Turbine assembly of turbo-pump unit

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 (0.05÷0.25) 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 8÷15, 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 (24÷45)°. Total number of blades exceeds by 2.6÷34.4 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

 

The invention relates to turboboosting, namely turbine site turbopump unit designed to supply industrial water to the steam boilers and oil products in oil, gas, chemical and petrochemical, metallurgical and other enterprises.

Known turbopump Assembly containing the pump housing, turbine housing, bearing housing of the pump and the turbine, the spring-loaded rotor, the node unloading axial forces and fixed to the housings restrictive stops. Case turbine bearing support rigidly mounted in the intermediate casing. The emphasis in the case of turbine bearings made movable in the axial direction in the form of an elastic element and sleeve with stop axial movement by a bearing (EN 2083860 C1, publ. 10.07.1997).

Known turbopump Assembly containing two turbines installed in the housing with the inlet and exhaust pipes and including a nozzle apparatus and impellers. Both turbines are gas. The impeller of the first turbine installed in the rear cavity of the turbine housing in its Central part. Channel for supplying gas to the second turbine is made inside the outer shaft and reports the cavity inlet branch pipe of the turbine with the cavity before the second turbine. The channel of the exhaust gas is made in the form of an annular slit, connect the sequence of the rear cavity of the turbine with the exhaust gas outlet of the turbine (EN 2418986 C1, publ. 20.01.2011).

Known turbopump Assembly including turbine site with the collector supply of the working fluid with a nozzle device, a rotor with impeller turbine housing outlet spent working fluid, the reference node, the pump Assembly with the impeller and the machine axial unloading. (Waluchow YEAR, Veselov NR. Experimental testing turbopump Assembly TNA 100/580 with mechanical seals on the bearings rolling: Proceedings of the VI international scientific-technical conference "SINT"P", LLC "Voronezh international Conference, UDC(063), ISBN 978-5-904786-98-4, p.42-45).

The disadvantages of the known solutions are increased structural complexity of the turbine sites and the low durability of the unit as a whole.

The present invention is to develop a turbine site, endowed with enhanced life, reliability and efficiency in the turbopump Assembly when applying the pumped liquid from the cold, hot water to oil, oil products to the consumer while reducing material consumption and increasing the compactness and efficiency of the unit by reducing electricity consumption per unit mass of fluid.

The problem is solved in that the turbine site turbopump Assembly according to the invention forms a drive turbopump Assembly and includes the building is with the supply of the working fluid, combined with the nozzle device made in the form of a disk inclined, preferably supersonic nozzles, which are made confused-diffuser, as well as active, at least a single-stage turbine having a shaft with impeller, consisting of at least one disk with blades and interscapular channels, and also located behind the turbine of the vector flow of the working fluid enclosure exhaust of the working fluid, and the housing supply working fluid turbine Assembly is provided with inlet pipe and a collector comprising an axisymmetric ring sealed envelope, at least a large part of which has the form of longitudinally type a truncated fragment of a torus or doughnut, which is tightly connected with the discharge side radially equidistant about the axis of the shaft of the turbine to the nozzle disk apparatus on the outer and inner annular edges, with nozzle nozzle of the device is made in the disk 8÷15 and the longitudinal axes radially equidistant removed from the axis of the turbine, and are separated by an imaginary circle at equal angles in the range (24÷45)°, and the impeller blades of the turbine are made convex-concave width, the radial height of ΔR, component (0,05÷0,25)R, where R is the radius of the disk the impeller of the turbine, and the thickness of the blades 8 adopted variable in the direction of the vector of flow of the working fluid with the maximum δ maxmainly in the middle part of the link width of the blade, and link the width of the blades in the projection conditional on link a plane connecting the input and output side edges of the blades, adopted not greater than the radial height of the blade and the impeller blades of the turbine radially removed from the axis of the turbine shaft is not less than 0,8R, where R is the radius of the disc of the impeller of the turbine, and evenly spaced around the circumference of the disk with a gradient Radiani density G determined in the range .G=(10÷44) [u/rad], where .G - numerical characteristics of the blades placed in the angular range of one radian, and the total number of blades of the impeller of the turbine taken 2.6÷34,4 times the number of nozzles in the nozzle unit.

This interscapular channel impeller can be performed confused-diffuser in the direction of the above-mentioned vector flow of the working fluid with the maximum narrowing of the cross-flow area S defined in the zone of maximum thickness of the blades δmaxfrom the expression

S=ΔR(2πR-Tδmax)/T,

where ΔR is the radial height interscapular channel, T is the number of interscapular channels according to the number of blade disk impeller turbines,

Spatial destruction of the axes of the nozzles may be fixed at the point of intersection of the latter with a nominal plane of the disk nozzle apt the rata, as the radial distance of each of these points from the axis of the turbine shaft made of not less than one third of the radial height of the impeller blades of the turbine radial distance transverse root sections mentioned blades to the turbine shaft.

