EP0385833A1 - Turbine rotor blade having a compensated foot moment - Google Patents
Turbine rotor blade having a compensated foot moment Download PDFInfo
- Publication number
- EP0385833A1 EP0385833A1 EP90400501A EP90400501A EP0385833A1 EP 0385833 A1 EP0385833 A1 EP 0385833A1 EP 90400501 A EP90400501 A EP 90400501A EP 90400501 A EP90400501 A EP 90400501A EP 0385833 A1 EP0385833 A1 EP 0385833A1
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- Prior art keywords
- blade
- foot
- gravity
- sections
- curve
- 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.)
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Classifications
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- 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
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- 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
Definitions
- the present invention relates to a movable blade of a turbomachine whose compensated bending moments at the foot of the blade are compensated.
- FR-A 2 556 409 defines a blade with reduced centrifugal stresses for which the geometrical location of the centers of gravity of the blade sections is nonlinear and has two parts of inclinations opposite with respect to a radial straight line.
- Figure 2 of the drawings schematically shows this solution and the curve 1a representing the area centers of gravity with respect to the platform 2a and 3a at the foot of the blade.
- Another proposed solution shown diagrammatically in FIG. 3 shows a non-linear curve 1b of the geometrical location of the centers of gravity of the cross sections of the blade of the blade between the platform 2b and the foot 3b on the one hand and the radially external end. on the other hand.
- the curve 1b in this case has a variable inclination which corresponds to the application of a continuous law of compensation for bending moments.
- the invention defines a movable blade of a turbomachine which does not have the drawbacks of known prior solutions while ensuring cancellation of the bending moments at the foot of the blade by compensation.
- Said blade is characterized in that the geometrical location of the centers of gravity of the cross sections whose stacking forms the blade of the blade is a curve of which one end has its starting point, in the plane of axial symmetry of the foot of blade, at the meeting point of the radial straight line passing through the axis of rotation of the motor with the zone of connection of the blade with the platform and the foot of the blade and which then progressively connects to at least one first line segment parallel to said radial line and axially spaced apart.
- the geometrical location of the centers of gravity of the cross sections comprises, in addition to said line segment, a second line segment located between said fin and the radially outer end of blade , axially spaced from the first segment and progressively connecting to said first segment at said fin.
- a blade 10 according to the invention of the movable blade type of a turbomachine is shown diagrammatically in FIG. 4 by its foot 11, its platform 12 and the curve 13 which represents the geometrical location of the centers of gravity of the cross sections whose stacking forms the aerodynamic blade of the blade 10.
- the curve 13 has an origin at the level of the platform 12 at the center point 0 where the radial straight line passing through the axis of rotation A of the engine and contained in the plane of symmetry of the foot 11 meets the platform 12 and the foot 11.
- the curve 13 comprises along the blade of the blade 10 a straight part axially offset with respect to said radial straight line 1 shown in dotted lines in FIG.
- the blade has an evolving part for connecting the blade to the foot which corresponds to a connecting part 13a of the curve of the geometric location of the centers of gravity of the sections.
- a blade 20 shown diagrammatically in FIG. 5 comprises intermediate heels or fins carried laterally by the blade of the blade and symbolized at 23 in FIG. 5, the curve of the geometrical location of the centers of gravity of the cross sections of the blade of the blade 20 takes the form indicated in FIG. 5.
- the curve includes, as before, an origin 0 centered on the foot 21 and the platform 22 of the blade 20, a continuous evolving part of connection 24a to a first part right 24 axially offset from the radial line 1 up to the level of the fin 23 and beyond the fin 23 again a offset by a continuous evolving part connecting 25a to a second straight part 25 to the end of the blade of the blade 20.
- FIG. 6 shows an example of the actual curves obtained in the application to a movable blade of a turbomachine and representing the geometrical location of the centers of gravity of the cross sections of the blade, one 30 according to axial coordinates and the other 40 according to tangential coordinates, and comprising, remarkably in accordance with the invention, the right-hand parts offset with respect to the central radial straight line.
- FIG. 7 shows an example in the application to a movable blade of a turbomachine comprising intermediate heels or fins carried laterally by the blade of the blade.
