EP3899207A1 - Ensemble de turbomachine comprenant des aubes de soufflante à bord de fuite prolongé - Google Patents
Ensemble de turbomachine comprenant des aubes de soufflante à bord de fuite prolongéInfo
- Publication number
- EP3899207A1 EP3899207A1 EP19848803.3A EP19848803A EP3899207A1 EP 3899207 A1 EP3899207 A1 EP 3899207A1 EP 19848803 A EP19848803 A EP 19848803A EP 3899207 A1 EP3899207 A1 EP 3899207A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- extension
- assembly
- trailing edge
- radial
- 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
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 47
- 239000004606 Fillers/Extenders Substances 0.000 claims description 23
- 230000007704 transition Effects 0.000 claims description 14
- 125000006850 spacer group Chemical group 0.000 claims description 11
- 239000007789 gas Substances 0.000 claims description 10
- 239000002131 composite material Substances 0.000 description 5
- 239000011159 matrix material Substances 0.000 description 5
- 239000000853 adhesive Substances 0.000 description 4
- 230000001070 adhesive effect Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 4
- 230000002787 reinforcement Effects 0.000 description 4
- 210000003462 vein Anatomy 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 229920000642 polymer Polymers 0.000 description 3
- 238000009941 weaving Methods 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 230000000750 progressive effect Effects 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 238000001721 transfer moulding Methods 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013536 elastomeric material Substances 0.000 description 1
- 229920006332 epoxy adhesive Polymers 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 229910001026 inconel Inorganic materials 0.000 description 1
- 238000003780 insertion Methods 0.000 description 1
- 230000037431 insertion Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
- F05D2240/55—Seals
-
- 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
- F05D2300/10—Metals, alloys or intermetallic compounds
-
- 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
- the invention relates generally to the field of double-flow turbomachines, and more particularly that of the blowers of these turbomachines and their interaction with the inlet of the primary stream.
- a double-flow turbomachine generally comprises, from upstream to downstream in the direction of gas flow, a fan, an annular stream of primary flow and an annular stream of secondary flow.
- the mass of air sucked in by the blower is thus divided into a primary flow, which circulates in the primary flow vein, and in a secondary flow, which is concentric with the primary flow and circulates in the secondary flow vein.
- the primary flow stream passes through a primary body comprising one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more stages of turbines, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
- a primary body comprising one or more stages of compressors, for example a low pressure compressor and a high pressure compressor, a combustion chamber, one or more stages of turbines, for example a high pressure turbine and a low pressure turbine, and a gas exhaust nozzle.
- the blower includes a rotor disc carrying a plurality of blades, the feet of which are engaged and retained in substantially axial grooves formed at the periphery of the disc.
- the grooves are separated two by two by teeth.
- These blades are associated at their radially internal end with inter-blade platforms which are arranged in the extension of an inlet cone of the blower and are configured to delimit, on the interior side, the annular air inlet vein in the blower.
- the turbomachine comprises, immediately downstream of the blower, at the inlet of the primary stream, a part which can correspond, according to the embodiment of the blower, to a booster drum (for low pressure compressor in English ), which corresponds to the internal ferrule of the booster on which the rotating vanes of the booster are fixed, an internal ferrule of an IGV (English acronym for Inlet Guide Vane, i.e. the first stator stage of the booster in the primary body of a turbomachine) or a rotating spacer which is formed by an annular flange extending between the blower and the booster drum and which rotates at the same speed as the blower.
- a booster drum for low pressure compressor in English
- IGV International acronym for Inlet Guide Vane
- the internal shell of the IGV must be dimensioned so as to adopt an aerodynamically robust design.
- robust is meant that the shell must be able to withstand poor quality flows without creating excessive losses or detachments.
- the counterpart of this design is that the efficiency of the blading of such an IGV is lower than that of conventional IGVs. The presence of these cavities therefore degrades the functioning of the booster
- An objective of the invention is therefore to propose a turbomachine whose functioning of the booster is not degraded, by limiting or even eliminating the gas recirculations and the leakage rates downstream of the foot of the fan blades.
