WO2015092263A1 - Pièce de turbomachine à surface non-axisymétrique - Google Patents
Pièce de turbomachine à surface non-axisymétrique Download PDFInfo
- Publication number
- WO2015092263A1 WO2015092263A1 PCT/FR2014/053373 FR2014053373W WO2015092263A1 WO 2015092263 A1 WO2015092263 A1 WO 2015092263A1 FR 2014053373 W FR2014053373 W FR 2014053373W WO 2015092263 A1 WO2015092263 A1 WO 2015092263A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- curve
- control point
- extremal
- intrados
- extrados
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
- F04D29/329—Details of the hub
-
- 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
-
- 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
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
Definitions
- the present invention relates to a turbomachine part comprising blades and a platform having a non-axisymmetric surface.
- a blower (or “fan”) is a rotating part of large diameter at the inlet of a turbofan engine formed of a substantially conical hub (the “spinner”) on which are fixed radially extending blades, such visible on the left of Figure 1 (reference 1).
- the blower compresses a large mass of cold air, partially injected into the compressor, the remainder forming a cylindrical flow enveloping the engine and directed rearwardly to create thrust.
- the optimization of the performance and performance of a blower passes in particular by increasing the mass flow through the blades.
- the parameters of the fan blade or to modify the walls of the vein that is to say the set of channels between the blades for the flow of fluid (in other words the inter-blade sections), in particular at the level of the hub ("fan foot”, that is to say the part of the fan which is in front of the primary, the first wheel of the booster, in in other words the part of the fan blade that will directly supply the low-pressure air compressor and which is therefore the first mobile wheel thereof).
- axisymmetric geometries (an example of which is represented in FIG. 2a) of these walls remain perfectible: the search for an aeromechanical geometrical optimum on the "feet of fan "(that is to say at the base of the blades, at the junction with the hub) leads today to obtain parts having a locally non-axisymmetric wall (that is to say that a section along a plane perpendicular to the axis of rotation is not circular) at the level of the vein, in view of the particular conditions that prevail there.
- the non-axisymmetric vein defines a generally annular surface of a three-dimensional space (a "slice" of the turbomachine).
- the patent application EP1 126132 thus proposes a non-axisymmetric vein geometry (see FIG. 2b) in which the wall of a blade platform (in other words the local surface of the hub of the fan at which the blade is fixed) has in particular a hollow extending along the blades.
- this non-axisymmetric vein degraded the performance of the flow through the fan. Indeed, starting from a "healthy" situation of the flow with an axisymmetric vein, the establishment of the non-axisymmetric vein has shown after calculations of the Navier-Stockes 3D type of the important aerodynamic detachments in foot of fan at the trailing edge of the blades. Due to this negative aerodynamic effect, the fan's performance was degraded and this aerodynamic detachment was very restrictive for the fan's operability (performance, compression ratio and power supply of the booster in particular).
- the present invention thus proposes a part or set of turbomachine parts comprising at least first and second blades, and a platform from which the blades extend, characterized in that the platform has a non-axisymmetric surface limited by a first and a second extremal plane, and defined by at least two class C 1 construction curves each representing the value of a radius of said surface as a function of a position between the intrados of the first blade and the extrados of the second blade in a plane substantially parallel to the extremal planes, of which:
- each construction curve being defined by at least one extremal intrados control point and an extrados extremal control point, respectively on each of the first and second blades between which said surface extends, such that:
- Any other tangent to a building curve at an extremal control point is inclined at least 5 °.
