Turbine nozzle box of gas-turbine engine |
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IPC classes for russian patent Turbine nozzle box of gas-turbine engine (RU 2260700):
        
 The cooled jet vane of a gas turbine / 2237811
 To allow the apparatus axial turbine / 2232902
The invention relates to low-flow turbines, which are widely used in power industry, shipbuilding
 Supporting and locking means for the nozzles high pressure stage in gas turbines / 2223406
The invention relates to a supporting and locking means for the nozzles high pressure stage in a gas turbine
 System steam supply to the turbine cylinder / 2217598
The invention relates to power engineering and can be used to create a new steam turbine or their modernization
 The stator part of the first stages of the medium pressure cylinder of a steam turbine with reheat / 2176736
 Guide vane stage of a turbine / 2173780
The invention relates to turbidostat and can be used in diaphragms wet steam speed turbines
 Belopotosky to allow the apparatus aircraft gas turbine engine / 2164603
The invention relates to gas turbine engines and can be used in the aviation motors with radial and diagonal turbines and stationary gas turbines
 Turbine nozzle box of gas-turbine engine / 2260700
Proposed nozzle box of turbine of gas-turbine engine has nozzle vanes with trunnions and ring projections. Inner ring with ring groove is fixed on inner flanges of nozzle vanes in which vane ring projection is fitted. One of flanges of inner ring is furnished with axially extended ring bead with radial slot in which trunnion of vane nozzle is arranged. Difference between distance from axis of bolt of fastening flange of inner ring and inner surface of ring projection of nozzle vane and distance between axis of bolt of fastening flange of inner ring and outer machined surface of nozzle vane trunnion is greater than zero.
 Axial-flow turbine stator blade / 2272151
Proposed blades of axial-flow turbine stator has channel expanding into cone to pass flow of gas through turbine. Blade is provided with flat at its root which is connected with stator housing with provision of tight fit and reliable locking of joint. Stator blade root is made in form of hollow profile with radially inner flat of blade root which is made to suit contour of channel to pass flow of gas through turbine and radially outer flat of blade root arranged at a distance inner flat from and made to suit contour of stator housing, and also side wall or two, mainly parallel, side walls. Outer flat is provided with at least one hole to accommodate corresponding attachment part by means of which said is secured on stator housing.
 Device to control position of blades with adjustable angle of setting / 2272913
Proposed device to control position of blades with adjustable angle of setting in turbomachine has tie-rod, mating devices, locking devices and means for holding said tie-rod on said root of blade for combined turning without play. Mating devices forming hinge joint between first end part of tie-rod and rotary ring are provided with pin passing through first through hole made in first end part of tie-rod and getting into radial socket in rotary ring. Said pin is held in position by locking with ports to pass pins and installed for displacement on rotary ring. Locking devices used to hold second end part of tie-rod on root of adjustable blade are provided with locking screw passing through second through hole made in second end part of tie-rod and getting into groove in root of adjustable blade.
 Gas turbine stator / 2278274
Proposed stator of gas turbine has housing with channel to pass gases, ring member arranged around stator housing at a distance in radial direction and functionally coupled with housing, and intermediate members holding ring member at a distance from stator housing in radial direction. Intermediate member are arranged over circumference of ring member at distance from each other and are provided with movable member. Said movable member thrusts against stator housing or ring member with possibility of displacement. At least one of intermediate members features elastic properties in direction of stator radius, and at least one other intermediate member has no such properties.
 Turbine adjustable nozzle assembly / 2294439
Invention can be used in transport gas-turbine engines and turbocompressors of internal combustion engines. Proposed adjustable nozzle assembly of turbine has vanes with turnable axles arranged between housing. Turnable axles are sectional, being made of material with memorized shape effect. Iron and nickel-based alloys are used as memorized shape effect materials in which martensite transformation takes place at different temperatures.
 Steam turbine flow path / 2296228
Invention is aimed at increasing economy of first non-controlled stages of steam turbines with nozzle steam distribution. According to invention flow path of known steam turbine containing nozzle box assembly accommodating nozzle blades, controlled stage working wheel, diaphragm of first non-controlled stage with fitted-in nozzle blades, working wheel and chamber formed between said wheel of controlled stage and diaphragm of first non-controlled stage is furnished with convex-concave screen installed before nozzle assembly of diaphragm provided with perforations, convex part being arranged opposite to nozzle assembly and pointed into chamber, and concave part is extended in radial direction towards rotor axis. Holes of perforation are of different size. Diameter of holes in part far from rotor axis is at least twice as small as diameter of holes located close to rotor axis.
 Steam turbine intake hole and method of its modification / 2302533
Pair of ports of intake hole is arranged at opposite sides of steam turbine casing to provide passing of steam in opposite directions along circumference in ring-shaped steam chamber to first stages of turbine through axial opposite outlet holes. Parts of chamber in upper and lower casings has cross sections decreasing in common direction along circumference from sections of intake hole for steam to provide uniform flow of steam relative to chamber in common inner direction and through axial outlet holes and near holes.
