Turbine, including the device, preventing rotation of coil seal

FIELD: machine engineering.

SUBSTANCE: turbine contains a number of stages, each of which includes a disk and blades located on it. A pair of adjacent discs forms an annular gap therebetween and has opposite slots for receiving a sealing tape to seal the annular gap. A through hole is formed in the sealing tape, located midway between the edges of the sealing tape. Between the edges of the sealing strip within the annular gap is a base portion of the rotation preventing member, which also includes a connecting portion extending axially from the base portion to engage with a cutout portion of at least one of the discs. Inside the annular gap, from the base portion, via the through hole in the sealing strip, protrusion forms a fastening structure that attaches the rotation-preventing member to the sealing tape.

EFFECT: invention makes it possible to prevent the sealing tape from moving around the circumference.

8 cl, 4 dwg

 



 

Same patents:

FIELD: machine building.

SUBSTANCE: straight-toothed cylindrical engagement between rotors of the movable parts of the turbine machine contains two toothed rims. Each toothed rim is located at end of the movable part and is in engagement with another toothed rim providing free passage for air between throats of the surrounding parts, and ends of the surrounding parts of teeth. The toothed rim of at least one movable part continues in radial direction relatively to another toothed rim to form external or internal extension of the toothed rim against the element surrounded by the movable part or surrounding the movable part installed on another toothed rim. To protect the air passage in joint between the rotors of the movable parts one end of the joint is continued in radial direction relatively to the another end to form the external or internal expansion. The expansion is made against the element surrounded by the movable part or surrounding the movable part installed at another end of the joint. This invention of the group relates to the rotor line of the turbine machine containing multiple specified above straight-toothed cylindrical engagements between the rotors of compressors and turbines.

EFFECT: group of inventions excludes closing of air passage in joint between rotors of the turbine machine.

9 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: turbine of a double-circuit gas turbine engine includes turbines of high and low pressures with supports of turbine rotors. Inside the rotor of the low pressure turbine there is an air cavity of high pressure connected at the inlet to the air cavity of the first nozzle block of the low pressure turbine, and at the outlet via the rear labyrinth seal - with a flow path of the low pressure turbine. The air cavity of high pressure is limited at the inner side - by the first and second labyrinth seals. Seals separate the air cavity of high pressure from the air cavity of low pressure. The air cavity of low pressure is divided into front and rear cavities. The front cavity is arranged between the high pressure turbine support and a cone flange of the low pressure turbine shaft. The rear cavity is located between the cone flange of the low pressure turbine shaft and low pressure turbine support. The first and second labyrinth seals are located relative to each other in such a manner that the ratio of the minimum diameter along sealing combs of the first labyrinth seal to the minimum diameter along sealing combs of the second labyrinth seal makes 1.2…2.0.

EFFECT: invention makes it possible to increase reliability and efficiency of a turbine.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rotors of high-temperature turbomachines of gas turbine engines of aviation and ground use. In a rotor (1) of a high-temperature turbomachine between the first (7) and second (8) and the last but one (9) and the last (10) along gas flow (11) sealing combs in a rim (6) of an intermediate disc 5 there are radial channels (13) and (14), connecting an air disc-to-disc cavity (4) with a gas cavity (12) of the turbine. Radial walls (15) and (16) of channels (13) and (14) are made flat, and walls (17) and (18) that connect them are made cylindrical. The ratio of the length L of the channel in circumferential direction to the radius R of the cylindrical wall of the channel is within 2…6.

EFFECT: by exclusion of contamination of inner surface of an intermediate disc and reduced concentration of stresses in a disc rim, high-temperature turbomachine rotor reliability increases.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: low-pressure turbine comprises vanned discs engaged with turbine shaft via bevelled claw. Vanned discs and bevelled claw comprise circular flanges with ledges composed of alternating solid and hollow parts at inner and outer periphery, respectively. Solid parts have passages for fasteners. Every solid part is engaged with periphery of the disc or bevelled claw by asymmetric concaved recesses. Other inventions of the set relates to low-pressure turbine disc and bevelled claw and gas turbine engine with such turbine.

EFFECT: longer life of disc flanges and bevelled claw.

