Verfahren zur Belichtung eines dreidimensionalen Bereichs

Verfahren zur Belichtung eines dreidimensionalen Bereichs (1), wobei der dreidimensionale Bereich in zumindest zwei aufeinanderfolgende Schichten (2) unterteilt wird, die in zeitlicher Abfolge belichtet werden, wobei jede Schicht (2) in zumindest zwei Belichtungsfelder (3) mit zumindest einem ersten Teilbereich (4), einem zweiten Teilbereich (4'), gegebenenfalls einem dritten Teilbereich (4'') sowie gegebenenfalls weiteren Teilbereichen unterteilt wird, wobei benachbarte Belichtungsfelder (3) in einzelnen Teilbereichen (4', 4'') zur Vermeidung fehlbelichteter Gebiete überlappen.

Device For Processing Photo-Polymerizable Material For Layer-By-Layer Generation Of A Shaped Body

A device for processing of highly viscous photopolymerizable material for layer-by-layer generation of a shaped body comprises a vat including a bottom which is at least in certain areas thereof transparent, a build platform, an exposure unit for exposing a material layer formed between the lower side of the build platform and the vat bottom in a locally selective manner, a control unit in order to adapt the relative position of the build platform to the vat bottom after each exposure step for a layer, in order to successively build up the shaped body in the desired shape, and a moveably guided doctor blade arrangement including a drive unit for moving the doctor blade arrangement back and forth underneath the build platform. The doctor blade arrangement comprises two doctor blades spaced apart in movement direction, which doctor blades are moveable at a constant distance to the vat bottom along the bottom. The vat includes vat end walls such that the doctor blade leading in movement direction in each case moves towards one of the vat end walls. Between the two doctor blades a chamber is formed which is open at its lower side, wherein walls of the chamber include at least one opening extending through the wall in movement direction for forming an overflow channel, so that material piling up between the leading doctor blade and the facing vat end wall is pressed through they at least overflow channel into the chamber. 1. Device for processing highly viscous photopolymerizable material for layer-by-layer generation of a shaped body comprisinga vat having a bottom which is at least in a subregion thereof transparent, into which vat photopolymerizable material can be filled,a build platform which is held at an adjustable height over the vat bottom,an exposure unit controllable for exposing in a locally selective manner a material layer formed between a lower side of the build platform and the vat bottom, said exposing being from below through the vat bottoma control ...

Device for processing photo-polymerizable material for layer-by-layer generation of a shaped body

A device for processing of highly viscous photopolymerizable material for layer-by-layer generation of a shaped body comprises a vat including a bottom which is at least in certain areas thereof transparent, a build platform, an exposure unit for exposing a material layer formed between the lower side of the build platform and the vat bottom in a locally selective manner, a control unit in order to adapt the relative position of the build platform to the vat bottom after each exposure step for a layer, in order to successively build up the shaped body in the desired shape, and a moveably guided doctor blade arrangement including a drive unit for moving the doctor blade arrangement back and forth underneath the build platform. The doctor blade arrangement comprises two doctor blades spaced apart in movement direction, which doctor blades are moveable at a constant distance to the vat bottom along the bottom. The vat includes vat end walls such that the doctor blade leading in movement direction in each case moves towards one of the vat end walls. Between the two doctor blades a chamber is formed which is open at its lower side, wherein walls of the chamber include at least one opening extending through the wall in movement direction for forming an overflow channel, so that material piling up between the leading doctor blade and the facing vat end wall is pressed through they at least overflow channel into the chamber.

METHOD FOR EXPOSING A THREE-DIMENSIONAL REGION

A method for illuminating a three-dimensional area (), the three-dimensional area being divided into at least two successive layers (), which are illuminated temporally sequentially, each layer () being divided into at least two illumination fields () with at least one first subarea (), one second subarea (′), if appropriate a third subarea (″) and if appropriate further subareas, wherein adjacent illumination fields () overlap in individual subareas (″) to avoid defectively illuminated regions. 11223444344. A method for illuminating a three-dimensional area () , the three-dimensional area being divided into at least two successive layers () , which are illuminated temporally sequentially , each layer () being divided into at least two illumination fields () with at least one first subarea () , one second subarea (′) , if appropriate a third subarea (″) and if appropriate further subareas , wherein adjacent illumination fields () overlap in individual subareas (′ , ″) to avoid defectively illuminated regions.2444. The method according to claim 1 , wherein to avoid over-illumination claim 1 , the average illumination intensity in the overlapping subareas (′ claim 1 , ″) is lower than in the non-overlapping subareas ().3442. The method according to claim 2 , wherein the illumination intensity in the overlapping subareas (′ claim 2 , ″) of adjacent layers () is different.444. The method according to claim 3 , wherein the illumination intensity in the overlapping subareas (′ claim 3 , ″) varies in one or two location coordinates claim 3 , so that the illumination intensity in these areas is dependent on location.544. The method according to claim 3 , wherein in individual overlapping subareas (′) claim 3 , a locally constant illumination intensity is provided claim 3 , and a locally variable illumination intensity is provided in other overlapping subareas (″).64423. The method according to claim 3 , wherein the illumination intensity in the overlapping subareas (′ claim ...

PROFILED STRUCTURE AND ASSOCIATED TURBOMACHINE

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions. 1. A profiled air flow structure comprising:a body;porous acoustically absorbent regions;an upstream leading edge and/or a downstream trailing edge; andalong the upstream leading edge and/or the downstream trailing edge line, a serrated profile line showing a succession of teeth and depressions,wherein the porous acoustically absorbent regions locally form bottoms for the depressions where the porous acoustically absorbent regions occupy a part of the body to define, together with the body, the serrated profile line at the upstream leading edge and/or the downstream trailing edge.2. The profiled structure according to further comprising: along the chord, the serrated profile line has a maximum amplitude, h, and', {'br': None, 'i': 'd=h/', '10, within 30%.'}, 'the porous acoustically absorbent region has a geometric centre located at a distance d downstream of the upstream leading edge or upstream of the downstream trailing edge, at the bottom of the depressions such that], 'between upstream and downstream, a chord in which3. The profiled structure according to further comprising: along the upstream leading edge or the downstream trailing edge, the serrated profile line has a distance between two consecutive tooth tips,', 'along the chord, the serrated profile line has a maximum amplitude, h, and', along the upstream leading edge and/or the downstream trailing edge, two limits separated by a distance a such that a is equal to one third of said distance between two consecutive tooth tips, to within 30%,', 'along the chord, two limits separated by a distance b such that b=h/3, within 30%., 'the porous acoustically absorbent region has], 'between ...

AIRCRAFT PROPULSION UNIT COMPRISING AN UNDUCTED-FAN TURBINE ENGINE AND AN ATTACHMENT PYLON

A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection. 1. A propulsion assembly for aircraft , the assembly comprising:a turbojet having at least one unducted propulsion propeller; andan attachment pylon for attaching the turbojet to a structural element of the aircraft, said pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge;wherein the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, said cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection.2. The propulsion assembly according to claim 1 , wherein the trailing edge of the airfoil of the pylon presents a geometrical profile that is curved.3. The propulsion assembly according to claim 1 , wherein the cutout of the trailing edge of the airfoil of the pylon extends longitudinally over the trailing edge between a point of the trailing edge situated at less than 80% of the height of the propeller and a point of the trailing edge situated at more than 110% of the height of the ...