- the curves 50 and 60 representing the geometrical location of the centers of gravity of the cross sections of the blade, respectively according to axial coordinates and tangential coordinates, comprise from an origin O at the center of the foot of the blade, a portion 51 or 61 of connection corresponding to a continuous evolving zone of connection of the blade to the plane of symmetry of the foot of the blade, then a part of line 52 or 62 offset relative to the radial line 1 centered on the foot, which corresponds to a "block" offset of the sections of the blade of the blade, followed by a new portion of curve 53 or 63 at the level of the fin which is connected to a new portion of straight line 54 or 64 which has an additional offset by with respect to said radial straight line 1 and corresponds to the offset of a second "en bloc" part of sections of the blade of the blade.
- FIG. 8 schematically shows an example of production of movable blades in accordance with the invention. Only a very precise geometrical analysis makes it possible to determine the geometrical place of the centers of gravity of the transverse sections of blade which is not a curve materialized on part. We find on a blade 70, a foot 71, a platform 72, a blade 73 and the fins 74 carried by said blade as well as a zone 73a for connecting the blade 73 to the foot 71.
- the offset in parts and in block of the cross sections of the blade of the blades according to the invention makes it possible to obtain the creation of induced return moments in the centrifugal field and in the case of fins, also to balance the induced effects. This gives rise to a cancellation of the bending moments at the foot of the blade which is the mechanically most stressed area.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
La présente invention concerne une aube mobile de turbomachine dont les moments de flexion résultants au pied de l'aube sont compensés.The present invention relates to a movable blade of a turbomachine whose compensated bending moments at the foot of the blade are compensated.
Elle est applicable aussi bien à des aubes mobiles de compresseur ou de turbine axiaux qu'à des hélices.It is applicable both to moving blades of an axial compressor or turbine and to propellers.
De manière connue, les études aérodynamiques de définition du profil de pale d'une aube mobile conduisent à prévoir un lieu géométrique des centres de gravité de l'ensemble des sections transversales de la pale d'aube représenté par une droite radiale passant par l'axe longitudinal de rotation du moteur et contenu dans le plan médian coupant le pied et la plate-forme de l'aube. La figure 1 des dessins joints schématise ce résultat et montre une droite 1, lieu des centres de gravité des sections transversales de pale, rencontrant l'axe A du moteur et centrée sur la plate-forme 2 et le pied 3 de l'aube.In a known manner, aerodynamic studies defining the blade profile of a movable blade lead to providing a geometrical location of the centers of gravity of all of the cross sections of the blade of the blade represented by a radial straight line passing through the longitudinal axis of rotation of the motor and contained in the median plane intersecting the foot and the platform of the blade. Figure 1 of the accompanying drawings shows this result schematically and shows a
Ce résultat ne répond toutefois pas aux exigences mécaniques du comportement d'une telle aube en fonctionnement sous l'effet des contraintes internes susceptibles d'induire des déformations et dues aux forces aérodynamiques sous l'effet des efforts des gaz, aux forces centrifuges et aux efforts résultant des effets de couplage en flexion et torsion du profil de pale. Les solutions connues actuellement de définition d'un profil de pale d'aube conduisent généralement à une inégalité de répartition des charges des deux côtés du pied de l'aube. Cette répartition dissymétrique des efforts transmis au disque qui porte les aubes d'un étage mobile et résultant des forces s'exerçant sur la pale de l'aube ne permet pas de tirer le meilleur parti des caractéristiques mécaniques de résistance du disque.This result does not however meet the mechanical requirements of the behavior of such a blade in operation under the effect of internal stresses liable to induce deformations and due to aerodynamic forces under the effect of gas forces, centrifugal forces and forces resulting from the coupling effects in bending and torsion of the blade profile. The currently known solutions for defining a blade profile of the blade generally lead to an uneven distribution of the loads on the two sides of the blade root. This asymmetrical distribution of the forces transmitted to the disc which carries the blades of a movable stage and resulting from the forces exerted on the blade of the blade does not make it possible to take the best advantage of the mechanical characteristics. disc resistance.
