EP1489266A1 - Retention of a blade with an asymmetric hammerhead foot using platform stiffeners - Google Patents
Retention of a blade with an asymmetric hammerhead foot using platform stiffeners Download PDFInfo
- Publication number
- EP1489266A1 EP1489266A1 EP04291450A EP04291450A EP1489266A1 EP 1489266 A1 EP1489266 A1 EP 1489266A1 EP 04291450 A EP04291450 A EP 04291450A EP 04291450 A EP04291450 A EP 04291450A EP 1489266 A1 EP1489266 A1 EP 1489266A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- downstream
- upstream
- disk
- blade
- rib
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 241000251131 Sphyrna Species 0.000 title 1
- 230000014759 maintenance of location Effects 0.000 title 1
- 239000003351 stiffener Substances 0.000 title 1
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 27
- 210000003462 vein Anatomy 0.000 claims description 12
- 238000007789 sealing Methods 0.000 claims description 5
- 230000000717 retained effect Effects 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 abstract description 8
- 230000035939 shock Effects 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010790 dilution Methods 0.000 description 1
- 239000012895 dilution Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
Images
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
-
- 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
Definitions
- the invention relates to a turbomachine blisk which extends into a conical vein and is retained in a throat device of said disk by hammer-type fasteners, each said vanes further comprising a platform whose face radially outer delimits the vein of the gas flow and whose face radially inner has an upstream rib and a downstream rib arranged in planes perpendicular to the axis of rotation of said disk and respectively adjoining an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove to ensure sealing in these areas.
- the radius of the primary flow vein decreases from upstream to downstream in the compressor low pressure.
- the conicity of this vein is very high at the level of last stages of this compressor.
- the blades of these floors extend obliquely in the vein relative to the plane perpendicular to the axis of compressor rotation, that is to say, obliquely to the radial direction of centrifugal forces.
- the invention relates more specifically to the blisk discs of this type, in which the blades are retained by a fastener type hammer in a peripheral groove of the disc, this groove being delimited by an upstream lip and a downstream lip, whose surfaces connected to the bottom of the groove form spans on which the flanks of the dawn feet are supported during the operation of the turbomachine, these spans supporting reaction forces whose resultant is preferably in the plane of the centrifugal forces to which the blades are subject.
- EP 0 695 856 proposed a fastener Asymmetrical hammer, that is to say that the angle of the reach of the lip upstream, which has the largest diameter, with respect to a perpendicular plane to the axis of rotation, is greater than the angel formed between the scope of the downstream lip and said plane.
- Figure 4B of this document shows the link dawn-disk in the case where dawn, subjected to axial stress significant, as a result of a shock of a debris ingested by the turbomachine, has tendency to rotate around a center of rotation C located at the end upstream of the range of the downstream lip. Due to the conformation of the throat and the dawn foot, the dawn can be released in case of significant shock.
- No. 5,271,718 describes blades of the symmetrical hammer tie type which have platforms having on their radially inner face ribs which extend in the circumferential and axial direction and which are intended to avoid vibratory resonances, two these circumferential ribs cooperating with rings formed at the periphery of the disk to ensure sealing in these areas.
- the axial thickness of these ribs is substantially equal to the thickness of the rings.
- This document shows that the axial ribs formed on the radially inner face of the platforms have a height less than that of the ribs cooperating with the rings.
- the downstream rib supports a large part of the generated forces and can skip axially on the downstream ring, which can cause the release of the blade.
- the ends of these ribs can rip on the rings which, failing to cause the release of the blade, may cause an overlap of the adjacent edges of two neighboring blades.
- the object of the invention is to provide a modified blade that overcomes these disadvantages.
- This arrangement makes it possible to offer a flat contact surface and homogeneous between the rib and the disc ring that presents possibly a groove for receiving a sealing ring.
- the thickness of the upstream rib in the axial direction is greater than the thickness of the upstream ring.
- the height of said ribs is sufficiently large to limit the possibility of overlapping platforms.
- Figure 1 shows a blade 1 whose foot 2 in the form of dovetail comprises an upstream flank 3a and a downstream flank 3b whose surfaces are supported on bearings 4a, 4b of the internal faces of a upstream lip 5 and a downstream lip 6 which delimit a groove 7 formed in the periphery of a disk 12 and whose bottom 8 is connected to the bearings 4a and 4b by rounded surfaces respectively 9a and 9b.