PROPULSION ASSEMBLY FOR AN AIRCRAFT HAVING A TURBOJET WITH A NON-DUCTED FAN AND AN ATTACHMENT PYLON

A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented. 1. A propulsion assembly for an aircraft , the assembly comprising:a turbojet having at least one unducted propulsive propeller; andan attachment pylon for attaching the turbojet to a structural element of the aircraft, said attachment pylon being positioned on the turbojet upstream from the unducted propulsive propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge;wherein the attachment pylon has a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, said blow nozzles being positioned over at least a fraction of the trailing edge of the attachment pylon that extends longitudinally facing at least a portion of the unducted propulsive propeller.2. A propulsion assembly according to claim 1 , wherein the blow nozzles open out in line with the trailing edge of the attachment pylon.3. A propulsion assembly according to claim 1 , wherein the blow nozzles open out in one and/or both of the side faces of the attachment pylon.4. A propulsion assembly ...

PROFILED STRUCTURE FOR AN AIRCRAFT OR TURBOMACHINE FOR AN AIRCRAFT

The invention relates to a profiled structure, 2. A profiled structure according to claim 1 , wherein the successive scaling varies so that said geometric pattern evolves homothetically.3. A profiled structure according to claim 1 , wherein a series of at least three consecutive peaks and three troughs claim 1 , starting from said part of the length which is free of serrations claim 1 , has an increasing distance claim 1 , along said direction of elongation claim 1 , between two tops of consecutive peaks or troughs.4. A profiled structure according to claim 2 , wherein a series of at least three consecutive peaks and three troughs claim 2 , starting from said part of the length which is free of serrations claim 2 , has an increasing distance claim 2 , along said direction of elongation claim 2 , between two tops of consecutive peaks or troughs.5. A set of profiled structures claim 1 , each according to claim 1 , whose respective directions of elongation radially extend about an axis of revolution claim 1 , and whose said distance and/or said amplitude of the serrations is greater at a radially outer end of the length exposed to an airflow than at a radially inner end of this length.6. A set of profiled structures claim 2 , each according to claim 2 , whose respective directions of elongation radially extend about an axis of revolution claim 2 , and whose said distance and/or said amplitude of the serrations is greater at a radially outer end of the length exposed to an airflow than at a radially inner end of this length.7. A set of profiled structures claim 3 , each according to claim 3 , whose respective directions of elongation radially extend about an axis of revolution claim 3 , and whose said distance and/or said amplitude of the serrations is greater at a radially outer end of the length exposed to an airflow than at a radially inner end of this length.8. A turbomachine comprising a rotor and a stator claim 1 , the stator and/or rotor comprising profiled ...

MODULATION OF VANE END SERRATIONS

A stator vane including a vane root, a vane tip, a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness, wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness. 1. A stator vane comprising:a vane root,a vane tip,a leading edge extending between the root and the tip, the leading edge having a serrated profile having a succession of teeth and of troughs each having an amplitude and a thickness,wherein a series of at least three teeth and three consecutive troughs starting from the vane root and/or from the vane tip have a growing amplitude and/or thickness.2. The vane according to claim 1 , wherein the series comprises at least four teeth and four troughs or extends between 20 and 50% of the length of the vane.3. The vane according to claim 1 , wherein the serrated profile is sinusoidal and wherein claim 1 , within the series the amplitude and/or the thickness of the teeth and of the troughs is combined with a linear claim 1 , parabolic claim 1 , sinusoidal or exponential function.4. The vane according to claim 1 , wherein the serrated profile is expressed in the following form:{'br': None, 'i': c', 'r', 'c', '+h', 'r, 'sub': '0', '()=·sin(2π/λ)'}{'sub': '0', 'wherein cis the reference chord, h the amplitude and λ the wavelength of the undulations and r the radius'}{'sub': '0', 'and wherein, within the series, the amplitude and/or the thickness of the teeth and of the troughs is combined with a linear function so that the profile is expressed within said series: c(r)=c+h·sin(2πr/λ)·K·r'}where K is a constant,or {'br': None, 'i': c', 'r', 'c', '+h', 'r', 'L·r', 'L, 'sub': '0', 'sup': '2', '()=·sin(2π/λ)·where is a constant,'}, 'a parabolic function so that the profile is expressed within said seriesor {'br': None, 'i': c', 'r', 'c', ...

HIGH-THROUGHPUT, HIGH-PRECISION METHODS FOR DETECTING PROTEIN STRUCTURAL CHANGES IN LIVING CELLS

Methods for identifying a compound that alters fluorescence resonance energy transfer (FRET) of a protein. The methods include use of a genetically engineered cell that includes a target protein. The target protein includes one or more heterologous domains. In one embodiment, a target protein includes two heterologous domains, and in another embodiment, the target protein includes a heterologous domain and the cell further includes a second protein that includes a heterologous domain. A heterologous domain may include a chromophore or an amino acid to which a fluorescent dye attaches. The fluorescence lifetime of one or more chromophore, one or more fluorescent dye, or the combination thereof, is measured after contacting the cell with a compound A difference between the fluorescence lifetime in the presence of the test compound and the fluorescence lifetime in the absence of the test compound indicates that the test compound alters the FRET of the target protein. 1. A method for identifying a compound that alters fluorescence resonance energy transfer (FRET) of a protein comprising: 'wherein the target protein comprises two heterologous domains, wherein a first heterologous domain comprises a first chromophore, and wherein a second heterologous domain comprises a second chromophore;', 'providing a genetically engineered cell comprising a target protein,'}contacting the cell with a test compound to form a mixture; and wherein the measuring occurs over a period of time no greater than 0.5 seconds,', 'wherein the coefficient of variation (CV) is no greater than 0.5%, and', 'wherein a difference between the fluorescence lifetime in the presence of the test compound and the fluorescence lifetime in the absence of the test compound indicates that the test compound alters the FRET of the target protein., 'measuring the fluorescence lifetime of the first chromophore, the second chromophore, or the combination thereof,'}2. The method of wherein the fluorescence lifetime of ...

VARIABLE PITCH BLADED DISC

A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination. 1. A bladed wheel with variable pitches comprising:a plurality of blades, each with a variable pitch along an axis of rotation of a blade and each having a root, the plurality of blades comprising at least one first blade and at least one second blade,a plurality of rotor connection shafts, each shaft having a root and a head, the root of each blade being mounted on the head of a corresponding rotor connection shaft through a pivot so as to allow the rotation of each blade along the blade rotation axis,wherein the first blade has a first tilt of the axis of rotation, such that the blade rotation axis of the first blade is tilted in a fixed way with respect to a radial axis of the bladed wheel passing through the root of the corresponding shaft, and the second blade has a second tilt of the axis of rotation different from the first tilt of the axis of rotation.2. The bladed wheel according to claim 1 , wherein the first tilt of the axis of rotation comprises a tangential tilt component in the plane of the bladed wheel.3. The bladed wheel according to claim 1 , wherein the first tilt of the axis of rotation comprises a tilt component towards the upstream or the downstream side with ...