- the invention proposes an assembly of a turbomachine having an axis of revolution and comprising, from upstream to downstream in the direction of flow of the gases in the turbomachine, a fan and a part, the part extending immediately downstream of the blower and comprising an upstream edge separated from the blower by a cavity,
- blower comprising:
- a fan disc having a radial face configured to receive the blades, and a downstream face extending opposite the upstream edge of the part
- each platform being attached and fixed to the radial face, each platform being configured to cover the radial face and extend beyond the downstream face of the fan disc towards the upstream edge of the part so as to at least partially cover the cavity,
- the assembly being characterized in that the shield attached and fixed to the trailing edge of the blade is an extension of each fan blade and this extension extends beyond the downstream face of the fan disc towards the edge upstream of the part and at least partially covers the cavity.
- the part comprises a rotor, in particular a rotating spacer or a drum of a low pressure compressor.
- the part includes a stator, in particular an internal ferrule of an IGV.
- the assembly also includes an attached gasket fixed to the extension and configured to fill the cavity between the extension and the upstream edge of the part.
- the blade has an aerodynamic surface and all or part of the extenders extend from the adjacent platform of the blade, over a height less than a height of said aerodynamic surface, where the height of the aerodynamic surface corresponds to a dimension, according to an axis radial to the axis of revolution passing through the trailing edge, between said platform and a blade head and where the height of the extender corresponds to a dimension, along this radial axis, between the platform and an external radial face end of the extension.
- the part also has a radially external upstream end, configured to separate a primary flow entering the part from a secondary flow bypassing the part, and a first external radius corresponding to a radial distance between the radially external end upstream and l 'axis of revolution, the extension has a second external radius, corresponding to a radial distance between the external radial end face of the extension and the axis of revolution and the external radius of the extension being substantially equal to the external radius of the part.
- the extension has a nose, configured to extend the trailing edge of the blade axially downstream, said nose being more rounded than the trailing edge of the blade.
- the assembly further comprises, for each fan blade, a transition piece, fixed on an external radial face of the extension, said transition piece having an evolutive shape between an inner radial end, where the transition piece has a shape and a thickness substantially identical to that of the external radial face of the extension, and an external radial end, where the transition piece has a shape and a thickness substantially identical to that of the trailing edge of the blade.
- FIG. 1 illustrates an exemplary embodiment of an example of the assembly of a turbomachine according to the invention.
- Figure 2 is a cross-sectional view of an exemplary embodiment of a trailing edge of a fan blade that can be used in an assembly of a turbomachine according to the invention.
- FIG. 3 is a side view of an exemplary embodiment of a fan blade that can be used in an assembly of a turbomachine according to the invention.
- FIG. 4 is a partial and diagrammatic side view of a first embodiment of a fan blade and of the upstream edge of a part which can be used in an assembly of a turbomachine according to the invention.
- FIG. 5 is a partial and schematic side view of a second embodiment of a fan blade and of the upstream edge of a part which can be used in an assembly of a turbomachine according to the invention.
- the upstream and downstream are defined with respect to the normal direction of flow of the gas in the turbomachine 1.
- the axis of revolution of the turbomachine is called the axis X of radial symmetry of the turbomachine.
- the axial direction corresponds to the direction of the axis X of the turbomachine, and a radial direction is a direction perpendicular to this axis and passing through it.
- an axial plane is a plane containing the axis X of the turbomachine and a radial plane is a plane perpendicular to this axis X and passing through it.
- the tangential (or circumferential) direction is a direction perpendicular to the X axis and not passing through it.
- internal and external are used with reference to a radial direction so that the part or the face internal (ie radially internal) of an element is closer to the X axis than the part or the external face (ie radially external) of the same element.
- the part 3 may comprise a booster drum, an internal shroud of an IGV or a rotating spacer.
- the blower 2 comprises a blower disc 10 having an upstream face, a downstream face 14 and a radial face 12. It carries a plurality of blower blades 20 associated with inter-blade platforms 16 20. Axial grooves, separate two by two by teeth, are formed in the radial face 12 of the disc 10.
- the blades 20 are associated at their radially internal end with inter-blade platforms 16.