Des améliorations ont cependant déjà été proposées. FR-A 2 556 409 définit une aube à contraintes centrifuges réduites pour laquelle le lieu géométrique des centres de gravité des sections de pale est nonlinéaire et présente deux parties d'inclinaisons opposées par rapport à une droite radiale. La figure 2 des dessins schématise cette solution et montre la courbe 1a représentant ce lieu des centres de gravité par rapport à la plate-forme 2a et au pied 3a de l'aube. Une autre solution proposée schématisée sur la figure 3 montre une courbe 1b non linéaire du lieu géométrique des centres de gravité des sections transversales de pale d'aube entre la plate-forme 2b et le pied 3b d'une part et l'extrémité radialement externe de l'aube d'autre part. La courbe 1b présente dans ce cas une inclinaison variable qui correspond à l'application d'une loi continue de compensation des moments de flexion.Improvements have, however, already been proposed. FR-A 2 556 409 defines a blade with reduced centrifugal stresses for which the geometrical location of the centers of gravity of the blade sections is nonlinear and has two parts of inclinations opposite with respect to a radial straight line. Figure 2 of the drawings schematically shows this solution and the
Ces méthodes connues présentent toutefois des inconvénients, notamment dans certaines applications particulières. La non-linéarité des profils obtenus et notamment du bord d'attaque et du bord de fuite de l'aube est à l'origine de difficultés supplémentaires de réalisation et rend également plus difficile les contrôles en utilisation. Ces méthodes imposent également pour obtenir une définition satisfaisante de l'aube des itérations souvent très laborieuses. En outre, notamment dans le cas d'aubes de grandes dimensions telles que des aubes de soufflante de turbomachine, ces méthodes ont l'inconvénient d'écarter sensiblement la tête de l'aube d'une position radiale dans l'axe du pied d'aube, en particulier dans le sens axial, ce qui entraîne, notamment dans une veine à paroi externe conique, des jeux trop importants entre l'extrémité d'aube et le carter correspondant. De même dans le cas d'aubes notamment de grandes dimensions, comportant des ailettes latérales dites nageoires, un appui correct en fonctionnement entre nageoires voisines devient difficile à obtenir, ce qui contrarie leur fonction d'amortissement des vibrations.However, these known methods have drawbacks, in particular in certain specific applications. The non-linearity of the profiles obtained and in particular of the leading edge and the trailing edge of the blade is at the origin of additional difficulties of production and also makes controls in use more difficult. These methods also require, in order to obtain a satisfactory definition of the dawn, often very laborious iterations. In addition, in particular in the case of large blades such as turbine engine fan blades, these methods have the drawback of substantially moving the head of the blade from a radial position in the axis of the foot of the blade. '' blade, in particular in the axial direction, which causes, especially in a vein with conical outer wall, excessive play between the blade tip and the housing corresponding. Similarly, in the case of particularly large blades, comprising lateral fins called fins, correct support in operation between neighboring fins becomes difficult to obtain, which counteracts their vibration damping function.
L'invention définit une aube mobile de turbomachine ne présentant pas les inconvénients des solutions antérieures connues tout en assurant une annulation des moments de flexion au pied de l'aube par compensation. Ladite aube est caractérisée en ce que le lieu géométrique des centres de gravité des sections transversales dont l'empilement forme la pale de l'aube est une courbe dont une extrémité a son point de départ, dans le plan de symétrie axiale du pied d'aube, au point de rencontre de la droite radiale passant par l'axe de rotation du moteur avec la zone de raccordement de la pale avec la plate-forme et le pied de l'aube et qui ensuite se raccorde progressivement à au moins un premier segment de droite parallèle à ladite droite radiale et axialement écarté.The invention defines a movable blade of a turbomachine which does not have the drawbacks of known prior solutions while ensuring cancellation of the bending moments at the foot of the blade by compensation. Said blade is characterized in that the geometrical location of the centers of gravity of the cross sections whose stacking forms the blade of the blade is a curve of which one end has its starting point, in the plane of axial symmetry of the foot of blade, at the meeting point of the radial straight line passing through the axis of rotation of the motor with the zone of connection of the blade with the platform and the foot of the blade and which then progressively connects to at least one first line segment parallel to said radial line and axially spaced apart.
Avantageusement, lorsqu'une aube comporte des talons intermédiaires dits nageoires, ladite courbe, lieu géométrique des centres de gravité des sections transversales comporte en plus dudit segment de droite un second segment de droite situé entre ladite nageoire et l'extrémité radialement externe d'aube, écarté axialement du premier segment et se raccordant progressivement audit premier segment au niveau de ladite nageoire.Advantageously, when a blade has intermediate heels called fins, said curve, the geometrical location of the centers of gravity of the cross sections comprises, in addition to said line segment, a second line segment located between said fin and the radially outer end of blade , axially spaced from the first segment and progressively connecting to said first segment at said fin.