- Each upstream curve is associated with an axial position along the blade rope such that the curves are located at regular intervals in terms of the relative length of the blade rope;
- the surface is defined by four upstream curves including a first attack curve, a second attack curve, a first central curve and a second central curve;
- Each construction curve is further defined by an intermediate intrados control point and an extrados intermediate control point, respectively close to the first and second blades between which said surface extends, and each located between the points extremal control of the construction curve, such as:
- the extremal and intermediate extrados control points of the downstream curve have an abscissa difference of at least 15 mm; - all the other extremal and intermediate control points of extrados or intrados of a construction curve have a difference of abscissa of at most 20 mm;
- the extremal and intermediate extrados control points of the downstream curve have a difference in abscissa of between 15 and 30 mm;
- the extremal and intermediate intrados control points of the downstream curve have a difference in abscissa of between 5 and 15 mm;
- each construction curve is entirely determined by eight parameters including:
- the parameterization being implemented according to one or more parameters defining at least one of the extreme control points; (b) determining optimized values of said parameters of said curve;
- the part or set of parts is a fan for a turbomachine with a double flow.
- the invention relates to a turbomachine comprising a part or set of parts according to the first aspect.
- FIG. 1 previously described represents an example of a turbomachine
- FIGS. 2a-2b previously described illustrate two known examples of fan foot geometries with and without non-axisymmetric platform
- FIGS. 3a-3b show a preferred embodiment of a part according to the invention.
- FIG. 4 represents a preferred embodiment of a part according to the invention.
- the present piece 1 (or set of parts if it is not a monobloc) of a turbomachine has at least two consecutive blades 3E, 31 and a platform 2, from which the blades 3E extend, 31.
- the term platform is here interpreted in the broad sense and refers generally to any element of a turbomachine on which blades 3E, 31 are able to be mounted (extending radially) and having a wall against which the air circulates.
- the platform 2 may be one-piece or formed of a plurality of elementary members each supporting a single blade 3E, 31 (a "foot” of the blade) so as to constitute a blade of the type of those shown in FIG. 3a.
- these are “reported” platforms, that is to say separate blades (they are independent parts).
- integrated platforms (which will be mentioned again later) for which each blade is linked to a "half" platform, and the junction between two neighboring platforms is then in the middle of the vein. It will be understood that the present invention is not limited to any particular structure of platform 2.
- the platform 2 delimits a radially inner wall of the part 1 (the air passes around) by defining a hub.
- the piece 1 or set of parts is advantageously a fan.
- the present part 1 is distinguished by a particular geometry (non-axisymmetric) of a surface S of a platform 2 of the part 1, of which we observe an example of advantageous modeling in Figures 3a and 3b.
- the surface S extends between two blades 3E, 31 (shown in FIG. 3a, but not in FIG. 3b to better observe the surface S. However, their base is found, which limits it tangentially.
- the surface S is indeed part of a larger surface defining a substantially toroidal shape around the part 1, which is here as explained the fan.
- the wall consists of a plurality duplicate identical surfaces between each pair of blades 3E, 31.
- the surfaces S ' also visible in FIGS. 3a and 3b are thus a duplication of the surface S.
- This structure corresponds to an embodiment of the "integrated platforms" type mentioned above, in which the platform 2 is composed of a plurality of elementary members. Each of these elementary members forms the vein at the foot of the blade Fan. The vein at the foot of blade Fan thus extends on both sides of the blade 3E, 31, from which the surface S comprises juxtaposed surfaces associated with two distinct blade roots. Piece 1 is then a set of at least two vanes (blade / vein assembly at the bottom of the blade) juxtaposed. As already indicated, it will be understood that the present invention is not limited to any particular structure of platform 2.
- the surface S is limited upstream by a first extremal plane, the "separation plane” PS and downstream by a second extremal plane, the "plane of connection” PR, which each define an axisymmetric, continuous and continuous derivative contour (the curve corresponding to the intersection between each of the planes PR and PS and the surface of the part 1 as a whole is closed and forms a loop).
- the surface S has substantially the shape of a "parallelogram" which has two curved sides, and extends axially (along the motor axis) between the two end planes PS, PR, and tangentially between the two blades 3E, 31 of a couple of consecutive blades. One of the blades of this pair of blades is the first blade 31, or blade of intrados.
- the other blade is the second blade 3E, or blade of extrados. In fact, it has its extrados on the surface S.
