EP3717749A1 - Ensemble pour turbomachine axiale, turbomachine axiale, procédé d'assemblage et joint d'étanchéité associés - Google Patents
Ensemble pour turbomachine axiale, turbomachine axiale, procédé d'assemblage et joint d'étanchéité associésInfo
- Publication number
- EP3717749A1 EP3717749A1 EP18762286.5A EP18762286A EP3717749A1 EP 3717749 A1 EP3717749 A1 EP 3717749A1 EP 18762286 A EP18762286 A EP 18762286A EP 3717749 A1 EP3717749 A1 EP 3717749A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- seal
- platform
- assembly
- housing
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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- 238000007789 sealing Methods 0.000 title abstract description 3
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- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 241000826860 Trapezium Species 0.000 description 1
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
- F01D25/06—Antivibration arrangements for preventing blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/64—Mounting; Assembling; Disassembling of axial pumps
- F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/232—Three-dimensional prismatic conical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/24—Three-dimensional ellipsoidal
- F05D2250/241—Three-dimensional ellipsoidal spherical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/37—Retaining components in desired mutual position by a press fit connection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
Definitions
- AXIAL TURBOMACHINE ASSEMBLY, AXIAL TURBOMACHINE, ASSEMBLY METHOD AND JOINT SEAL THEREFOR
- the invention relates to an axial turbomachine assembly. More specifically, the invention relates to a turbomachine casing and a blade provided with a platform at one of its radial ends. The invention also relates to a turbomachine with such an assembly.
- EP 2 930 308 A1 discloses a turbomachine compressor in which the housing wall is made of composite material and has, on its inner surface, flat facets to ensure the fixing of the stator vanes.
- the blades are provided with platforms arranged at the outer radial end of each blade, each of the platforms coming into contact with a facet. This makes it possible to reduce the stress concentrations between the casing wall and the blades.
- a layer of abradable material is provided on the inner face of the housing wall. This abradable layer is arranged at the junction of the platforms and ensures the continuity of the airflow guiding surface.
- this provision is insufficient to seal the flow, and in particular air leakage may occur under certain conditions of pressure and temperature, between the platforms and the housing wall. This mainly impacts the performance of the turbomachine and can affect the durability of the mechanical strength of the blade attachment.
- the invention aims to solve at least one of the problems posed by the prior art. More specifically, the invention aims to to increase the efficiency of the turbomachine and to ensure the reliability of the attachment of the blades to the housing.
- the invention relates to an assembly for an axial turbomachine, in particular an aircraft turbojet engine, the assembly comprising: an annular casing with an internal surface; an annular row of stator vanes with at least one stator blade comprising a blade extending radially from a fixing platform, said attachment platform being fixed to the housing and having a polygonal contour; remarkable in that it further comprises a seal comprising a frame whose contour matches the polygonal contour of the attachment platform, said frame being in radial contact with the fixing platform and the housing to ensure a seal.
- the blade and the platform of the blade can be monobloc.
- the housing may be at least partially made of organic matrix composite material.
- the frame defines a sealed manner a pocket radially between the fixing platform and the housing, said pocket extending in particular on the majority of the attachment platform.
- the frame is formed of bars along the sides of the platform.
- the frame of the seal has a generally parallel and preferably rectangular outer shape.
- the shape can be trapezoidal, oval, round, etc.
- the general external shape of the seal corresponds to the shape of the platform, seen in section in a plane normal to the radial orientation of the blade.
- the platform has a fixing pin which passes through an orifice of the housing, and in that the fixing axis passes through the seal.
- a portion of the seal is toric or cylindrical, and surrounds the attachment axis.
- the toric portion may be oval, elliptical or circular.
- segments connect the toric or cylindrical portion to the frame.
- the segments comprise two circumferential segments oriented in the circumferential direction of the turbomachine and at least one axial segment oriented in the axial direction of the turbomachine.
- the circumferential segments comprise a larger section than the axial segment, the circumferential segments having an axial dimension greater than the circumferential dimension of the axial segment.
- the thickness of the segments in the radial direction may be identical.
- the axial dimension of the circumferential segments and / or the circumferential dimension of the axial segments may be greater than the thickness of the segments.
- the toric or cylindrical portion is enclosed in the upstream half of the seal.
- the seal comprises a downstream reinforcement tongue, preferably extending mainly in the circumferential direction of the turbomachine.