7 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: insert (10) and the method of adjustment of steam balance through-hole (54) in a wheel (52) of steam turbine rotor are proposed. The insert (10) includes a housing (12) with have longitudinal axle (14) and oppositely located first and second ends (16, 18). Insert flange (20) is oriented in radial direction from the second end (18) of the housing (12). The exterior surface (22) is located along the housing (12) periphery between the named first end (16) and the flange (20). The first bore (24), made in the body (12), forms the first opening (28) in the first end (16), while the named first channel (24) and exterior surface (22) of the housing (12) together confine among themselves the wall (32), capable of being plastically deformed in a radially outward direction. The second bore (26), made in the housing (12), communicates with the named first bore (24) and has a smaller cross-section, than the first bore (24). The installation method entails the installation of the insert (10) in the through-hole (54) and expansion of the wall (32) to clamp the axial thickness of the wheel (52) between the flange (20) and expanded wall (32) of the insert (10).

EFFECT: simple installation of the insert is achieved, which can be executed by one employee without modifying of the wheel, the risk of strain of adjoining wheels is eliminated during the installation.

7 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed rotor comprises discs jointed by thread joints arranged their mid part in rotor lengthwise axis. Peripheral circular section of one disc on its inner side is furnished with ledges and lengthwise slits alternating therewith and arranged in disc circle. Peripheral circular section of the other disc in contact with the former is provided with lugs with ledges and lengthwise slits alternating therewith on its outer size in quantity equal to that of disc lengthwise slits. End surfaces of said ledges are tapered. Lugs are extended over disc circle beyond said contact surface to allow engagement between ledges of one disc with conical surface of the other disc ledges.

EFFECT: higher reliability of gas turbine engine rotor.

2 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine rotor comprises working wheel discs connected by the surfaces of locating ring elements with cylindrical radial through bores made therein with retaining elements. Extended section is made on the part of every said bore on inner surfaces of locating ring elements, on the side of their outer surface. Retaining elements are composed of sleeves with internal thread arranged at extended sections and pints with appropriate outer thread locked at said bores by expansion. Working wheel discs are interconnected at their mid part along rotor lengthwise axis.

EFFECT: higher reliability, manufacturability and reparability.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: radial ring flange of turbine rotor or stator element comprises alternating ledges and recesses with bottom areas made at inner or outer peripheral part. Ledges have bores for fastening bolts. Recessed part bottom area to prevent inadequate joint at said inner or outer peripheral part is arranged radially inside or outside with respect to circle centred at flange centre and tangent inside or outside relative to ledge bores. Both parts with recesses arranged on their both sides feature concave bottom located radially inside or outside relative to, in fact flat bottoms of other recessed parts. Other inventions of this set relate to low-pressure turbine including abode described flange and to gas turbine engine with such turbine.

EFFECT: higher reliability of ring flange.

9 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to multistage gas turbines for aircraft engines and surface power generation plants. Proposed gas turbine comprises rotor wheels interconnected by flanges with axial studs. Coupling shaft is arranged at inner side of wheel hubs. First turbine rotor wheel is locked at in coupling shaft input extension by radial rib in radial and axial directions. Radial rib is arranged between wheels, right between rotor tightening nut and adjusting ring.

EFFECT: decreased overall dimensions, higher reliability.

2 dwg

FIELD: machine building.

SUBSTANCE: radial ring flange on its outer or inner periphery comprises alternating projections with holes for fastening tightening bolts and hollows as well as tools to prevent faulty angle joint by preventing bolts from entering a hollow. The tools to prevent faulty angle joint are formed by the bottom of at least one hollow of the inner or, respectively, outer periphery with its radius in relation to the turbomachine axis being less or, respectively, greater than the radius of the circle externally or, respectively, internally tangent to the holes for the bolts to pass through the projections. The other invention of the group relates to the connection of gas-turbine engine elements comprising the above said flange fixed by the bolts with ring clamps. The bolts are placed between the clamps' holes and in the flange projections' holes; the bottom of smaller or, respectively, greater radius is placed between the two flange projections and two projections of at least one of the clamps. One more invention of the group refers to a gas-turbine engine comprising the above connection.

EFFECT: invention eliminates risk of faulty ring flange installation.

8 cl, 6 dwg

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

FIELD: engines and pumps.

SUBSTANCE: proposed seal comprises two resilient graphite rings with crosswise cut-outs fitted at turbomachine rotor. Contact rings have their end surface staying in contact with end surfaces of resilient graphite rings. Spacer sleeve is fitted at turbomachine rotor between contact rings and bush. Additionally, this seal includes resilient ring with crosswise cut-out fitted at turbomachine rotor between resilient graphite rings. Note also that outer surface of resilient ring contacts with inner surfaces of resilient graphite rings. Note that contact surfaces of resilient ring and resilient graphite rings are conical.