D'autres caractéristiques et avantages de l'invention seront mieux compris à la lecture de la description qui va suivre d'exemples de réalisation de l'invention, en référence aux dessins annexés sur lesquels :
- - la figure 1 précédemment décrite en détails représente une vue schématique, d'aube suivant une définition théorique connue antérieure ;
- - La figure 2 précédemment décrite en détails représente une vue schématique analogue à celle de la figure 1, d'une aube suivant une définition connue antérieure ;
- - la figure 3 précédemment décrite en détails représente une vue schématique, analogue à celles des figures 1 et 2, d'une aube suivant une définition connue antérieure ;
- - la figure 4 représente, selon une vue schématique analogue à celles des figures 1, 2 et 3, une aube suivant un mode de réalisation conforme à l'invention ;
- - la figure 5 représente, selon une vue schématique analogue à celles des figures 1 à 4, une aube comportant des talons intermédiaires ou nageoires suivant un mode de réalisation conforme à l'invention ;
- - la figure 6 représente, dans un premier exemple d'application à une aube conforme à l'invention, les courbes du lieu géométrique des centres de gravité des sections transversales de la pale de l'aube, respectivement suivant des coordonnées en direction axiale et en direction tangentielle ;
- - la figure 7 représente, dans un deuxième exemple d'application à une aube conforme à l'invention et comportant des talons intermédiaires ou nageoires, les courbes analogues à celles de la figure 6 du lieu géométrique des centres de gravité des sections transversales de la pale de l'aube, respectivement suivant des coordonnées en direction axiale et en direction tangentielle ;
- - la figure 8 montre une vue schématique en perspective d'aubes conformes à l'invention.
- - Figure 1 previously described in detail shows a schematic view of a blade according to a previously known theoretical definition;
- - Figure 2 previously described in detail shows a schematic view similar to that of Figure 1, of a blade according to a known prior definition;
- - Figure 3 previously described in detail shows a schematic view, similar to those of Figures 1 and 2, of a blade according to a previously known definition;
- - Figure 4 shows, in a schematic view similar to those of Figures 1, 2 and 3, a blade according to an embodiment according to the invention;
- - Figure 5 shows, in a schematic view similar to those of Figures 1 to 4, a blade comprising intermediate heels or fins according to an embodiment according to the invention;
- FIG. 6 represents, in a first example of application to a blade according to the invention, the curves of the geometrical location of the centers of gravity of the cross sections of the blade of the blade, respectively according to coordinates in the axial direction and in tangential direction;
- - Figure 7 shows, in a second example of application to a blade according to the invention and comprising intermediate or fin heels, the curves similar to those of Figure 6 of the geometric location of the centers of gravity of the cross sections of the blade of the blade, respectively in coordinates in axial direction and in tangential direction;
- - Figure 8 shows a schematic perspective view of blades according to the invention.
Une aube 10 conforme à l'invention du genre aube mobile de turbomachine est schématisée sur la figure 4 par son pied 11, sa plate-forme 12 et la courbe 13 qui représente le lieu géométrique des centres de gravité des sections transversales dont l'empilement forme la pale aérodynamique de l'aube 10. La courbe 13 a une origine au niveau de la plate-forme 12 au point centre 0 où la droite radiale passant par l'axe de rotation A du moteur et contenue dans le plan de symétrie du pied 11 rencontre la plate-forme 12 et le pied 11. La courbe 13 comporte le long de la pale de l'aube 10 une partie de droite axialement décalée par rapport à ladite droite radiale 1 représentée en traits pointillés sur la figure 4, ce qui correspond à un désaxage "en bloc" des sections transversales de la pale de l'aube, suivant une définition remarquable, conforme à l'invention. Entre la plate-forme et le point centré de la courbe 13 d'une part et ladite partie de droite, d'autre part, l'aube présente une partie évolutive de raccordement de la pale au pied qui correspond à une partie de raccordement 13a de la courbe du lieu géométrique des centres de gravité des sections.A
Dans le cas où une aube 20 schématisée sur la figure 5 comporte des talons intermédiaires ou nageoires portées latéralement par la pale de l'aube et symbolisées en 23 sur la figure 5, la courbe lieu géométrique des centres de gravité des sections transversales de la pale de l'aube 20 prend la forme indiquée sur la figure 5. La courbe comporte comme précédemment une origine 0 centrée sur le pied 21 et la plate-forme 22 de l'aube 20, une partie évolutive continue de raccordement 24a à une première partie de droite 24 axialement décalée par rapport à la droite radiale 1 jusqu'au niveau de la nageoire 23 et au delà de la nageoire 23 à nouveau un décalage par une partie évolutive continue de raccordement 25a à une deuxième partie de droite 25 jusqu'à l'extrémité de la pale de l'aube 20.In the case where a
La figure 6 montre un exemple des courbes réelles obtenues dans l'application à une aube mobile de turbomachine et représentant le lieu géométrique des centres de gravité des sections transversales de l'aube, l'une 30 selon des coordonnées axiales et l'autre 40 selon des coordonnées tangentielles, et comportant, de manière remarquable conforme à l'invention, les parties de droite décalées par rapport à la droite radiale centrale.FIG. 6 shows an example of the actual curves obtained in the application to a movable blade of a turbomachine and representing the geometrical location of the centers of gravity of the cross sections of the blade, one 30 according to axial coordinates and the other 40 according to tangential coordinates, and comprising, remarkably in accordance with the invention, the right-hand parts offset with respect to the central radial straight line.