The longitudinal axis of each nozzle nozzle apparatus may be located in an imaginary plane parallel to the axis of the turbine shaft, is normal to the radius and inclined at the specified plane at an angle to an imaginary plane of the disk nozzle apparatus in a direction opposite to the direction of rotation of the impeller of the turbine at an angle (12÷25)°.

Case exhaust of the working fluid can be made watertight with a beveled annular wall, an opposed output edges interscapular channels of the impeller of the turbine, and is equipped with a predominantly tangential outlet nozzle spent working fluid.

The annular shell collector turbine site can be hermetically attached to the drive nozzle apparatus with the gamut of the input estuaries nozzles on the outer and inner annular edges, preferably by welding.

Case exhaust of the working fluid in the turbine unit may be equipped with mechanical seals to ensure the integrity of structural connectors.

Turbine site turbopump Assembly may be destined acen to work on the energy used as the working fluid vapor or gas.

Turbine site turbopump Assembly variant may be designed for pumping liquids, including, at least, hot, cold, industrial water, oil and products of petroleum cracking with the possibility of creating a working pressure of up to 750 m and the feed rate of the pumped medium from 20 to 1000 m3/h, including at rated rotor speed turbopump Assembly, preferably, 9,85·104(±20%)/min

Technical result achieved is given by a set of signs is the development of the turbine site, endowed with enhanced life, reliability and efficiency of the turbopump Assembly. This is achieved by a set designed in the invention, design and technology solutions for the major part of the turbine site Assembly and parameters of their work, namely, the design of the impeller turbines, nozzles nozzle apparatus with the stated parameters, the shape of the manifold inlet and the housing outlet of the working fluid in the turbine site. Thus the performance of the turbine site turbopump unit in the proposed invention the execution eliminates leakage of the pumped fluid and the working fluid (vapor or gas), as well as significantly reduce the consumption of materials and to increase the compactness and efficiency of the unit as a whole. In addition p is the physical alteration to drive a steam or gas turbine significantly reduces energy consumption.

The invention is illustrated by drawings, where:

figure 1 shows the turbine site turbopump Assembly, longitudinal section;

figure 2 - the impeller blades of the turbine section;

figure 3 - location of the nozzle in the nozzle disk apparatus, a longitudinal section.

Turbine site turbopump Assembly forms the drive of the specified unit. Turbine site includes a housing 1 for supplying the working fluid, combined with the nozzle device 2, as well as active, at least a single-stage turbine and located behind the turbine of the vector flow of the working fluid housing 3 exhaust of the working fluid.

Nozzle apparatus 2 is made in the form of a disk with 4 sloped, preferably supersonic nozzles 5, which are made confused-diffuser. The turbine is provided with a shaft 6 impeller 7, consisting of at least one disk with vanes 8 and located between interscapular channels 9.

The housing 1 for supplying the working fluid turbine Assembly is provided with the inlet pipe 10, the collector 11 and the cover 12. The collector 11 includes an axisymmetric ring sealed envelope, at least a large part of which has the form type longitudinally truncated fragment of a torus or doughnut, which is tightly connected with the discharge side radially equidistant about the axis of the shaft 6 of the turbine to the drive 4, the nozzle is on unit 3 on the outer and inner annular edges 13.

Nozzle 5 nozzle apparatus 2 is a disk 4 of 8÷15 and the longitudinal axes radially equidistant removed from the axis of the turbine, and are separated by an imaginary circle at equal angles in the range (24÷45)°.

The blades 8 of the impeller 7 of the turbine is made convex-concave width, the radial height of ΔR, component (0,05÷0,25)R, where R is the radius of the disc of the impeller 7 of the turbine. The thickness of the blades 8 is adopted for the variable in the direction of flow of the working fluid with the maximum δmaxmainly in the middle part of the link width lopatki. Link width of the blades 8 in the projection conditional on link a plane connecting the input and output side edges of the blades, adopted not greater than the radial height of the blade 8.

The blades 8 of the impeller 7 of the turbine radially removed from the axis of the shaft 6 of the turbine, not less than 0,8R, where R is the radius of the disc of the impeller 7 of the turbine, and evenly spaced around the circumference of the disk with a gradient Radiani density G determined in the range

.G=(10÷44) [u/rad],

where .G - numerical characteristics of the blades placed in the angular range of one radian.