- Each "second blade” 3E is the "first blade” 31 of a neighboring surface such as the surface S 'in FIG. 2 (since each blade 3E, 31 has a lower surface and an extrados).
- Surface S is defined by building curves, also called "Construction Plans”. At least two, advantageously three or even four, and preferably five (or even more) PC-1, PC-2, PC-3, PC-4 and PC-5 construction curves are required to obtain the geometry of the present invention. In the remainder of the present description we will take the preferred example of five curves (including four "upstream” curves (a first PC-1 drive curve, a second PC-2 drive curve, a first curve). PC-3 central and a second PC-4 central curve), and a "downstream” curve PC-5), but it will be understood that only one upstream curve among the curves PC-1, PC-2, PC-3, PC-2 4 and a PC-5 downstream curve (see below) are essential for the definition of the non-axisymmetric S surface.
- each construction curve is a curve of class C 1 representing the value of a radius of said surface S (value of this variable radius, by definition of a non-axisymmetric platform) as a function of a position between the intrados of the first blade 31 and the extrados of the second blade 3E in a plane parallel to the extremal planes PS, PR.
- radius means the distance between a point of the surface and the axis of the part 1, as can be seen for example in Figure 4, which shows an example of a construction curve which will be described in more detail below.
- An axisymmetric surface thus has a constant radius, by definition
- the non-axisymmetric fan foot geometries (both the present geometry and those known from the state of the art) define a "digging" of the platform.
- its construction curves have a "U” shape, with 3 parts: 2 "flanks” (intrados and extrados) and the "bottom” of the non-axisymmetric vein, which is the most hollow part of the vein. This geometry is visible in FIG.
- the inventors have discovered that the problems of separation of the known geometries were due to very strong "slopes" at the flanks, in particular near the trailing edge of the extrados blade.
- the present geometry therefore has a reduced slope at this location.
- the building curves are arranged on substantially parallel planes, which form "axial" planes since they are orthogonal to the axis of the part 1.
- the first or the first curves PC-1, PC-2, PC-3, PC-4 are "upstream” curves because disposed near the leading edge BA of the blades 3E, 31 between which it extends (even if this set includes both attack curves (located very close to the leading edge BA) as central curves located in the intermediate portion of the blades 31, 3E).
- the last curve PC-5 is a curve "Downstream", or "leakage” curve, as arranged near the trailing edge of the blades 3E FF 31, between which it extends.
- downstream curve PC-5 is associated with an axial position situated between 50% and 80% in relative length of blade rope 3E, 31.
- the upstream curve (s) PC-1, PC-2, PC-3, PC-4 are associated with a position located at a relative length of blade rope 3E, 31 lower than that of the PC-5 downstream curve.
- all the building curves are associated with axial positions arranged at regular intervals along the blade rope 3E, 31, for example every 25% in the case of four curves, or 20% in the case of five curves. so as to be able to draw the flank shapes desired by the designer of the platform (too few construction curves limit the possible shapes)
- the first curve PC-1 drive is associated with an axial position located at 0% relative length of blade rope 3E
- the second PC-2 drive curve is associated with an axial position located at about 20% relative length of blade rope 3E
- the first central curve PC-3 is associated with an axial position located at about 40% relative length of blade rope 3E
- the second central curve PC-4 is associated with an axial position located at about 60% relative length of blade rope 3E
- the downstream curve PC-5 is associated with an axial position located at about 80% relative length of blade rope 3.
- the PC-1, PC-2, PC-3, PC-4 upstream curves can be arranged anywhere on the front part of the vein.
- each curve has a specific geometry designed to limit the slope at the trailing edge BF, in particular the PC-5 downstream curve.
- Each construction curve PC-1, PC-2, PC-3, PC-4, PC-5 is typically a spline consisting of 3 parts: the 2 sides and the bottom of the vein, as previously mentioned.
- the points ⁇ Po, PI. .. PN ⁇ are called "implicit" control points of the curve and are the variables by which a construction curve can be parameterized.