Device for Processing Photopolymerizable Material in Order to Construct a Shaped Body Layer by Layer

The method for processing photopolymerizable material for the layered construction of a shaped body comprises 123-. (canceled)24. A method for processing photopolymerizable material for the layered construction of a shaped body , comprisinga) providing a tank having a bottom transparent at least in some region thereof, in which the photopolymerizable material is contained, wherein the photopolymerizable material has a viscosity of at least 20 Pa·s at room temperature (20° C.), and the photopolymerizable material forming a layer in the tank;b) moving a construction platform to such a height that a layer of the photopolymerizable material with a specified thickness is defined between the lower side of the construction platform or, if already present, the lowermost cured layer of the part of the shaped body formed thereon and the tank bottom;c) exposing the layer from below through the tank bottom by position-specific exposure to light so as to cure the material layer in the desired shape; andd) repeating steps b) and c) until the last layer of the shaped body is formed,{'b': 6', '6', '2', '2', '2, 'wherein before b) the method includes heating the layer of the photopolymerizable material () in the tank to a temperature of at least 30° C. so as to lower its viscosity, characterized in that heating of the layer of the photopolymerizable material (), and optionally maintaining of the temperature, is effected by the input of heat over a large area and directly on the tank bottom () and only in a process zone, in particular by at least one heating element disposed on or in the tank bottom (), e.g. heating films, the process zone comprising the region between the transparent tank bottom () and the shaped body being constructed.'}256. A method according to claim 24 , characterized in that the temperature of the photopolymerizable material () is maintained at a temperature of at least 30° C. during steps b) claim 24 , c) claim 24 , and d).266. A method according to claim 24 , ...

VARIABLE PITCH BLADED DISC

A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination. 1. A bladed wheel with variable pitches comprising:a plurality of blades each with a variable pitch along an axis of rotation of a blade and each having a root, the plurality of blades comprising at least one first blade and at least one second blade,a plurality of rotor connection shafts, each shaft having a root and a head, the root of each blade being mounted on the head of a corresponding rotor connection shaft through a pivot so as to allow the rotation of each blade along the blade rotation axis,wherein the first blade has a first blade tilt, such that the first blade is tilted in a fixed way with respect to the blade rotation axis of the first blade, and the second blade has a second blade tilt different from the first blade tilt.2. The bladed wheel according to claim 1 , wherein each shaft corresponding to a first blade has a joint tilting the head of the shaft with respect to the remainder of the shaft claim 1 , and thus tilting the first corresponding blade according to the first tilt of the axis of rotation.3. The bladed wheel according to claim 1 , wherein the first blade and the second blade have the same geometrical shape.4. The bladed wheel according to claim 1 , wherein the first blade has a first tilt of the axis of ...

BAFFLE

A baffle or reinforcement element for sealing and/or reinforcing a cavity, in particular a cavity of a vehicle, comprising: a carrier plate with a first plate surface and a second plate surface, and at least a first and a second expandable element, in particular expandable foam element, supported by the carrier plate, wherein the first expandable element covers, at least substantially, the entire first plate surface and forms a first outer surface of the baffle or reinforcement element and the second expandable element covers, at least substantially, the entire second plate surface thereby forming a second outer surface of the baffle element. 1. A baffle or reinforcement element for sealing and/or reinforcing a cavity , comprising:a carrier plate with a first plate surface and a second plate surface, and a first and a second expandable element, supported by the carrier plate,wherein the first expandable element covers, at least substantially, the entire first plate surface and forms a first outer surface of the baffle or reinforcement element and the second expandable element covers, at least substantially, the entire second plate surface and forms a second outer surface of the baffle element.2. The baffle or reinforcement element of claim 1 , wherein the first and/or second expandable element covers at least parts of an edge area of the carrier plate.3. The baffle or reinforcement element of claim 1 ,{'sup': '2', 'wherein a weight of the first and/or second expandable element per surface area of the carrier plate is more than 0.05 g/cm.'}4. The baffle or reinforcement element of claim 1 , wherein a thickness of the carrier plate is more than 1.0 mm.5. The baffle or reinforcement element of claim 1 , wherein at least part of the edge area of the carrier plate is kept free from any expandable material.6. The baffle or reinforcement element of claim 1 , wherein the carrier plate is free from any through-holes.7. The baffle or reinforcement element of claim 1 , wherein ...

TURBOMACHINE WITH MULTI-DIAMETER PROPELLER

A turbomachine including at least two unducted propellers, one of which is an upstream propeller and one a downstream propeller, the upstream propeller including a plurality of blades, at least one first blade of which has a different length from that of a second blade. 1. A turbomachine comprising at least two unducted propellers including one upstream propeller and one downstream propeller , the upstream propeller comprising a plurality of blades at least one first blade of which has a tip radius different from at least one second blade.2. The turbomachine according to claim 1 , wherein two consecutive blades of the upstream propeller have different tip radii.3. The turbomachine according to claim 1 , wherein the blades of the upstream propeller are divided into n∈2;+√[ groups of blades with equal tip radius claim 1 , including at least one group of first blades and at least one group of second blades.4. The turbomachine according to claim 3 , wherein all the groups of blades have different blade tip radii.5. The turbomachine according to claim 3 , wherein all the groups of blades comprise an equal number of blades.6. The turbomachine according to claim 5 , wherein the blades are positioned around the upstream propeller so that each sub-assembly of n consecutive blades comprises one blade from each group.7. The turbomachine according to claim 3 , wherein the upstream propeller comprises 2kn claim 3 ,k∈* claim 3 , blades claim 3 , two diametrically opposed blades on the upstream propeller belonging to the same group.8. The turbomachine according to claim 3 , wherein the upstream propeller comprises (2k+1)n claim 3 , k∈ claim 3 , blades claim 3 , the turbomachine comprising at least one counterweight positioned diametrically opposite to a first blade.9. The turbomachine according to claim 3 , wherein the number n of groups of blades is two or three.10. The turbomachine according to claim 1 , wherein said second blade is a truncated first blade.11. The turbomachine ...

Device for forming dimensionally stable objects

The invention relates to a device for forming dimensionally stable objects through section-by-section solidification of a dimensionally unstable substance ( 3 ), in particular one that can be hardened by light, by means of exposure to radiation from a radiator ( 4 ), in particular an electromagnetic radiator, comprising a trough ( 2 ) for receiving the substance ( 3 ) as well as a construction platform ( 1 ) which is arranged above the trough ( 2 ) and can be lowered and lifted with respect to the trough for adhering to and lifting solidified substance layers ( 5 ), at least one light source ( 6 ) and at least one light sensor ( 7 ) detecting the light of the light source ( 6 ) being arranged in the area of the bottom of the trough ( 2 ) in such a way that a deformation of the trough ( 2 ) can be detected by changing the light intensity of the light source ( 6 ) detected by the light sensor ( 7 ).

TURBINE ENGINE WITH A FLOW SPLITTER HAVING A PROFILE WITH INCLINED SERRATIONS

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile. The serrated profile has a succession of teeth and depressions, characterized in that, along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location. 1. A turbomachine for an aircraft , the turbomachine comprising:a general axis about which rotating parts of the turbomachine rotate, the rotating parts including blades of a front fan;an annular airflow dividing wall for an air flow, the annular airflow dividing wall having a leading edge and arranged downstream of the front fan, the annular airflow dividing wall separating the air flow into a primary flow and a secondary flow;first guide vanes for guiding the primary flow in the turbomachine, each first guide vane having a leading edge;second guide vanes for guiding the secondary flow in the turbomachine, each second guide vane having a leading edge, the first guide vanes for guiding the primary flow and the second guide vanes guiding the secondary flow being connected to the annular airflow dividing wall; anda serrated leading edge profile including a succession of teeth and depressions, and such that, along the leading edge, from a first location to a second location, the teeth of the serrated leading edge profile are individually inclined towards the second location, wherein:a) the teeth are, circumferentially around said general axis and downstream of the front fan, individually inclined towards a generally oblique orientation of the air flow with respect to said general axis, to face it generally, orb) on the annular airflow dividing wall where they are present, the teeth are oriented in the direction of a camber line of the first guide vanes at the leading edge thereof, orc) about said general axis, at least some of said depressions of the serrated leading edge profile are angularly offset with respect ...