- the seal is at least partially made of foam, polymer and / or elastomer.
- the attachment platform is a platform of a first blade, the seal being in contact with an identical seal associated with a platform of a second blade, adjacent to the first platform .
- the joints may each have two sides oriented along the axis of the turbomachine, each side being in contact with one side of the joint of the adjacent platform.
- the seal is interposed between the housing and several adjacent blade platforms, said seal conforming to the polygonal contours of each of said plurality of platforms adjacent blades.
- several adjacent pairs of platforms and facets may share the same joint.
- the casing comprises an inner surface with an annular array of facets receiving the stator vanes, the outer radial surface of the platform being inclined with respect to the associated facet and / or the thickness radial of the joint is larger downstream than upstream. Because of the non-direct contact between the two respective surfaces of the platform and the facet, they may not be parallel because they are not in contact with one another. Thus, it is possible but not essential, that the seal has a greater thickness downstream than upstream, that is to say where the pressure of the air flow is the largest.
- a layer of abradable material is provided on the inner face of the housing, in particular upstream and / or downstream of the facets, and axially distance from the platforms and / or the seal.
- the invention also relates to an axial turbomachine with a low-pressure compressor, remarkable in that the compressor comprises an assembly according to one of the embodiments described above and in that the housing is at least partially made of organic matrix composite material in contact with the seal.
- the invention also relates to a method of assembling a turbomachine assembly, remarkable in that the assembly is one of the embodiments described above and that the method comprises a step (A) the establishment of the seal between the casing and the blade platform, and a step (b) of fixing the blade to the casing during which seal is compressed radially between the platform of the blade and the casing.
- the seal is more compressed downstream than upstream.
- the fixing step (b) comprises tightening a nut on the fastening axis so as to generate the compression of the seal.
- the invention also relates to a seal for an axial turbomachine stator vane mounting platform, in particular an aircraft turbojet engine, said attachment platform having a polygonal contour, the seal comprising: a frame whose contour is adapted to fit the polygonal contour of the attachment platform, and thermoformed pads.
- the pads are molding inserts of the seal.
- the studs comprise holes, preferably open, capable of cooperating with pins provided on the platform.
- the invention also relates to a seal for an axial turbomachine stator vane mounting platform, in particular an aircraft turbojet engine, said attachment platform having a polygonal contour, the seal comprising: a frame whose contour is adapted to conform to the polygonal contour of the attachment platform, and an adhesive element at least on part of the frame.
- the adhesive element is an adhesive layer provided on the part of the frame adapted to come into contact with the platform.
- the adhesive element is covered with a cover.
- the assembly method is remarkable in that the seal is according to one of the embodiments described above, the step (a) of implementation. placing the seal between the casing and the blade platform comprising a substep of pre-assembly of the seal to the platform.
- the pre-assembly sub-step comprises fixing the studs to pawns provided on the platform.
- the pre-assembly sub-step comprises the removal of the cap and the attachment by adhesion of the seal to the platform via the adhesive element.
- the blade platforms comprise sides of polygons in contact with each other.
- the polygonal contour of the platform encircles the outline of the frame.
- the frame forms a continuous loop, and / or the contour is closed.
- the seal including the frame, forms a closed and sealed loop which is inscribed in the polygonal contour of the attachment platform.
- the loop is in radial contact with the platform and the housing over its entire circumference.
- the invention also relates to an assembly for a turbomachine, the assembly comprising an outer casing and a stator blade including an annular row of identical stator blades, at least one stator blade comprising a fixing platform fixed against the surface internal of the housing, and a blade extending radially from the platform; remarkable in that it further comprises a seal forming an outer rim of the platform, and / or a seal forming a bead along the contour of the platform; said seal being in contact with the platform and the housing.
- the invention relates to an axial turbomachine assembly, in particular an aircraft turbojet engine, the assembly comprising: a casing comprising a tubular wall having flat facets on its inner surface, each facet comprising less than one orifice; at least one annular row of stator vanes each comprising a blade extending substantially radially and a fixing platform at the end external radial of the blade; each blade attachment platform comprises a fastening pin passing through an associated facet, all being remarkable in that a seal traversed by the fastening pin is provided on the platform.