EFFECT: decreased friction and wear due to lower load at graphite rings.

1 dwg

FIELD: machine building.

SUBSTANCE: invention relates to a turbomachine shaft seal. A turbomachine shaft seal comprises a process gas seal charged by process gas and blocked on the process side and an atmospheric seal charged by air and blocked on the atmosphere side. A ventilation chamber is provided around the turbomachine shaft and set between the process gas seal and the atmospheric seal to collect and withdraw process gas leaks penetrating through the process gas seal, and air leaks penetrating through the atmospheric seal; the ventilation chamber comprises a leak inlet hole on its side radially set inside, and a leak outlet hole - on its side radially set outside as well as nozzles between the leak inlet hole and the leak outlet hole. The nozzles are made so that the ventilation chamber can block flame in respect to the inflammation of leak at the leak inlet hole, and/or leak in the ventilation chamber is flameproof.

EFFECT: invention improves reliability of a seal.

14 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: turbine blade comprises root extending from the turbine flange and cradles made on both sides of turbine flange. Cradle on first side of turbine flange serves to accommodate the first sliding seal between the cradle front and rear walls on turbine flange first side. Cradle on turbine flange first side comprises bulged surface arranged between front and rear walls and concaved surface. Cradle on second side serves to accommodate the part of second sliding seal. In assembly of turbine rotor with aforesaid blade, first turbine blade in fitted in the rotor to accommodate sliding seal in first turbine blade lateral cradle. Then second turbine blade is fitted in turbine rotor parallel with turbine rotor rotational axis while damper is arranged nearby said first turbine blade.

EFFECT: structural integrity of turbine blade flange without increase in its depth.

9 cl, 7 dwg

FIELD: machine building.

SUBSTANCE: radial-end contact seal of a turbomachine support comprises two elastic graphite rings with cross cuts installed at the turbomachine rotor, contact rings with their end surfaces contacting the end surfaces of the said elastic graphite rings, and a bush. The seal comprises the third elastic graphite ring with a cross cut placed between the said elastic graphite rings and installed at the turbomachine rotor with the outer rotor surface contacting the inner bush surface; the contacting surfaces of the third elastic graphite ring and the said contact rings are tapered.

EFFECT: increased service life of a graphite seal due to slipping in the area of contact of graphite rings in respect to the contact rings and the bush.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: sealing element of leakage channel between turbine nozzle external platform and its support ring includes leaf seal and a plate forming impact jets. Support ring and external platform include surfaces arranged perpendicular to nozzle segment axis and forming the first and the second sealed surfaces accordingly. Sealed surfaces are in the same plane and have a radial gap in between. Leaf seal closes a gap between sealed surfaces. The plate forming impact jets provides impact-jet cooling of radial external surface of external platform and is designed with possibility of its rigid fixation to turbine nozzle. Another invention relates to gas turbine nozzle device containing support ring and nozzle segments, each of them containing external platform forming segment of external wall of operating gas flow channel, at least one guide blade and above mentioned sealing element. One more invention of the group refers to gas turbine containing above mentioned nozzle device.

EFFECT: group of inventions allows simplifying sealing element of gas turbine.

14 cl, 5 dwg

FIELD: engines and pumps.

SUBSTANCE: object of this invention is sealing gasket of intermediate platform between two adjacent blades in prolonged turbomachine rotor with inlet and outlet ends containing transversally in width direction a contact part, a fastening part and a flexible part between the fastening part and the contact part. It differs by the fact that its transverse section has a form changing between its two ends, at that the flexible part is narrower than the contact part.

EFFECT: higher tightness between blades and platforms of turbomachine rotor.

9 cl, 5 dwg

FIELD: turbine manufacture.

SUBSTANCE: invention can be used in end seal of steam turbine cylinders. Proposed end seal of steam turbine cylinder contains housing with shells carrying sealing rings and connected with cylinder with shell carrying sealing rings forming intermediate chambers between shells and rotor one of which, from side of passage part of cylinder being high temperature one, and the other being cooled and connected with manifold to supply steam to seal. Additional shell is installed in cylinder dividing high-temperature chamber into two parts, one of which is connected with manifold to supply steam to seal. Invention improves operating characteristics of steam turbine including efficiency and reliability of end seal owing to reduction of level and differential temperatures at end seal members and complete prevention of heating and warping of housing and shells of end seal.

EFFECT: improved performance characteristics of steam turbine.

1 dwg

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