Housing with edges for axial turbine machine compressor

FIELD: machine building.

SUBSTANCE: present invention relates to an outer housing of a composite material for an axial compressor of a turbine machine; at the same time, the housing usually contains a round wall with the matrix and fibrous stiffener. The housing (28) contains a round wall (32) with the inner surface (40), which has a continuous curvature on the circumference of the wall (32). The wall contains flat edges (42), which are made level with the inner surface of the curved wall. The edges (42) are arranged in circular rows to let the annular rows of stator blades be placed on them. The edges (42) are made as flat discs to support the blades for optimizing the position of the blades and, at the same time, to reduce the stress concentration in the areas of platform/wall cooperation.

EFFECT: invention makes it possible to reduce the stress concentration between the wall of the housing and the blade platform, increases the accuracy of the blade's orientation, facilitates the regulation of the chord of the blades' orientation or blades' angle.

21 cl, 6 dwg

 



 

Same patents:

Double-flow engine // 2549398

FIELD: engines and pumps.

SUBSTANCE: double-flow engine comprises a fan impeller, straightening blades and a low pressure compressor downstream the impeller, and also air flow divider between external and internal circuits of the double-circuit engine. Blades of the inlet guiding device together with the flow divider are installed on the front external circular radial rib of the external housing of the low pressure compressor and fixed by axial bolts with the extended hexagonal heads. Bolts are located in the circular, opened towards the channel of an external cavity loop between front and back circular ribs of the external housing. The back rib is designed with axial holes coaxial to hexagonal heads of bolts. Axial movement of hexagonal bolt head is limited by the internal shelf of the straightening fan blade located downstream. Blades of the inlet guiding device are fixed also in the flow divider with the bolts with countersunk head restricted from axial movement with a front circular rib. Total amount of bolts with hexagonal and with countersunk heads equally to amount of blades of the inlet guiding device of the low pressure compressor.

EFFECT: invention allows to improve reliability of the double-flow gas-turbine engine.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: housing of a jet-turbine engine has the possibility of installing into it of a variety of blades and includes attachment devices of the end of each blade, which are located on the housing side opposite to blades. Attachment devices include a ring-shaped element passing around the housing, and the housing includes holes through which ends of blades pass for their interaction with attachment devices. The housing is made of long fibres connected with thermoplastic resin. The ring-shaped element is obtained by pultrusion and soaked with thermoplastic resin welded with thermoplastic resin of the housing; besides, the whole assembly is connected by means of hot pressing. The other invention of the group relates to a jet-turbine engine containing the above housing and many blades, each of which has an end connected to the housing.

EFFECT: group of inventions allows simplifying production and assembly of a jet-turbine engine housing.

5 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: casing of an axial turbomachine compressor and method to manufacture the casing. The casing comprises a support (34), in whole, of cylindrical shape, made from composite material, a metal ring (36) adjoining the internal surface of the support (34) by cohesion, and an abradable material layer (22) adjoining the internal surface of the metal ring (36) by plasma spraying. The metal ring (36) is preferable to be produced from stainless steel and preferable to be perforated. The perforation provides for better cohesion of adhesive substance and allows for its degassing. The external surface of the metal ring (36) is preferable to be treated by sand blasting prior to cohesion. Its internal surface is also preferable to be treated by sand blasting prior to plasma spraying of the abradable material.

EFFECT: simplicity and efficiency of manufacturing such a casing providing for the reduction of the compressor weight.

24 cl, 5 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Composite housing is made with load-bearing structure for stationary blades made as a single-piece part from titanium or titanium alloy. Said part has thermal protection means composed by at least one element making refractory alloy shield non-flammable by burning titanium. Said shield is connected with single-piece part by fastening means arranged relative to said shield so that make an inner wall limiting the outer contour of compressor airflow channel.

EFFECT: decreased weight, reliable protection.

16 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: body (5) for a turbocompressor rotor, in particular, for a fan of a turboject engine. The body comprises a peripheral band (6), which forms a circular clamp around the body. The specified band has at least one mounting eye or a flange for fixation of equipment. The band (6) may be made in the form of a strip capable of closure (9, 10) with itself (7, 8). The body may be immediately made as capable of receiving facilities of band fixation designed specially for this purpose and will not require structural changes for direct installation of eyes and flanges related to auxiliary equipment. Besides, if eyes or flanges are added, these elements may be easily added to the band without risk of damaging integrity of the body by addition of new facilities of fixation. In case of damage or wear of the band, eyes or flanges, replacement of these elements is considerably simplified.

EFFECT: proposed peripheral band surrounding the fan body may be used to support fastening elements and flanges for auxiliary mechanisms of an engine nacelle or turbojet engines designed for fixation to the specified body.

9 cl, 8 dwg

FIELD: machine building.

SUBSTANCE: turbine wheel case comprises inner, in fact, cylindrical wall with multiple circular grooves. Every said groove features, in fact, constant cross-section in axial plane. Area of circular groove cross-section reduces from inlet to outlet from first groove to the last one.