- the invention relates to an axial turbomachine assembly, in particular an aircraft turbojet engine, the assembly comprising: a blade provided with a blade and a platform for attaching to a ferrule or a housing, the blade having a leading edge, a trailing edge and a camber line connecting the leading edge to the trailing edge; the assembly being remarkable in that it comprises a seal adapted to come into contact with a surface of the platform and a surface of said shell or said housing, the seal having a thickness which varies in the direction of the camber line.
- the presence of the seal allows a simpler and more flexible design: the abradable layer which must be contiguous to the platform in known systems can be positioned remotely because it is no longer essential to the sealing function . Also, the accuracy of machining and positioning of the surfaces of veneers and blade platforms is no longer as important because the manufacturing tolerances can be enlarged through the presence of the seal.
- FIG. 1 represents an axial turbomachine according to the invention
- Figure 2 is a diagram of a turbomachine compressor
- Figure 3 outlines an axial view of the casing of the turbomachine compressor according to the invention.
- Figure 4 illustrates a stator blade with a platform in contact with a facet of the housing
- Figure 5 shows a top view of the blade
- Figure 6 shows a housing wall portion on which is fixed a blade
- Figure 7 shows a top view of an embodiment of a seal
- FIG. 8 represents an isometric view of a joint according to a second embodiment
- Figure 9 shows a third embodiment of the seal
- FIG. 10 represents an isometric view of the seal of FIG. 9;
- Figure 11 shows a fourth embodiment of the seal
- Figure 12 shows a fifth embodiment of the seal
- Figure 13 shows a sixth embodiment of the seal.
- inside and outside refer to a positioning relative to the axis of rotation of an axial turbomachine.
- the axial direction is along the axis of rotation, and the radial direction is perpendicular to the axial direction.
- the lateral direction is heard circumferentially, and may be perpendicular to the axis.
- FIG. 1 represents a double-flow turbojet engine 2.
- the turbojet engine 2 comprises a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and a turbine 10.
- the mechanical power of the turbine 10 transmitted via the central shaft to the rotor 12 sets in motion the two compressors 4 and 6.
- the compressors comprise several rows of rotor blades associated with rows of stator vanes.
- the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate a progressively compressed air flow to the combustion chamber 8.
- FIG. 2 is a sectional view of a compressor of an axial turbomachine such as that of FIG. 1.
- the compressor may be a low-pressure compressor 4.
- the rotor 12 may comprise several rows of rotor blades 24.
- the low-pressure compressor 4 comprises at least one rectifier which contains an annular row of stator vanes 26. Each rectifier is associated with the fan 16 or a row of rotor blades 24 to straighten the air flow, so as to convert the speed of the flow into pressure.
- the compressor comprises at least one casing 28.
- the housing 28 may have a generally circular or tubular shape. It can be an external compressor casing and can be made of composite materials, which makes it possible to reduce its mass while optimizing its rigidity.
- the casing 28 may comprise fixing flanges 30, for example annular fixing flanges 30 for fixing the separation spout 22 and / or for fixing to an intermediate blower casing of the turbomachine.
- the casing then provides a function of mechanical connection between the separation spout 22 and the intermediate casing 32.
- the casing also ensures a centering function of the partition spout 22 with respect to the intermediate casing, for example by means of its annular flanges. .
- the annular flanges 30 may be composite and include attachment holes (not shown) to allow for bolt attachment, or lockbolts. Flanges 30 may include centering surfaces, such as centering holes.
- the housing 28 may comprise a wall 32 generally circular or arcuate, whose axial edges may be delimited by the flanges 30.
- the wall 32 may have a profile of revolution about the axis of rotation 14.
- the wall 32 may be of composite material, with a matrix and a reinforcement.
- the wall 32 may have an ogival shape, with a variation of radius along the axis 14.
- the housing may be formed of half-shells or half-casings, which are separated by an axial plane. The half-shells of the housing are connected by means of axial flanges.
- the stator vanes 26 extend essentially radially from the wall 32, at the level of annular regions for receiving vanes. These zones may comprise fixing means such as annular grooves, or fixing holes.
- the blades 26 can be fixed individually, or form segments of blades attached to the wall 32.
- the wall forms a mechanical link between several blades of different rows and / or the same row of blades.
- the stator vanes 26 each comprise a mounting platform 34, possibly provided with fixing pins 36 such as threaded rods or any other equivalent means.
- the wall may comprise annular layers of abradable material 38 between the platforms 34 of the blades, so as to form a barrier between the primary flow 18 and the wall 32.