- Each construction curve PC-1, PC-2, PC-3, PC-4, PC-5 is thus defined by at least one extremal intrados control point and an extremal extrados control point, respectively on each of the first and second blades 31, 3E between which said surface S extends.
- PC-4, PC-5 is furthermore advantageously defined by an intermediate control point of intrados and an intermediate control point of extrados, respectively close to the first and second blades 31, 3E between which said surface S extends, and each located between the extreme control points of the PC-1, PC-2, PC-3, PC-
- the parameter or parameters defining a control point are thus chosen from an abscissa of the point, an ordinate of the point, a tangent orientation to the curve at the point and a point (in the case of an extremal control point, one does not can take into account that half-tangent in the field of definition of the curve, left or right following the point) or two (in the case of an intermediate control point) voltage coefficients each associated with a half tangent to the curve at the point.
- any other tangent to an upstream curve PC-1, PC-2, PC-3, PC-4, or any other tangent to a construction curve PC-1, PC-2, PC-3, PC-4, PC -5 (in other words including the tangent to the PC-5 downstream curve at the endal control point of the intrados) at a control point extremal is inclined at least 5 ° (and preferably at most 30 °).
- At least one PC-1, PC-2, PC-3, PC-4 upstream curve has tangents at its extremal control points inclined by at least 20 °. In the case of four upstream curves, it is the second PC-2 attack curve (which has the highest inclinations of all the building curves).
- any tangent to an upstream curve PC1, PC-2, PC-3, PC-4 at the extreme pressure intrados control point is more inclined than the tangent to the PC-5 downstream curve at the control point extremal of intrados.
- the inclination of intrados can be decreasing by traversing the vein (whereas it is known that it is increasing), or increasing and then decreasing.
- At least two PC-1, PC-2, PC-3, PC-4 upstream curves are such that the inclination of the tangents to each construction curve PC-1, PC-2, PC-3 , PC-4, PC-5 at the endal control point of the intrados then decreases while traversing the PC-1, PC-2, PC-3, PC-4, PC-5 construction curves of the leading edge (BA) at the edge leakage of the blade 31, 3E.
- the maximum inclination of the tangent at the end-point control point is reached for a curve other than the first PC-1 drive curve and the PC-5 downstream curve. In practice this maximum is reached at the level of the second PC-2 attack curve (see below).
- each construction curve PC-1, PC-2, PC-3, PC-4, PC-5 is defined by eight parameters among all the parameters mentioned before.
- the last four parameters are the voltage coefficient of a half-tangent left to the curve at the intermediate control point of extrados, the voltage coefficient of a half -tangent straight to the curve at the Extrados upper control point, the tension coefficient from a left half tangent to the curve at the endal control point of intrados, and the tension coefficient of one half straight tangent to the curve at the intermediate intrados control point.
- All voltage coefficients associated with a half-tangent at a control point can be equal across all PC-1, PC-2, PC-3, PC-4, PC-5 construction curves.
- the extremal and intermediate extrados control points of the PC-5 downstream curve have an abscissa difference of at least 15 mm;
- control points of a PC-1, PC-2, PC-3, PC-4, PC-5 construction curve (thus including the control points extremal and intermediate intrados of the downstream curve PC-5) have an abscissa difference of at most 20 mm, and advantageously at most 15 mm.
- the extremal and intermediate extrados control points of the PC-5 downstream curve have an abscissa difference of between 15 and 25 mm, and advantageously between 15 and 20 mm;
- the endal and intermediate intrados control points of the PC-5 downstream curve have a difference in abscissa of between 5 and 15 mm, advantageously between 5 and 10 mm.
- the parameterization being implemented according to one or more parameters defining at least one of the extreme control points (advantageously all or part of the eight parameters mentioned previously);
- Some parameters of the extremal or intermediate control points for example the inclination intervals of the tangents, are fixed so as to respect the desired slope conditions.
- criteria can be chosen as criteria to be optimized when modeling each curve.
