Axial turbine machine stator blades retaining ring and axial turbomachine

FIELD: turbo-machines.

SUBSTANCE: group of inventions relates to axial turbine machine low pressure compressor stator. Stator comprises circular row of stator blades 26, having radial ends, passing through inner casing 28 holes 36, and containing radial fixing slots 38. Slots 38 have conicity formed by hooks 44. Stator comprises ring 30 for fixation of blades 26 on casing 28. Ring 30 is bent along circumference for its installation in fixing slots 38 and has shape of strip with arc-shaped lateral cross-section, which is in contact with cones and rests against them so, that ring 30 was retained inside slots 38. Casing 28 comprises abraded material 32 circular layer, which surrounds ring so, that to block ring 30 arched shape curvature in order to prevent disengagement of its contact with slots 38 cones.

EFFECT: group of inventions is aimed at improvement of fixation between blade and ring with arc-shaped lateral cross-section in axial turbomachine, as well as at increasing of stator with blades service life.

24 cl, 4 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises distributor segment revolution locking device arranged inside engine circular case and heat insulation sheet fitted between case inner wall and distributor segment outer wall. Revolution locking device comprises locking pin fitted simultaneously in recess made in distributor segment and in case seat. Heat insulation sheet includes lug resting on locking pin. Locking device comprises surface section arranged radially between said lug and said case inner wall to make the thrust at possible radial shift of said heat insulation sheet in operation of gas turbine engine. Another invention of this set relates to versions of locking pin used in this gas turbine engine. In compliance with one version, said locking pin comprises straight rod and heat with first side parallel with rod axis and surface section perpendicular to said first side arranged opposite said rod. In compliance with the other version, this pin includes extra lug perpendicular to straight rod axis. Note here that surface section perpendicular to first side is composed said lug.

EFFECT: lower case wear owing to ruled out contact with heat-protection sheet.

9 cl, 6 dwg

Axial gas turbine // 2543101

FIELD: machine building.

SUBSTANCE: gas turbine comprises a rotor with alternating rows of air cooled working blades and rotor heat shields and a stator with alternating rows of air cooled guide blades and stator heat shields which are installed in the guide blade holder. The stator encloses the rotor from outside so that a hot gas path is formed between them and the working blade rows and heat shields of the rotor and guide blade rows and heat shields of the stator are set opposite each other respectively. A row of guide blade and the next row of working blades in the flow downstream direction form a turbine stage. Each working blade of a turbine stage is fitted by a tip at its end. Each guide blade of a turbine stage is fitted by an external platform of the guide blade. The external platforms of guide blades in the turbine stage and the adjacent heat shields of the stator are matched to each other due to the fact that every external guide blade platform is fitted by a projection on its back wall in the downstream direction. The projection passes downstream to the front edge of the working blade tip and into the respective recess made in the adjacent heat shield of the stator. The stator heat shields in the turbine stage are cooled by the introduction of cooling air into the cavity located at the back of each stator heat shield. The cooling air enters the hot gas path through the holes in the side surface of the stator heat shield passing upstream and downstream. The cavity for the cooling air to enter through the hole is located at the back of the external platform of every guide blade in the turbine stage. The cooling air jets are delivered to the working blade tips from the cavity by means of the holes passing through the said projection downstream. It is provided for the grooves passing in downstream direction through the projections to direct the cooling air flow exactly into the gap between the adjacent circumferential heat shields of the stator.

EFFECT: invention is aimed at cooling efficiency increase, decrease of cooling air mass flow rate.

3 cl, 7 dwg

FIELD: process engineering.