 Nozzle guide assembly of radial-flow turbine / 2306425
Proposed nozzle guide assembly of radial-flow turbine contains nozzle vanes, drive and adjusting device. Nozzle vanes are uniformly spaced around axle of turbine wheel and are installed by trunnions in turbine casing for adjustable turning in channel formed by walls of casing. Adjusting device is made in form of ring turn synchronizer engaging with nozzle vanes through guides secured on their trunnions. Each guide is made in form of bellcrank whose free ends are arranged in radial slots of turn synchronizer. Said turn synchronizer is made in form of two concentric disks, inner and outer ones, interconnected for relative turning, each disk being located by radial slots from free ends of bellcranks pointed to disk.
 Nozzle box assembly for high-temperature cylinder of steam turbine / 2307254
Proposed nozzle box assembly of high-temperature cylinder of steam turbine includes supply section, transient section and section delivering steam to nozzle segments. Nozzle box assembly is made up of sections welded together, supply section is made of pipe, transient section is made in form of cone changing from pipe into oval, and steam dispensing section is made of two rings, outer and inner ones, with blanks on end faces. Proposed invention provides minimum labor input and metal usage in manufacture, reduced to minimum time taken for heating nozzle box assembly owing to use of more thin walls of welded structure and, consequently, reduced time of starting of high-temperature steam turbine.
 Cooled turbine guide blade and turbine having said blades / 2308601
Guide blade of gas turbine engine comprises front and rear edges, pocket, wing back, as well as opened perforated insert, inlet orifice to supply cooling air inside insert and outlet orifice to remove cooling air portion from blade. The insert defines annular cavity arranged between outer side wall thereof and inner blade wall. Blade has bridges located in cavity part between the insert and inner surface of rear edge to increase blade rigidity. One insert end is fixed to blade. Another one is installed so that the insert end may slide along inner edge of blade under the action of mutual thermal insert expansion relatively inner blade wall. Orifices are created in opened insert so that the orifices are located only in two insert areas. Orifices of the first group are opposite to inner surface of front edge. Orifices of the second group are opposite to inner surface of rear edge to prevent air jet impingement upon bridges.
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FIELD: gas-turbine engines. SUBSTANCE: proposed nozzle box of turbine of gas-turbine engine has nozzle vanes with trunnions and ring projections. Inner ring with ring groove is fixed on inner flanges of nozzle vanes in which vane ring projection is fitted. One of flanges of inner ring is furnished with axially extended ring bead with radial slot in which trunnion of vane nozzle is arranged. Difference between distance from axis of bolt of fastening flange of inner ring and inner surface of ring projection of nozzle vane and distance between axis of bolt of fastening flange of inner ring and outer machined surface of nozzle vane trunnion is greater than zero. EFFECT: improved reliability and efficiency of gas-turbine engine owing to provision of high accuracy of manufacture of aligning elements of nozzle box parts. 2 cl, 4 dwg
The invention relates to energy and transport machinery and can be used in the construction of aircraft gas turbine engines and gas turbines applications. A known design of jet turbine apparatus, in which the inner ring nozzle apparatus setentrional on the radial pins of nozzle blades [1]. In this construction to provide thermal expansions between the surface of the annular protrusion, the most remote from the stud on the blade and related surface of the inner ring provides a thermal gap. Therefore, certain non-nominal modes of operation of the engine in the connection between the inner shelf of the vanes and the inner ring will be a flow of gas, passing a portion of the turbine blade. Thus the efficiency of the turbine and the efficiency of the entire unit as a whole will be low. Known also other design nozzle apparatus in which the axial fixing of the inner ring is made by means of two annular projections on the blade in contact on the outer side surfaces with the inner surfaces of the annular grooves made in the inner ring. Radial location of the inner ring is performed by Zapf rectangular shape, the side surfaces which are in contact with the response surface is Rostami on the inner ring [2]. However, the known design has several disadvantages. Because, when the lateral contacting surfaces of the stud on the blade and groove on the inner ring there is no exit for the grinding wheel, the pin on the blade and the groove in the inner ring can be processed only finger-milling, which does not allow for the required precision of the data elements as size and offset from the nominal position in the circumferential direction and significantly worsen the alignment of the inner ring on the nozzle blades. Due to the fact that the shelf blades in working condition always hotter than the inner ring, to ensure mutual expansion in the axial direction between the surfaces of the annular projections on the shelf blades and mating surfaces of the annular grooves on the ring shall be provided for the "heat" of clearance in the axial direction, which can occur in some modes of operation of the engine, which in turn leads to leakage of gas from the flowing part of the engine and reduce its efficiency The technical challenge is to improve the reliability and efficiency of the gas turbine engine by providing a high manufacturing accuracy of the centering parts nozzle apparatus and a reliable seal against flow of gas. The invention