The method for compressing gases
(57) Abstract:The compression method in the radial centripetal the turbomachine occurs through centripetal rotation of the gas streams around the axis of the turbomachine in the opposite direction and education on the exit of a cylindrical vortex. The compression is carried out in a long, tapering, curved channels, in which the length and width of the channel is significantly larger than its height. Cylindrical vortex at the output goes into a tapering along the axis of the cone. The invention increases the compression ratio and efficiency. 1 Il. The invention relates to the field of mechanical engineering. There is a method of compressing gas using radial centripetal turbine (see A. M. Borysenko "Gas dynamics engine", page 151, Fig.9.1.3. g) 1962).The disadvantages of this method are:
1) the volumetric loss and return of contamination due to the high gradients of velocity and pressure in the cross sections of the channels and the clearances between the casing and the turbine, to fix that with this method of compression is impossible, because the channels extend in the direction of reducing the radius of rotation, which in turn does not allow you to lengthen the channels for the purpose of alignment of velocity and pressure on the tee.2) Large size, weight and complexity of geometric shapes stationary casing compared to the diameter of the rotating turbine is the main element of compression.Object of the invention is:
1) increasing the compression ratio and efficiency.2) reducing the weight, size and cost of manufacture.The problem is solved due to the fact that (see drawing) long AB>>h1, B>>h1, tapering h1>h2 and curvilinear channels revolve around a fixed point "O", and the flow of gas moving in the channels from a to B, while rotating in the opposite channels direction around the same point "O" with a gradually decreasing radius from "R" point a to g at the point B and the transition into a cylindrical vortex at the exit of the channels, which in turn moves along the axis of rotation in one or two opposite directions in cone bushings with decreasing cross-sectional area towards the exit of the vortex.Structurally, the channels formed between the curved guides 2 and the side disks 1, the latter is connected with the tapered bushing 3. Thus, the disk 1, the guides 2 and sleeve 3 fixed relative to each other and rotate together. Around the path of rotation can be located R is audacia channels.The invention has the following new benefits:
1) the Length and shape of the channels eliminate almost completely the gradients of velocity and pressure in the cross sections. There are no gaps, because there is no stationary casing, therefore, no harmful vortices and backward contamination.2) In the compression process included new factor that increases the amount of flow of gas is inversely proportional to the decreasing of the radius of rotation of the flow around a stationary axis in accordance with theorem of the constancy of angular momentum. Thus, the invention achieves greater compression efficiency and reduce the weight, size and complexity of the manufacturing process. The compression method in the radial centripetal the turbomachine by the inward rotation of the gas streams around the axis of the turbomachine in the opposite direction and education on the exit of the cylindrical vortex, characterized in that the compression is carried out in a long, tapering, curved channels, in which the length and width of the channel is significantly larger than its height, and a cylindrical vortex at the output goes into a tapering along the axis of the cone.
SUBSTANCE: proposed method includes suction of air from upper surface of wing by means of impeller of centripetal fan and directing this air flow under lower surface of wing with the aid of centrifugal fan impeller. Air flow formed in radial direction relative to annular wing having asymmetric profile creates lifting force due to difference in pressures on lower and upper surfaces of wing.
EFFECT: enhanced efficiency of creating lifting force.
2 cl, 1 dwg
FIELD: machine building.
SUBSTANCE: compressor unit (1) comprises a compressor (5), a suction line (2) and a return line (3), a block (20) that controls the compressor (5). Moreover, in line (2) the suction is ensured by at least one device (21, 22) to detect amounts of non-gaseous fluid medium in the fluid to be compressed, on their way to the entrance to compressor (5), and detection device (21, 22) is connected to management block (20) ensuring signal transmission, and compressor unit (1) contains dissolution unit (30), which dissolves the amount of non-gas on its way to the entrance of compressor (5), while the dissolution is initiated when the amount of detected non-gaseous fluid exceeds a certain limit.
EFFECT: any damage caused by a number of non-gaseous fluid into the suction inlet to the compressor is excluded.
7 cl, 1 dwg
SUBSTANCE: invention relates to a centripetal delivery compressor for the ventilation system, comprising: a casing, an air inlet in the casing, an air outlet in the casing, an impeller, and a blade drive, at that the layer of centrifugal blades and the layer of centripetal blades are arranged on the inner side of the impeller, the layer of the centrifugal blades and the layer of centripetal blades are staggered at intervals in the axial direction. The centrifugal blades form a centrifugal channel, and the centripetal blades form a centripetal channel. The guide walls for protection of the impeller edges from the air flow are arranged on the outer sides of the centrifugal channel and the centripetal channel, and the reverse channels of the impeller edge are arranged between the guide walls for protection of the impeller edge from the air flow and the centrifugal blades and between the guide walls for protection of the impeller edge from the air flow and the centripetal blades.
EFFECT: obtaining a compressor of simple design, high efficiency, and a wide range of applications, energy saving.
10 cl, 17 dwg
FIELD: machine engineering.
SUBSTANCE: rotor of the supersonic compressor and a method for compressing fluid are disclosed. The rotor comprises first and second rotor discs, a first set and a second set of rotor blades. The first set and the second set of rotor blades are connected to the first and second rotor discs and arranged therebetween. In addition, the first set of rotor blades is offset from the second set of rotor blades. The rotor comprises a first set of flow passages defined by the first set of rotor blades located between the first and second rotor discs. Similarly, the rotor comprises a second set of flow passages defined by the second set of rotor blades located between the first and second rotor discs. In addition, the rotor has an inclined compression section located on the rotor blade surface opposite to the surface of adjacent rotor blade.
EFFECT: increased efficiency.