SUBSTANCE: nozzle element is made of composite including fibrous reinforcement compacted by ceramic matrix. It comprises sections of inner and outer bases and at least one blade attached thereto. Base sections extend at every zone of their attachment to the blade. Fibrous reinforcement comprises fibrous structure woven by 3D or multiple ply weaving that features continuity in the entire volume of nozzle element and over the entire periphery of one or every blade. Solid fibrous blank is woven that contains in lengthwise direction, at least the following elements: one pattern including first segment that makes the blade preform blank, second segment extending the first one at its one lengthwise end to make two wings facing each other. Third element extends the first one at its opposite end to make two wings facing each other. This blank is turned to make wings of the second and third segments extend perpendicular to first segment. Blank shape is developed to make fibrous preform of nozzle element. Note here that blade part making the preform is produced by shaping the first segment. Parts that make the preforms of base sections are produced from wings. Then, preforms are compacted by matrix to make a solid nozzle element with fibrous reinforcement. Fibrous reinforcement comprises fibrous structure that features continuity in the entire volume of nozzle element and over the entire periphery of one or every blade. Other inventions of the set relate to turbine nozzle made as described above and to gas turbine with such nozzle.

EFFECT: higher mechanical properties.

15 cl, 30 dwg

FIELD: engines and pumps.

SUBSTANCE: each sector of an internal platform is connected to a sector of a radial partition. The internal peripheral part of each sector of the partition is equipped with teeth and comprises solid parts that alternate with parts that contain grooves. Elements from worn material are fixed on the continuous circular bracket, comprising facilities of fixation on partition sectors. The bracket is made as capable of rotation and turning in the circumferential direction between the assembly position and the disassembly position and the blocking position, in which fixation facilities interact with solid parts of partition sectors for provision of bracket retention on the partition. Fixation facilities form sections of a circular groove opening in the radial direction to outside, in which solid parts of partition sectors are placed in the blocking position. Other inventions of the group relate to the sector and the continuous circular bracket of the guide vanes specified above, and also to the lower pressure turbine and the gas turbine engine including such guide vanes.

EFFECT: group of inventions makes it possible to simplify manufacturing of guide vanes sectors.

15 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: aircraft turbine stator module ring has multiple through bores to accommodate stator vanes. Every said bore defines mid line extending between first edge for vane trailing edge location and second edge for vane leading edge location. Stator vane locating bore is aligned with mechanical load release through cutout made at said ring opposite and spaced from said first edge of the bore in direction of mid line. Other invention of the set relates to stator part including above described ring and multiple vanes, to aircraft turbine module with said stator part and to turbine engine with said module.

EFFECT: lower probability of cracking at stator ring in the area of blade trailing edge.

13 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: high-pressure turbine comprises assembly of guide vanes including stationary flow-levelling vanes and rotor vanes. Guide vane outer edge rests on turbine outer casing in axial direction. Guide vane inner edge slides axially in contact with inner casing outline that allows free displacement of said edge in engine axis to constrict axial displacement owing to axial support by vane outer edge. Every outer edge comprises ledges extending in direction of inner casing outline and shaped to cramp. One set of ledges is directed forward in turbine axis. Said cramps are connected in the pair of flanges. Part of ledges of front guide vanes and front flanges are arranged to make the passage for air feed to said assembly of guide vanes. Other inventions of the set relate to the sector of said guide vane assembly, ring flange connected with one of sets of said cramps, and to aircraft engine with described high-pressure turbine.

EFFECT: compensation for difference in axial expansion of outer and inner casings.

14 cl, 7 dwg

Gas turbine engine // 2521528

FIELD: engines and pumps.

SUBSTANCE: gas turbine comprises stator blade to direct hot combustion gases to rotor blades. Stator blade comprises shroud arranged at the blade radially inner side relative to engine rotational axis. Said shroud has the part of trailing edge downstream of hot gas flow behind the stator blade. Besides, gas turbine incorporates structural and cooling system to direct coolant to top upstream end of the shroud trailing edge. Said edge is turned radially inward relative to turbine rotational axis. Structural and cooling system also directs said coolant axially towards the edge bottom downstream end. Said coolant cools training edge part at flowing over said edge. Said edge includes turbulence promoters to up the heat transfer from the part of trailing edge at coolant flowing over said edge. Said turbulence promoters extend axially across the turbine rotational axis. The edge turned radially inward comprises several wall webs extending axially to separate said edge to several separate cooling channels extending axially. Turbulence promoters of said edge are arranged in cooling channels.