EFFECT: optimised efficiency and increased surge margin.

10 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed assembly comprises pumps of condensate first and second lift integrated in common rigid outer housing. Said outer housing with all units arranged there inside are centrally symmetric about fixed vertical axis. Elliptic outer housing is furnished with sealed cover. Suction chamber side walls has condensate intake openings at the level of condenser bottom. Booster presser chamber accommodates even number of identical vertical low- and high-rpm axial polyrow pumps of first lift with one-side condensate inflow and identical horizontal low- and high-rpm axial polyrow pumps of second lift with double-side condensate inflow and discharge into pressure pipes of symmetric chamber of booster chambers. Impeller and distributors of all pumps are multiplanar components with the number of impeller vane cascades making 2-5 and 1-3. Said first cascades are shaped to truncated augers. Impellers and distributors with their casings are composed of cartridges tightly fitted in assembly outer housing.

EFFECT: better anti-cavitation properties, higher reliability, longer life.

5 dwg

Diagonal fan // 2455528

FIELD: mechanics.

SUBSTANCE: diagonal fan comprises a body of conical shape, an impeller with a conical bushing and with blades, a fairing, a blade straightener, besides, the ratio of bushing and body taper angles makes 1.33-1.28.

EFFECT: expanded field of stable operation and industrial usage of a fan by a reduced rotation stall in its blade rings.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine compressor stator includes outer and inner housings connected to each other by elastic elements; at that, outer housing is made as a whole part. Front and rear blasting cavities are located between housings, and there is extraction cavity with extraction openings between blasting cavities. Outer wall of rear blasting cavity is combined with elastic element. There is ring in extraction cavity, which is an integral part of elastic element and outer housing.

EFFECT: invention allows improving reliability, efficiency and service life of engine, reducing its weight and manufacturing cost.

2 cl, 2 dwg

Blade device // 2371589

FIELD: machine building.

SUBSTANCE: blade device comprises body with layers of composite-fiber material, rotor with vanes and vane catcher. Part of body layers is made of woven material with S-shaped folding lines in tangential direction. Preferably S-shaped folding lines are arranged at the angle nearing angle of vanes installation.

EFFECT: improved reliability of body due to braking action of S-shaped folding lines at broken parts of rotor.

2 cl, 3 dwg

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

FIELD: process engineering.

SUBSTANCE: in repair of crankcase flange with bores for equipment fastening bots and made of unweldable materials a countersunk recess of made in said flange around the bore for bolt. Then, countersunk recess bottom is anodized to fit the washer therein and glued thereat by appropriate adhesive. Another invention of this set relates to crankcase of turbo machine such as aircraft turbojet or turboprop made of aluminium, steel or composite which includes the circular flange with bore for bolt. Circular flange is repaired as described above while said bore fits in countersunk recess whereto said washer is glued.

EFFECT: simplified repair.

10 cl, 4 dwg

FIELD: process engineering.

SUBSTANCE: production of the jacket of high-power turbine unit for public power generation systems comprises installation of turbine unit jacket. The latter comprises at least one front section, one mid section and one end section. Jacket production mould is modified to allow the change of rpm for turbine unit to be adapted to the other frequency of power generation system limited by the mould variations for making of the jacket mid section. In compliance with this invention claimed modifications simply turbine unit moulding at changeover to other standards and specs of the other power generation units.

EFFECT: lower production costs.

10 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: low-pressure steam turbine (105) has exhaust branch pipe (115). Internal casing (125) is directly supported by beam web (131) of the foundation (130) by means of the carrying brackets (180). Due to this effect of pressure differences in excluded in the exhaust branch (115), and effect of temperature variations in the exhaust branch is reduced in comparison with location of the inside casing and rotor in the branch pipe. The shaft bearings can be located outside the exhaust branch pipe and are installed in the socle support (140) made directly in the foundation (130). The end inserted seal of the rotor can be secured in the support (140). The exhaust branch pipe (115) can have more simple design with lesser number of the structural supports, its manufacturing requires less time.

EFFECT: simplified maintenance as shaft bearings are not covered under the exhaust branch pipe (115), and ring inserted seals (166, 176) can be removed without removal of the large-scale section of the exhaust branch pipe.

10 cl, 8 dwg

FIELD: power engineering.

SUBSTANCE: support stand (430) for a steam turbine diaphragm comprises the main vertical part (435) with a bulge (447), which passes from the specified part (435) substantially perpendicular to it. The bulge comprises the first bulge, stretching from the upper end of the main vertical part (435), and the second bulge stretching from the area near the lower end of the main vertical part (435). The first bulge is at a certain distance from the second bulge. The first and second bulges are designed for coupling with an appropriate slot (450), made in the turbine diaphragm. In the bulges there is a hole (455), which passes via them vertically and is designed to place a fastening element (460), stretching via the first and second bulges (447) to ensure vertical attachment of the main vertical part (435) and specified bulges (447) to the turbine diaphragm.