20 cl, 8 dwg
FIELD: manufacture of compressors, namely of low-capacity high-pressure centrifugal compressors.
SUBSTANCE: centrifugal compressors includes housing 1 in which rotor 2 with impellers 3, diaphragms 4,5 and built-up diaphragms 6 - 11 are mounted. Impellers 3, diffusers 12, rotary elbows 14 b reverse guiding apparatuses 13 form stage 15. Heat insulation members 16 - 21 whose thickness increases from first to last stage are built in built-up diaphragms 6 - 11. Invention provides enhanced polytropic efficiency of centrifugal compressor due to lowered inner heat fluxes between stages of flow-through portion.
EFFECT: enhanced efficiency.
FIELD: designs of centrifugal pumps.
SUBSTANCE: welded impeller of centrifugal pump includes driving and covering discs between which blades are arranged. Along outer edges of blades there are spines whose length exceeds by 3 - 5 times thickness value of blades. Said spines are spaced one form another by distance multiple to 1 -1.3 length values of them. Driving and covering discs have through openings in which blade spines are arranged with gaps along width and along length. At outer side of discs along contour openings are chamfered for welded seams. Spines of blades are rectangular, their height exceeds by 1 - 2 mm thickness of disc wall and they are arranged in openings with gaps 0.1 - 0.15 along width and along length. Chamfers along contour of openings consist 0.3 - 0.5 of blade thickness value. Spines of blades assembled with discs are welded around by means of electric arc welding. Inlet portion of blade is tapered along radiuses of cone generatrix.
EFFECT: small-cost effective pump impeller, possibly with increased maximum diameter.
4 cl, 4 dwg
FIELD: mechanical engineering.
SUBSTANCE: invention relates to design of blades of axial-flow fans which can be used for cooling automobile engines. Proposed blade of axial-flow fan contains convex leading edge, concave trailing edge, root part and upper edge. Angles of inclination of straight lines, connecting edges of root part, middle part and upper edge, to plane of rotation of blade are 2.5:1.6:1. Use of proposed invention in design of axial-flow fan increases its capacity and efficiency of delivering of air mass and reduces intensity of vorticity and noise level.
EFFECT: increased capacity, improved efficiency of blowing.
FIELD: mechanical engineering; testing facilities.
SUBSTANCE: invention can be used for stand tests of pumps of any application. According to proposed method full pressure at pump input is maintained constant by means of reservoir with free surface of liquid exposed to constant (atmospheric) pressure installed in intake pipeline. Working liquid saturated vapor pressure at pump input is changed by heating. Periodical measurement of required parameters in process of liquid heating makes it possible to calculate sought for cavitation margin Δh. Method is implemented by test stand containing pump to be tested, output throttle, flow meter, heat exchanger, service tank, pipe fittings, all arranged in closed hydraulic circuit, and reservoir with free surface of working liquid in combination with capsule made of heat conducting material connected to circuit at pump input. Space of capsule is divided into two parts, one of which is partly filled with working liquid and sealed, and other communicates with circuit.
EFFECT: improved accuracy of measurements and simplified determination of pump cavitation characteristics.
3 cl, 1 dwg
FIELD: slotted seals for centrifugal screw pumps of turbo-pumping units of liquid-propellant rocket engines.
SUBSTANCE: proposed centrifugal screw pump has housing 1, inlet branch pipe 2, centrifugal impeller 3, screw 11, floating rings 6 and front sealing bead 4 of impeller 3. Bead 4 of impeller 3 is provided with additional slotted seal behind main slotted seal 7. Additional cavity hydraulically communicated with inlet of branch pipe 2 by means of pipe line 10 is made between slotted seals in inlet branch pipe 2 at level of main slotted seal. Such construction of slotted seal excludes penetration of hot jet from under slotted seal to cavity between screw II and centrifugal impeller 3, thus excluding harmful effect of this jet on physical properties of liquid and on curve of velocities at inlet of centrifugal impeller 3. This effect is clearly defined for cryogenic fluids.
EFFECT: increased cavitation and power characteristics of pump.
FIELD: centrifugal fire pumps.
SUBSTANCE: proposed pump has housing 1 with passages A, blade-type guiding apparatus 13-16, circular chamber B at outlet of last stage and at least two impellers secured on shaft 5. Shaft 5 is mounted in housing on two supports. One support is located on side of pump drive and is isolated from liquid being delivered and second support is brought in contact with liquid being delivered; it is made in form of sliding bearing consisting of races 7 and 8. Sliding bearing is so mounted that it divides impellers in two groups. Located on one side are impellers 9 and 10 of first group which are secured as cantilever on shaft 5 and their inlet funnels are oriented towards inlet hole of pump. Located on other side near sliding bearing is impeller 12 of second group whose inlet funnel is oriented to opposite direction relative to impellers 9 and 10; this is impeller of last stage of pump. Impellers 11 and 12 of second group are located between supports. Chamber B is located in one cross-section with sliding bearing between two guiding apparatus 14 and 16. Guiding apparatus 16 is provided with sliding bearing which performs function of slotted seal between stages located near it.
EFFECT: improved dimensional and mass characteristics; enhanced reliability.
FIELD: engine engineering.
SUBSTANCE: thrust bearing comprises disk with three working areas uniformly arranged over periphery and two bearing washers between which a disk is mounted. The areas are provided with flat projections and hollows. The wall of the flat hollow of each area has the shape of hyperbola in the longitudinal direction. There is a port for supplying oil at the center of the flat hollow. The depth of the flat hollow does not exceed the width of the clearance between the projection of the working area and face surface of the bearing washer.
EFFECT: decreased mechanical losses.