembly under item 1, characterized in that after the profiled channels are bypass holes or channels, and between the profiled channels and the bypass holes made ring header.

6. Turbopump Assembly under item 1, characterized in that at the entrance to the profiled channels are ring collector, after shaped channels made the bypass holes or channels, and between the profiled channels and the bypass holes made the ring the second header.

7. Turbopump Assembly under item 1, characterized in that at the entrance to the profiled channels are ring collector, after shaped channels made the bypass holes or channels, between the profiled channels and the bypass holes are ring manifold at the outlet of the bypass channels are manifold with overflow holes or channels.



 

Same patents:

FIELD: machine building.

SUBSTANCE: assembly (10) of a turbo-compressor is divided along axis (12) of rotor (11) into three sections (13, 18, 22): supporting section (13), and those of (18) engine and (22) compressor. Supporting section (13) has active magnetic bearing (14) for support of rotor (11). Engine section (18) includes engine (19) having stator (20) located along axis (12) of rotor (11). Stator (20) is enveloped with annular gap (21) of the engine, which is formed between stator (20) and rotor (11). Compressor section (22) has compressor (23) for compression of cooling fluid medium (30). Additionally, assembly (10) of the turbo-compressor includes common gas-tight housing (26) and cooling system (27). Housing (26) encloses rotor (11), supporting section (13), engine section (18) and compressor section (22). Cooling system (27) has inlet (28) for supply of compressed cooling fluid medium (30) to supporting section (13) and engine section (18) through fluid medium pass (29) located between supporting section (13) and engine section (18). Cooling system (27) includes throttle device (31) in the form of a labyrinth seal, which is located near gap (21) of the engine to restrict the flow of cooling fluid medium (30) from pass (29) of fluid medium to engine gap (21).

EFFECT: improvement of efficiency of a turbo-compressor assembly by reduction of recirculation flows.

13 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: method to improve efficiency of axial multistage compressor operation is implemented by the injection of water. Water is supplied into the air flow through calibrated outlet channels provided on the surface of guide vane blades. The water is injected under the saturation temperature corresponding to the sum of local pressure in the compressor stages and pressure difference in the said outlet channels. Water injection is started in those compressor stages where temperature of the environment becomes higher than the water saturation temperature at local pressure in compressor stages.

EFFECT: reduction of power consumed by a compressor due to the determination of optimal place and parameters of water injected into the flowpath of a multistage compressor.

2 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: set of inventions relates to turbopump units of liquid-propellant rocket engines and nuclear rocket engines. Turbopump unit comprises pump 1, turbine 2, shaft 3 running in ball bearings 4, wheel 6 of turbine 2 and impeller 6 fitted on shaft 3, housing 8, separation chamber 9 with shaft seals 11 on the side of pump chamber and chamber ahead of turbine wheel 6. Separation chamber 9 is connected via channel 12 and external discharge pipeline 13 with engine main line wherein pressure is lower than that inside turbine 2. External pipeline 13 can be connected with gas circuit downstream of turbine 2, with line feeding fluid to pump 1 and lined feeding fluid into engine. Separation chamber 9 can be communicated with gas circuit downstream of turbine via channel or channels in shaft 3 and turbine wheel 6.

EFFECT: higher reliability and efficiency.

5 cl, 2 dwg

FIELD: machine building.

SUBSTANCE: invention relates to the method of a hybrid unit control and to the hybrid unit in which this method can be implemented. Control method for a unit 1 comprising at least a compressor plant 2 and/or a drying unit on one side and a heat regeneration system 3 on the other side. The heat regeneration system 3 absorbs heat from the compressor plant 2. Additionally the hybrid unit 1 comprises a controller 5 and a device 6 to set one or more system parameters. The controller 5 performs control both of the compressor plant 2 and/or the drying unit and the heat regeneration system 3 on the basis of the said system parameters along with the optimisation of the overall efficiency of the hybrid unit.