EFFECT: reduced duration and cost of maintenance cycle, since it provides for possibility of access for extraction of a lower half (410) of the diaphragm for maintenance without rotor removal.

9 cl, 7 dwg

Radial expander // 2548998

FIELD: machine building.

SUBSTANCE: invention relates to a radial expander. The radial expander comprises at least one section of the radial expander located in a common casing. The radial expander section includes impeller blades and a variety of diaphragms. The impeller blades are combined into two or more stages between the bearings on the same shaft. The diaphragms are coupled in axial direction. Every diaphragm comprises a knuckle bend to connect the adjacent stages. Each of the knuckle bends is fitted by a nozzle blade and a return blade. Every section has a gas input and a gas output. The gas input is communicated with the suction hole of the common casing. The gas output is communicated with the outlet hole of the common casing.

EFFECT: invention is aimed at the increase of expander reliability.

4 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

Axial gas turbine // 2547542

FIELD: machine building.

SUBSTANCE: axial gas turbine (GT) contains a rotor with alternating rows of air cooled rotor blades and heat protecting rotor screens, and a stator with alternating rows of air cooled guide vanes and heat protecting stator screens installed in the internal ring elements. The stator coaxially encloses the rotor from outside creating between them the hot gas flowing path such that rows of rotor blades and heat protecting screens of the stator and roes of the guide vanes and heat protecting screens of the rotor are located against each other, respectively. The guide vanes row and next rotor blades row below as per direction of the flow create the turbine stage. The rotor blades are equipped with end external platforms of the rotor blades. The external platforms of the rotor blades contain on their external surface a row of teeth in parallel with each other in the circular direction and located one after another in direction of the gas flow. The teeth are divided to primary and secondary teeth. The secondary teeth are located downstream the primary teeth. The primary teeth are located against the projection of the adjacent guide vanes of the turbine stage passing downwards along the flow, and secondary teeth are against the appropriate heat protecting screens of the stator.

EFFECT: increased cooling efficiency.

9 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: casing of an axial turbomachine compressor and method to manufacture the casing. The casing comprises a support (34), in whole, of cylindrical shape, made from composite material, a metal ring (36) adjoining the internal surface of the support (34) by cohesion, and an abradable material layer (22) adjoining the internal surface of the metal ring (36) by plasma spraying. The metal ring (36) is preferable to be produced from stainless steel and preferable to be perforated. The perforation provides for better cohesion of adhesive substance and allows for its degassing. The external surface of the metal ring (36) is preferable to be treated by sand blasting prior to cohesion. Its internal surface is also preferable to be treated by sand blasting prior to plasma spraying of the abradable material.

EFFECT: simplicity and efficiency of manufacturing such a casing providing for the reduction of the compressor weight.

24 cl, 5 dwg

FIELD: power engineering.

SUBSTANCE: gas turbine ring fastening device enclosing the moving blades impelled by a gas flow has inlet and outlet hooks. The inlet hook faces towards the turbine inlet and is located in the inlet groove of the ring open downstream. The outlet hook faces towards outlet exit and is located in the output groove of the ring open upstream. Between the inlet and outlet hooks a positive pressure cavity is located which is fed by cooling gas. Upstream the inlet hook the cooling gas supply devices for cooling of the inlet hook are located, and downstream the output hook - the cooling gas supply devices for cooling of the outlet hook are located. The cooling gas supply devices are designed with a possibility of cooling gas supply without passing through the named positive pressure cavity. One more invention of the group relates to the assembly consisting of the named above device and the turbine ring containing the inlet groove open downstream and the outlet groove open upstream. Inlet and/or outlet grooves have a curved contact surface for contact with the respective hook. Other inventions of the group relate to the turbine comprising the named above fastening device or the named assembly and also to the turbomotor comprising such turbine.

EFFECT: group of inventions allows to provide the constancy of the form of hooks irrespective of the turbine operating mode, and also to improve their reliability.

8 cl, 6 dwg

FIELD: mechanical engineering; turbines.

SUBSTANCE: proposed casing consists of one shell and two flanges. Thickness of walls in upper zone pointed from flanges, in two middle zones and in two lower zones pointed to flanges changes so that upper zone, pointed form flanges, is reinforced as compared with lower zone pointed to flanges. Thickness of walls of middle zones changes so that both zones, adjoining the middle zones, smoothly change one into the other. Lower zones pointed to flanges are more flexible, as compared with flanges secured by bolts, and partially reinforced middle zones, respectively, and reinforced upper zone, and they act as joint preventing deformation mainly in radial direction. Thanks to it, casing remains considerably more round in process of operation of turbine. Smaller radial clearance between casing and ends of turning blades caused by lower deformation provides increased efficiency in process of operation of turbine.

EFFECT: increased efficiency.

4 cl, 1 dwg

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