- the casing 28, or at least its wall 32 may be made of a composite material.
- the composite material can be made using a fiber reinforcement pre-impregnated and cured by autoclave, or by injection.
- the injection may consist in impregnating a fibrous reinforcement with an optionally organic resin such as epoxy.
- the impregnation can be according to a method of RTM (acronym for Resin Transfer Molding) type.
- the fibrous reinforcement may be a woven preform, possibly three-dimensionally, or comprise a stack or a winding of different fibrous sheets or fibrous folds, which may extend over the wall, and on at least one or more flanges.
- the plies may comprise carbon fibers, and / or graphite fibers, and / or glass fibers to avoid galvanic corrosion, and / or Kevlar fibers, and / or carbotitanium fibers. Thanks to the evoked materials, a turbomachine casing can measure between 3 and 5 mm thick for a diameter greater than 1 meter.
- FIG. 3 represents a half-shell of the axial turbine casing, for example an external compressor casing, possibly low-pressure.
- the housing is seen axially from the upstream.
- the present teaching can be applied to any casing of the turbomachine, such as a fan casing or a turbine casing.
- the wall 32 has a curved inner surface 40.
- the 40 may comprise a continuous curvature along the circumference of the circular wall and / or in the axial direction.
- the inner surface 40 may be circular around the axis of rotation 14 of the turbomachine, and possibly opposite said axis.
- the wall 32, or at least the inner surface 40 may be annular, possibly generally tubular.
- the curvature of the inner surface 40 may be monotonous, and possibly constant.
- the curvature may vary axially, for example be more curved downstream.
- the inner surface 40 may be a conical surface portion, a spheroidal surface portion, possibly spherical, or a combination of each of these surfaces.
- the wall 32 may comprise facets 42, possibly arranged in at least one annular row along the circumference of the wall 32.
- Each facet 42 defines a flat surface.
- the facets 42 of a row can be regularly distributed angularly.
- the wall 32 may comprise several annular rows of facets 42 spaced axially along the length of the wall 32. At least one or each facet 42 is flush with the inner surface 40 of the wall. By flush it can be understood that a facet is level, and / or extends, and / or touches the inner surface.
- the facets 42 may have different shapes, possibly the facets of the same row have the same shape. Each row may have different shapes of facets.
- the facets 42 may have disc shapes, oval shapes. The average diameters of the facets 42 may vary progressively, they may increase toward the end of the wall 32 having a minimum diameter, which in the example illustrated in Figure 2 is the direction from upstream to downstream.
- the facets 42 of the same row may be distant from each other. They can then be separated by internal surface portions 40 which have continuous curvatures.
- Each facet 42 of the same row may be surrounded by the inner surface 40.
- the facets 42 of the same row may be tangent to each other, they may be in contact at the point of contact. Or, the facets of the same row can be truncated laterally. These facets can be joined according to joining lines 44.
- each facet 42 may comprise a fixing means, such as a fixing orifice 46, which can cooperate with a blade attachment axis.
- a fixing orifice 46 is disposed at the center of the associated facet.
- the fixing orifices 46 may be arranged in one or more annular rows. These can be distributed axially along the wall 32.
- At least one or each axial flange 48 may be integral with the wall 32, as at least one or each annular flange 30. Alternatively, at least one type of flange, or each flange may be attached to the wall .
- the wall may be composite and the flanges may be metallic and fixed to the wall.
- FIG. 4 represents a turbomachine blade, for example a stator vane 26 of a low-pressure compressor stator.
- Dawn can also be a turbine blade.
- the blade 26 comprises a body 50, or blade, forming a profiled surface intended to extend into the primary flow. Its shape makes it possible to modify the flow of the flow.
- the blade extends axially from a leading edge 60 to a trailing edge 62.
- the "lower” and “upper” faces connect the leading edge 60 to the trailing edge 62 and an average camber (noted 64 on Figure 5) is defined equidistant from these two faces.
- the platform 34 for fixing the blade 26 to the housing wall may have a general shape of plate. It may comprise at least one or two zones of lesser thickness 52, and possibly an area of extra thickness 54. The zone of extra thickness 54 may be surrounded by a zone of lesser thickness 52, or be placed between two zones of lesser thickness 52.
- the fixing pin 36 may extend opposite the blade 50 of the blade.