- Each platform 16 has an upstream end, configured to extend at the level of the upstream face of the fan disc 10, and a downstream end configured to come opposite the part 3 extending immediately downstream of the fan 2.
- the platform 16 delimits radially inside the flow path in the fan 2, so that each blade 20 has an aerodynamic surface corresponding to the part of the blade 20 extending in the gas flow.
- the radially inner limit of the aerodynamic surface is defined by the platform 16.
- the aerodynamic surface of the blade 20 has a main direction of extension, defining the extension axis Y of the blade 20 which is substantially radial to the axis of revolution X of the turbomachine.
- the aerodynamic surface also has a height H corresponding to a distance between a lower limit of the aerodynamic surface and a head 22 of the blade 20, at an intersection between the trailing edge 25 and the lower limit.
- the lower limit corresponds to the interface between the blade 23 and the adjacent platform 16.
- Each blade 20 has a foot 21 configured to be inserted in a groove of the fan disc 10, a head 22 (or top) and a blade 23 having a leading edge 24, a trailing edge 25, a lower surface wall 26 and a lower surface wall 27.
- the leading edge 24 is configured to extend opposite the flow of gases entering the turbomachine. It corresponds to the front part of an aerodynamic profile which faces the air flow and which divides the air flow into a lower surface flow and an upper surface flow.
- the trailing edge 25 it corresponds to the rear part of the aerodynamic profile, where the intrados and extrados flows meet.
- downstream face 14 of the fan disc 10 and the upstream edge 4 of the part 3 are separated by a functional clearance creating an annular cavity 6 opening into the flow stream.
- each platform 16 extends beyond the downstream face 14 of the fan disc 10, in the direction of the upstream edge 4 of the part 3.
- the downstream end of the platform 16 can be fixed on the upstream edge 4 of the piece 3.
- the piece 3 comprises a stator, typically an internal ferrule of an IGV
- the downstream end of the platform 16 extends opposite the upstream edge 4 of the piece 3 without coming into contact with that -this.
- each fan blade 20 has an extension 30, attached and fixed to the trailing edge 25 of its blade 23 and which extends beyond the downstream face 14 of the fan disc 10 in the direction of the upstream edge 4 of the part 3.
- the extension 30 therefore has the function of extending the trailing edge of the blade 23 beyond the downstream face 14 of the disc 10 to cover the at least partially the cavity 6.
- the extension 30 does not penalize for the mounting of the vanes 20 on the fan disc 10, since it does not block access to the grooves.
- the extension 30 therefore forms, in the zones of the vane 20 on which it is fixed, the trailing edge of the vane 20 since it is at its level that the intrados and extrados flows which bypass the vane 20 meet. , and no longer at the trailing edge 25 of the blade 23.
- the trailing edge 25 of the blade 23 also forms the trailing edge of dawn 20.
- the extension 30 can be attached and fixed to the trailing edge 25 of the blade 23 by any means, for example by gluing.
- the type of adhesive 40 chosen will depend on the material constituting the blade 23 and the extension 30.
- an epoxy adhesive 40 can be used in the case where the blade 23 and / or the extension 30 comprise a metal of the aluminum, titanium type. , Inconel, or a composite material comprising a fibrous reinforcement densified by a polymer matrix.
- the extension 30 is fixed on the trailing edge 25 of the blade 23 so as to come into contact with the platform 16, and more particularly its outer radial face. However, the extension 30 does not cover the entire trailing edge 25 of the blade 23. In other words, a height h of the extension 30 is less than the height H of the aerodynamic surface of the blade 20, knowing that the height h of the extender 30 corresponds to the dimension of the extender 30 between its internal and external radial faces 34, 35 along the axis Y. In this way, the extenders 30 do not unnecessarily penalize the mass of the blower 2 and extend only on the height necessary to maintain them on the blades 23 and cover the cavity 6.
- the extender 30 comprises a nose 31, configured to extend the trailing edge 25 of the blade 23 downstream, a lower surface wing 32 configured to partially cover the lower surface wall 26 of the blade 23 and an upper surface wing 33 configured to cover partially the upper surface 27 of the blade 23.
