EP0705958B1 - Chamfering of stressed regions in a fir-tree turbine blade root - Google Patents
Chamfering of stressed regions in a fir-tree turbine blade root Download PDFInfo
- Publication number
- EP0705958B1 EP0705958B1 EP95402163A EP95402163A EP0705958B1 EP 0705958 B1 EP0705958 B1 EP 0705958B1 EP 95402163 A EP95402163 A EP 95402163A EP 95402163 A EP95402163 A EP 95402163A EP 0705958 B1 EP0705958 B1 EP 0705958B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- root
- zone
- blade
- tang
- clearance
- 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.)
- Expired - Lifetime
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
Definitions
- the present invention relates to an arrangement for clipping of stress points in the anchor a turbine fin, comprising a root called Fir-foot including notches, in a profile groove corresponding on a disc.
- British patent GB-A-1482308 describes the general principle of such fins.
- a known assembly of steam turbine fins on a rotor disc consists in that each fin has at its base a foot or an anchoring root in the rotor disc.
- This root is called “Fir-tree” and the envelope of its profile forms an isosceles trapezium whose large base is closest to the base of the fin and the small base moves away from it. His exact profile, from this envelope, contains a series of narrowing called “passes”. The part of the profile between two passes is called "a notch".
- the rotor disc On a fin root there can be 3 to 5 notches.
- the rotor disc carries a series of grooves for mounting the fins. Each groove has a profile complementary to the so-called "Fir-tree" profile of the roots fins.
- the object of the present invention is to reduce these stress spikes.
- the subject of the invention is therefore a provision for the clipping of stress points in the anchoring of a turbine fin, comprising a root known as "Fir-foot" including notches, in a profile groove corresponding on a disc, characterized in that the profile of each notch, upper side of the root of the fin, is such that the assembly game of the root in its groove on the upper side is not uniform but has at least one area where this game follows an evolution, this area corresponding to an area of the notch considered where, in the case of a constant clearance assembly all along said notch would produce, at nominal rotational speed of the fitted disc of its fins, a point of constraint compared to the average stress along the notch, the evolution of said clearance along a so-called area evolving in the same direction as said stress point.
- said zone is located on the trailing edge side. This translates into the machining of the notches of the root by more machining notch deep in said area, for example by modification of the angle of the cutter path machining for a straight root or by reducing the radius of curvature of the path of the milling cutter for a curved root.
- Figure 1 shows a turbine fin with a root in "Pied-Sapin”.
- Figure 2 shows the stress along a notch of a root in Fir-tree during rotation in nominal speed of the turbine, in the absence of the arrangement of the present invention.
- Figure 3 is a view showing the arrangement according to the invention.
- the view is schematic and partial according to a section parallel to the plane of the fin anchoring disc and made on the side of the root corresponding to the trailing edge fin.
- Figure 4 shows schematically a fin view perpendicular to the plane of the disc with below a diagram representing, for a notch, the evolution of the game between the notch and the corresponding wall of the groove of the side of the trailing edge.
- Figure 1 shows a steam turbine fin 1 with a root 2 in "Pied-sapin" including a plurality of notches such as 3.
- the fin has an edge attack 4 which is the side by where between the steam and a trailing edge 5.
- the fins such as 1 are threaded by their root 2 in complementary geometry grooves made in a rotor disc of the turbine.
- FIG. 2 represents the stress curve c which exists, during nominal disc rotation, along a notch of the root of the fin between the E side corresponding to the leading edge of the fin and that S corresponding to its trailing edge.
- Figure 3 shows the root 2 of a fin 1 in a groove 6 of the rotor disk 7 of a turbine.
- the side marked A corresponds to the lower side and the side marked B corresponds to the upper side.
- the root of the fin shown has four notches 3A, 3B, 3C and 3D.
- This figure 3 shows the root in section by a plane perpendicular to the axis of the disc 7 and on the side of the root corresponding to the trailing edge of the fin, i.e. where a spike usually occurs constraint in the notches.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
La présente invention concerne une disposition pour l'écrêtement des pointes de contraintes dans l'ancrage d'une ailette de turbine, comportant une racine dite en Pied-sapin comprenant des crans, dans une rainure de profil correspondant sur un disque. Le brevet anglais GB-A-1482308 décrit le principe général de telles ailettes.The present invention relates to an arrangement for clipping of stress points in the anchor a turbine fin, comprising a root called Fir-foot including notches, in a profile groove corresponding on a disc. British patent GB-A-1482308 describes the general principle of such fins.
Un montage connu d'ailettes de turbine à vapeur sur un disque rotorique consiste en ce que chaque ailette comporte à sa base un pied ou une racine d'ancrage dans le disque rotorique. Cette racine est appelée "Pied-sapin" et l'enveloppe de son profil forme un trapèze isocèle dont la grande base est le plus près de la base de l'ailette et la petite base s'en éloigne. Son profil exact, à partir de cette enveloppe, comporte une série de rétrécissements appelés "cols". La partie du profil entre deux cols est appelée "un cran".A known assembly of steam turbine fins on a rotor disc consists in that each fin has at its base a foot or an anchoring root in the rotor disc. This root is called "Fir-tree" and the envelope of its profile forms an isosceles trapezium whose large base is closest to the base of the fin and the small base moves away from it. His exact profile, from this envelope, contains a series of narrowing called "passes". The part of the profile between two passes is called "a notch".