- the or each platform 34 comprises an outer radial bearing surface 56 intended to come opposite a facet.
- FIG. 5 represents a model of a blade platform seen from the outside radially (or seen from above with respect to the view of FIG. 4).
- the blade blade 50 which is on the other side of the platform 34 is shown in dashed line.
- Platform models can change from one row of blades to another.
- the platform 34 may have a general shape of a quadrilateral such as a parallelogram, a trapezium or a rectangle.
- the contour of the platform 34 comprises opposite lateral edges 58, possibly coming into contact with the adjacent lateral edges 58 of the other blades of the same row, and the upstream and downstream edges 59.
- the lateral edges 58 can be bent or arched to limit their rotation when tightening their fasteners.
- the platform 34 is made of metal, preferably titanium.
- It can also be in organic matrix composite. It may be integral with the body of the blade 26. To respect a precise shape, its contour is machined, possibly rectified to meet strict tolerances.
- the thickened area 54 may have a disk shape, the fixing pin 36 being optionally disposed in the center of the disk and / or the rectangle.
- the axis can be arranged eccentrically and not in the center of the platform.
- the center of the axis 36 may be at a distance of 20 to 50% of the axial dimension of the platform on the upstream side.
- the axis 36 may be circumscribed in the first half or the first upstream third of the platform.
- FIG. 6 represents a stator blade 26 fixed to the wall 32.
- the wall 32 may have a generally constant thickness, for example at least one or each facet 42. Its outer surface 70 may be curved at each facet 42, preferably with a continuous curvature and / or monotonically axially and / or circumferentially to the right of each facet 42. Alternatively, the outer surface 70 of the wall 32 may comprise a flat 72 at the level of at least one facet 42, preferably at the level of every facet. One or each flat 72 may be parallel to the associated facet 42. A flat 72 forms a flat surface, possibly smooth. It can form a discontinuity of the curvature of the outer surface 70. The flat surface provides a flat surface for a clamping means 74 of the fixing pin 36, preferably a nut 74 on a threaded pin 36.
- the outer radial surface 56 of the or each platform 34 faces the facet 42.
- This surface 56 and this face 42 facing can be parallel and of substantially similar dimensions.
- the surfaces 42, 56 can be inclined relative to each other.
- the surface 56 of the platform may not be flat.
- the area of extra thickness 54 comes into contact with the facet 42 and the axis 36 enters the orifice (noted 46 in FIG. 3) of the facet 42.
- the abradable 38 can be inserted between the surfaces 42 and 56.
- the abradable 38 may stop at the edges of the platform or be at axial distance thereof.
- the or each facet 42 forms a discontinuity in the inner surface 40.
- the contour of at least one or each facet 42 may form a breaking line of the curvature of the inner surface. All around each facet 42, the tangents of the inner surface may be inclined relative to the facet 42.
- the facets 42 may form flattenings in the inner surface 40, the flattening being inwardly.
- the wall has a continuity of matter between the facets and the inner surface, and possibly a geometric discontinuity.
- a seal 80 of elastic material to prevent air leakage between the platform and the housing.
- This seal encloses a pocket 68 delimited by the seal 80, the outer radial surface 56 of the platform 34 and the wall 32 of the casing.
- the illustrated example shows a casing with facets, the casing may not be provided with facets and the surface 56 therefore comes opposite the tubular or cylindrical wall 32.
- the seal can be made of bars. Its outer contour may correspond at least partially to the contour of the surface 56 and therefore be in the form of a polygon, in particular trapezoidal, parallelogram or rectangle. Three of the segments of the seal 82, 84, 86 forming the polygon are visible in FIG. 6. Alternatively, the seal may comprise planar portions.
- One or both surfaces 42 and 56 may have housings for example grooves to receive one or more segments of the seal 80.
- FIG. 7 details the seal 80 in this same embodiment.
- the seal 80 has a frame 81 composed of upstream segments 82 upstream and downstream 84 and axial outer segments 86, 88 forming a rectangle.
- the seal may further comprise a toric portion 90 preferably connected to the frame 81 by 90 ° segments, particularly in this example two axial segments 92, 94 and two circumferential segments 96, 98, that is to say which extend mainly along the circumference.
- the toric portion 90 can be connected to the frame 81 by means of a cross, in particular formed by the segments.
- the toric portion 90 is in the center of the seal 80. This can alternatively be offset on the upstream or downstream, that is to say in the direction of the segment 82 or 84 respectively.