TURBOMACHINE WITH SERRATED-PROFILE FLOW-SPLITTER NOSE

A front fan turbomachine comprising an annular separating wall () having a slat () for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; IGV blades for guiding the primary flow and OGV blades for guiding the secondary flow. 17.-. (canceled)9. Turbomachine according to claim 8 , wherein:{'b': '24', 'the first guide vanes (, IGV) have an angular position (β) with respect to the general axis (X), and'}{'b': 32', '28', '24', '32', '24, 'around said general axis (X), at least some of said depressions () of the serrated profile () are angularly offset with respect to the angular position (β) of the first guide vanes (, IGV), so that said at least some of the depressions () are angularly interposed between two of said first guide vanes (, IGV) circumferentially successive.'}10. Turbomachine according to claim 8 , wherein:{'b': 14', '38, 'the front fan () is adapted to rotate in a predetermined direction (Y) about said general axis (X) such that the airflow () downstream of the fan is generally obliquely oriented with respect to said general axis (X) at an angle (α), and'}{'b': 30', '14, 'the teeth () are inclined circumferentially around said general axis (X) towards the generally oblique orientation (α) of the airflow downstream of the front fan (), to face it generally.'}11. Turbomachine according to claim 9 , wherein:{'b': 14', '38, 'the front fan () is adapted to rotate in a predetermined direction (Y) about said general axis (X) such that the airflow () downstream of the fan is generally obliquely oriented with respect to said general axis (X) at an angle (α), and'}{'b': 30', '14, 'the teeth () are inclined circumferentially around said general axis (X) towards the generally oblique orientation (α) of the airflow downstream of the front fan (), to face it generally.'}12. Turbomachine according to claim 8 , wherein:{'b': 24', '240', '25, 'the first guide vanes (, IGV) individually have a camber line () and a leading ...

Aircraft propulsion unit comprising an unducted-fan turbine engine and an attachment pylon

The invention relates to an aircraft propulsion unit comprising: a turbine engine (1) having at least one unducted propulsion fan (4a), and an attachment pylon (3) intended to attach the turbine engine to a structural element (2) of the aircraft, said pylon being positioned on the turbine engine upstream of the fan (4a) and having an aerodynamic profile (30) extending transversally between a leading edge (31) and a trailing edge (32), the trailing edge of the aerodynamic profile of the pylon comprising a cutout (34) extending longitudinally over part of the trailing edge facing at least part of the fan, said cutout being configured in order locally to increase the distance between the trailing edge and the fan, the outline of the cutout having a curved shape exhibiting at least two points of inflection.

SLEEVE PROFILE STRUCTURE WITH TREATED SURFACES

L'invention concerne une structure profilée d'écoulement d'air présentant un bord d'attaque profilé (164) ayant, suivant une ligne de bord d'attaque (164a), un profil en serrations présentant une succession de dents (30) et de creux (32), caractérisé en ce qu'elle comprend une région (52) poreuse acoustiquement absorbante localisée vers le fond des creux (32). The invention relates to a profiled air flow structure having a profiled leading edge (164) having, along a leading edge line (164a), a serration profile having a succession of teeth (30) and recess (32), characterized in that it comprises an acoustically absorbing porous region (52) located towards the bottom of the recesses (32).

AUBAGEE WHEEL WITH VARIABLE CALIBRATIONS

Roue aubagée à calages variables comprenant : - une pluralité de pales (2), chacune à calage variable selon un axe de rotation de pale et chacune présentant un pied, la pluralité de pales comprenant au moins une première pale (21) et au moins une deuxième pale (22), - une pluralité d'arbres de liaison de rotor, chacun présentant un pied et une tête, chaque pied étant monté sur la tête d'un arbre correspondant de liaison de rotor par l'intermédiaire d'un pivot de manière à permettre la rotation de chaque pale (2) selon l'axe de rotation de pale, la première pale (21) présentant une première inclinaison de pale, telle que la première pale (21) est inclinée de manière fixe par rapport à l'axe de rotation de pale de la première pale (21), et la deuxième pale (22) présentant une deuxième inclinaison de pale différente de la première inclinaison de pale. Variable timing bladed wheel comprising: - a plurality of blades (2), each of variable pitch along an axis of blade rotation and each having a foot, the plurality of blades comprising at least a first blade (21) and at least one second blade (22); - a plurality of rotor linkage shafts, each having a foot and a head, each foot being mounted on the head of a corresponding rotor linkage shaft via a pivot of in order to allow rotation of each blade (2) along the axis of blade rotation, the first blade (21) having a first blade inclination, such that the first blade (21) is inclined in a fixed manner relative to the blade axis of blade rotation of the first blade (21), and the second blade (22) having a second blade inclination different from the first blade inclination.

PROFILE STRUCTURE IN INCLINED LOCKINGS

L'invention concerne une structure profilée d'écoulement d'air présentant un bord d'attaque et/ou de fuite profilé(s) ayant un profil (28) en serrations présentant une succession de dents (30) et de creux, caractérisée en ce que, le long du bord d'attaque et/ou de fuite, depuis un premier endroit (21) vers un second endroit (23), les dents (30) du profil en serrations sont individuellement inclinées vers le second endroit. The invention relates to a profiled air flow structure having a leading and / or trailing edge (s) having a profile (28) in clamps having a succession of teeth (30) and depressions, characterized in that, along the leading and / or trailing edge, from a first location (21) to a second location (23), the teeth (30) of the clamped profile are individually inclined towards the second location.

AIRCRAFT COMPRISING A CARENE REAR PROPELLER WITH INLET STATOR INCLUDING A BLOWING FUNCTION

L'invention concerne un aéronef comprenant un fuselage (1) et un ensemble propulseur, ledit ensemble propulseur comprenant au moins un rotor de soufflante (7, 8) placé à l'arrière du fuselage (1), dans le prolongement de celui-ci suivant un axe (XX) longitudinal, et une nacelle (14) formant un carénage dudit au moins un rotor de soufflante (7, 8) dans lequel passe un flux d'air (F), aéronef caractérisé en ce qu'il comporte une pluralité de bras radiaux (15) de stator montés en amont dudit au moins un rotor de soufflante (7, 8) et s'étendant entre le fuselage (1) et la nacelle (14), lesdits bras radiaux (15) comportant des moyens de soufflage configurés pour souffler, dans l'environnement d'un bord de fuite (15b) desdits bras radiaux (15), un flux d'air additionnel (Fs) s'additionnant audit flux d'air (F) dans le prolongement du bord de fuite (15b). The invention relates to an aircraft comprising a fuselage (1) and a propulsion assembly, said propulsion assembly comprising at least one fan rotor (7, 8) placed at the rear of the fuselage (1), in the extension thereof. along a longitudinal axis (XX), and a nacelle (14) forming a fairing of said at least one fan rotor (7, 8) through which an air flow (F) passes, aircraft characterized in that it comprises a plurality of stator radial arms (15) mounted upstream of said at least one fan rotor (7, 8) and extending between the fuselage (1) and the nacelle (14), said radial arms (15) comprising means supply air configured to blow, in the environment of a trailing edge (15b) of said radial arms (15), an additional air flow (Fs) added to said air flow (F) in the extension of the trailing edge (15b).

PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE

L'invention concerne une structure profilée, - allongée suivant une direction selon laquelle la structure présente une longueur exposée à un écoulement d'air, et - transversalement à laquelle la structure présente un bord d'attaque (164) et/ou un bord de fuite, dont l'un au moins est profilé et présente, suivant ladite direction d'allongement, des serrations (28a) définies par des dents (30) et des creux (32) se succédant. Le long du bord d'attaque et/ou du bord de fuite profilé(s), les dents (30) et creux (32) se succédant ne s'étendent que sur une partie de ladite longueur exposée à l'écoulement sur laquelle l'amplitude et/ou espacement des dents varie de manière monotone à l'exception des quelques dents les plus proches de chaque extrémité de ladite partie, une partie restante (280) de ladite longueur étant lisse. The invention relates to a profiled structure, - elongated in a direction in which the structure has a length exposed to an air flow, and - transversely to which the structure has a leading edge (164) and / or a leading edge. leakage, at least one of which is profiled and has, along said direction of elongation, serrations (28a) defined by successive teeth (30) and recesses (32). Along the leading edge and / or the profiled trailing edge (s), the successive teeth (30) and recesses (32) extend only over a part of said length exposed to the flow over which the The amplitude and / or spacing of the teeth varies monotonically with the exception of the few teeth closest to each end of said part, a remaining part (280) of said length being smooth.

PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE

L'invention concerne une structure profilée, - allongée suivant une direction selon laquelle la structure présente une longueur exposée à un écoulement d'air, et - transversalement à laquelle la structure présente un bord d'attaque (164) et/ou un bord de fuite, dont l'un au moins est profilé et présente, suivant ladite direction d'allongement, des serrations (28a) définies par des dents (30) et des creux (32) se succédant. Le long du bord d'attaque et/ou du bord de fuite profilé(s), les dents (30) et creux (32) se succédant ne s'étendent que sur une partie de ladite longueur exposée à l'écoulement sur laquelle l'amplitude et/ou espacement des dents varie de manière monotone à l'exception des quelques dents les plus proches de chaque extrémité de ladite partie, une partie restante (280) de ladite longueur étant lisse. The invention relates to a profiled structure, - elongated in a direction in which the structure has a length exposed to an air flow, and - transversely to which the structure has a leading edge (164) and / or a trailing edge, at least one of which is profiled and has, along said direction of elongation, clamps (28a) defined by teeth (30) and successive hollows (32). Along the leading edge and / or the profiled trailing edge (s), the successive teeth (30) and recesses (32) extend only over a part of said length exposed to the flow over which the The amplitude and / or spacing of the teeth varies monotonically with the exception of the few teeth closest to each end of said part, a remaining part (280) of said length being smooth.

CURRENT PATHWAY IN A DAWN

Aube (100) de turbomachine comprenant ; une portion amont (130), qui comprend un bord d'attaque (120) avec un profil en serration, une portion aval (140), qui comprend le bord de fuite (145) et des zones de fixation (113, 118) pour attacher l'aube (100) à un moyeu (200) et/ou un carter (250), caractérisé en ce que la portion amont (103) est moins rigide que la portion aval (140) de sorte que portion aval (140) supportent la majorité des efforts transitant par l'aube (100). A turbomachine blade (100) comprising; an upstream portion (130), which includes a leading edge (120) with a serration profile, a downstream portion (140), which includes the trailing edge (145), and attachment regions (113, 118) for attaching the blade (100) to a hub (200) and / or a housing (250), characterized in that the upstream portion (103) is less rigid than the downstream portion (140) so that the downstream portion (140) withstand the majority of dawn-related efforts (100).

STRUCTURE WITH A PROFILE IN SERRATIONS WITH TREATED SURFACES

L'invention concerne une structure profilée d'écoulement d'air présentant un bord d'attaque profilé (164) ayant, suivant une ligne de bord d'attaque (164a), un profil en serrations présentant une succession de dents (30) et de creux (32), caractérisé en ce qu'elle comprend une région (52) poreuse acoustiquement absorbante localisée vers le fond des creux (32). A profiled air flow structure having a profiled leading edge (164) having, along a leading edge line (164a), a serrated profile having a succession of teeth (30) and hollow (32), characterized in that it comprises an acoustically absorbent porous region (52) located towards the bottom of the hollow (32).

PROFILE STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT

L'invention concerne une structure profilée, - allongée suivant une direction selon laquelle la structure présente une longueur (L1) exposée à un écoulement d'air (U), et - transversalement à laquelle la structure présente un bord d'attaque (164) et/ou un bord de fuite (165), dont l'un au moins est profilé et présente, suivant ladite direction d'allongement, des motifs géométriques de serration (28) définies par des dents (30) et des creux (32) se succédant. Le long du bord d'attaque et/ou du bord de fuite profilé(s), les motifs de serration (28) présentent un motif géométrique qui se répète suivant la direction d'allongement (L1), dont la forme présente un étirement et/ou une contraction : - transversalement à la direction d'allongement, et/ou - suivant la direction d'allongement. The invention relates to a profiled structure, - elongated along a direction in which the structure has a length (L1) exposed to an air flow (U), and - transversely to which the structure has a leading edge (164) and/or a trailing edge (165), at least one of which is profiled and has, along said direction of elongation, geometric tightening patterns (28) defined by teeth (30) and hollows (32) succeeding each other. Along the leading edge and/or the profiled trailing edge(s), the serration patterns (28) have a geometric pattern which is repeated in the direction of elongation (L1), the shape of which presents a stretch and /or a contraction: - transversely to the direction of elongation, and/or - along the direction of elongation.

HOOD RELATED TO TIGHTENING PROFILE FOR DAWN

Capot aérodynamique (300) pour aube (100) de stator, comprenant un bord d'attaque (310) présentant un profil en serration, le capot (300) étant configuré pour être rapporté sur une aube (100) de stator de sorte que le bord d'attaque (310) du capot (300) soit le bord d'attaque de l'aube (100). Ensemble comprenant une aube et un tel capot. Aerodynamic cover (300) for a stator vane (100), comprising a leading edge (310) having a clamping profile, the cover (300) being configured to be attached to a stator vane (100) so that the leading edge (310) of the cover (300) is the leading edge of the blade (100). Assembly comprising a blade and such a cover.

MODULATION OF THE SERRATIONS IN THE END OF DAWN

L'invention concerne une aube (100) de stator comprenant : - un pied d'aube (110), - une tête d'aube (115), - un bord d'attaque (120) s'étendant entre le pied (110) et la tête (115), le bord d'attaque ayant un profil en serration présentant une succession de dents (122) et de creux (124) ayant chacune une amplitude et une épaisseur, caractérisée en ce qu'une série (300) d'au moins trois dents (122) et trois creux (124) consécutifs à partir du pied d'aube (110) et /ou de la tête d'aube (115) présente une amplitude et/ou une épaisseur croissante. The invention relates to a stator blade (100) comprising: - a blade root (110), - a blade head (115), - a leading edge (120) extending between the foot (110) ) and the head (115), the leading edge having a serration profile having a succession of teeth (122) and recesses (124) each having an amplitude and a thickness, characterized in that a series (300) at least three teeth (122) and three recesses (124) consecutive from the blade root (110) and / or the blade head (115) has an amplitude and / or increasing thickness.