- the lower and upper wings 32, 33 therefore extend upstream, when the extension 30 is fixed on the blade 23, without reaching the leading edge 24 of the blade 23.
- the internal radial face 34 of the extension 30 is moreover configured to bear against the platform 16.
- each wing 32, 33 is chosen so as to ensure sufficient maintenance of the extender 30 on the blade 20.
- each wing of the extender 30 covers the blade 23 over a length of between 5% and 20% of a chord of the blade 23 at this point, where the chord corresponds to the distance between the leading edge 24 and the trailing edge 25 of the blade 23 at this point.
- the blade 20 therefore has an excess of rope at the level of the platform 16, this excess of rope being due to the presence of the extension 30.
- the extension 30 therefore creates a hunchbacked shape at the trailing edge of the blade 20 by relative to the trace of the trailing edge 25 of the blade 23 devoid of extension 30 (see the diagram in FIG. 3).
- the extension 30 extends to the upstream edge 4 of the part 3, without covering it.
- the extension 30 therefore covers well the cavity 6, but not the part 3.
- This embodiment is suitable for the part 3 to comprise a rotor (booster drum or rotating spacer) or a stator (internal ferrule of an IGV), since the extender 30 does not come into contact with the part 3.
- a rotor booster drum or rotating spacer
- a stator internal ferrule of an IGV
- this embodiment makes it possible to remove the rotating spacer.
- the initial function of a rotating spacer is to reduce the size of the cavity 6 between the inner shell of an IGV and the fan 2 in a turbomachine.
- extensions 30 on the blades 23 in combination with the platforms 16 which are dimensioned so as to cover the cavity 6 it is no longer necessary to reduce the size of the cavity 6 by adding such a spacer. turning. Consequently, the attachment of extenders 30 to the trailing edges of the blades 23 makes it possible to reduce the mass of the assembly 1 of the turbomachine by eliminating the rotating spacer as well as the associated fixing means (generally, an annular flange and a connection bolted).
- the extension 30 covers the upstream edge 4 of the part 3. In other words, the extension 30 cuts and crosses a plane radial to the axis of revolution and passing through the edge upstream 4 of part 3.
- This embodiment is more particularly suitable when the part 3 comprises a rotor (booster drum or rotating spacer), the relative movements between the extender 30 and the rotor being reduced.
- a rotor booster drum or rotating spacer
- the blower 2 may further comprise a seal 7, attached and fixed to the extension 30 and configured to fill the cavity 6.
- the seal 7 is configured to come into the field with the upstream edge 4 of the part 3.
- the seal 7 is fixed on the extension 30 so as to extend between the extension 30 and the upstream edge 4 of the part 3, being housed in the cavity 6.
- the seal 7 is fixed on the internal radial face 34 of the extension 30, in the zone of the extension 30 which covers the cavity 6. In other words, the seal 7 is fixed on the part of the extension 30 which projects from the downstream face 14 of the fan disc 10.
- the seal 7 is preferably made of an elastomeric material, for example rubber.
- the seal 7 can only be fixed against the internal radial face 34 of the extension 30, without covering the lower and upper surfaces 26, 27 of the blade 23 nor the lower and upper wings 32, 33.
- the seal 7 can on the contrary partially cover the lower and upper walls 26, 27 in order to provide a seal for said walls 26, 27.
- the seal 7 then extends under the platform 16, that is to say outside the vein of flow.
- the part of the seal 7 which is fixed to the extension 30 and the part of the seal 7 which partially covers the lower and upper surfaces 26, 27 may be in one piece, or alternatively comprise two separate seals 7.
- the seal 7 arrives in the field with the downstream end of the nose 31 of the extension 30, in order to guarantee a sufficient seal between the fan disc 10 and the part 3.
- the seal 7 can extend to the downstream end of the nose 31 of the extension 30, without however exceeding it, as illustrated in FIG. 5. If necessary, the seal 7 can have an additional thickness at the cavity 6, in order to fill said cavity 6, and a thinned zone in the part configured to come opposite, or even bear, against the upstream edge 4 of the part 3.