Sur une racine d'ailette, il peut y avoir de 3 à 5 crans. Le disque rotorique porte une série de rainures pour le montage des ailettes. Chaque rainure a un profil complémentaire du profil dit en "Pied-sapin" des racines des ailettes.On a fin root there can be 3 to 5 notches. The rotor disc carries a series of grooves for mounting the fins. Each groove has a profile complementary to the so-called "Fir-tree" profile of the roots fins.
Lors de la rotation de la turbine, ce sont ces crans et ceux complémentaires des rainures effectuées dans le disque qui retiennent les ailettes; il se crée donc un champ de contraintes dans la racine et dans le disque le long de ces crans.When the turbine rotates, it is these notches and those complementary to the grooves made in the disc holding the fins; so a stress field in the root and in the disk the along these notches.
Le long d'un cran il existe une contrainte moyenne, cependant, la contrainte n'est pas constante le long d'un cran et il existe des pointes de contraintes.Along a notch there is a medium constraint, however, the constraint is not constant along a notch and there are spikes in constraints.
La présente invention a pour but de diminuer ces pointes de contraintes.The object of the present invention is to reduce these stress spikes.
L'invention a ainsi pour objet une disposition pour l'écrêtement des pointes de contrainte dans l'ancrage d'une ailette de turbine, comprenant une racine dite en "Pied-sapin" comprenant des crans, dans une rainure de profil correspondant sur un disque, caractérisé par le fait que le profil de chaque cran, côté extrados de la racine de l'ailette, est tel que le jeu de montage de la racine dans sa rainure, côté extrados, n'est pas uniforme mais comporte au moins une zone où ce jeu suit une évolution, cette zone correspondant à une zone du cran considéré où, dans le cas d'un montage à jeu constant tout le long dudit cran se produirait, à vitesse de rotation nominale du disque équipé de ses ailettes, une pointe de contrainte par rapport à la contrainte moyenne le long du cran, l'évolution dudit jeu le long d'une dite zone évoluant dans le même sens que ladite pointe de contrainte.The subject of the invention is therefore a provision for the clipping of stress points in the anchoring of a turbine fin, comprising a root known as "Fir-foot" including notches, in a profile groove corresponding on a disc, characterized in that the profile of each notch, upper side of the root of the fin, is such that the assembly game of the root in its groove on the upper side is not uniform but has at least one area where this game follows an evolution, this area corresponding to an area of the notch considered where, in the case of a constant clearance assembly all along said notch would produce, at nominal rotational speed of the fitted disc of its fins, a point of constraint compared to the average stress along the notch, the evolution of said clearance along a so-called area evolving in the same direction as said stress point.
Selon une réalisation particulière, ladite zone est située du côté du bord de fuite. Ceci se traduit, lors de l'usinage des crans de la racine par un usinage plus profond du cran dans ladite zone, par exemple par modification de l'angle de la trajectoire de la fraise d'usinage pour une racine rectiligne ou par diminution du rayon de courbure de la trajectoire de la fraise d'usinage pour une racine courbe.According to a particular embodiment, said zone is located on the trailing edge side. This translates into the machining of the notches of the root by more machining notch deep in said area, for example by modification of the angle of the cutter path machining for a straight root or by reducing the radius of curvature of the path of the milling cutter for a curved root.
On peut également être amené à pratiquer un tel profil de cran, se traduisant par une zone où le jeu est évolutif, du côté correspondant au bord d'attaque de l'ailette.One can also be brought to practice such notch profile, resulting in an area where the game is scalable, on the side corresponding to the leading edge of the fin.
On va maintenant donner la description d'un exemple de mise en oeuvre de l'invention en se reportant aux dessins annexés dans lesquels :We will now give the description of an example implementing the invention with reference to annexed drawings in which:
La figure 1 montre une ailette de turbine comportant une racine en "Pied-Sapin".Figure 1 shows a turbine fin with a root in "Pied-Sapin".
La figure 2 représente la contrainte le long d'un cran d'une racine en Pied-sapin au cours de la rotation en régime nominal de la turbine, en l'absence de la disposition de la présente invention.Figure 2 shows the stress along a notch of a root in Fir-tree during rotation in nominal speed of the turbine, in the absence of the arrangement of the present invention.
La figure 3 est une vue montrant la disposition selon l'invention. La vue est schématique et partielle selon une coupe parallèle au plan du disque d'ancrage des ailettes et faite du côté de la racine correspondant au bord de fuite de l'ailette.Figure 3 is a view showing the arrangement according to the invention. The view is schematic and partial according to a section parallel to the plane of the fin anchoring disc and made on the side of the root corresponding to the trailing edge fin.