EFFECT: reduction of total power consumption by the hybrid unit.

3 cl, 1 dwg

FIELD: heating.

SUBSTANCE: invention relates to a fan header and method of its manufacturing. With the help of a laser they cut shells, flanges in the form of a circumference segment, connection flanges and stands in the form of stiffening ribs. Flanges and stands are made with T-shaped slots, and shells - with response cogs. Flanges in the form of the circumference segment, connection flanges and stands in the form of stiffening ribs are welded into metal frames. Frames are fixed to shells by means of joint cogs in T-shaped slots and welding in points of jointing to form sectors. Then the produced structure undergoes hot galvanisation.

EFFECT: increased durability of a product due to fine cutting of a header and a shell blanks, and hot galvanisation of items.

3 cl, 4 dwg

FIELD: electricity.

SUBSTANCE: invention relates to electrical engineering and may be used in submersible electric motor with enclosed-type stator. Electrical machine has stator frame (4) and winding package (11) surrounding rotor (2) of the electrical machine (1), which is located in stator frame (4) and has axial-directed operating zone (16), which is designed for electrodynamic interaction of winding package (11) with rotor (2); at that stator frame (4) at the side faced to rotor (2) has a circumferential open gap, which in its axial lengths complies with axial length of the winding package (11) operating area (16) and where electrically non-conductive separator pipe (19) of the electric machine (1) is installed and this pipe is sealed in regard to stator frame (4) so that winding package (11) is separated hermetically from rotor (2), at that separator pipe (19) passes in axial direction only in the operating area (16) of winding package (11).

EFFECT: improving durability and efficiency factor.

12 cl, 2 dwg

FIELD: power industry.

SUBSTANCE: method of energy recovery by gas compression in compressor plant (1) with two or more compression stages. Each stage is formed by a compressor (2, 3). A heat exchanger (4, 4) consisting of first and second part two is placed downstream of each compressor. Cooling agent is fed in sequence through the second part of at least two heat exchangers (4, 5). Sequence of cooling agent passage through heat exchangers (4, 5) is selected so that temperature at the inlet of the first part of at least one next heat exchanger was not lower than temperature at the inlet of previous heat exchanger if viewed along the flow of cooling agent. At least one heat exchanger (4 and/or 17) has a third part for cooling agent.

EFFECT: higher energy recovery compared to existing methods of energy recovery.

25 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: pump comprises motor chamber accommodating part of metal shaft and drive half-coupling with set of permanent magnets engaged therewith, sealing shield to separate motor chamber from pump chamber accommodating drive half-coupling with drive shaft and impeller. Note here that said drive half-coupling is composed of toothed magnetic core made from metal related to group of ferromagnetics with high Curie temperature Tc, for example iron (Tc=769C) while motor chamber is evacuated. Note also that vacuum clearance between drive half-coupling and sealing shield makes a heat barrier integrated in magnetic coupling. Besides, motor chamber housing also incorporates heat shield while drive shaft exploits liquid cooling system.

EFFECT: pump with heat-resistant magnetic coupling for transfer of fused metals and hot media.

15 cl, 2 dwg

FIELD: machine building.

SUBSTANCE: in axial-centrifugal compressor, the rotor of which includes impeller (6), axial gap (8) is adjusted by special air ventilation in the rotor, with a device containing two parallel channels (11, 13), in which flow velocities are adjusted with corresponding valves (12, 14). At that, temperature in one of them is changed by heat exchanger (15). Thus, adjustment of temperature and flow velocity of ventilation air is performed.

EFFECT: providing adjustment of an axial gas in an extended section of an axial-centrifugal compressor due to difference of thermal deformations.

FIELD: engines and pumps.