AUBAGEE WHEEL WITH VARIABLE CALIBRATIONS

MEMBRANE WITH ACTUATORS FOR DAWN ATTACK EDGE

L'invention concerne un ensemble pour redresseur, comprenant : - une aube de stator (100), - une membrane (300) définissant un bord d'attaque (310) de l'aube (100), - une pluralité d'actionneurs (400) disposés entre l'aube (100) et la membrane (300) pour modifier la forme du bord d'attaque (310). The invention relates to a rectifier assembly, comprising: - a stator blade (100), - a membrane (300) defining a leading edge (310) of the blade (100), - a plurality of actuators ( 400) disposed between the blade (100) and the diaphragm (300) to change the shape of the leading edge (310).

Variable pitch bladed disc

Profiled structure for an aircraft or turbomachine for an aircraft

A turbomachine for an aircraft has a stator 55 and a rotor (fig.1,14). The stator includes an annular separation wall 16 having a perimeter about an axis X which splits the airflow downstream of a fan 14 rotating about the axis. The stator has profiled structures, each being: elongated, in a direction of elongation, having a length L exposed to an airflow; transverse the direction of elongation, a leading edge 164 and/or a trailing edge, at least one of which is has serrations 28 defined by a series of peaks (fig.20,30) and troughs (fig.20,32) in the direction of elongation. The serrations have a geometric pattern transformed over at least part of the length by successive scaling via multiplicative factors in, and/or transverse to, the direction of elongation, where, defined with reference to a radial distribution of the integral scale of turbulence, the pattern evolves in a non-periodic manner according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution, and evolves homothetically.

Profiled structure for an aircraft or turbomachine for an aircraft

A profiled structure for an aircraft or a turbomachine for an aircraft, having an elongated structure with a length L1 exposed to an airflow U and transversely a leading edge 164 and trailing edge 165. The leading edge and/or trailing edge are profiled, in the direction of elongation with serrations 28 defined by a succession of peaks 30 and troughs 32 having a geometric pattern transformed over at least part of the length L1. The geometric pattern that is transformed is formed by successive scaling, via multiplicative factors and evolves in a non-periodic manner in the direction of elongation L2 and/or transverse to the direction of elongation d. The non-periodic manner is according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution.

Baffle

PROFILED STRUCTURE FOR AIRCRAFT OR TURBOMACHINE FOR AIRCRAFT

L'invention concerne une structure profilée, - allongée suivant une direction selon laquelle la structure présente une longueur (L1) exposée à un écoulement d'air (U), et - transversalement à laquelle la structure présente un bord d'attaque (164) et/ou un bord de fuite (165), dont l'un au moins est profilé et présente, suivant ladite direction d'allongement, des motifs géométriques de serration (28) définies par des dents (30) et des creux (32) se succédant. Le long du bord d'attaque et/ou du bord de fuite profilé(s), les motifs de serration (28) présentent un motif géométrique qui se répète suivant la direction d'allongement (L1), dont la forme présente un étirement et/ou une contraction : - transversalement à la direction d'allongement, et/ou - suivant la direction d'allongement. The invention relates to a profiled structure, - elongated in a direction in which the structure has a length (L1) exposed to an air flow (U), and - transversely to which the structure has a leading edge (164) and / or a trailing edge (165), at least one of which is profiled and presents, along said direction of elongation, geometric patterns of tightening ( 28) defined by successive teeth (30) and recesses (32). Along the leading edge and / or the profiled trailing edge (s), the tightening patterns (28) have a geometric pattern which repeats in the direction of elongation (L1), the shape of which exhibits a stretch and / or a contraction: - transversely to the direction of elongation, and / or - following the direction of elongation.

Turbomachine for aircraft and corresponding aircraft

REINFORCED HOOD FOR TANK FOR DARK

Capot aérodynamique (300) pour aube (100) de stator, comprenant un bord d'attaque (310) présentant un profil en serration, le capot (300) étant configuré pour être rapporté sur une aube (100) de stator de sorte que le bord d'attaque (310) du capot (300) soit le bord d'attaque de l'aube (100). Ensemble comprenant une aube et un tel capot. An aerodynamic hood (300) for a stator blade (100), comprising a leading edge (310) having a serration profile, the hood (300) being configured to be attached to a stator blade (100) so that the leading edge (310) of the hood (300) is the leading edge of the blade (100). Set comprising a blade and such a hood.

Device for processing of photopolymerisable material for building up a moulded body in layers

Aircraft propulsion unit comprising an unducted-fan turbine engine and an attachment pylon

The invention relates to an aircraft propulsion unit comprising: a turbine engine (1) having at least one unducted propulsion fan (4a), and an attachment pylon (3) intended to attach the turbine engine to a structural element (2) of the aircraft, said pylon being positioned on the turbine engine upstream of the fan (4a) and having an aerodynamic profile (30) extending transversally between a leading edge (31) and a trailing edge (32), the trailing edge of the aerodynamic profile of the pylon comprising a cutout (34) extending longitudinally over part of the trailing edge facing at least part of the fan, said cutout being configured in order locally to increase the distance between the trailing edge and the fan, the outline of the cutout having a curved shape exhibiting at least two points of inflection.

Device for processing photopolymerizable material in order to construct a shaped body layer by layer

The invention relates to a method for processing photopolymerizable material in order to construct a shaped body layer by layer, which method comprises: a) providing a tub having a base that is light-permeable at least in some regions, b) moving a construction platform to such a height that a layer of the photopolymerizable material having a specified thickness is defined between the lower face of the construction platform or, if already present, the lowest cured layer of the shaped body part formed thereon and the tub base, c) exposing the layer to light from below through the tub base in a locationally selective manner in order to cure the material layer in the desired shape, and d) repeating steps b) and c) until the last layer of the shaped body is formed. The photopolymerizable material has a viscosity of at least 20 Pa⋅s at room temperature (20 °C), and the layer of the photopolymerizable material is heated up in the tub to a temperature of at least 30 °C in order to lower the viscosity.

turbomachine

a presente invenção se refere a uma turbomáquina (1) que compreende pelo menos duas hélices não carenadas (10, 11) sendo uma hélice a montante (10) e uma hélice a jusante (11), sendo que a hélice a montante (10) compreende uma pluralidade de pás (2) em que pelo menos uma primeira pá apresenta um comprimento diferente de pelo menos uma segunda pá. the present invention relates to a turbomachine (1) which comprises at least two non-faired propellers (10, 11) being an upstream propeller (10) and a downstream propeller (11), the upstream propeller (10) being comprises a plurality of blades (2) wherein at least one first blade has a length different from at least one second blade.

Profiled structure for an aircraft or turbomachine for an aircraft

The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.

Turbomachine with multi-diameter propeller

La présente invention concerne une turbomachine (1) comprenant au moins deux hélices non carénées (10, 11) dont une hélice amont (10) et une hélice aval (11), l'hélice amont (10) comprenant une pluralité de pales (2) dont au moins une première pale présentant une longueur différente d'au moins une deuxième pale.

Device for forming dimensionally stable objects

A device for forming dimensionally stable objects by consolidating certain regions of a substance (3) that is not dimensionally stable, in particular a light-curable substance, by exposing it to radiation from an emitter, in particular an electromagnetic emitter (4), the device comprising a pan (2) for receiving the substance (3) and a building platform (1), which is arranged over the pan (2) and can be lowered and raised with respect to it, for bonding on and lifting off cured layers of substance (5), wherein at least one light source (6) and at least one light sensor (7), which detects the light of the light source (6), are arranged in the region of the bottom of the pan (2) in such a way that it is possible to detect a deformation of the pan (2) caused by changing of the light intensity of the light source (6) detected by the light sensor (7).