- dawn 1 extends into a vein strongly conical, that is to say that the upstream lip 5 has a larger diameter than the downstream lip 6, and the bearings 4a and 4b are, with the plane perpendicular to the axis of rotation of the disk 2, different angles.
- the disc 12 presents upstream a first radial extension 20, referred to as upstream ring in this specification, thin axial, and downstream a second radial extension 21, called downstream ring, which has a groove 22 intended to receive a sealing ring shown in the drawings for the sake of clarity.
- the upstream and downstream rings 21 have surfaces cylindrical peripherals 20a and 21a, of revolution about the axis of rotation of the disc 12.
- Dawn 2 presents between the foot 2 and the aerodynamic part a platform 30 whose radially outer face 30a delimits the conical vein, and whose radially inner face 30b has a upstream rib 32 and a downstream groove 33 which extend circumferentially in the immediate vicinity of the peripheral surfaces 20a and 21a of the upstream and downstream rings 20 and 21.
- These ribs 32 and 33 have portions of cylindrical surfaces, respectively 32a and 32b, of revolution around the axis of rotation of the disc 1 which covers the peripheral surfaces 20a and 21a upstream 21 and downstream 22 rings, and whose width in the direction axial is greater than the width of the peripheral surfaces 20a and 21a.
- the width of the surfaces 32a and 33a is calculated so as to always provide sufficient seating on rings 20 and 21 in all the ranges of movement of the blade 1 in operation.
- the height of the ribs 32 and 33 is calculated in such a way that regardless of the displacement of the adjacent blades, as a result of a tangential stress, the adjacent edges of the platforms 30 of two consecutive vanes 1a and 1b can not overlap, as this is shown in Figure 2.
- This figure 2 shows blades 1a and 1b which present in in addition to other stiffening ribs disposed between the upstream rib 32 and the downstream rib 33.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
L'invention concerne un disque aubagé de turbomachine qui s'étend dans une veine conique et qui est retenu dans une gorge périphérique dudit disque par des attaches du type marteau, chacune desdites aubes comportant en outre une plate-forme dont la face radialement extérieure délimite la veine du flux gazeux et dont la face radialement intérieure présente une nervure amont et une nervure aval disposées dans des plans perpendiculaires à l'axe de rotation dudit disque et jouxtant respectivement un anneau amont et un anneau aval formés à la périphérie dudit disque de part et d'autre de ladite gorge afin d'assurer l'étanchéité dans ces zones.The invention relates to a turbomachine blisk which extends into a conical vein and is retained in a throat device of said disk by hammer-type fasteners, each said vanes further comprising a platform whose face radially outer delimits the vein of the gas flow and whose face radially inner has an upstream rib and a downstream rib arranged in planes perpendicular to the axis of rotation of said disk and respectively adjoining an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove to ensure sealing in these areas.
Dans les turboréacteurs à grand taux de dilution, le rayon de la veine du flux primaire diminue de l'amont vers l'aval dans le compresseur basse pression. La conicité de cette veine est très élevée au niveau des derniers étages de ce compresseur. Les aubes de ces étages s'étendent obliquement dans la veine par rapport au plan perpendiculaire à l'axe de rotation du compresseur, c'est-à-dire obliquement par rapport à la direction radiale des forces centrifuges.In turbojet engines with a high dilution ratio, the radius of the primary flow vein decreases from upstream to downstream in the compressor low pressure. The conicity of this vein is very high at the level of last stages of this compressor. The blades of these floors extend obliquely in the vein relative to the plane perpendicular to the axis of compressor rotation, that is to say, obliquely to the radial direction of centrifugal forces.
L'invention concerne plus précisément les disques aubagés de ce type, dans lesquels les aubes sont retenues par une attache de type marteau dans une gorge périphérique du disque, cette gorge étant délimitée par une lèvre amont et une lèvre aval, dont les surfaces raccordées au fond de la gorge forment des portées sur lesquelles les flancs des pieds d'aube sont en appui lors du fonctionnement de la turbomachine, ces portées supportant des efforts de réaction dont la résultante est de préférence dans le plan des forces centrifuges auxquelles les aubes sont soumises.The invention relates more specifically to the blisk discs of this type, in which the blades are retained by a fastener type hammer in a peripheral groove of the disc, this groove being delimited by an upstream lip and a downstream lip, whose surfaces connected to the bottom of the groove form spans on which the flanks of the dawn feet are supported during the operation of the turbomachine, these spans supporting reaction forces whose resultant is preferably in the plane of the centrifugal forces to which the blades are subject.