- the toric portion 90 can also be shifted circumferentially, that is to say towards the segment 86 or the segment 88.
- the section of the circumferential segments 96, 98 is greater than the section of the segments 92, 94. If the segments are all of the same thickness - the thickness being their dimension in the radial direction which is perpendicular to the plane of Figure 7 -, the section of the circumferential segments 96, 98 is larger because of their dimension in the axial direction which is larger than the circumferential dimension of the segments 92, 94.
- the thickness of the downstream segment 84 of the frame 81 may be greater than the thickness of the upstream segment 82 of the frame 81.
- Figure 8 shows an isometric view of a seal 180 according to a second embodiment.
- the segments of the joint 180 are incremented by 100 with respect to that of FIG. 7.
- the O-ring portion 190 is connected to the frame 181 formed by the segments 182, 184, 186, 188 only by three segments 192, 196 and 198.
- This example shows in particular the variation of thickness Alongside the seal 180.
- the downstream segment 184 has in particular a greater thickness than the upstream segment 182. This allows a compression ratio of the seal 180 more important downstream when the surfaces 42 and 56 are parallel. This also allows the assembly of a seal between two surfaces 42 and 56 which are not parallel, the variable thickness of the seal "catching" the variable gap between the two surfaces 42 and 56.
- FIG. 10 illustrates a seal 280 according to a third embodiment.
- the segments of the gasket 280 are incremented by 100 relative to that of FIG. 8.
- the toric portion 290 has an oval shape and the latter is not arranged in the middle of the gasket but in the upstream half.
- the toric portion 290 is connected to the frame 281 by the circumferential segments 296, 298 and the axial segment 292.
- FIG. 10 illustrates this strip 284 and highlights the important variation thickness between upstream and downstream.
- the strip 284 can also be complementary to a downstream segment (such as segment 184 of the previous embodiment), the strip extending upstream or downstream of such a segment, possibly at a distance from it.
- the frame 281 is formed by the segments 282, 286, 288 and the strip 284.
- the joints of two adjacent platforms can come into contact with each other.
- the outer axial segments 86, 88, 186, 188, 286, 288 of two adjacent platform joints may be parallel and come into contact with each other.
- a platform may have one side of the contour parallel to one side of an adjacent platform and come into contact with this side.
- two or more adjacent joints may form a single joint 380 joint multiple platforms.
- This seal 380 comprises an upstream segment 382 and a downstream segment 384 common to several platforms.
- O-ring portions 390 are provided to circumcise each the attachment axis of the respective platforms and inner segments are provided to connect the O-ring portions 390 to the upstream 382 and downstream 384 segments.
- O-ring portions 390 and respective inner segments corresponds to the arrangement of the platforms.
- certain toric portions may be positioned at different locations axially, and the size of the joint portions facing a platform may be greater or smaller.
- the fact that the seal 380 is not symmetrical can serve as a key during assembly of the turbomachine.
- the seal can follow the polygonal contours of each of the adjacent blade platforms.
- the seal is formed of several frames 381 and two adjacent frames can share a segment in common.
- Such a seal 380 may cooperate with several blades of the annular row of blades, such as two or four adjacent blades, or all blades facing a half-casing.
- a seal may cooperate with a plurality of adjacent blades, at least one of which is attached to a half-casing and at least one other is attached to the other half-casing.
- the joint may also be common to all the blades of a row of blades and be in the form of a crown.
- FIGs 12 and 13 illustrate a seal 480, 580 according to the invention.
- This may have the various elements already described in the other embodiments (toric portion, tab, a single joint common to several platforms, etc.).
- the seal 480 has 483 thermoformed pads, made in the form of molding inserts. These pads 483 are preferably arranged at the frame 481 of the seal. Alternatively, one or more pads may be disposed at other locations of the seal 480. These pads may include a hole that can cooperate with pins provided on the platform. The pieces may be such that a tight assembly in the studs is obtained. This allows to pre-assemble the seal on the platform.
- the pads may alternatively be provided with a thread for receiving a threaded rod of the platforms.
- the pads are 2, 4 or 6.
- the pads may be of identical or different dimensions, particularly when the seal is thicker downstream as shown in Figure 12. Alternatively a single pad may also be provided on the seal .
- the adhesive element may be a glue spot or an adhesive layer 583, which may be covered with a cap 585.
