US20110110788A1 - Blade with 3d platform comprising an inter-blade bulb - Google Patents
Blade with 3d platform comprising an inter-blade bulb Download PDFInfo
- Publication number
- US20110110788A1 US20110110788A1 US12/919,781 US91978109A US2011110788A1 US 20110110788 A1 US20110110788 A1 US 20110110788A1 US 91978109 A US91978109 A US 91978109A US 2011110788 A1 US2011110788 A1 US 2011110788A1
- Authority
- US
- United States
- Prior art keywords
- airfoil
- blade
- inter
- boss
- ring
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/70—Shape
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- This invention relates to a blade for a turbomachine impeller comprising an airfoil formed with a pressure surface, a suction surface, a trailing edge, and a leading edge, and a platform extending at one of the ends of the airfoil in a direction which is globally perpendicular to a longitudinal direction of the airfoil, the blade being adapted to be arranged with a plurality of substantially identical blades to form a ring around a ring axis and define therealong an upstream and a downstream area, wherein the airfoils are arranged substantially radially in the ring, and the adjacent blade platforms join in pairs so as to form an inter-airfoil surface linking the pressure surface of an airfoil to the suction surface of the neighboring airfoil.
- This impeller may be mobile, and thus receive energy from the jet, or communicate energy to the jet traveling through the impeller; it may also be fixed, and in this case, its function is to canalize the jet.
- the blade can be a distinct part as such, or integrated with other blades so as to form for instance a distributor sector or a multiple bladed disk.
- a turbomachine comprises several blade stages, forming a series of fixed or mobile impellers, successively arranged along the fluid path through the turbomachine (There may be several paths, especially in the case of bypass engines).
- the efficiency of the turbomachine is directly related to the capability of each of the impellers, and thus in particular each of the blades belonging thereto, to efficiently interact with the jet, i.e. without unnecessarily dissipating energy.
- jet speeds may be significant, namely supersonic: for a blade arranged in such a jet, it is essential to optimize the flow quality of the jet around the blade.
- the shape of the airfoil must naturally be optimized so as to efficiently guide the jet, in which the airfoil is located, or to receive or transmit maximum energy to the jet without dissipating energy by heating.
- the shape of the airfoil is important, it has been found that the shape of the surface of the platform on the side of the airfoil also plays an essential part for the flow quality of the jet through the blade. Thus, the phenomena, which the platforms of an impeller may affect can account for 30% of the total losses thereat.
- a platform surface designates the surface of the platform on the side of the airfoil, without repeating on which side of this surface it is located.
- FIGS. 1 and 2 The passage of the jet around the blades as those indicated in the preamble is illustrated in FIGS. 1 and 2 .
- FIG. 1 shows three identical blades 10 , which are part of an impeller 100 presented in FIG. 2 .
- Each blade 10 is designed to be assembled with other identical blades 10 so as to form an impeller 100 .
- This impeller is essentially composed of the blades 10 mounted on a rotor disk 20 .
- the blades 10 are mounted periodically around the axis A of the wheel. Globally, the fluid jet flows along the axis A of an upstream side to a downstream side of the impeller.
- Each blade 10 comprises an airfoil 50 , a platform 60 , as well as a root 66 in the represented specific case of a rotor blade for fixing the blade to a rotor disk.
- the platform 60 extends in a direction which is globally perpendicular to the longitudinal direction of the airfoil 50 and comprises a platform surface 62 on the side of the airfoil.
- the platforms thereof join in pairs so as to create a substantially continuous surface, the so-called ‘inter-airfoil’ surface 70 extending from the pressure surface 56 of one airfoil to the suction surface 58 of the neighboring airfoil.
- the inter-airfoil surface groups the adjacent portions of the platform surfaces 62 of two adjacent blades 10 , 10 ′ located between their respective airfoils 50 .
- the platform surface 62 is linked to the outer surfaces of the airfoil 50 by connecting surfaces 18 (which are substantially connecting fillets having a tapered radius).
- the surface 62 of the platform 60 is a surface of revolution, i.e. that the area thereof is substantially part of a surface of revolution around the axis A of the impeller.
- a surface of revolution around an axis designates a surface generated by rotating a curve around said axis. Such a shape is common for blade platform surfaces for turbomachine impellers.
- FIG. 3 schematically presents how the pressure field is established in the ‘inter-airfoil channel’ 30 extending between the airfoils.