EFFECT: higher efficiency of cooling.

11 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: turbo machine comprises housing, turbine wheel to run therein made of segments and fitted concentrically around said wheel and locating element. The latter comprises mounting section secured to said housing and make a spring and seat section coupled with resilient section to thrust axially against the ring segment. Seat element is secured to said housing to bring axial force to at least one ring segment to press it axially to housing section. In compliance with one version, said seat element includes the support with mounting section. In compliance with another version, said seat element includes a flexible support acting axially to the ring first segment and flexible support acting axially to the ring second segment to press it against the housing section.

EFFECT: improved tightness of turbo machine housing.

14 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed assembly comprises casing, angular sectors furnished with blades rigidly secured in casing, ring of wearing material resting on the support and rigidly secured in casing by screw joints and studs for radial fixation of said angular sectors. Every said sector comprises flange and fastening rib extending from said flange radially inside. Screw joints extend via ring support of wearing material. Studs for radial fixation of said angular sectors are fitted in holes made in fastening ribs and clamp arranged opposite ring of wearing material relative to casing. Said clamp and casing make the groove to accommodate fastening ribs, clamp being rigidly secured in said casing by screw joints. Another invention of the set relates to gas turbine engine that comprises abode said assembly.

EFFECT: decreased weight and length.

14 cl, 11 dwg

FIELD: machine building.

SUBSTANCE: circular fixed element for use with a steam turbine (100). The fixed element comprises a radially external first ring (228), a radially internal second ring (226) and at least one airfoil (212). The first ring (228) comprises the first cavity (262), formed in it, and multiple channels (264) of the first ring, connected with the first cavity (262) and stretching radially from the first cavity (262). The second ring (226) comprises the second cavity (242) and at least one outlet hole (244), formed in it. The second cavity (242) is connected along the flow with an outlet hole (244). The second ring (226) is located radially inside the first ring (228). At least one airfoil (212) stretches between the first ring (228) and the second ring (226). The airfoil comprises a through hole (280), which stretches through it. The through hole (280) of the airfoil is connected with at least one channel (264) of the first ring and the second cavity (242). The diameter (D0) of the channel (264) of the first ring is more than the diameter (DA) of the through hole (280).

EFFECT: invention provides for cooling of a rotary element in a steam turbine without change in external geometries of an element, element materials and/or temperature, and/or steam pressure for provision of reliable long-term operation of a steam turbine rotor with blades.

10 cl, 3 dwg

FIELD: power engineering.

SUBSTANCE: invention relates to power engineering. A flexible rotary structure of nondestructive check comprises a longitudinal body and a device making it possible to vary bending of a part of a longitudinal body, besides, the drive is retained by a holder coupled with a longitudinal body, the distal part of which is arranged at the side or is displaced relative to the longitudinal body and is connected with the part of the longitudinal body by means of a tension wire.

EFFECT: invention makes it possible to ensure more accurate installation of a bent part of a longitudinal body.

10 cl, 9 dwg

FIELD: power engineering.

SUBSTANCE: invention relates to power engineering. A plant for determination of efficiency factor of a steam turbine section, which includes a physical computing device with a material machine readable information medium containing a code. The specified code is designed for determination of the efficiency factor of the steam turbine section based on the dependence between values of enthalpy difference and values of steam leak flow between adjacent sections of the steam turbine. The specified dependence comprises a point, in which leak enthalpy is compared to enthalpy in the place, where the leak is going. Also a plant is presented for determination of true efficiency factor of the medium pressure section of the steam turbine, as well as a plant for steam turbine control.

EFFECT: invention makes it possible to measure efficiency factor and leaks in a steam turbine.

19 cl, 8 dwg

The invention relates to the field of engineering, primarily to aircraft gas turbine engines

The invention relates to the turbines and can be used for the installation or repair of turbine to install the bearings in the correct position for smooth weight multi-line shafting, either with prescribed values

The invention relates to the field of research hard-to-reach cavities of complex shapes, in particular to a device for the delivery of flexible endoscopes and other diagnostic tools for monitoring the status of hard-to-reach places and cavities of various machines, namely in the flowing part of the gas turbine engine

FIELD: machine building.

