Device for sampling air by means of a centripetal flow
The invention relates to azotobacteria and involves the installation of air sampling using centripetal currents provided between the two discs of the compressor of the gas turbine engine. The device comprises an annular bracket mounted on one side of one of the disks, and many tubes air sampling mounted essentially in the radial direction in the holes formed in the bracket. Each tube is equipped with means designed to reduce vibration of the tube during operation of this gas turbine engine. These tools are designed to reduce vibration tube air sampling, contain a shock-absorbing tube is held in the circular hole of the bracket and covering the outside in the radial direction of the part of the tube air sampling. The inner radial end of the shock absorbing tube compresses the appropriate zone tube air sampling, and the annular space provided between the average area of this shock tube and tube air sampling. The invention reduces the dynamic tension in the tube air sampling by dissipation of mechanical energy of deformation. 3 C.p. f-crystals, 7 Il. gas turbine engine.More specifically, the invention concerns a device for the selection of air by means of a centripetal flow provided between the two discs of the compressor of the gas turbine engine, and this device comprises an annular bracket mounted on one side of one of the disks, and many tubes air sampling mounted essentially radially into the holes formed in the annular bracket, and each such tube air sampling equipped with means designed to reduce vibration of the tube during operation of this gas turbine engine.A similar device is described in patent US 5472313. Shock-absorbing tube is inserted into the inner cavity of the inner radial direction of each tube air sampling. This shock-absorbing tube is in its outer in the radial direction of the longitudinal slit so as to form axial lugs or lobes, which under the action of centrifugal force during operation of this gas turbine engine, pressed against the inner wall of the tube air sampling. The friction between these tabs or petals shock absorbing tube and the outer tube selection ostrognai tube.At the end of these longitudinal cracks, which are areas of concentration of mechanical stresses, are through holes. This requires additional mechanical processing, and lifetime of these internal shock-absorbing tubes is less than 100,000 cycles.Harmonic frequency 1F vibrational movement of the tube centripetal air bleed from the 6-speed compressor of the gas turbine engine type GE 90-115B is 950 Hz.Because this gas turbine engine contains 12 tubes air sampling, harmonic frequency 8F oscillatory movement during operation of the engine at the level 7125 rpm is 950 Hz (71258/60). This frequency is equal to the harmonic frequency 1F.The first task of the invention is to reduce the dynamic stresses in the tube air sampling by dissipation of mechanical energy of deformation.The second objective of this invention is to provide a device for the selection of air by means of a centripetal flow in which the system vibrations tubes air sampling allows a substantial increase of the frequency of the so-called first harmonic oscillations of Ishi the p> The task is solved in accordance with the invention that the means for reducing vibration of the tube air sampling contain a shock-absorbing tube is held in the circular hole of the bracket and covering the outside in the radial direction of the corresponding tube air sampling, with the inner radial direction of the end of this shock tube compresses the appropriate zone tube air sampling, and a free annular space is provided between the average area of the shock absorbing tube and this tube air sampling.Thus, amortization of this centripetal system air sampling is implemented on the basis of two principles. Existing flexibility at the level of the mechanical contact between the outer impact absorbing tube and the tube air sampling operates on the principle of a spring. Available rigidity at the level of this mechanical contact for the dissipation of energy, as it is in the spring. In addition, this outer shock absorbing tube may be subjected to bending. The stiffness of the shock absorbing tube bending allows to provide energy dissipation.The proposed device allows reducing the s of the first harmonic vibrational motions of bending, or the so-called harmonic 1F, due to the increase of the equivalent rigidity of this system air sampling.In addition, as proposed here, the outer shock-absorbing tube does not contain cracks and through-holes formed at the ends of these slits, its manufacture is simpler than machining the inner damping tube with petals.In accordance with a first variant implementation of the invention the inner radial end of the shock tube is objitem and is in mechanical contact with the peripheral wall of the tube air sampling along the axial many areas.In accordance with a second embodiment of the proposed invention the tube air sampling provides, against the inner radial direction of the end of the shock tube, a circular protrusion adapted to