De manière analogue, la figure 7 monte un exemple dans l'application à une aube mobile de turbomachine comportant des talons intermédiaires ou nageoires portées latéralement par la pale de l'aube. Les courbes 50 et 60 représentant le lieu géométrique des centres de gravité des sections transversales de l'aube, respectivement selon des coordonnées axiales et des coordonnées tangentielles, comportent à partir d'une origine O au centre du pied de l'aube, une portion 51 ou 61 de raccordement correspondant à une zone évolutive continue de raccordement de la pale au plan de symétrie du pied de l'aube, puis une partie de droite 52 ou 62 décalée par rapport à la droite radiale 1 centrée sur le pied, qui correspond à un désaxage "en bloc" des sections de la pale d'aube, suivie d'une nouvelle portion de courbe 53 ou 63 au niveau de la nageoire qui se raccorde à une nouvelle portion de droite 54 ou 64 qui présente un décalage supplémentaire par rapport à ladite droite radiale 1 et correspond au désaxage d'une seconde partie "en bloc" de sections de la pale d'aube.In a similar manner, FIG. 7 shows an example in the application to a movable blade of a turbomachine comprising intermediate heels or fins carried laterally by the blade of the blade. The
La figure 8 montre schématiquement un exemple de réalisation d'aubes mobiles conformes à l'invention. Seule une analyse géométrique très précise permet de déterminer le lieu géométrique des centres de gravité des sections transversales de pale qui n'est pas une courbe matérialisée sur pièce. On retrouve sur une aube 70, un pied 71, une plate forme 72, une pale 73 et les nageoires 74 portées par ladite pale ainsi qu'une zone 73a de raccordement de la pale 73 au pied 71.Figure 8 schematically shows an example of production of movable blades in accordance with the invention. Only a very precise geometrical analysis makes it possible to determine the geometrical place of the centers of gravity of the transverse sections of blade which is not a curve materialized on part. We find on a
Le désaxage par parties et en bloc des sections transversales de la pale des aubes conformes à l'invention permet d'obtenir la création de moments de rappel induits dans le champ centrifuge et dans le cas de nageoires, d'équilibrer également les effets induits. On obtient ainsi une annulation des moments de flexion au pied de l'aube qui est la zone mécaniquement la plus sollicitée.The offset in parts and in block of the cross sections of the blade of the blades according to the invention makes it possible to obtain the creation of induced return moments in the centrifugal field and in the case of fins, also to balance the induced effects. This gives rise to a cancellation of the bending moments at the foot of the blade which is the mechanically most stressed area.