The total number of blades 8 of the impeller 7 of the turbine taken 2.6÷34,4 times the number of nozzles 5 in the nozzle vane 2.

Interscapular channel 9 of the impeller 7 are confused-cone in n the Board of the vector of flow of the working fluid with the maximum narrowing of the cross-bore S, defined in the zone of maximum thickness of the blades δmaxfrom the expression

S=ΔR(2πR-Tδmax)/T,

where ΔR is the radial height interscapular channel, T is the number of interscapular channels according to the number of disk blades of the impeller of the turbine.

Spatial destruction of the axes of the nozzles 5 is fixed at the point of intersection of the latter with a nominal plane of the disk 4 of the nozzle vane 2. The radial distance of each of these points from the axis of the shaft 6 of the turbine taken not less than one-third of the radial height of the blade 8 of the impeller 7 of the turbine radial distance transverse root sections mentioned blades 8 to the shaft 6 of the turbine.

The longitudinal axis of each nozzle 5 nozzle apparatus 5 is located in an imaginary plane parallel to the axis of the shaft 6 of the turbine, is normal to the radius and inclined at the specified plane at an angle to an imaginary plane of the disk 4 of the nozzle vane 2 in the direction opposite to the direction of rotation of the impeller 7 of the turbine at an angle (12÷25)°.

Case 3 exhaust of the working fluid of the turbine site is airtight with a beveled annular wall 14, opposed the output edges interscapular channels 9 of the impeller 7 of the turbine. Case 3 allotment provided mainly tangential inlet 15 of the output of the spent working fluid.

The annular shell collector 11 is Urbanova node hermetically attached to the disk 4 of the nozzle apparatus 2 with the gamut of the input estuaries nozzles 5 to the outer and inner annular edges 13, preferably, by welding.

Case 3 exhaust of the working fluid in the turbine Assembly is provided with end seals 16 to ensure the integrity of structural connectors.

Turbine site turbopump Assembly is designed to work on the energy used as the working fluid vapor or gas.

Turbine site turbopump Assembly variant is designed for pumping liquids, including, at least, hot, cold, industrial water, oil and products of petroleum cracking with the possibility of creating a working pressure of up to 750 m and the feed rate of the pumped medium from 20 to 1000 m3/h, including at rated rotor speed turbopump Assembly, preferably, 9,85·104(±20%)/min

The operation of the turbine site turbopump Assembly is as follows.

Turbine node forms the drive of the turbopump Assembly. The drive unit exercise turbine from an external source that supplies the working fluid or water vapor, or gas.

And turbopump Assembly run after warming up the design of the turbine site, and drain out of the body cavity 3 exhaust of the working fluid.

Open adjustable valve that supplies the working fluid under pressure into the reservoir 11 and twelve nozzles 5 coplow the nd apparatus 2 to the turbine inlet. Dispersing the working body under the differential to supersonic speeds, passing the impeller 7 of the turbine kinetic energy. When the rotor of the turbine enters the rated speed 170-1(10200 rpm).

The unbalanced area of the turbine creates on the rotor axial force in the direction of the pump, which after reaching the rated speed compensates for the machine axial discharge (not shown).

The mechanical seal 16 in the housing cavity 3 exhaust of the working fluid does not pass pumping and cooling them with liquid on one side of the cavity of the turbine to prevent water hammer when the liquid gets into the hot cavity and avoid wetting of the working fluid, leading to erosion of structural elements. On the other hand do not allow the condensate into the cavity reference node 17 turbopump Assembly.

During operation, the rotor is fixed by the speed sensors and vibration sensors. Fixed velocity, which must not exceed allowable values.

Stop turbopump Assembly is carried out, closing the supply valve of the working fluid. The fluid for cooling mechanical seals 16 are served in the cavity of the turbine site to cool the turbine casing.

Thus, due to the developed invention constructive and technological solutions turbine site unit settings raboteg the turbine wheel and nozzle apparatus achieve greater resource and reliability, as well as the efficiency of feed fluid to the consumer while reducing material consumption and increase compactness turbopump node.