- the fixing of an extension 30 added and fixed to the trailing edge 25 of the blade 23 has the advantage of making it possible to produce this extension 30 in a material distinct from that of the rest of the blade 23.
- the extension 30 does not play in effect not a structural role, so that the stresses it is likely to undergo are different from those undergone by the blade 23. It can therefore have a lower modulus of elasticity than the material of the blade 23 and / or lower density.
- the blade 23 is made of a composite material comprising a fibrous reinforcement densified by a matrix, in particular a polymer matrix.
- the fibrous reinforcement is generally formed from a fibrous preform obtained by three-dimensional weaving with progressive thickness, the matrix then being injected under vacuum using processes of the RTM type (for “Resin Transfer Molding”), or else VARRTM (for Vacuum Resin Transfer Molding).
- RTM Resin Transfer Molding
- VARRTM Vacuum Resin Transfer Molding
- this technology does not make it possible to directly obtain, at the outlet of the mold, a trailing edge 25 whose thickness is thin and rounded.
- the trailing edge 25 is generally truncated and has a substantially angular section which promotes cracks and harms the general acoustics of the blower 2.
- the attachment of the extension 30 to the trailing edge 25 allows therefore to cover this angular trailing edge 25 with an envelope made of a different material, so that its shape can be more easily controlled.
- the extension 30 can be made of metal.
- the extension 30 can be made of aluminum, insofar as this metal is of low density.
- its Young's modulus is not too high, which makes it possible to limit the shear stresses in the adhesive 40 at the interface between the blade 23 and the extension 30.
- the extension 30 can be made of a composite material comprising a two-dimensional fabric reinforced with a polymer matrix in order to limit the shear stresses in the adhesive 40 between the blade 23 and the extension 30.
- the extension 30 is simply obtained by successive draping of ribbons or filamentary deposit and / or comprises short fibers making it possible to achieve thinner thicknesses.
- the blade 23 is made of composite material comprising a fibrous reinforcement produced from a fibrous preform obtained by three-dimensional weaving with progressive thickness, it also becomes possible to obtain a blade 20 whose trailing edge 25 is thin and rounded , as opposed to the angular and thick trailing edges which can be obtained with current three-dimensional weaving technologies.
- the extender 30 therefore also makes it possible to reduce the thickness of the wakes of the blade 20 of fan 2 and therefore the performance of fan 2, but also to improve the flow at the inlet of the booster and of its first stage of rectifiers in making the flow more homogeneous, in addition to improving the seal between the blower 2 and the part 3.
- the aerodynamic sections of the blades 20 of fan 2 being thinner towards the head 22 of the blade 20, it is not necessary to apply the extender 30 over the entire height H of the aerodynamic surface.
- the extension 30 therefore preferably extends between the line for separating the primary and secondary flows and the platform 16, so that only the flow entering the primary body (the booster) benefits from the thinning of the trailing edge 25 of the blade 20 thanks to the extender 30.
- the external radius R2 of the extender 30, corresponding to the distance between the external radial face 35 of the extender 30 and the axis X of revolution, in a radial plane, is therefore substantially equal ( to within 10%) at the external radius R1 of the part 3, corresponding to the distance between the radially external end 5 of the part 3 most upstream of the part 3 (that is to say at the level of the line flow separation) and the X axis of revolution.
- the extension 30 can be attached and fixed to the trailing edge 25 of the blade 23 using conventional techniques for attaching a structural shield to a blade 23 made of composite material. Thus, a routing of the lower and upper walls 26, 27 of the blade 23 can be carried out in order to facilitate the assembly of the extension 30 (see FIG. 2). The extension 30 is then attached and fixed to the machined parts of the blade 23 using an adhesive 40.
- transition between the extension 30, whose nose 31 is rounded and has a small thickness in comparison with the trailing edge 25 of the blade 23, and the angular trailing edge 25 of the blade 23 can be achieved using 'a transition piece 8, fixed between the outer radial face 35 of the extension 30 and the blade 23.