- FIG. 3 is a sectional view perpendicular to the respective axes of the airfoils of two blades 10 and 10 ′ mounted side by side in an impeller. More particularly, FIG. 3 shows approximately the pressure field which can usually be observed close to the inter-airfoil surface 70 between the suction surface 58 of a first airfoil and the pressure surface 56 ′ of a second airfoil.
- FIG. 3 comprises an iso-pressure curve 40 corresponding to a relatively high pressure, and an iso-pressure curve 42 corresponding to a relatively low pressure, these pressures being observed in the jet during operation of the turbomachine.
- a steep pressure gradient J is created between the pressure surface and the suction surface of the two airfoils due to pressure being greater close to the pressure surface than close to the suction surface.
- a transverse flow to the ‘inter-airfoil’ channel 30 is generated at the root (and head) of the airfoils, and particles thus deflected are pushed towards the suction surface of the airfoil 50 .
- strong secondary flows not directed in the main direction of flow are created which will generate eddies, namely close to the suction surface.
- the U.S. Pat. No. 7,220,100 proposes an inter-airfoil surface shape comprising mainly a convex ramp located immediately adjacent to the pressure surface of the airfoil, and a concave area located immediately adjacent to the suction surface of the airfoil, each of these areas being located substantially at the mid-point of the airfoil chord.
- the U.S. Pat. No. 6,283,713 proposes another shape for the inter-airfoil surface, on the one hand comprising a convex region adjacent to the suction surface of the blade, and a concave region adjacent to the pressure surface of the blade, with these two regions having a significant dimension as they extend over most of the length of the chord of the blade.
- the blade comprises at the trailing edge a boss and a recess, respectively located on the side of the suction surface and the pressure surface.
- these configurations of the inter-airfoil surface do not allow for the problem of unnecessary energy dissipation near this surface to be solved efficiently.
- the inter-airfoil surface in an upstream half of the airfoil, comprises a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the pressure surface.
- a major advantage of the invention is due to the fact that the special shape of the platform surface previously exhibited allows for significant reduction of stray flows between the airfoils close to this surface between the airfoils. Furthermore, this surface may still be very easy to machine as a large part of the surface can be a surface of revolution.
- the presence of the boss results in the speed of the jet increasing as pressure thereof is decreasing, namely in the area neighboring the pressure surface, which usually has greater pressure.
- the result will be that the high pressure area is reduced, and this will lead to a decrease in the pressure gradient in the inter-airfoil channel and a reduction of the undesirable energy dissipating eddies.
- the objective of keeping a recess between this boss and the pressure surface is to center the high pressure reduction effect indicated above, precisely on the high pressure area. Due to such centering of the boss, not against the pressure surface but at a distance therefrom, the effect of the boss (attenuation of the harmful high pressure area) is at a maximum.
- the recessed passage substantially located along the pressure surface, generates a slight relative pressure increase in this area, thus contributing to dividing the high pressure area from the low pressure area, located opposite to the vicinity of the suction surface of the neighboring airfoil.
- the various examples used present a blade having a platform located on the inner side with respect to the airfoil, in the radial direction, and not on the outside. It should be noted in this respect that the invention equally aims at a blade comprising a platform located at the head of the airfoil, i.e. on the side radially opposite the center of the ring, and a blade comprising a platform located at the root of the airfoil, on the inside with respect to the ring.
- a blade comprising both of these platforms, at the head and the root of the airfoil, is also possible, with at least one platform arranged so that an inter-airfoil surface according to the invention can be formed.
- the invention aims at any blade capable of being integrated into a turbomachine, and in particular into aeronautical turbomachines.
- the inventive blade turns out to be particularly useful in turbine stages, especially of low pressure turbines.
- the platform of the blade is defined with respect to a profile perpendicular to ring axis A.
- the inter-airfoil surface has a profile located in a plane perpendicular to the axis of the ring and located axially in an upstream half of the airfoil, said airfoil successively comprising a recess followed by a boss, starting from the pressure surface of the airfoil.
- the efficiency of the invention is particularly great when the recessed shape followed by a boss appears in a section of the inter-airfoil surface perpendicular to axis A.
- a position axially defined with respect to the airfoil can also be defined equivalently with respect to the extension along axis A, of a cross-section of the airfoil close to the platform of the blade. Indeed, as the airfoil is arranged radially in the ring, the extension thereof along axis A, or the extension of a cross-section are substantially identical.