1. Turbine site turbopump Assembly, characterized in that it forms the drive turbopump Assembly and includes a housing supply working fluid, combined with the nozzle device made in the form of a disk inclined, preferably supersonic nozzles, which are made confused-diffuser, as well as active, at least a single-stage turbine having a shaft with impeller, consisting of at least one disk with blades and interscapular channels, and also located behind the turbine of the vector flow of the working fluid enclosure exhaust of the working fluid, and the housing supply working fluid turbine Assembly is provided with inlet pipe and a collector comprising an axisymmetric ring sealed envelope, at least a large part of which has the form type longitudinally truncated fragment of a torus or doughnut, which is tightly connected with the discharge side radially equidistant about the axis of the shaft of the turbine to the nozzle disk apparatus on the outer and inner annular edges, with nozzle nozzle of the device is made in the disk 8÷15 and the longitudinal axes radially equidistant from the Alena from the axis of the turbine, and are separated by an imaginary circle at equal angles in the range (24÷45)°, and the impeller blades of the turbine are made convex-concave width, the radial height of ΔR, component (0,05÷0,25)R, where R is the radius of the disc of the impeller of the turbine, and the thickness of the blade δ adopted variable in the direction of flow of the working fluid with the maximum δmaxmainly in the middle part of the link width of the blade, and link the width of the blades in the projection conditional on link a plane connecting the input and output side edges of the blades, adopted not greater than the radial height of the blade and the impeller blades of the turbine radially removed from the axis of the shaft of the turbine, not less than 0,8R, where R is the radius of the disc of the impeller of the turbine, and evenly spaced around the circumference of the disk with a gradient Radiani density G determined in the range .G=(10÷44) [u/rad], where .G - numerical characteristics of the blades, placed in the angular range of one radian, and the total number of blades of the impeller of the turbine taken 2.6÷34,4 times the number of nozzles in the nozzle unit.

2. Turbine site turbopump Assembly according to claim 1, characterized in that the interscapular channel impeller made confused-diffuser in the direction of the above-mentioned vector flow of the working fluid with the maximum narrowing of the space pop the river bore S, defined in the zone of maximum thickness of the blades δmaxfrom the expression
S=ΔR(2πR-Tδmax)/T,
where ΔR is the radial height interscapular channel, T is the number of interscapular channels according to the number of blade disk impeller turbines,

3. Turbine site turbopump Assembly according to claim 1, characterized in that the spatial destruction of the axes of the nozzles are fixed at the points of intersection of the latter with a nominal plane of the disk nozzle apparatus, and the radial distance of each of these points from the axis of the turbine shaft made of not less than one third of the radial height of the impeller blades of the turbine radial distance transverse root sections mentioned blades to the turbine shaft.

4. Turbine site turbopump Assembly according to claim 1, characterized in that the longitudinal axis of each nozzle nozzle apparatus is located in an imaginary plane parallel to the axis of the turbine shaft, is normal to the radius and inclined at the specified plane at an angle to an imaginary plane of the disk nozzle apparatus in a direction opposite to the direction of rotation of the impeller of the turbine at an angle (12÷25)°.

5. Turbine site turbopump Assembly according to claim 1, characterized in that the housing of the exhaust of the working fluid is airtight with a beveled annular wall, an opposed output edges interscapular channels working the second turbine wheel, and provided with a mainly tangential outlet nozzle spent working fluid.

6. Turbine site turbopump Assembly according to claim 1, characterized in that the annular shell collector turbine site is hermetically attached to the drive nozzle apparatus with the gamut of the input estuaries nozzles on the outer and inner annular edges, preferably by welding.

7. Turbine site turbopump Assembly according to claim 1, characterized in that the housing of the exhaust of the working fluid in the turbine Assembly is provided with mechanical seals to ensure the integrity of structural connectors.

8. Turbine site turbopump Assembly according to claim 1, characterized in that it is designed to work on the energy used as the working fluid vapor or gas.

9. Turbine site turbopump Assembly according to claim 1, wherein the variant is designed for pumping liquids, including, at least, hot, cold, industrial water, oil and products of petroleum cracking with the possibility of creating a working pressure of up to 750 m and the feed rate of the pumped medium from 20 to 1000 m3/h, including at rated rotor speed turbopump Assembly, preferably, 9,85·104(±20%) rpm



 

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9 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: turbo-machine includes a stage having blades with a variable setting angle, which are arranged in the housing in a circumferential direction. Each blade includes a control rod radially projecting on the housing outer side and connected by means of a lever to a common control ring coaxial to the above housing and installed with possibility of being rotated on the outside of the housing. Control ring includes two sections fixed with connection side jaws and with an insert on one and the other sides of the above sections at least near ends of the latter. Sections include side grooves into which the above connection jaws are installed.

EFFECT: invention allows increasing control ring stiffness.

9 cl

FIELD: machine building.