SUBSTANCE: gas turbine with axial flow contains rotor blades, guide vanes and rotating element. The rotor blades are secured on the rotor by means of the fish-bone shanks installed in the turned axial rotor channels. The blade bases create a heat protecting screens of the rotor shafts and have cavities connected with each other and with cooling air source. Between the adjacent bases of the adjacent rotor blades in direction along the circumference there is a clearance connected with cavities and passing between the bases transversely to the direction along circumference at each side of the separating plane passing through the clearance centre. The clearance is sealed at side of the gas flow by the plate sealing straps. The longitudinal end faces of the heads are located in opposite grooves of the side surfaces of bases or heat protecting screens looking towards the separating plane. The first sealing strap is installed at edges of the side surfaces at side of the gas flow passing in axial direction of the rotor shaft. Additional sealing strap is installed at the end face of the adjacent bases at edges of the side surfaces of the clearance passing in radial direction of the rotor shaft. The rotating element ensures axial locking of the rotor blade shank on the rotor, at that in the locked position it covers by the drive handle the radially opened ends of the grooves, in which the additional strap is inserted. The other invention of the group relates to the axial compressor comprising the said rotor blades, guide vanes and rotating element.

EFFECT: group of inventions improves efficiency of sealing of the clearances between blades.

7 cl, 4 dwg

Brush seal // 2555948

FIELD: machine building.

SUBSTANCE: brush seal passing in circumferential direction, located between fixed and rotating components of the machinery, and during the machinery operation having area of elevated pressure at inlet side and area of reduced pressure at outlet side, contains bristles creating bristle blocks, pressing plate and pad for bristles block. The bristles block is located on the fixed component and in cantilever fashion projects towards the rotating component. The pressing plate is installed at the outlet side of the bristles block and on the fixed component. The bristles block pad is installed between the bristles block and pressing pad, and on the fixed component. The pad has slots passing in radial direction and with spacing in circumferential direction, the slots exit to opposite sides of the specified pad, and are located at its internal and external circumferential edges.

EFFECT: invention simplifies production of the brush seal, and excludes bristles damage.

11 cl, 14 dwg

FIELD: machine building.

SUBSTANCE: turbine stage comprises a rotor disk mounted inside a ring divided into sectors and held by the external casing. Every annular sector comprises a rear edge with an annular groove confined by the front circular stop member, the rear circular stop member and the bottom wall. The external casing comprises a circular protruding edge located in the said groove to fix the rear edge of the annular sector. The bottom wall of the annular sector's annular groove is shifted in the radial direction in respect to the circular protruding edge of the external casing and can form insulating heat space in-between. The bottom wall of the annular groove comprises units for radial setting on the circular protruding edge which are formed by two contact patch pieces protruding over the bottom wall of the annular groove. The other invention of the group refers to a turbomachine comprising the above turbine stage.

EFFECT: group of inventions allows for higher reliability of a turbine stage.

9 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: each sector of an internal platform is connected to a sector of a radial partition. The internal peripheral part of each sector of the partition is equipped with teeth and comprises solid parts that alternate with parts that contain grooves. Elements from worn material are fixed on the continuous circular bracket, comprising facilities of fixation on partition sectors. The bracket is made as capable of rotation and turning in the circumferential direction between the assembly position and the disassembly position and the blocking position, in which fixation facilities interact with solid parts of partition sectors for provision of bracket retention on the partition. Fixation facilities form sections of a circular groove opening in the radial direction to outside, in which solid parts of partition sectors are placed in the blocking position. Other inventions of the group relate to the sector and the continuous circular bracket of the guide vanes specified above, and also to the lower pressure turbine and the gas turbine engine including such guide vanes.

EFFECT: group of inventions makes it possible to simplify manufacturing of guide vanes sectors.

15 cl, 8 dwg

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