- This transition piece 8 therefore has an evolutive shape between its inner radial end, where the transition piece 8 has a shape and a thickness substantially identical to those of the external radial face 35 extension 30, and an external radial end, where the transition piece 8 has a shape and a thickness substantially identical to those of the blade 23.
- the transition piece 8 can be integrated directly into the extension 30 or alternatively be attached and fixed thereto.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1873734A FR3090733B1 (fr) | 2018-12-21 | 2018-12-21 | Ensemble de turbomachine comprenant des aubes de soufflante à bord de fuite prolongé |
PCT/FR2019/053234 WO2020128384A1 (fr) | 2018-12-21 | 2019-12-20 | Ensemble de turbomachine comprenant des aubes de soufflante à bord de fuite prolongé |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3899207A1 true EP3899207A1 (fr) | 2021-10-27 |
EP3899207B1 EP3899207B1 (fr) | 2022-07-27 |
Family
ID=68281472
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19848803.3A Active EP3899207B1 (fr) | 2018-12-21 | 2019-12-20 | Ensemble de turbomachine comprenant des aubes de soufflante à bord de fuite prolongé |
Country Status (5)
Country | Link |
---|---|
US (1) | US11473430B2 (fr) |
EP (1) | EP3899207B1 (fr) |
CN (1) | CN113423921B (fr) |
FR (1) | FR3090733B1 (fr) |
WO (1) | WO2020128384A1 (fr) |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7144221B2 (en) * | 2004-07-30 | 2006-12-05 | General Electric Company | Method and apparatus for assembling gas turbine engines |
US8016561B2 (en) * | 2006-07-11 | 2011-09-13 | General Electric Company | Gas turbine engine fan assembly and method for assembling to same |
JP5370046B2 (ja) * | 2009-09-25 | 2013-12-18 | 株式会社Ihi | 航空機エンジン用ファン |
US9121294B2 (en) * | 2011-12-20 | 2015-09-01 | General Electric Company | Fan blade with composite core and wavy wall trailing edge cladding |
US9399922B2 (en) * | 2012-12-31 | 2016-07-26 | General Electric Company | Non-integral fan blade platform |
US20160003060A1 (en) * | 2013-03-07 | 2016-01-07 | United Technologies Corporation | Hybrid fan blades for jet engines |
GB201408824D0 (en) * | 2014-05-19 | 2014-07-02 | Rolls Royce Plc | Fan disc |
US10099434B2 (en) * | 2014-09-16 | 2018-10-16 | General Electric Company | Composite airfoil structures |
US9745851B2 (en) * | 2015-01-15 | 2017-08-29 | General Electric Company | Metal leading edge on composite blade airfoil and shank |
FR3038653B1 (fr) * | 2015-07-08 | 2017-08-04 | Snecma | Assemblage d'une plateforme rapportee d'aube de soufflante sur un disque de soufflante |
US10730112B2 (en) * | 2016-08-02 | 2020-08-04 | Raytheon Technologies Corporation | Micro lattice hybrid composite fan blade |
EP3409892B1 (fr) * | 2017-05-31 | 2020-07-15 | Ansaldo Energia Switzerland AG | Pale de turbine à gaz comprenant des ailettes pour compenser des forces centrifugales |
-
2018
- 2018-12-21 FR FR1873734A patent/FR3090733B1/fr active Active
-
2019
- 2019-12-20 CN CN201980091919.7A patent/CN113423921B/zh active Active
- 2019-12-20 US US17/416,897 patent/US11473430B2/en active Active
- 2019-12-20 WO PCT/FR2019/053234 patent/WO2020128384A1/fr unknown
- 2019-12-20 EP EP19848803.3A patent/EP3899207B1/fr active Active
Also Published As
Publication number | Publication date |
---|---|
US11473430B2 (en) | 2022-10-18 |
WO2020128384A1 (fr) | 2020-06-25 |
EP3899207B1 (fr) | 2022-07-27 |
FR3090733B1 (fr) | 2020-12-04 |
FR3090733A1 (fr) | 2020-06-26 |
CN113423921A (zh) | 2021-09-21 |
CN113423921B (zh) | 2023-03-24 |
US20220056803A1 (en) | 2022-02-24 |
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