SUBSTANCE: unit includes in-series connected multistage bladed pump, a protector and an electric motor with housings to be arranged under the tubing string in the inner space of the casing string. The pump is provided with an inlet module including a separator with supporting wheels at the inlet, grids of blades in a separating drum, a device for removal of light impurities in the form of a separator with a system of tightly insulated channels, and a disperser. The unit is equipped with an annular tube to be installed with a radial gap in the tubing. The submersible electric motor is equipped with a flange having the possibility of direct stiff and tight attachment to lower base of the tubing above the protector and the submersible pump. The pump is arranged on the protector side opposite to the above flange of the electric motor. The annular tube is made so that the protector and submersible electric pump can be installed in it with formation of a transfer channel around them for supply of the working medium from the pump to the tubing.

EFFECT: creation of an effective submersible pumping unit with improved reliability and durability.

8 cl, 23 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used in rocketry, turbopump units of liquid-propellant and nuclear rocket engines. Turbopump unit comprises pump 1, turbine 2 running in bearings 4 and 5, shaft 3 supporting turbine 2 wheel 6 and impeller 7, case 8, separation chamber 9 with shaft 3 seals 10 and 11, chamber 12 arranged downstream of seal 11 between separation chamber 9 and pump 1, and chamber 13 downstream of impeller 7. Seals 10 and 11 separated turbine 2 chamber from pump 1 chamber. Separation chamber 9 is connected with high-pressure chamber 13 via channel 14. Chamber 12 behind seal 11, between separation chamber 9 and pump 1, is integrated with chamber 13 downstream of impeller 7.

EFFECT: higher reliability of engine starting owing to improved cavitation properties of the pump.

6 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: set of inventions relates to turbopump units of liquid-propellant rocket engines and nuclear rocket engines. Turbopump unit comprises pump 1, turbine 2, shaft 3 running in ball bearings 4, wheel 6 of turbine 2 and impeller 6 fitted on shaft 3, housing 8, separation chamber 9 with shaft seals 11 on the side of pump chamber and chamber ahead of turbine wheel 6. Separation chamber 9 is connected via channel 12 and external discharge pipeline 13 with engine main line wherein pressure is lower than that inside turbine 2. External pipeline 13 can be connected with gas circuit downstream of turbine 2, with line feeding fluid to pump 1 and lined feeding fluid into engine. Separation chamber 9 can be communicated with gas circuit downstream of turbine via channel or channels in shaft 3 and turbine wheel 6.

EFFECT: higher reliability and efficiency.

5 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: turbopump comprises housing (4) with working chamber (9), shaft (7) with external drive, impeller fitted on shaft (7) and aligned therewith inside said chamber (9). Impeller comprises first and second discs (1, 2) aligned with axial clearance there between and having inlet holes (6) at central area. Impeller has first inlet of fluid (5) for axial feed to axial clearance between said first and second discs (1, 2) via inlet of first disc (1). Impeller has second inlet of fluid for axial feed to axial clearance between said first and second discs (1, 2) via inlet (6) of second disc (2). Besides, it has outlet for discharge of first and second fluids from working chamber (9) periphery. Said impeller comprises extra mid solid disc (3) fitted aligned between discs (1, 2) and with clearance there between and discs (1, 2). OD of mid disc (3) is smaller than OD of discs (1, 2) and larger than that of outer circle on inlets (6) of discs (1, 2).

EFFECT: simple design, lower production and operating costs, power saving, higher reliability.

10 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: turbo-pump unit includes a turbine assembly comprising a steam inlet housing, a nozzle block with inclined convergent-divergent nozzles, a turbine having a shaft with a runner, and a waste steam outlet housing located downstream of the turbine. The steam inlet housing is equipped with a supply connection pipe and a header including an axisymmetrical annular cover, the larger part of which has the shape of a tore or toroid fragment. The header is attached to the nozzle block disc. The nozzles of the block are made in the disc in the amount of 815, are located radially at equal distance with their longitudinal axes from the turbine axis and equally spaced in a circumferential direction at equal angles determined in the range of (2445). Longitudinal axis of each nozzle is located in a conditional plane parallel to the turbine shaft axis normally to the turbine shaft axis, normally to radius and inclined in the above plane at an angle to the conditional plane of the disc in the direction opposite to rotation vector of the turbine runner at an angle of (1225). The pump assembly of the unit includes a pump housing with a screw centrifugal impeller.