this end. Mostly this circular ledge is a few flat parts in order to reduce the surface area of contact.Other characteristics and advantages of the invention will be better understood from the following description of examples of implementation, where reference is made to when the compressor of the gas turbine engine, which illustrates the location of the it device selection of air by means of a centripetal flow in accordance with the invention; - Fig.2 is a schematic view illustrating in an enlarged scale and in axial section of a device in accordance with the invention; - Fig. 3 is a schematic view in axial section along the plane passing through the axis of the tube air sampling device in accordance with the first method of implementation of the invention; - Fig. 4 is a schematic view in section along the line IV-IV shown in Fig.3; - Fig. 5 is a schematic perspective view of the ring holder and the outer shock tube; - Fig. 6 is a schematic view showing an embodiment of the tube air sampling; - Fig.7 is a schematic view in section along the line VII-VII shown in Fig.6.In Fig.1 shows schematically the rotor of the high-pressure compressor 1 of a gas turbine engine having a longitudinal axis X, which contains several stages of moving blades 2 mounted on the periphery of the disk 3. Two consecutive drive this comp is the ability for interaction with the inner ends of the crowns of the stationary guide vanes of the stator of the compressor. These crowns stationary vanes, not shown in Fig.1, is inserted between the rows of moving blades 2.The air sampling is carried out between the two speed drive. Selected air is used for cooling high-pressure turbine, which drives the high-pressure compressor 1.As can be seen in Fig.2, the circular shell 4 linking the disks 3A and 3b, and back flow from the inner ends of the stationary guide blades 6, which are located between the crown of the blades 2A of the disk 3A and the crown of blades 2b of the disk 3b, holes 5.The air taken through the holes 5, enters the annular space 1, limited located against each other by the sides of the disks 3A and 3b.Located behind the flow disk 3b contains in its inner region of the annular projection 8 having L-shaped cross-section, on which by means of bolts 9 is fixed ring 10, having an axis X that hosts many tubes air sampling 11, which are located essentially in the radial direction.As is schematically illustrated in Fig.5, the ring 10 includes a front radial wall 12 and the rear radial wall 13 connected between sobi 16. The rear radial wall 13 includes openings 17, intended for placement of bolts 9, and the annular protrusion 18, which is designed for insertion under the circular protrusion 8 in order to ensure the proper radial positioning of the ring 10. With the front radial wall 12 also includes an annular projection 19, which is located in the immediate vicinity of the corresponding annular protrusion 19a provided on the disk 3A and shown in Fig.2.As can be seen in Fig.3, the outer radial portion of the tube to the bleed air 11 is placed inside the outer shock-absorbing tubes 20. This outer shock absorbing tube 20 has at its inner radial end of the rectangular base 21, which rests on the inner surface of wall 14 of the ring 10 and overlaps, at least partially rectangular cut-outs 16. Outside in the radial direction of the portion 22 of the outer tube 20 has an outer diameter essentially equal to the diameter of the hole 15 made in the partition 14 of the ring 10, so that this part 22 can be clamped is inserted in the hole 15. In the case when all the outer tube 20 is installed in otgbk bleed air 11 is in its outer radial part of the thickening 23, which is in thrust contact with the inner radial end of the outer tube 20. The thickening 23 continues from the inside out from the inside in the radial direction of the portion 22 of the outer tube 20 in a circular protrusion 24, the outer diameter which is essentially equal to the inner diameter part 22, so that the circular protrusion 24 has been squeezed in this part 22. Position 25 marked ring locking of the outer tube 20 and tube air sampling 11 on the ring 10. Ring lock 25 has an inverted T-shaped cross-section, the wings of which are based on the inside in the radial direction of the end surface of the front radial wall 12 of the ring 10 and tubes air sampling 11 and the wall which is located between the rear surface of the front radial wall 12 and the thickening 23 tubes air sampling 11. Wings ring 25 may be different from each other in length and thickness in the radial direction in order to provide the ability to reliably predictable installation, i.e. installation, provided always in the same direction.Outside in the radial direction of the end 26 of the outer tube 20 is in mechanical contact with a corresponding area of 27 tubes air sampling 11.Fig.3 and 4, the end 26 is made objitem and contains a number of axial zones 28 in contact compression formed by the outer wall of the zone 27. These axial zone 28 made, for example, by compression of the end 26 of the outer tube 20 by means of the jaws of the vise. In