Claims (2)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR8902639A FR2643940B1 (en) | 1989-03-01 | 1989-03-01 | MOBILE VANE OF TURBOMACHINE WITH MOMENT OF COMPENSATED FOOT |
FR8902639 | 1989-03-01 |
Publications (2)
Publication Number | Publication Date |
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EP0385833A1 true EP0385833A1 (en) | 1990-09-05 |
EP0385833B1 EP0385833B1 (en) | 1992-04-01 |
Family
ID=9379241
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP90400501A Expired - Lifetime EP0385833B1 (en) | 1989-03-01 | 1990-02-23 | Turbine rotor blade having a compensated foot moment |
Country Status (4)
Country | Link |
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US (1) | US5044885A (en) |
EP (1) | EP0385833B1 (en) |
DE (1) | DE69000050D1 (en) |
FR (1) | FR2643940B1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1994012390A2 (en) * | 1992-11-24 | 1994-06-09 | United Technologies Corporation | Coolable rotor blade structure |
DE19823555A1 (en) * | 1998-05-27 | 1999-12-02 | Claas Saulgau Gmbh | Haymaking machine |
WO2017013053A1 (en) * | 2015-07-20 | 2017-01-26 | Nuovo Pignone Tecnologie Srl | Unshrouded turbomachine impeller with improved rigidity |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2665005B2 (en) * | 1989-10-24 | 1997-10-22 | 三菱重工業株式会社 | Blades of axial flow machines |
US5203676A (en) * | 1992-03-05 | 1993-04-20 | Westinghouse Electric Corp. | Ruggedized tapered twisted integral shroud blade |
US6299412B1 (en) * | 1999-12-06 | 2001-10-09 | General Electric Company | Bowed compressor airfoil |
US6331100B1 (en) * | 1999-12-06 | 2001-12-18 | General Electric Company | Doubled bowed compressor airfoil |
EP1564374A1 (en) * | 2004-02-12 | 2005-08-17 | Siemens Aktiengesellschaft | Turbine blade for a turbomachine |
US7204676B2 (en) * | 2004-05-14 | 2007-04-17 | Pratt & Whitney Canada Corp. | Fan blade curvature distribution for high core pressure ratio fan |
US8356975B2 (en) * | 2010-03-23 | 2013-01-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured vane platform |
US9976433B2 (en) | 2010-04-02 | 2018-05-22 | United Technologies Corporation | Gas turbine engine with non-axisymmetric surface contoured rotor blade platform |
GB2483061A (en) * | 2010-08-23 | 2012-02-29 | Rolls Royce Plc | A method of damping aerofoil structure vibrations |
FR2967202B1 (en) * | 2010-11-10 | 2013-01-11 | Snecma | METHOD FOR OPTIMIZING THE PROFILE OF A BLADE IN COMPOSITE MATERIAL FOR A TURBOMACHINE MOBILE WHEEL |
US9920625B2 (en) | 2011-01-13 | 2018-03-20 | Siemens Energy, Inc. | Turbine blade with laterally biased airfoil and platform centers of mass |
US11767761B2 (en) | 2018-08-02 | 2023-09-26 | Horton, Inc. | Low solidity vehicle cooling fan |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1541657A (en) * | 1924-05-24 | 1925-06-09 | Parsons | Turbine blading |
US2398140A (en) * | 1943-12-08 | 1946-04-09 | Armstrong Siddeley Motors Ltd | Bladed rotor |
GB609322A (en) * | 1945-11-07 | 1948-09-29 | Power Jets Res & Dev Ltd | Improvements relating to axial-flow compressors and like machines, and blading thereof |
GB610786A (en) * | 1943-02-13 | 1948-10-20 | Centre Nat Rech Scient | Steam turbines |
FR2556409A1 (en) * | 1983-12-12 | 1985-06-14 | Gen Electric | IMPROVED VANE FOR GAS TURBINE ENGINE AND METHOD OF MANUFACTURE |
EP0260175A1 (en) * | 1986-09-12 | 1988-03-16 | Ecia - Equipements Et Composants Pour L'industrie Automobile | Profiled propeller blade and its use in motor-driven fans |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3128939A (en) * | 1964-04-14 | Szydlowski | ||
US1127143A (en) * | 1908-08-01 | 1915-02-02 | Wiedling Mfg Company | Propeller. |
US1027201A (en) * | 1911-07-08 | 1912-05-21 | Willibald Grun | Turbine-blade. |