- it is possible to try to maximize mechanical properties such as resistance to mechanical stresses, frequency responses, blade displacements 3E, 31, aerodynamic properties such as efficiency, pressure rise, capacity flow rate or pumping margin, etc.
- optimization consists in varying (generally randomly) these various parameters under stress, until they determine their optimal values for a predetermined criterion.
- a “smoothed" curve is then obtained by interpolation from the determined crossing points.
- the number of calculations required is then directly related to the number of input parameters of the problem. Indeed, most often the number of calculation for a correct answer surface is two power the number of parameters
- connection curve (visible for example in FIG. 2b), which can be the subject of a specific modeling, notably also via the use of splines and user control points.
- FIG. 5b clearly shows the appearance of a "pocket" of negative axial speed at the trailing edge BF, representative of a peeling phenomenon.
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- Engineering & Computer Science (AREA)
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (7)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP14828221.3A EP3084133B1 (fr) | 2013-12-19 | 2014-12-16 | Pièce de turbomachine à surface non-axisymétrique |
BR112016013823-6A BR112016013823B1 (pt) | 2013-12-19 | 2014-12-16 | Parte ou conjunto de partes de uma turbomáquina e turbomáquina |
US15/105,453 US10344771B2 (en) | 2013-12-19 | 2014-12-16 | Turbomachine component with non-axisymmetric surface |
JP2016541268A JP6576927B2 (ja) | 2013-12-19 | 2014-12-16 | 非軸対称形表面を有するターボ機械の構成要素 |
RU2016129369A RU2672990C1 (ru) | 2013-12-19 | 2014-12-16 | Деталь газотурбинного двигателя с неосесимметричной поверхностью |
CN201480073420.0A CN106414903B (zh) | 2013-12-19 | 2014-12-16 | 具有非轴对称表面的涡轮机部件或部件组 |
CA2933776A CA2933776C (fr) | 2013-12-19 | 2014-12-16 | Piece de turbomachine a surface non-axisymetrique |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1363061 | 2013-12-19 | ||
FR1363061A FR3015552B1 (fr) | 2013-12-19 | 2013-12-19 | Piece de turbomachine a surface non-axisymetrique |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2015092263A1 true WO2015092263A1 (fr) | 2015-06-25 |
Family
ID=50729555
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2014/053373 WO2015092263A1 (fr) | 2013-12-19 | 2014-12-16 | Pièce de turbomachine à surface non-axisymétrique |
Country Status (9)
Country | Link |
---|---|
US (1) | US10344771B2 (fr) |
EP (1) | EP3084133B1 (fr) |
JP (1) | JP6576927B2 (fr) |
CN (1) | CN106414903B (fr) |
BR (1) | BR112016013823B1 (fr) |
CA (1) | CA2933776C (fr) |
FR (1) | FR3015552B1 (fr) |
RU (1) | RU2672990C1 (fr) |
WO (1) | WO2015092263A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
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JP6708995B2 (ja) * | 2017-04-17 | 2020-06-10 | 株式会社Ihi | 軸流流体機械の翼の設計方法及び翼 |
CN111435399B (zh) * | 2018-12-25 | 2023-05-23 | 中国航发商用航空发动机有限责任公司 | 风扇组件的造型方法 |
US11480073B2 (en) * | 2020-11-24 | 2022-10-25 | Rolls-Royce Plc | Gas turbine engine nacelle and method of designing same |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
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FR1353439A (fr) | 1963-04-17 | 1964-02-21 | Basf Ag | Procédé pour la production de n-cyanamides cycliques |