Fig.4 schematically presents which four pairs of diametrically opposite axial zone 28, however, the number of axial zones 28 may be different from four.In Fig. 6 and 7 schematically shows a second method of implementation of mechanical contact between the end 26 of the outer tube and the area 27 of the tube air sampling 11. In this case, the area 27 includes a circular thickening 29, representing many flat sections 30. The outer diameter of the circular protrusion 29 is essentially equal to the inner diameter of the end 26 of the outer tube 20 to provide a positive mechanical contact between the two tubes 20 and 11 against the circular protrusion 29.Regardless of the implementation method of mechanical contact between the outer in the radial direction of the end 26 of the outer shock tube 20 and tube air sampling 11 average area 31 of the outer tube 20 is not in mechanical contact with the tube air sampling 11 and separated from the tube annular chamber 32.T and end in the outer tube 20 and is held with a certain degree of flexibility, inside in the radial direction of the end 26 of the outer tube 20. This outer tube 20 operates in this place like a spring, and the existing level of this mechanical contact stiffness provides the dissipation of mechanical energy by type of spring.Due to the presence of the annular chamber 32 of the outer tube 20 is also subjected to vibratory forces bending moments. The bending stiffness of this outer tube 20 also allows for the dissipation of mechanical energy. Due to the increase of the equivalent stiffness of the system, consisting of two tubes 20 and 11, compared with the current level of technology in this field, defined by the patent document US 5472313, the frequency of the first harmonic oscillatory motion of bending, or the so-called harmonic 1F, increases substantially.Thus, the use of damping system with external damping tube 20 leads to an increase in frequency harmonics 1F 6-stage high-pressure compressor of the gas turbine engine type GE 90-115B from 950 Hz to 1653 Hz for the length of the tube 20, the component to 58.1 mm, and from 950 Hz to 1921 Hz for the length of the tube 20 constituting 45 mm cross between a harmonica 1F and Monica 8F in the case of the high pressure compressor of the gas turbine engine type GE 90-115B, is 1505 Hz.
Claims1. Device selection of air by means of a centripetal flow provided between the two discs (3A, 3b) of the compressor (1) gas turbine engine containing ring bracket (10) mounted on one side of one of the disks (3A, 3b), and many tubes air sampling (11) mounted essentially in the radial direction in the holes (15) made in the bracket (10) with each tube (11) is equipped with means designed to reduce vibration of the tube (11) in the operation of this gas turbine engine, characterized in that the means intended to reduce the vibration tube air sampling (11) contain a shock absorbing tube (20), held in the hole (15) of the annular bracket (10) and covering the outside in the radial direction of this tube air sampling (11), with the inner radial end (26) of the shock absorbing tube (20) compresses the appropriate zone (27) tube air sampling (11), and the annular space (32) provided between the average area (31) of the shock absorbing tube (20) and tube air sampling (11).2. The device according to p. 1, otlichayetsa in mechanical contact with the peripheral wall of the tube air sampling (11) along the axial many areas (28).3. The device under item 1, characterized in that the tube air sampling (11) provides against the inner radial direction of the end (26) shock tube (20) circular protrusion (29) adapted to this end (26).4. The device according to p. 3, characterized in that the circular protrusion (29) contains many flat areas (30).
FIELD: road and flying vehicles.
SUBSTANCE: according to invention, engine contains housing, reciprocating pistons, timing mechanism, fuel, lubrication, cooling and engine starting systems. Housing accommodates rotating cylinder with two double-acting pistons forming three working spaces with end face heads. Piston delivers air from one extreme space, in turn, into two independent combustion chambers operating according to four-stroke cycle. Gas flow coming out of combustion chambers rotates turbine and rotating cylinder on which turbine is installed. On middle part of pistons sinusoidal spherical links are made into which ball pins secured in rotating cylinder get and set pistons in reciprocating motion. Piston sucks air into other extreme space of rotating cylinder and compresses the air after which compressed air escapes outside creating impulse of reactive thrust. Vacuum is built in space between pistons moving from each other. Vacuum is transmitted by vacuum channels to spherical bowl made outside engine housing, thus creating impulse of reactive thrust, and space between pistons is filled with air. With pistons moving to each other, air in space between pistons is compressed. At end of compression, ports in rotating cylinder open, and compressed air rushes into divergent channels and nozzle, thus creating reactive thrust.