Baffle

A baffle or reinforcement element for sealing and/or reinforcing a cavity, in particular a cavity of a vehicle, comprising: a carrier plate with a first plate surface and a second plate surface, and at least a first and a second expandable element, in particular expandable foam element, supported by the carrier plate, wherein the first expandable element covers, at least substantially, the entire first plate surface and forms a first outer surface of the baffle or reinforcement element and the second expandable element covers, at least substantially, the entire second plate surface thereby forming a second outer surface of the baffle element.

MULTI-DIAMETER PROPELLER TURBOMACHINE

La présente invention concerne une turbomachine (1) comprenant au moins deux hélices non carénées (10, 11) dont une hélice amont (10) et une hélice aval (11), l'hélice amont (10) comprenant une pluralité de pales (2) dont au moins une première pale présentant une longueur différente d'au moins une deuxième pale. The present invention relates to a turbomachine (1) comprising at least two unducted propellers (10, 11) including an upstream propeller (10) and a downstream propeller (11), the upstream propeller (10) comprising a plurality of blades (2). ) of which at least a first blade having a different length of at least a second blade.

TURBOMACHINE WITH FLOW SEPARATION NOZZLE WITH SERRATED PROFILE

Est concernée une turbomachine à soufflante avant, comportant une paroi (160) annulaire de séparation pourvue d'un bec (16), pour la séparation d'un flux d'air entre un flux primaire et un flux secondaire, le bec (3) présentant un bord d'attaque ; des aubes IGV (24) de guidage du flux primaire et des aubes OGV (26) de guidage du flux secondaire. Le bord d'attaque du bec (16) présente un profil (28) à serrations présentant une succession de dents et de creux. This concerns a turbomachine with a front fan, comprising an annular separation wall (160) provided with a nozzle (16), for the separation of an air flow between a primary flow and a secondary flow, the nozzle (3) having a leading edge; IGV vanes (24) for guiding the primary flow and OGV vanes (26) for guiding the secondary flow. The leading edge of the nose (16) has a profile (28) with serrations having a succession of teeth and hollows.

AUBAGEE WHEEL WITH VARIABLE CALIBRATIONS

AERONAUTICAL THRUSTER

Propulseur aéronautique (10) d’axe longitudinal (X) comprenant un moyeu (12) et au moins deux rangées annulaires de pales (18) non carénées comprenant une rangée annulaire amont (14) et une rangée annulaire aval (16) espacées l’une de l’autre suivant ledit axe longitudinal (X), la rangée annulaire amont (14) étant mobile en rotation autour de l’axe longitudinal (X), ladite rangée annulaire aval (16) comprenant une série de pales incluant une première pale (18a) et une deuxième pale (18b) s’étendant chacune selon une direction radiale depuis le moyeu (12) de sorte à définir une dimension radiale entre ledit moyeu (12) et une extrémité radialement externe de la pale (18a ; 18b) respective, caractérisé en ce que la dimension radiale de la première pale (18a) est supérieure à la dimension radiale de la deuxième pale (18b). Figure de l’abrégé : Figure 4 Aeronautical thruster (10) of longitudinal axis (X) comprising a hub (12) and at least two annular rows of unducted blades (18) comprising an upstream annular row (14) and a downstream annular row (16) spaced apart one from the other along said longitudinal axis (X), the upstream annular row (14) being rotatable around the longitudinal axis (X), said downstream annular row (16) comprising a series of blades including a first blade (18a) and a second blade (18b) each extending in a radial direction from the hub (12) so as to define a radial dimension between said hub (12) and a radially outer end of the blade (18a; 18b) respective, characterized in that the radial dimension of the first blade (18a) is greater than the radial dimension of the second blade (18b). Abstract Figure: Figure 4

TURBOMACHINE HAVING A SERRATION PROFILE FLOW SEPARATION SEPARATION

Est concernée une turbomachine à soufflante avant, comportant une paroi (160) annulaire de séparation pourvue d'un bec (16), pour la séparation d'un flux d'air entre un flux primaire et un flux secondaire, le bec (3) présentant un bord d'attaque ; des aubes IGV (24) de guidage du flux primaire et des aubes OGV (26) de guidage du flux secondaire. Le bord d'attaque du bec (16) présente un profil (28) à serrations présentant une succession de dents et de creux. A turbomachine with a front blower, comprising an annular partition wall (160) provided with a spout (16), for separating an air flow between a primary flow and a secondary flow, the spout (3). having a leading edge; IGV vanes (24) for guiding the primary flow and OGV vanes (26) for guiding the secondary flow. The leading edge of the spout (16) has a profile (28) with serrations having a succession of teeth and troughs.

Profiled structure for an aircraft or turbomachine for an aircraft

A turbomachine for an aircraft comprises a stator 55 comprising a profiled structure having an elongated structure with a length L1 exposed to an airflow U and transversely a leading edge 164 and trailing edge 165. The leading edge and/or trailing edge are profiled, in the direction of elongation with serrations 28 defined by a succession of peaks 30 and troughs 32 having a geometric pattern transformed over at least part of the length L1. The geometric pattern that is transformed is formed by successive scaling, via multiplicative factors and evolves in a non-periodic manner in the direction of elongation L2 and/or transverse to the direction of elongation d. The non-periodic manner is according to a linear, quadratic, hyperbolic, exponential or logarithmic law of evolution. On each stator, each profiled structure has a distance L between two tops of consecutive peaks or troughs, and an amplitude d, wherein the distances L and amplitudes d of the serrations is greater at a radially outer end of the length than at a radially inner end. The geometric pattern may evolve homothetically.

Profiled structure for an aircraft or turbomachine

Turbomachine with multi-diameter propeller

The invention relates to a turbomachine (1) comprising at least two unducted propellers (10, 11), one of which is an upstream propeller (10) and one a downstream propeller (11), the upstream propeller (10) comprising a plurality of blades (2), at least one first blade of which has a different length from that of a second blade.

Variable pitch bladed disc

A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

Profiled structure for an aircraft or turbomachine for an aircraft

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

Turbine engine with a flow splitter having a profile with inclined serrations

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

Profiled structure and associated turbomachine

An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

Propulseur aeronautique

Propulseur aéronautique (10) d’axe longitudinal (X) comprenant un moyeu (12) et au moins deux rangées annulaires de pales (18) non carénées comprenant une rangée annulaire amont (14) et une rangée annulaire aval (16) espacées l’une de l’autre suivant ledit axe longitudinal (X), la rangée annulaire amont (14) étant mobile en rotation autour de l’axe longitudinal (X), ladite rangée annulaire aval (16) comprenant une série de pales incluant une première pale (18a) et une deuxième pale (18b) s’étendant chacune selon une direction radiale depuis le moyeu (12) de sorte à définir une dimension radiale entre ledit moyeu (12) et une extrémité radialement externe de la pale (18a ; 18b) respective, caractérisé en ce que la dimension radiale de la première pale (18a) est supérieure à la dimension radiale de la deuxième pale (18b). Figure de l’abrégé : Figure 4

Propulseur aeronautique a integration amelioree

Propulseur aéronautique (40) d’axe longitudinal (X) et comprenant une rangée rotorique amont et une rangée statorique aval (16) de pales (18) non carénées. Deux pales adjacentes de la rangée statorique aval (16) présentent entre elles, autour de l’axe longitudinal (X), un espacement azimutal (Δθ) qui, quand les pales sont situées de part et d’autre d’une structure de fixation (27) et/ou d’une proéminence (270), dans un plan perpendiculaire à l’axe longitudinal (X), est entre 1° et 75° supérieur au plus petit espacement azimutal existant sur ladite rangée statorique aval de pales statoriques (16). Figure de l’abrégé : Figure 4

Variable pitch bladed disc

A variable pitch bladed disc including a plurality of blades, each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each shaft having a root and a tip, the root of each blade being mounted on the tip of a corresponding rotor connecting shaft via a pivot so as to allow each blade to be rotated about the blade axis of rotation, the first blade having a first rotation axis inclination such that the rotation axis thereof is inclined in a fixed manner with respect to a radial axis passing through the root of the corresponding shaft, and the second blade has a second rotation axis inclination different from the first rotation axis inclination.