- the cross-section of the airfoil can for instance be the section in the plane (P) represented in FIG. 1 , and represented by the profiles 72 and 72 ′ in FIG. 3 .
- This section axially extends from line 46 at the highest upstream point of the airfoil (close to the platform surface), to line 48 corresponding to the lowest downstream point of the airfoil.
- the inter-airfoil surface comprises a part of revolution having a shape of revolution with respect to the axis of the ring, located on the side of the suction surface of the airfoil neighboring the boss.
- the boss is linked to said part of revolution by a radially descending surface.
- the surface between the boss and the part of revolution descends monotonously, without having intermediate folds, recesses, or bosses.
- the recessed passage comprises one part having a shape of revolution with respect to the axis of the ring.
- the inter-airfoil surface comprises a part having a shape of revolution with respect to the ring axis and extending axially throughout the downstream half of the airfoil.
- the three possibly complementary embodiments presented above allow for minimizing the production cost of the blade by keeping significant-sized parts of revolution, be it in a part of the inter-airfoil surface corresponding to the recessed passage or in a part of the inter-airfoil surface located between the boss and the suction surface of the neighboring airfoil, or else in the (axially) downstream half of the inter-airfoil surface.
- the part of the production tools corresponding to the surfaces of revolution is thus particularly easy to make, thereby providing an equivalent reduction in the production cost of the blade.
- the boss can continue or extend upstream or downstream of the inter-airfoil surface.
- a second object of the invention is to propose a high performance turbomachine distributor sector, and the production cost of which is still reasonable. This objective is achieved in that the turbomachine distributor sector comprises at least one blade like those defined before.
- a third object of the invention is to propose a high performance impeller, and the production cost of which is still reasonable. This objective is achieved in that the impeller comprises a plurality of blades like those defined before.
- a fourth object of the invention is to propose a high performance turbomachine, and the production cost of which is still reasonable. This objective is achieved in that the turbomachine comprises at least one impeller like the one defined before.
- FIG. 1 already described is a perspective view of three known blades arranged in their relative position as they are mounted in an impeller;
- FIG. 2 already described is a perspective view of an impeller comprising the blades of FIG. 1 ;
- FIG. 3 already described is a section perpendicular to the axis of the airfoils of two airfoils of the aerodynamic blades represented in FIG. 1 showing the pressure fields in the space separating both blades;
- FIG. 4 is a section similar to the section of FIG. 3 , but with both airfoils being part of blades according to the invention;
- FIG. 5 is a section of two aerodynamic blades according to the invention, showing the shape of the inter-airfoil surface by means of contour lines;
- FIG. 6 is a section substantially perpendicular to the ring axis, of the inter-airfoil channel between two aerodynamic blades according to the invention.
- the present invention defines a platform surface shape allowing to minimize stray turbulent phenomena close to the inter-airfoil surface, and thereby to increase the efficiency of the blade and thus the impeller. Comparing FIGS. 3 and 4 shows the relative effect of the invention on the pressure field in the inter-airfoil channel 30 allowing to obtain the specific shape of an inventive blade.
- FIG. 5 shows sections 72 and 72 ′ respectively of the two airfoils 50 and 50 ′ in a radial view of the airfoils, i.e. substantially along the longitudinal axis of these two airfoils.
- Section 72 (like the identical section 72 ′) is a section of airfoil 50 established close to the platform of the blade, on the flow side, at a distance from the platform sufficient for the section to represent the lower part of the airfoil and not to show the connecting surfaces 18 between the airfoil and the platform.
- Sections 72 and 72 ′ axially extend between lines 46 and 48 , respectively corresponding to the highest upstream point and the lowest downstream point of the section, thus defining a scale along the section, respectively going from 0% to 100% from line 46 to line 48 along axis A.
- FIG. 6 shows the profile 80 going through the inter-airfoil surface 70 between two inventive blades.
- Profile 80 is a sectional profile recorded in a plane perpendicular to axis A of the ring. This profile is located axially in the upstream half of the section of the airfoil.
- FIG. 6 shows by means of contour lines the shapes of the inter-airfoil surface 70 between the two contours 72 and 72 ′ previously presented in relation with FIG. 6 .
- Inter-airfoil surface 70 comprises a boss 32 , located at a distance from the pressure surface 56 ′, but still close thereto, and separated therefrom by a recessed passage 34 following therealong and facilitating the jet going along the pressure surface.
- Boss 32 is located axially mainly in the upstream half of section 72 of airfoil 50 .