SUBSTANCE: gas-turbine engine includes an annular combustion chamber, a sectoral turbine nozzle guide vanes located at the chamber outlet and sealing devices axially arranged between combustion chamber and nozzle guide vanes. Sealing devices include a circumferential seal with axial elasticity, which includes axial support devices on exit edge of the combustion chamber and exit circumferential edge that is of sectoral type. Each sector of exit edge is arranged in one line with sector of nozzle guide vanes and includes axial support devices on entry edge of the sector of the nozzle guide vanes. The other invention of the group refers to a seal packing for the above gas-turbine engine, which is made as a single part and contains two circumferential edges. One of the edges has radial slots setting the sectors between themselves, which has the possibility of free movement irrespective of each other.

EFFECT: inventions allow improving tightness between a combustion chamber and nozzle guide vanes and simplifying installation of sealing devices.

15 cl, 10 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine transition compartment comprises first and second ends and housing extending there between. Said housing comprises inner and outer surfaces and turbulence promoter. Turbulence promoter extends continuously in spiral and make an integral structure over the entire outer surface. It features semicircular cross-section and is configured so that first part of air flow descends in spiral around transition compartment while second part is forced over spiral turbulence promoter to facilitate cooling of said compartment. Besides, this invention covers the gas turbine engine comprising combustion chamber unit and transition compartment described above and attached to combustion chamber to extend therefore.

EFFECT: higher engine efficiency and longer life.

10 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: guide stage of a gas-turbine engine compressor includes a row of blades with a variable setting angle. Each blade includes a bucket, an external cylindrical trunnion being a blade rotation axis and entering a seat of an external casing, and an internal cylindrical trunnion installed in a mounting place of the inner ring. The internal trunnion of each blade is arranged parallel to the blade rotation axis and at some distance from that axis and installed in the mounting seat of the ring by means of a ball hinge system. The hinge system includes a ball coupling put on the blade internal trunnion and installed into the ring mounting place. Ball coupling includes an internal element installed with possibility of axial shift to the side on the blade internal trunnion, and an external element entering the ring mounting seat. External element includes an external circular projection meant for arrangement between a radially internal end of the blade bucket and the annular projection of the inner ring.

EFFECT: invention allows providing the possibility of axial movement of an inner ring for control of a labyrinth seal located on it.

6 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: proposed module comprises low-pressure and high-pressure compressors with their shafts running in bearings, and radial pipes of inner chamber supercharging. Shafts are separated from inner chamber by labyrinth seals fitted on seal disc. Said disc is fitted at reducing housing. Supercharge pipe communicate said chamber with compressed air line extending through reducing housing. Pipe ends are tightly fitted in reducing housing radial pipelines and radial guides of deal disc bushes. Pipe ends can be locked in said radial pipes. Seal disc guide bushes feature radial size sufficient for said ends to displace between working position whereat radial outer ends are tightly fitted in reducing housing pipelines and mounting position whereat said radial ends extend from reducing housing pipelines. Another invention of the set covers above described inner chamber disc with guide bush radial ends are tapered. One more invention of this set covers turbo machine with above described compressor.

EFFECT: simple and easier mounting of supercharge pipes.

9 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: proposed device comprises control lever, pin and two free spherical plain bearings. Upper end of said pin is engaged with control lever while lower end is connected with vane. First free spherical plain bearing is fitted on pin lower end while second one is arranged on pin upper end. Free spherical plain bearing comprises inner and outer racers to make one ball joint. Inner racer and pin interlocked. Another invention of this set covers stator comprising case, aforesaid control devices and vanes arranged in said case. Every vane is rigidly secured to pin while aforesaid bearings are fitted in case bore. Other inventions of the set relate to compressor with said stator and gas turbine engine with said compressor.

EFFECT: longer life.

10 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: outlet casing of gas turbine engine includes two coaxial internal and external cylindrical walls connected by means of radial posts, and a cylindrical casing. Cylindrical casing is connected to rear end of radially internal wall and restricts the hub cavity together with radially internal wall and waste gas passage space together with radially external wall. Cylindrical casing is provided on its front end with a radial annular part directed inside the gas turbine engine. Radial annular part of the casing is provided on its inner end with an annular shoulder interacting due to tight radial sliding with internal cylindrical wall of the outlet casing. The other invention of the group refers to cylindrical casing for the above outlet casing, which is provided on one of its ends with an annular flange, and on the other one with a radial annular part that is directed inwards. Radial annular part is provided on its inner end with a radial annular shoulder having a cylindrical collar. One more invention of the group refers to gas turbine engine containing the above outlet casing.

EFFECT: inventions allow increasing service life of radial posts of gas turbine engine.

10 cl, 4 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 0.05÷0.25 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 2.6÷34.4 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

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