Pour obtenir ce résultat, EP 0 695 856 a proposé une attache marteau asymétrique, c'est-à-dire que l'angle de la portée de la lèvre amont, qui a le plus grand diamètre, par rapport à un plan perpendiculaire à l'axe de rotation, est supérieure à l'ange formé entre la portée de la lèvre aval et ledit plan. La figure 4B de ce document montre la liaison aube-disque dans le cas où l'aube, soumise à une sollicitation axiale importante, par suite d'un choc d'un débris ingéré par la turbomachine, a tendance à pivoter autour d'un centre de rotation C situé à l'extrémité amont de la portée de la lèvre aval. Du fait de la conformation de la gorge et du pied d'aube, l'aube peut se dégager en cas de choc important. To obtain this result, EP 0 695 856 proposed a fastener Asymmetrical hammer, that is to say that the angle of the reach of the lip upstream, which has the largest diameter, with respect to a perpendicular plane to the axis of rotation, is greater than the angel formed between the scope of the downstream lip and said plane. Figure 4B of this document shows the link dawn-disk in the case where dawn, subjected to axial stress significant, as a result of a shock of a debris ingested by the turbomachine, has tendency to rotate around a center of rotation C located at the end upstream of the range of the downstream lip. Due to the conformation of the throat and the dawn foot, the dawn can be released in case of significant shock.
US 5 271 718 décrit des aubes de type attache marteau
symétrique qui présentent des plates-formes ayant sur leur face
radialement intérieure des nervures qui s'étendent dans le sens
circonférentiel et dans le sens axial et qui sont destinées à éviter les
résonances vibratoires, deux de ces nervures circonférentielles coopérant
avec des anneaux formés à la périphérie du disque pour assurer
l'étanchéité dans ces zones. L'épaisseur axiale de ces nervures est
sensiblement égale à l'épaisseur des anneaux. Ce document montre que
les nervures axiales formées sur la face radialement intérieure des plates-formes
ont une hauteur inférieure à celle des nervures coopérant avec les
anneaux. En cas de sollicitation axiale importante, la nervure située en
aval supporte une grande partie des efforts générés et peut riper
axialement sur l'anneau aval, ce qui peut provoquer le dégagement de
l'aube.
En outre, en cas de sollicitation tangentielle, les extrémités de ces
nervures peuvent riper sur les anneaux ce qui, à défaut d'entraíner le
dégagement de l'aube, peut entraíner un chevauchement des bords
adjacents de deux aubes voisines.No. 5,271,718 describes blades of the symmetrical hammer tie type which have platforms having on their radially inner face ribs which extend in the circumferential and axial direction and which are intended to avoid vibratory resonances, two these circumferential ribs cooperating with rings formed at the periphery of the disk to ensure sealing in these areas. The axial thickness of these ribs is substantially equal to the thickness of the rings. This document shows that the axial ribs formed on the radially inner face of the platforms have a height less than that of the ribs cooperating with the rings. In case of significant axial stress, the downstream rib supports a large part of the generated forces and can skip axially on the downstream ring, which can cause the release of the blade.
In addition, in case of tangential stress, the ends of these ribs can rip on the rings which, failing to cause the release of the blade, may cause an overlap of the adjacent edges of two neighboring blades.
Ces désordres peuvent se produire notamment dans un disque
aubagé du type mentionné dans l'introduction du présent mémoire, dans
lequel les aubes s'étendent dans une veine fortement conique.
Le but de l'invention est de proposer une aube modifiée qui permette de
pallier ces inconvénients.These disorders can occur in particular in a blisk of the type mentioned in the introduction of this memo, wherein the blades extend in a strongly conical vein.
The object of the invention is to provide a modified blade that overcomes these disadvantages.
Ce but est atteint selon l'invention par le fait que l'épaisseur de la nervure aval, dans la direction axiale, est supérieure à l'épaisseur de l'anneau aval.This object is achieved according to the invention by the fact that the thickness of the downstream rib in the axial direction is greater than the thickness of the downstream ring.