- the boss has an apex ( 32 ) located axially between 0 and 50% of the airfoil ( 50 ) on the upstream side, and preferably between 0 and 25% thereof.
- Boss 32 is linked to the suction surface, following contour 80 , by a slope 36 (or a radially descending surface) continued by one part of a surface of revolution 38 .
- the part of the inter-airfoil surface located axially in the downstream half of the airfoil is formed by a surface of revolution 39 with respect to the axis A of the ring.
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0851274A FR2928173B1 (fr) | 2008-02-28 | 2008-02-28 | Aube avec plateforme 3d comportant un bulbe interaubes. |
FR0851274 | 2008-02-28 | ||
PCT/FR2009/050317 WO2009112774A2 (fr) | 2008-02-28 | 2009-02-27 | Aube avec plateforme 3d comportant un bulbe interaubes |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2009/050317 A-371-Of-International WO2009112774A2 (fr) | 2008-02-28 | 2009-02-27 | Aube avec plateforme 3d comportant un bulbe interaubes |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/591,576 Continuation US9518467B2 (en) | 2008-02-28 | 2015-01-07 | Blade with 3D platform comprising an inter-blade bulb |
Publications (1)
Publication Number | Publication Date |
---|---|
US20110110788A1 true US20110110788A1 (en) | 2011-05-12 |
Family
ID=40278893
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/919,781 Abandoned US20110110788A1 (en) | 2008-02-28 | 2009-02-27 | Blade with 3d platform comprising an inter-blade bulb |
US14/591,576 Active US9518467B2 (en) | 2008-02-28 | 2015-01-07 | Blade with 3D platform comprising an inter-blade bulb |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/591,576 Active US9518467B2 (en) | 2008-02-28 | 2015-01-07 | Blade with 3D platform comprising an inter-blade bulb |
Country Status (9)
Country | Link |
---|---|
US (2) | US20110110788A1 (ja) |
EP (1) | EP2257694B1 (ja) |
JP (1) | JP2011513626A (ja) |
CN (1) | CN101960093A (ja) |
BR (1) | BRPI0907535A2 (ja) |
CA (1) | CA2716244A1 (ja) |
FR (1) | FR2928173B1 (ja) |
RU (1) | RU2496986C2 (ja) |
WO (1) | WO2009112774A2 (ja) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20120051900A1 (en) * | 2010-08-31 | 2012-03-01 | General Electric Company | Turbine nozzle with contoured band |
US20140154068A1 (en) * | 2012-09-28 | 2014-06-05 | United Technologies Corporation | Endwall Controuring |
US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
US20170370234A1 (en) * | 2016-06-23 | 2017-12-28 | MTU Aero Engines AG | Blade or guide vane with raised areas |
US10344601B2 (en) | 2012-08-17 | 2019-07-09 | United Technologies Corporation | Contoured flowpath surface |
US10577955B2 (en) | 2017-06-29 | 2020-03-03 | General Electric Company | Airfoil assembly with a scalloped flow surface |
US11377960B2 (en) * | 2017-10-26 | 2022-07-05 | Safran Aero Boosters Sa | Shroud having elevations, for a turbomachine compressor |
EP2789802B1 (de) * | 2013-04-09 | 2022-07-13 | MTU Aero Engines AG | Schaufelgitter für eine Turbomaschine und zugehöriges Herstellungsverfahren |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2971539B1 (fr) * | 2011-02-10 | 2013-03-08 | Snecma | Ensemble pale-plateforme pour ecoulement subsonique |
GB201418948D0 (en) * | 2014-10-24 | 2014-12-10 | Rolls Royce Plc | Row of aerofoil members |
EP3219914A1 (de) * | 2016-03-17 | 2017-09-20 | MTU Aero Engines GmbH | Strömungskanal, zugehörige schaufelgitter und strömungsmaschine |
US10876411B2 (en) | 2019-04-08 | 2020-12-29 | United Technologies Corporation | Non-axisymmetric end wall contouring with forward mid-passage peak |
US10968748B2 (en) | 2019-04-08 | 2021-04-06 | United Technologies Corporation | Non-axisymmetric end wall contouring with aft mid-passage peak |
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US6283713B1 (en) * | 1998-10-30 | 2001-09-04 | Rolls-Royce Plc | Bladed ducting for turbomachinery |