EFFECT: increasing service life, improving compactness, efficiency and reliability of the unit and medium pumping effectiveness at simultaneous reduction of material consumption.

19 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: pump housing includes pumped medium inlet and outlet housings and a projection-shaped rear annular element, which together form a flow cavity for arrangement of a screw centrifugal impeller of a closed type and an automatic rotor axial unloading mechanism. Blades of the impeller are of different length and variable height as to length, which decreases towards the impeller outlet with observance of a quasiequality condition of the cross sectional area at an interblade channel inlet. Number of blades at the outlet is divisible and exceeds at least by two times the number of blades at the impeller inlet. Active volume of dynamic filling of a set of interblade channels of impeller is provided with possibility of releasing to flow part of (4.745)10-5 m3/rpm of pumped liquid per revolution of impeller. The automatic axial unloading mechanism includes adjacent annular shoe and belt, which form an end slot seal. The seal provides a self-adjustable flow of the pumped medium from the high pressure zone to the low pressure zone through overflow openings in the main disc and creates pulsating change of axial rotor unloading force.

EFFECT: increasing service life, improving reliability, compactness and operating efficiency of a pump assembly and an automatic axial unloading mechanism at simultaneous reduction of material consumption.

12 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: turbo-pump unit includes a turbine assembly comprising steam inlet and outlet housings, a nozzle block and a turbine. The unit includes a pump assembly comprising a housing with a screw centrifugal impeller of a closed type. The pump housing includes inlet and outlet housings and a projection-shaped rear annular element, which together form a flow cavity for arrangement of the impeller and an automatic rotor axial unloading mechanism. Blades of the impeller are of different length and variable height as to length, which decreases towards the impeller outlet with observance of a quasiequality condition of the cross sectional area at an interblade channel inlet. Number of blades at the outlet is divisible and exceeds at least by two times the number of blades at the inlet. Active volume of dynamic filling of a set of interblade impeller channels is equal to (4.745)10-5 m3/vol of pumped medium. A spiral tap of the pump assembly is made in the form of a two-way volatile with difference of surface areas of outlet and inlet sections of channels, which is related to the channel length, with an expansion gradient in swirling direction, which is accepted based on a quasiequality condition of velocities of flows in each channel of the volatile.

EFFECT: increasing service life, improving compactness, efficiency and operating reliability of the unit and medium pumping effectiveness at simultaneous reduction of material consumption.

18 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: turbo-pump unit includes turbine, support and pump assemblies. The turbine assembly includes steam inlet and outlet housings, a nozzle block and single-stage turbine. The pump unit includes a pump housing, a screw centrifugal impeller and an automatic rotor axial unloading device. The impeller s made in the form of a screw and a multiturn centrifugal pump of a closed type, which are combined. Blades of the latter are of different length and variable height as to length, which decreases towards the impeller outlet with observance of a quasiequality condition of the cross sectional area at an interblade channel inlet. Number of blades and interblade channels at the outlet is divisible, and exceeds at least by two times the number of blades and channels at the inlet. The screw is multiturn and has spiral blades and a hollow shaft; besides, it is equipped with smooth expansion in a transient zone of the screw channel to the multiturn channel of the centrifugal wheel. Screw blades have variable radius and/or pitch of spiral swirling and have a certain average gradient of swirling pitch increase.

EFFECT: increasing service life, improving operating reliability of a unit and pumping effectiveness of different liquid media to a consumer at simultaneous reduction of material consumption and improving compactness and efficiency of the unit.