EFFECT: provision of no-pollution jet engine capable of operating on any fuel.
7 cl, 2 dwg
FIELD: engines and pumps, electrical engineering.
SUBSTANCE: gas turbine unit designed to produce electric power, compressed air and to drive various equipment represents two functional modules, i.e. compressed air generator module representing auxiliary gas turbine engine and turbo drive module incorporating auxiliary systems connected by compressed air control system composed so as to carry out a discrete or a smooth compressed air distribution between outer loads, or between an outer load or an outer circuit and the turbo drive module.
EFFECT: production of electric power and compressed air, driving mechanical hardware.
7 cl, 2 dwg
FIELD: engines and pumps.
SUBSTANCE: multi-purpose gas turbine power plant is made in the form of two functional modules: compressed air generator module made in the form of an auxiliary gas turbine engine, and steam turbine generator module, with auxiliary module systems connected by means of controlled compressed air distribution station. The latter is made so that discrete or smooth distribution of compressed air can be performed between external consumer or external network and steam turbine generator module. Steam turbine generator module is made in the form of steam-air turbine and generator with kinematic connection between them, and consists of heat-recovery boiler and mixing chamber. Superheated steam is generated in heat-recovery boiler, and superheated steam from heat-recovery boiler is mixed with compressed air in the mixing chamber. Steam-air mixture from the mixing chamber is supplied to steam-air turbine. The installation can also include contact water vapour condenser, cooler and water service tank, controlled steam-air mixture extraction station located between the mixing chamber and steam-air turbine. Functional modules of compressed air generator and turbine generator with auxiliary module systems can be installed on individual underframes.
EFFECT: multifunctional performance and flexibility of choosing operating modes, increasing life time of steam turbine generator module and improving environmental characteristic of multi-purpose gas turbine power plant.
6 cl, 2 dwg
FIELD: machine building.
SUBSTANCE: invention refers to control of gas compressor units during gas transportation. Specified rotor speed values of injectors are determined as per ratio in the range of allowable values of load change of each gas compressor unit considering the limitation of maximum allowable load difference between neighbouring gas compressor units. Arbitrary load ratio specified by the operator is included in calculation, or load ratio corresponding to minimum fuel gas consumption is calculated as per optimisation method. Optimisation method of multidimensional models is applied at limitations for calculation of optimum load ratio. Search of optimum load ratio of injectors is performed within the whole range of allowable frequency values of injectors by considering limitations of maximum possible difference between loads of injectors. In the calculation the change in fuel gas consumed with the unit relates to change of energies of thermal interaction, mechanical interaction and gas dynamic interaction of working media in turbine according to energy saving principle. Change in the above four types of energy by means of mathematical models is expressed through the change in parameters measured in automatic control system of gas compressor units. As per the measured data and model relations there built are the main models of energy interaction in gas compressor units in current modes and a number of possible modes of various rotation frequencies of gas compressor units. As per model of energy interaction there calculated are values of volume and commercial efficiency of gas compressor unit, which correspond to those modes, as well as fuel gas consumption. Obtained sets of values are included in static relations. The latter and limitations are processed by applying optimisation calculation method, at operation of which there calculated are assignments of rotation frequencies of injectors by means of non-linear programming method, assignments of frequencies are supplied to control system of gas compressor unit as control action. Maximum allowable working limits of each individual gas compressor unit are calculated continuously as per functional relations, and creation of model relations of energy balance for optimisation calculation is performed momentarily for optimisation calculation.
EFFECT: enlarging the possibility of load distribution at a shop, and application of optimisation method in the whole operating range of gas compressor unit.