Cette disposition permet d'offrir une surface de contact plane et homogène entre la nervure et l'anneau du disque qui présente éventuellement une gorge pour recevoir un jonc d'étanchéité.This arrangement makes it possible to offer a flat contact surface and homogeneous between the rib and the disc ring that presents possibly a groove for receiving a sealing ring.
Selon une autre caractéristique avantageuse, l'épaisseur de la nervure amont dans la direction axiale est supérieure à l'épaisseur de l'anneau amont.According to another advantageous characteristic, the thickness of the upstream rib in the axial direction is greater than the thickness of the upstream ring.
De préférence, la hauteur desdites nervures est suffisamment grande pour limiter la possibilité de chevauchement des plates-formes. Preferably, the height of said ribs is sufficiently large to limit the possibility of overlapping platforms.
D'autres caractéristiques et avantages de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence aux dessins annexés dans lesquels :
- la figure 1 est une vue en coupe, selon un plan contenant l'axe de rotation, d'une liaison aube/disque selon l'invention, l'aube s'étendant dans une veine fortement conique, et l'attache étant du type marteau asymétrique, et
- la figure 2 est une vue en perspective et de dessous de deux aubes adjacentes 1a et 1b.
- FIG. 1 is a sectional view, along a plane containing the axis of rotation, of a blade / disk connection according to the invention, the blade extending in a strongly conical vein, and the fastener being of the type asymmetrical hammer, and
- Figure 2 is a perspective view from below of two
adjacent blades
La figure 1 montre une aube 1 dont le pied 2 en forme de
queue d'aronde comporte un flanc amont 3a et un flanc aval 3b dont les
surfaces sont en appui sur des portées 4a, 4b des faces internes d'une
lèvre amont 5 et d'une lèvre aval 6 qui délimitent une gorge 7 formée à la
périphérie d'un disque 12 et dont le fond 8 se raccorde aux portées 4a et
4b par des surfaces arrondies respectivement 9a et 9b.Figure 1 shows a
En cas de sollicitations axiales importantes par suite d'un choc
d'un débris sur la partie aérodynamique de l'aube 1, celle-ci a tendance à
pivoter autour de l'extrémité amont C de la portée 4b de la lèvre aval 6.
L'extrémité 10 du talon 11 du pied de l'aube 1, la plus éloignée du centre
de rotation C, est sollicitée à décrire un cercle géométrique C.In case of significant axial stresses due to a shock
debris on the aerodynamic part of
Il est à noter que l'aube 1 s'étend dans une veine fortement
conique, c'est-à-dire que la lèvre amont 5 a un diamètre plus grand que la
lèvre aval 6, et les portées 4a et 4b font, avec le plan perpendiculaire à
l'axe de rotation du disque 2, des angles différents.It should be noted that
Le disque 12 présente en amont une première extension radiale
20, appelé anneau amont dans le présent mémoire, de faible épaisseur
axiale, et en aval une deuxième extension radiale 21, appelé anneau aval,
qui comporte une gorge 22 destinée à recevoir un jonc d'étanchéité non
montré sur le dessins par souci de clarté.The
Les anneaux amont 20 et aval 21 présentent des surfaces
périphériques 20a et 21a cylindriques, de révolution autour de l'axe de
rotation du disque 12.The upstream and
L'aube 2 présente entre le pied 2 et la partie aérodynamique
une plate-forme 30 dont la face radialement extérieure 30a délimite la
veine conique, et dont la face radialement intérieure 30b comporte une
nervure amont 32 et une rainure aval 33 qui s'étendent
circonférentiellement au voisinage immédiat des surfaces périphériques
20a et 21a des anneaux amont 20 et aval 21.Dawn 2 presents between the
Ces nervures 32 et 33 présentent notamment des portions de
surface cylindriques, respectivement 32a et 32b, de révolution autour de
l'axe de rotation du disque 1 qui recouvrent les surfaces périphériques 20a
et 21a des anneaux amont 21 et aval 22, et dont la largeur dans le sens
axial est supérieure à la largeur des surfaces périphériques 20a et 21a.These