US20060127220A1 (en) * | 2004-12-13 | 2006-06-15 | General Electric Company | Fillet energized turbine stage |
US20060140768A1 (en) * | 2004-12-24 | 2006-06-29 | General Electric Company | Scalloped surface turbine stage |
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US20070258818A1 (en) * | 2006-05-02 | 2007-11-08 | United Technologies Corporation | Airfoil array with an endwall depression and components of the array |
US7354243B2 (en) * | 2005-09-13 | 2008-04-08 | Rolls-Royce, Plc | Axial compressor blading |
US8192153B2 (en) * | 2007-03-08 | 2012-06-05 | Rolls-Royce Plc | Aerofoil members for a turbomachine |
US8231353B2 (en) * | 2008-12-31 | 2012-07-31 | General Electric Company | Methods and apparatus relating to improved turbine blade platform contours |
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US20120201688A1 (en) * | 2011-02-08 | 2012-08-09 | Mtu Aero Engines Gmbh | Blade channel having an end wall contour and a turbomachine |
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JPH0633703A (ja) * | 1992-07-14 | 1994-02-08 | Hitachi Ltd | 蒸気タービンダイヤフラム |
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FR2928172B1 (fr) | 2008-02-28 | 2015-07-17 | Snecma | Aube avec plateforme non axisymetrique lineaire. |
-
2008
- 2008-02-28 FR FR0851274A patent/FR2928173B1/fr active Active
-
2009
- 2009-02-27 US US12/919,781 patent/US20110110788A1/en not_active Abandoned
- 2009-02-27 RU RU2010139777/06A patent/RU2496986C2/ru active
- 2009-02-27 BR BRPI0907535-6A patent/BRPI0907535A2/pt not_active IP Right Cessation
- 2009-02-27 JP JP2010548155A patent/JP2011513626A/ja active Pending
- 2009-02-27 CN CN2009801068808A patent/CN101960093A/zh active Pending
- 2009-02-27 WO PCT/FR2009/050317 patent/WO2009112774A2/fr active Application Filing
- 2009-02-27 CA CA2716244A patent/CA2716244A1/fr not_active Abandoned
- 2009-02-27 EP EP09718837A patent/EP2257694B1/fr not_active Revoked
-
2015
- 2015-01-07 US US14/591,576 patent/US9518467B2/en active Active
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Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
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US20120051900A1 (en) * | 2010-08-31 | 2012-03-01 | General Electric Company | Turbine nozzle with contoured band |
US8727716B2 (en) * | 2010-08-31 | 2014-05-20 | General Electric Company | Turbine nozzle with contoured band |
US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
US10344601B2 (en) | 2012-08-17 | 2019-07-09 | United Technologies Corporation | Contoured flowpath surface |
US20140154068A1 (en) * | 2012-09-28 | 2014-06-05 | United Technologies Corporation | Endwall Controuring |
EP2789802B1 (de) * | 2013-04-09 | 2022-07-13 | MTU Aero Engines AG | Schaufelgitter für eine Turbomaschine und zugehöriges Herstellungsverfahren |
US20170370234A1 (en) * | 2016-06-23 | 2017-12-28 | MTU Aero Engines AG | Blade or guide vane with raised areas |
US11319820B2 (en) * | 2016-06-23 | 2022-05-03 | MTU Aero Engines AG | Blade or guide vane with raised areas |
US10577955B2 (en) | 2017-06-29 | 2020-03-03 | General Electric Company | Airfoil assembly with a scalloped flow surface |
US11377960B2 (en) * | 2017-10-26 | 2022-07-05 | Safran Aero Boosters Sa | Shroud having elevations, for a turbomachine compressor |
Also Published As
Publication number | Publication date |
---|---|
EP2257694A2 (fr) | 2010-12-08 |
JP2011513626A (ja) | 2011-04-28 |
US20150147179A1 (en) | 2015-05-28 |
FR2928173B1 (fr) | 2015-06-26 |
WO2009112774A2 (fr) | 2009-09-17 |
RU2496986C2 (ru) | 2013-10-27 |
CA2716244A1 (fr) | 2009-09-17 |
CN101960093A (zh) | 2011-01-26 |
EP2257694B1 (fr) | 2013-01-23 |
WO2009112774A3 (fr) | 2009-10-29 |
BRPI0907535A2 (pt) | 2015-07-28 |
RU2010139777A (ru) | 2012-04-10 |
FR2928173A1 (fr) | 2009-09-04 |
US9518467B2 (en) | 2016-12-13 |
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