- the cap 585 is removed from the seal 580, then the seal is positioned on the platform. To this end, the cap has a portion 587 not adherent to the adhesive means to facilitate its removal.
- the seal adheres to the platform and facilitates the mounting of the platform and its seal in the housing.
- the seal of the various embodiments illustrated above can be made completely of elastomer, polymer or foam.
- One or more of the segments may comprise a rigid wire (metallic or otherwise) in its core coated with elastomer, polymer or foam.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BE2017/5874A BE1025753B1 (fr) | 2017-11-30 | 2017-11-30 | Etancheite plateforme d’aube - carter dans un compresseur de turbomachine axiale |
PCT/EP2018/073321 WO2019105610A1 (fr) | 2017-11-30 | 2018-08-30 | Ensemble pour turbomachine axiale, turbomachine axiale, procédé d'assemblage et joint d'étanchéité associés |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3717749A1 true EP3717749A1 (fr) | 2020-10-07 |
EP3717749B1 EP3717749B1 (fr) | 2021-09-29 |
Family
ID=60781413
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18762286.5A Active EP3717749B1 (fr) | 2017-11-30 | 2018-08-30 | Ensemble pour turbomachine axiale, procédé d'assemblage et joints d'étanchéité associés |
Country Status (5)
Country | Link |
---|---|
US (1) | US11421539B2 (fr) |
EP (1) | EP3717749B1 (fr) |
CN (1) | CN111108265B (fr) |
BE (1) | BE1025753B1 (fr) |
WO (1) | WO2019105610A1 (fr) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3108674B1 (fr) | 2020-03-27 | 2022-03-11 | Safran Aircraft Engines | Assemblage a etancheite renforcee pour turbomachine d’aeronef, comprenant une roue aubagee de stator ainsi qu’un carter exterieur agence autour de la roue aubagee |
BE1029166B1 (fr) | 2021-03-03 | 2022-10-03 | Safran Aero Boosters | Carter pour compresseur de turbomachine |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2989130B1 (fr) * | 2012-04-05 | 2014-03-28 | Snecma | Etage redresseur de compresseur pour une turbomachine |
EP2738356B1 (fr) * | 2012-11-29 | 2019-05-01 | Safran Aero Boosters SA | Aube de redresseur de turbomachine, redresseur de turbomachine et procédé de montage associé |
EP2896796B1 (fr) * | 2014-01-20 | 2019-09-18 | Safran Aero Boosters SA | Stator de turbomachine axiale et turbomachine associée |
EP2930308B1 (fr) * | 2014-04-11 | 2021-07-28 | Safran Aero Boosters SA | Carter à facettes de turbomachine axiale |
EP2977559B1 (fr) * | 2014-07-25 | 2017-06-07 | Safran Aero Boosters SA | Stator de turbomachine axiale et turbomachine associée |
BE1022809B1 (fr) * | 2015-03-05 | 2016-09-13 | Techspace Aero S.A. | Aube composite de compresseur de turbomachine axiale |
US10208614B2 (en) * | 2016-02-26 | 2019-02-19 | General Electric Company | Apparatus, turbine nozzle and turbine shroud |
US10371166B2 (en) * | 2016-12-16 | 2019-08-06 | Pratt & Whitney Canada Corp. | Stator vane seal arrangement for a gas turbine engine |
-
2017
- 2017-11-30 BE BE2017/5874A patent/BE1025753B1/fr not_active IP Right Cessation
-
2018
- 2018-08-30 EP EP18762286.5A patent/EP3717749B1/fr active Active
- 2018-08-30 CN CN201880058337.4A patent/CN111108265B/zh active Active
- 2018-08-30 US US16/644,359 patent/US11421539B2/en active Active
- 2018-08-30 WO PCT/EP2018/073321 patent/WO2019105610A1/fr unknown
Also Published As
Publication number | Publication date |
---|---|
CN111108265A (zh) | 2020-05-05 |
CN111108265B (zh) | 2022-06-07 |
EP3717749B1 (fr) | 2021-09-29 |
US20210062662A1 (en) | 2021-03-04 |
BE1025753B1 (fr) | 2019-07-04 |
WO2019105610A1 (fr) | 2019-06-06 |
BE1025753A1 (fr) | 2019-06-27 |
US11421539B2 (en) | 2022-08-23 |
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