En cas d'une sollicitation axiale de l'aube 1 par suite du choc
d'un débris, l'aube 1 a tendance à pivoter autour du point C. Cette
sollicitation entraíne un appui positif de la nervure aval 33 sur l'anneau
aval 21.In case of an axial stress of the
Du fait que la surface 32b est cylindrique et large dans le sens
axial, cette surface ne peut pas riper sur la surface périphérique 21a de
l'anneau 21. Cette disposition empêche le pied d'aube 2 de s'échapper de
la gorge 7 car elle limite le débattement de l'aube 1.Because the
En cas d'une sollicitation tangentielle importante, les extrémités
des deux nervures 32 et 33 sont en appui positif sur les surfaces
périphériques 20a et 21a des anneaux amont 20 et aval 21.In case of a significant tangential stress, the ends
two
La largeur des surfaces 32a et 33a est calculée de manière à
toujours offrir une assise suffisante sur les anneaux 20 et 21 dans toutes
les plages de déplacement de l'aube 1 en fonctionnement.The width of the
La hauteur des nervures 32 et 33 est calculée de telle manière
que, quel que soit le déplacement des aubes adjacentes, par suite d'une
sollicitation tangentielle, les bords adjacents des plates-formes 30 de deux
aubes consécutives 1a et 1b ne puissent se chevaucher, ainsi que cela est
montré sur la figure 2.The height of the
Cette figure 2 montre des aubes 1a et 1b qui présentent en
outre d'autres nervures de rigidification, disposées entre la nervure amont
32 et la nervure aval 33.This figure 2 shows
Cette aube pourrait également comporter des nervures dirigées axialement sans sortir du cadre de l'invention.This dawn could also include veins directed axially without departing from the scope of the invention.
Claims (3)
caractérisé par le fait que l'épaisseur de la nervure aval (33), dans la direction axiale, est supérieure à l'épaisseur de l'anneau aval (21).A turbomachine blade having vanes (1) which extend into a conical vein and which are retained in a circumferential groove (7) of said disk (12) by hammer-type fasteners, each of said vanes further comprising a platform form (30) whose radially outer face (30a) defines the vein of the gas flow and whose radially inner face (30b) has an upstream rib (32) and a downstream rib (33) arranged in planes perpendicular to the axis rotation of said disk and radially adjoining respectively an upstream ring (20) and a downstream ring (21) formed at the periphery of said disk (12) on either side of said groove (7), to ensure sealing in these areas,
characterized in that the thickness of the downstream rib (33) in the axial direction is greater than the thickness of the downstream ring (21).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0307214 | 2003-06-16 | ||
| FR0307214A FR2856105B1 (en) | 2003-06-16 | 2003-06-16 | IMPROVING THE RETENTION CAPACITY OF A DISSYMMETRIC HAMMER ATTACHED BLADE USING PLATFORM STIFFENERS |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1489266A1 true EP1489266A1 (en) | 2004-12-22 |
| EP1489266B1 EP1489266B1 (en) | 2007-08-15 |
Family
ID=33396778
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP04291450A Expired - Lifetime EP1489266B1 (en) | 2003-06-16 | 2004-06-10 | Retention of a blade with an asymmetric hammerhead foot using platform stiffeners |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US7080974B2 (en) |
| EP (1) | EP1489266B1 (en) |
| JP (1) | JP4227077B2 (en) |
| CA (1) | CA2470073C (en) |
| DE (1) | DE602004008153T2 (en) |
| ES (1) | ES2291833T3 (en) |
| FR (1) | FR2856105B1 (en) |
| RU (1) | RU2333366C2 (en) |
| UA (1) | UA81901C2 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2282010A1 (en) * | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Rotor blade for an axial flow turbomachine |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102004051116A1 (en) * | 2004-10-20 | 2006-04-27 | Mtu Aero Engines Gmbh | Rotor of a turbomachine, in particular gas turbine rotor |
| FR2897099B1 (en) * | 2006-02-08 | 2012-08-17 | Snecma | TURBOMACHINE ROTOR WHEEL |
| US8608447B2 (en) * | 2009-02-19 | 2013-12-17 | Rolls-Royce Corporation | Disk for turbine engine |