US2282077A (en) * | 1940-02-03 | 1942-05-05 | Hamilton K Moore | Changeable pitch propeller unit |
US2663493A (en) * | 1949-04-26 | 1953-12-22 | A V Roe Canada Ltd | Blading for compressors, turbines, and the like |
US2915238A (en) * | 1953-10-23 | 1959-12-01 | Szydlowski Joseph | Axial flow compressors |
DE2144600A1 (en) * | 1971-09-07 | 1973-03-15 | Maschf Augsburg Nuernberg Ag | TWISTED AND TAPERED BLADE FOR AXIAL TURBO MACHINERY |
CH541065A (en) * | 1972-01-20 | 1973-08-31 | Bbc Brown Boveri & Cie | Twisted rotor blade of a turbomachine with an axial flow |
GB1419381A (en) * | 1972-03-09 | 1975-12-31 | Rolls Royce | Fan for gas turbine engines |
US3989406A (en) * | 1974-11-26 | 1976-11-02 | Bolt Beranek And Newman, Inc. | Method of and apparatus for preventing leading edge shocks and shock-related noise in transonic and supersonic rotor blades and the like |
US4012172A (en) * | 1975-09-10 | 1977-03-15 | Avco Corporation | Low noise blades for axial flow compressors |
FR2505399A1 (en) * | 1981-05-05 | 1982-11-12 | Alsthom Atlantique | DIRECT DRAWING FOR DIVERGENT VEINS OF STEAM TURBINE |
US4460315A (en) * | 1981-06-29 | 1984-07-17 | General Electric Company | Turbomachine rotor assembly |
US4451205A (en) * | 1982-02-22 | 1984-05-29 | United Technologies Corporation | Rotor blade assembly |
US4585395A (en) * | 1983-12-12 | 1986-04-29 | General Electric Company | Gas turbine engine blade |
US4682935A (en) * | 1983-12-12 | 1987-07-28 | General Electric Company | Bowed turbine blade |
US4638602A (en) * | 1986-01-03 | 1987-01-27 | Cavalieri Dominic A | Turbine blade holding device |
-
1989
- 1989-03-01 FR FR8902639A patent/FR2643940B1/en not_active Expired - Lifetime
-
1990
- 1990-02-23 DE DE9090400501T patent/DE69000050D1/en not_active Expired - Lifetime
- 1990-02-23 EP EP90400501A patent/EP0385833B1/en not_active Expired - Lifetime
- 1990-03-01 US US07/486,825 patent/US5044885A/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1541657A (en) * | 1924-05-24 | 1925-06-09 | Parsons | Turbine blading |
GB610786A (en) * | 1943-02-13 | 1948-10-20 | Centre Nat Rech Scient | Steam turbines |
US2398140A (en) * | 1943-12-08 | 1946-04-09 | Armstrong Siddeley Motors Ltd | Bladed rotor |
GB609322A (en) * | 1945-11-07 | 1948-09-29 | Power Jets Res & Dev Ltd | Improvements relating to axial-flow compressors and like machines, and blading thereof |
FR2556409A1 (en) * | 1983-12-12 | 1985-06-14 | Gen Electric | IMPROVED VANE FOR GAS TURBINE ENGINE AND METHOD OF MANUFACTURE |
EP0260175A1 (en) * | 1986-09-12 | 1988-03-16 | Ecia - Equipements Et Composants Pour L'industrie Automobile | Profiled propeller blade and its use in motor-driven fans |
Non-Patent Citations (1)
Title |
---|
Brown Boveri Mitteilungen vol. 59, no. 1, 01 janvier 1972, Baden (CH) pages 42 - 53; A,Hohn et al: "Die Endschaufeln grosser Dampfturbinen" * |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1994012390A2 (en) * | 1992-11-24 | 1994-06-09 | United Technologies Corporation | Coolable rotor blade structure |
WO1994012390A3 (en) * | 1992-12-08 | 1994-08-18 | United Technologies Corp | Coolable rotor blade structure |
DE19823555A1 (en) * | 1998-05-27 | 1999-12-02 | Claas Saulgau Gmbh | Haymaking machine |
WO2017013053A1 (en) * | 2015-07-20 | 2017-01-26 | Nuovo Pignone Tecnologie Srl | Unshrouded turbomachine impeller with improved rigidity |
US10669864B2 (en) | 2015-07-20 | 2020-06-02 | Nuovo Pignone Srl | Unshrouded turbomachine impeller with improved rigidity |
Also Published As
Publication number | Publication date |
---|---|
US5044885A (en) | 1991-09-03 |
FR2643940A1 (en) | 1990-09-07 |
FR2643940B1 (en) | 1991-05-17 |
EP0385833B1 (en) | 1992-04-01 |
DE69000050D1 (en) | 1992-05-07 |
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