of zakluchaetsa, what in the nozzle apparatus of the turbine of the gas turbine engine containing the nozzle blades with pins and annular projections on the inner shelves which are fixed inner ring with an annular groove, in which is mounted the annular protrusion of the scapula, according to the invention one of the flanges of the inner ring fitted made in the axial direction of the annular collar with a radial groove in which is placed a pin to allow the blades, and the difference between the values of L1and L2greater than zero, where L1- the distance from the axis of the bolt mounting flange of the inner ring to the inner surface of the annular protrusion to allow the scapula; L2- the distance from the axis of the bolt mounting flange of the inner ring to the outer machined surface of the axle to allow the scapula. In addition, to simplify and improve the processing accuracy in the manufacture of the bottom surface of the radial groove of the annular collar is made parallel to the plane of attachment of the mounting flange of the inner ring. The implementation of the processed surfaces of the annular protrusion and the outer surface of the axle to allow the blades so that the difference between the values of L1and L2greater than zero, allows you to easily handle them "pass" grinding wheel or other tool to ensure tribemates sizes. If L1-L2is a negative value, it is possible to plunge into the inner surface of the annular protrusion on the blade. Supply of one of the flanges of the inner ring made in the axial direction of the annular collar with a radial groove in which the axial gap posted by axle to allow the blades, allows the contact pin blades only faces that are located in the circumferential direction. This allows to limit the mutual thermal movement of the shelf blades and the inner ring on the pivots of the blades and the seal from flowing gas under the inner shelf in the connection between the annular ledge on the shelf blades and the annular groove of the inner ring. To further improve the processing accuracy of the centering elements of the nozzle parts of the apparatus, the bottom surface of the radial groove of the ring clamp is parallel to the plane of attachment of the mounting flange of the inner ring. Figure 1 shows the inventive design of the nozzle of the apparatus, figure 2 - connection of the inner shelf to the inner ring to allow the blades. Figure 3 shows an axial section of the clamp and axle to allow the shoulder blades, and figure 4 is a radial cross-section of the trunnion of the nozzle vanes of the device. To allow the apparatus includes an outer case 1, the nozzle vanes 2, the inner ring 3. Inside the inner shelf 4 of the blade 2 is provided with trunnion 5, having in cross section a rectangular shape. The annular collar flange 6 of the inner ring 3 is made in the axial direction, it is made of the response of radial grooves 7. On the inner shelf 4 blades 2 are annular projections 8, which engages with mating annular grooves 9. The bottom surface 10 of the radial groove 7 is made parallel to the plane 11 fastening the mounting flange 12 of the inner ring 3. Between the bottom 10 of the radial groove 7 and the centering surface 13 of the trunnion 5 is made of thermal gap Δ1. The outer surface 14 of the trunnion 5 to allow the blade 2 when the Assembly is located at a distance of L2from the axis of the bolt 15 of the mounting flange 12. The inner surface 16 of the annular protrusion 8 of the blade 2 is located at a distance of L1from the axis of the bolt 15 of the mounting flange 12. Between the surface of the side face of the protrusion 8 on the shelf 4 of the blade 2 and the side surfaces of the groove 9 is made clearance Δ2. After Assembly, the mounting gap Δ2is 0.02-0.05 mm and is the minimum possible to ensure the collectability of the structure. In the process of working of gas turbine engine internal shelf 4 of the blade 2 and the inner ring 3 in the axial direction are expanded differently. Since the rectangular contact pins 5 of the blade 2 by the radial surfaces of the groove 7 of the ring clamp osushestvlyaetsya in the circumferential direction, and the gap Δ1greater than the magnitude of the mutual axial movements of the shelf 4 of the blade 2 and the inner ring 3, then these movements are not restricted in the axial direction. When the circumferential alignment of the inner ring 3 on the trunnions 5 of the blade 2 is stored as a seal against the flow of gas under internal shelf 4 in the connection between the annular ledge 8 of the shelf 4 of the blade 2 and the annular groove 9 on the inner ring 3, because the gap Δ2minimum. Sources of information: 1. SAUNO. Construction and design of aircraft gas turbine engines, Moscow, Mashinostroyeniye, 1981, str, RES a, b. 2. SAUNO. Construction and design of aircraft gas turbine engines, Moscow, Mashinostroyeniye, 1981, str, RES, 1. To allow the apparatus of the turbine of the gas turbine engine containing the nozzle blades with pins and annular projections on the inner shelves which are fixed inner ring with an annular groove, in which is mounted the annular protrusion of the blade, wherein one of the flanges of the inner ring fitted made in the axial direction of the annular collar with a radial groove in which is placed a pin to allow the blades, a L1-L2>0, where L1- the distance from the axis of the bolt mounting flange of the inner ring to the inner surface of the ring made the PA to allow the blades; L2- the distance from the axis of the bolt mounting flange of the inner ring to the outer machined surface of the axle to allow the scapula. 2. To allow the apparatus according to claim 1, characterized in that the bottom surface of the radial groove of the annular collar is made parallel to the plane of attachment of the mounting flange of the inner ring.
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