| US9097131B2 (en) | 2012-05-31 | 2015-08-04 | United Technologies Corporation | Airfoil and disk interface system for gas turbine engines |
| US9140136B2 (en) | 2012-05-31 | 2015-09-22 | United Technologies Corporation | Stress-relieved wire seal assembly for gas turbine engines |
| US9267386B2 (en) | 2012-06-29 | 2016-02-23 | United Technologies Corporation | Fairing assembly |
| EP2885506B8 (en) | 2012-08-17 | 2021-03-31 | Raytheon Technologies Corporation | Contoured flowpath surface |
| GB201800732D0 (en) | 2018-01-17 | 2018-02-28 | Rolls Royce Plc | Blade for a gas turbine engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2398140A (en) * | 1943-12-08 | 1946-04-09 | Armstrong Siddeley Motors Ltd | Bladed rotor |
| US2494658A (en) * | 1946-05-10 | 1950-01-17 | United Aircraft Corp | Blade mounting |
| US2656147A (en) * | 1946-10-09 | 1953-10-20 | English Electric Co Ltd | Cooling of gas turbine rotors |
| US4460315A (en) * | 1981-06-29 | 1984-07-17 | General Electric Company | Turbomachine rotor assembly |
| EP0530097A1 (en) * | 1991-08-28 | 1993-03-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbomachine motor with angular positioning of the blades |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4349318A (en) * | 1980-01-04 | 1982-09-14 | Avco Corporation | Boltless blade retainer for a turbine wheel |
| US4304523A (en) * | 1980-06-23 | 1981-12-08 | General Electric Company | Means and method for securing a member to a structure |
| US5622475A (en) * | 1994-08-30 | 1997-04-22 | General Electric Company | Double rabbet rotor blade retention assembly |
| FR2758364B1 (en) * | 1997-01-16 | 1999-02-12 | Snecma | TRIPOD BLADE BLADE DISC |
| GB2332024B (en) | 1997-12-03 | 2000-12-13 | Rolls Royce Plc | Rotary assembly |
| FR2812906B1 (en) | 2000-08-10 | 2002-09-20 | Snecma Moteurs | AXIAL RETAINER RING OF A FLANGE ON A DISC |
-
2003
- 2003-06-16 FR FR0307214A patent/FR2856105B1/en not_active Expired - Fee Related
-
2004
- 2004-06-10 ES ES04291450T patent/ES2291833T3/en not_active Expired - Lifetime
- 2004-06-10 EP EP04291450A patent/EP1489266B1/en not_active Expired - Lifetime
- 2004-06-10 DE DE602004008153T patent/DE602004008153T2/en not_active Expired - Lifetime
- 2004-06-15 RU RU2004118078/06A patent/RU2333366C2/en active
- 2004-06-15 JP JP2004176735A patent/JP4227077B2/en not_active Expired - Lifetime
- 2004-06-15 CA CA2470073A patent/CA2470073C/en not_active Expired - Lifetime
- 2004-06-15 US US10/866,678 patent/US7080974B2/en not_active Expired - Lifetime
- 2004-06-15 UA UA20040604706A patent/UA81901C2/en unknown
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2398140A (en) * | 1943-12-08 | 1946-04-09 | Armstrong Siddeley Motors Ltd | Bladed rotor |
| US2494658A (en) * | 1946-05-10 | 1950-01-17 | United Aircraft Corp | Blade mounting |
| US2656147A (en) * | 1946-10-09 | 1953-10-20 | English Electric Co Ltd | Cooling of gas turbine rotors |
| US4460315A (en) * | 1981-06-29 | 1984-07-17 | General Electric Company | Turbomachine rotor assembly |
| EP0530097A1 (en) * | 1991-08-28 | 1993-03-03 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Turbomachine motor with angular positioning of the blades |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2282010A1 (en) * | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Rotor blade for an axial flow turbomachine |
| US8951016B2 (en) | 2009-06-23 | 2015-02-10 | Siemens Aktiengesellschaft | Rotor blade for an axial flow turbomachine and mounting for such a rotor blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2470073C (en) | 2011-08-16 |
| FR2856105B1 (en) | 2007-05-25 |
| JP2005009492A (en) | 2005-01-13 |
| RU2004118078A (en) | 2006-01-10 |
| EP1489266B1 (en) | 2007-08-15 |
| ES2291833T3 (en) | 2008-03-01 |
| RU2333366C2 (en) | 2008-09-10 |
| JP4227077B2 (en) | 2009-02-18 |
| US7080974B2 (en) | 2006-07-25 |
| DE602004008153T2 (en) | 2008-05-15 |
| DE602004008153D1 (en) | 2007-09-27 |
| US20040253113A1 (en) | 2004-12-16 |
| CA2470073A1 (en) | 2004-12-16 |
| UA81901C2 (en) | 2008-02-25 |
| FR2856105A1 (en) | 2004-12-17 |
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