Propulseur aeronautique

Propulseur aéronautique (10) d'axe longitudinal (X) comprenant un moyeu (12) et au moins deux rangées annulaires de pales (18) non carénées comprenant une rangée annulaire amont (14) et une rangée annulaire aval (16) espacées l'une de l'autre suivant ledit axe longitudinal (X), la rangée annulaire amont (14) étant mobile en rotation autour de l'axe 5 longitudinal (X), ladite rangée annulaire aval (16) comprenant une série de pales incluant une première pale (18a) et une deuxième pale (18b) s'étendant chacune selon une direction radiale depuis le moyeu (12) de sorte à définir une dimension radiale entre ledit moyeu (12) et une extrémité radialement externe de la pale (18a; 18b) respective, caractérisé en ce que la dimension radiale de la première pale (18a) est supérieure à la dimension radiale de 10 la deuxième pale (18b).

Propulseur aeronautique a integration amelioree

Propulseur aéronautique (40) d'axe longitudinal (X) et comprenant une rangée rotorique amont et une rangée statorique aval (16) de pales (18) non carénées. Deux pales adjacentes de la rangée statorique aval (16) présentent entre elles, autour de l'axe longitudinal (X), un espacement azimutal (Δθ) qui, quand les pales sont situées de part et d'autre d'une structure de fixation (27) et/ou d'une proéminence (270), dans un plan perpendiculaire à l'axe longitudinal (X), est entre 1° et 75° supérieur au plus petit espacement azimutal existant sur ladite rangée statorique aval de pales statoriques (16).

Propulseur aeronautique a aerocoustique amelioree

Propulseur aéronautique (40) d'axe longitudinal (X) et comprenant une rangée rotorique amont et une rangée statorique aval (16) de pales (18) non carénées. Deux pales adjacentes de la rangée statorique aval (16) présentent entre elles, autour de l'axe longitudinal (X), un espacement azimutal (Δθ) dont certains au moins sont différents entre eux, de sorte que certaines au moins des pales du stator aval présentent une répartition hétérogène autour de l'axe longitudinal (X).

Propulseur pour un aéronef

L'invention concerne un propulseur aéronautique comprenant un moteur central (3), une série amont et une série aval de pales (9, 6), les pales (90, 60) de l'une au moins de ces séries étant adaptées pour pouvoir être entraînées en rotation autour de l'axe longitudinal central (X) par une turbine, une nacelle (5) qui renferme le moteur central. Certaines au moins des pales des deux séries sont à calage variable. L'une au moins des pales (90) de la première série de pales (9) présente un bord de fuite présentant des ondulations (93), et/ou l'une au moins des pales (60) de la deuxième série de pales (6) présente un bord d'attaque présentant des ondulations (63).

Propulseur aeronautique a aerocoustique amelioree

Propulseur aéronautique (40) d’axe longitudinal (X) et comprenant une rangée rotorique amont et une rangée statorique aval (16) de pales (18) non carénées. Deux pales adjacentes de la rangée statorique aval (16) présentent entre elles, autour de l’axe longitudinal (X), un espacement azimutal (Δθ) dont certains au moins sont différents entre eux, de sorte que certaines au moins des pales du stator aval présentent une répartition hétérogène autour de l’axe longitudinal (X). Figure de l’abrégé : Figure 4

Verfahren zur belichtung eines dreidimensionalen bereichs

Verfahren zur Belichtung eines dreidimensionalen Bereichs (1), wobei der dreidimensionale Bereich in zumindest zwei aufeinanderfolgende Schichten (2) unterteilt wird, die in zeitlicher Abfolge belichtet werden, wobei jede Schicht (2) in zumindest zwei Belichtungsfelder (3) mit zumindest einem ersten Teilbereich (4), einem zweiten Teilbereich (4'), gegebenenfalls einem dritten Teilbereich (4'') sowie gegebenenfalls weiteren Teilbereichen unterteilt wird, wobei benachbarte Belichtungsfelder (3) in einzelnen Teilbereichen (4', 4'') zur Vermeidung fehlbelichteter Gebiete überlappen.

Gerät zum Rauchen von verdichtetem Tabakrauch und ohne brennenden Tabak.

Estructura perfilada para aeronave o turbomáquina

La invención se refiere a una estructura perfilada que se alarga en una dirección en la que la estructura tiene una longitud expuesta a un flujo de aire, y transversalmente a la cual la estructura tiene un borde de ataque (164) y/o un borde de salida, al menos uno de que está perfilado y presenta, en el sentido de la elongación, abrazaderas (28a) definidas por sucesivos dientes (30) y rebajes (32). A lo largo del borde de ataque y/o del borde de salida perfilados, los sucesivos dientes (30) y rebajes (32) se extienden sobre solo una porción de la longitud expuesta al flujo, sobre cuya porción la amplitud y/o espaciado de los dientes varía monótonamente con a excepción de los pocos dientes más cercanos a cada extremo de dicha porción, siendo lisa una porción restante (280) de dicha longitud. (Traducción automática con Google Translate, sin valor legal)

Verfahren zur Überführung von Tabak oder Tabakersatzstoffen in eine zum menschlichen Genuß geeignete Form.

Verfahren zur belichtung eines dreidimensionalen bereichs

Verfahren zur Belichtung eines dreidimensionalen Bereichs (1), wobei der dreidimensionale Bereich in zumindest zwei aufeinanderfolgende Schichten (2) unterteilt wird, die in zeitlicher Abfolge belichtet werden, wobei jede Schicht (2) in zumindest zwei Belichtungsfelder (3) mit zumindest einem ersten Teilbereich (4), einem zweiten Teilbereich (4'), gegebenenfalls einem dritten Teilbereich (4'') sowie gegebenenfalls weiteren Teilbereichen unterteilt wird, wobei benachbarte Belichtungsfelder (3) in einzelnen Teilbereichen (4', 4'') zur Vermeidung fehlbelichteter Gebiete überlappen.

Profiled structure for an aircraft or turbomachine for an aircraft

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

Aeronautical thruster

An aeronautical thruster having a longitudinal axis and having a hub and at least two annular rows of unducted blades including an upstream annular row and a downstream annular row which are spaced apart from one another along the longitudinal axis, the upstream annular row being rotatable around the longitudinal axis, and the downstream annular row comprising a series of blades including a first blade and a second blade each extending in a radial direction from the hub to define a radial dimension between the hub and a radially outer end of the corresponding blade, wherein the radial dimension of the first blade is greater than the radial dimension of the second blade.