19 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: turbine assembly of the unit includes a working medium - steam supply housing, a nozzle block with inclined nozzles, a turbine having a shaft with a runner, and a waste steam outlet housing located downstream of the turbine in the steam flow direction. The steam supply housing is equipped with a header including an axisymmetrical annular cover having the shape of a flattened fragment of a tore or a toroid. The turbine runner us made at least of one disc with blades. Blades are convex-concave as to width and have radial height comprising (0.050.25) of the disc radius. The blade thickness is variable in the direction of steam flow with maximum in the middle part of the blade chord width. The chord width of the blade in the projection to a conditional chord plane attaching inlet and outlet side edges of the blade does not exceed radial height of the blade. The nozzles are made in the disc in the amount of 815, located radially at equal distance with their longitudinal axes from the turbine axis and equally spaced in a conditional circumferential direction at equal angles determined in the range of (2445). Total number of blades exceeds by 2.634.4 times the number of nozzles.

EFFECT: increasing service life, improving reliability and operating efficiency of a turbine assembly at simultaneous reduction of material consumption and improving compactness of the assembly.

9 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: turbo-pump unit includes a turbine assembly with working medium inlet and outlet housings, a nozzle block and a single-stage turbine. The unit includes a pump assembly with a screw centrifugal impeller. The working medium supply housing is equipped with a manifold including an axisymmetrical tight annular cover. The large part of the cover has the shape of a longitudinally flattened fragment of a tore or a toroid. Turbine runner blades are convex-and-concave as to width, radial height of 0.050.25 of the turbine runner disc radius. The blade thickness is accepted as variable in the direction of working medium flow vector with maximum in the middle part of the blade chord width. The chord width of the blade in the projection to a conditional chord plane attaching inlet and outlet side edges of the blade does not exceed radial height of the blade. The inter-blade channel is of a confuser-and-diffuser type in the direction of the steam flow vector with maximum constriction of flow cross sectional area determined in zone of maximum thickness of blades. Total number of turbine runner blades exceeds by 2.634.4 times the number of nozzles in the nozzle block.

EFFECT: increasing service life of a unit, improving reliability and pumping effectiveness, compactness and efficiency at simultaneous reduction of material consumption.

19 cl, 6 dwg

Turbo-pump unit // 2459118

FIELD: engines and pumps.

SUBSTANCE: unit contains pumps of oxidiser and fuel with spline joined shafts, turbine wheel is fastened on one of shafts. Unit contains dummy piston of automatic unloading machine, the piston is combined with the main propeller disk of one of pumps. Unloading machine is restricted by radial seal in peripheral part of the main disk and by control axial slot near propeller hub. Ball bearing of this pump is designed with outer ring installed in housing with axial gap, ball bearing of the second pump is designed with axial stop located in housing with gap along butt end of ball bearing outer ring. Shaft of one pump with backing butt-end rest on backing butt-end of shaft of the second pump. Gaps along butt-ends of axial stop of outer ring of ball bearing of pump without unloading machine are designed larger than corresponding axial gaps along butt-ends of outer ring of ball bearing of pump with unloading machine.

EFFECT: improving efficiency factor of turbo-pump unit and enhancing pump anticavitation properties.

3 cl, 3 dwg

FIELD: shipbuilding, rocketry, aircraft, chemical and other industries.

SUBSTANCE: invention relates to hydraulic machine building and it can be used in industries where stringent requirements to reliability, cavitation, and variable characteristics at minimum mass of construction are placed. Proposed turbopump contains sliding bearings lubricated by handled liquid, axial vortex stage with conical bushing of screw and additional channels with restrictors connecting pressure and intake parts. To reduce overall dimensions and increase reliability, hydraulic balancing device and rear bearing are combined. Pulsations are reduced owing to division of liquid and gas-phase leaks and their removal along separate pipelines. Relief holes are made in turbine disk to reduce axial force at non-standard conditions.

EFFECT: improved reliability and stability of turbopump set within wide range of changes of flow rate of handled liquid, improved cavitation characteristics, reduced weight and overall dimensions.

3 cl, 1 dwg

Up!