EP1126132A2 (fr) | 2000-02-18 | 2001-08-22 | General Electric Company | Paroi radiale profilée pour compresseur |
EP1239116A2 (fr) * | 2001-03-07 | 2002-09-11 | General Electric Company | Rotor intégral nervuré |
EP1995410A1 (fr) * | 2006-03-16 | 2008-11-26 | Mitsubishi Heavy Industries, Ltd. | Paroi de bout de grille d'aubes de turbine |
EP2085620A1 (fr) | 2008-01-30 | 2009-08-05 | Snecma | Compresseur de turboréacteur |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS57167203U (fr) * | 1981-04-17 | 1982-10-21 | ||
JP4856538B2 (ja) * | 2003-04-21 | 2012-01-18 | シーメンス、プラダクツ、ライフサイクル、マニジマント、ソフトウエア、インク | 曲率連続性を有する形で複数辺での曲面マッチングを行うためのシステムと方法 |
GB0518628D0 (en) * | 2005-09-13 | 2005-10-19 | Rolls Royce Plc | Axial compressor blading |
FR2940172B1 (fr) * | 2008-12-18 | 2011-01-21 | Snecma | Procede de fabrication d'une aube de turbomachine |
GB0903404D0 (en) * | 2009-03-02 | 2009-04-08 | Rolls Royce Plc | Surface profile evaluation |
FR2950942B1 (fr) * | 2009-10-02 | 2013-08-02 | Snecma | Rotor d'un compresseur de turbomachine a paroi d'extremite interne optimisee |
FR2971540B1 (fr) * | 2011-02-10 | 2013-03-08 | Snecma | Ensemble pale-plateforme pour ecoulement supersonique |
US8807930B2 (en) * | 2011-11-01 | 2014-08-19 | United Technologies Corporation | Non axis-symmetric stator vane endwall contour |
FR3011888B1 (fr) * | 2013-10-11 | 2018-04-20 | Snecma | Piece de turbomachine a surface non-axisymetrique |
-
2013
- 2013-12-19 FR FR1363061A patent/FR3015552B1/fr active Active
-
2014
- 2014-12-16 EP EP14828221.3A patent/EP3084133B1/fr active Active
- 2014-12-16 WO PCT/FR2014/053373 patent/WO2015092263A1/fr active Application Filing
- 2014-12-16 US US15/105,453 patent/US10344771B2/en active Active
- 2014-12-16 RU RU2016129369A patent/RU2672990C1/ru active
- 2014-12-16 CA CA2933776A patent/CA2933776C/fr active Active
- 2014-12-16 CN CN201480073420.0A patent/CN106414903B/zh active Active
- 2014-12-16 JP JP2016541268A patent/JP6576927B2/ja active Active
- 2014-12-16 BR BR112016013823-6A patent/BR112016013823B1/pt active IP Right Grant
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1353439A (fr) | 1963-04-17 | 1964-02-21 | Basf Ag | Procédé pour la production de n-cyanamides cycliques |
EP1126132A2 (fr) | 2000-02-18 | 2001-08-22 | General Electric Company | Paroi radiale profilée pour compresseur |
EP1239116A2 (fr) * | 2001-03-07 | 2002-09-11 | General Electric Company | Rotor intégral nervuré |
EP1995410A1 (fr) * | 2006-03-16 | 2008-11-26 | Mitsubishi Heavy Industries, Ltd. | Paroi de bout de grille d'aubes de turbine |
EP2085620A1 (fr) | 2008-01-30 | 2009-08-05 | Snecma | Compresseur de turboréacteur |
Also Published As
Publication number | Publication date |
---|---|
JP6576927B2 (ja) | 2019-09-18 |
EP3084133B1 (fr) | 2019-04-17 |
CA2933776A1 (fr) | 2015-06-25 |
RU2672990C1 (ru) | 2018-11-21 |
FR3015552B1 (fr) | 2018-12-07 |
BR112016013823A2 (fr) | 2017-08-08 |
EP3084133A1 (fr) | 2016-10-26 |
JP2017505399A (ja) | 2017-02-16 |
US20170023003A1 (en) | 2017-01-26 |
RU2016129369A (ru) | 2018-01-24 |
CA2933776C (fr) | 2022-04-05 |
CN106414903A (zh) | 2017-02-15 |
BR112016013823B1 (pt) | 2022-03-15 |
FR3015552A1 (fr) | 2015-06-26 |
CN106414903B (zh) | 2018-01-02 |
US10344771B2 (en) | 2019-07-09 |
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