La figure 4 représente schématiquement une ailette vue perpendiculairement au plan du disque avec en-dessous un diagramme représentant, pour un cran, l'évolution du jeu entre le cran et la paroi correspondante de la rainure du côté du bord de fuite.Figure 4 shows schematically a fin view perpendicular to the plane of the disc with below a diagram representing, for a notch, the evolution of the game between the notch and the corresponding wall of the groove of the side of the trailing edge.
La figure 1 montre une ailette 1 de turbine à vapeur
comportant une racine 2 en "Pied-sapin" comprenant une
pluralité de crans tels que 3. L'ailette comporte un bord
d'attaque 4 qui est le côté par où entre la vapeur et un
bord de fuite 5.Figure 1 shows a
Les ailettes telles que 1 sont enfilées par leur
racine 2 dans des rainures de géométrie complémentaires
pratiquées dans un disque rotorique de la turbine.The fins such as 1 are threaded by their
La figure 2 représente la courbe c de contrainte qui existe, en cours de rotation nominale du disque, le long d'un cran de la racine de l'ailette entre le côté E correspondant au bord d'attaque de l'ailette et celui S correspondant à son bord de fuite.FIG. 2 represents the stress curve c which exists, during nominal disc rotation, along a notch of the root of the fin between the E side corresponding to the leading edge of the fin and that S corresponding to its trailing edge.
En trait discontinu, on a figuré la contrainte moyenne m.In broken lines, we have shown the constraint medium m.
On constate sur cette courbe qu'il existe une forte pointe de contrainte du côté S correspondant au bord de fuite de l'ailette.We see on this curve that there is a strong stress point on the S side corresponding to the edge of flight of the fin.
En se référant maintenant aux figures 3 et 4 on va décrire la disposition de l'invention permettant d'écrêter une telle pointe.Referring now to Figures 3 and 4 we will describe the layout of the invention for clipping such a tip.
La figure 3 montre la racine 2 d'une ailette 1 dans
une rainure 6 du disque rotorique 7 d'une turbine. Le côté
repéré A correspond au côté intrados et le côté repéré B
correspond au côté extrados. La racine de l'ailette
représentée comporte quatre crans 3A, 3B, 3C et 3D.Figure 3 shows the
Cette figure 3 montre la racine en section par un
plan perpendiculaire à l'axe du disque 7 et du côté de la
racine correspondant au bord de fuite de l'ailette, c'est-à-dire
là où se produit habituellement une pointe de
contrainte dans les crans. On a représenté par la ligne
repérée 8 sur 18 figure 4 le plan correspondant à la
section de la racine 2 représentée sur cette figure 3.This figure 3 shows the root in section by a
plane perpendicular to the axis of the
On voit ainsi que du côté extrados et à ce niveau de
la racine, il existe un jeu J1, J2, J3, J4 entre chaque
cran 3A, 3B, 3C et 3D et la paroi correspondante de la
rainure 6.We can see that on the upper side and at this level of
the root, there is a game J1, J2, J3, J4 between each
Ce jeu n'existe pas tout le long de chaque cran comme
le montre la figure 4 : cette figure montre, au-dessous
d'un schéma représentatif de la racine de l'ailette avec
ses crans, vue perpendiculairement à la figure 3, un
diagramme de l'évolution du jeu J2, selon n (figure 3), le
long du cran 3B.This game does not exist all along each notch like
shown in Figure 4: this figure shows, below
a representative diagram of the root of the fin with
its notches, seen perpendicular to Figure 3, a
diagram of the evolution of the game J2, according to n (figure 3), the
On voit que le jeu J2 évolue dans le même sens que la pointe de contrainte (Figure 2) c'est-à-dire que l'on augmente le jeu plus on va vers le bord de fuite.We see that the J2 game evolves in the same direction as the stress point (Figure 2), i.e. increases the game the further we go towards the trailing edge.
Si cela est nécessaire, si il existe une pointe de contrainte trop élevée du côté correspondant au bord d'attaque de l'ailette, on peut prendre la même mesure de ce côté.If necessary, if there is a tip too high stress on the side corresponding to the edge attack of the fin, we can take the same measure of this side.
Pour obtenir ce jeu, on agit au cours de l'usinage sur le profil des crans. Par exemple on peut, dans le cas courant d'un pied d'ailette courbe comme celui représenté figure 1, modifier, à partir du point repéré 9 figure 4, le rayon de la trajectoire, (le diminuer) de la fraise d'usinage des crans, de façon à enlever plus de matière. Dans le cas d'un pied rectiligne, on modifie par exemple l'angle de la trajectoire.To obtain this clearance, one acts during the machining on the notch profile. For example we can, in the case current from a curved fin foot like the one shown figure 1, modify, starting from the point marked 9 figure 4, the radius of the trajectory, (reduce it) of the cutter machining of the notches, so as to remove more material. In the case of a straight foot, we modify for example the angle of the trajectory.
Claims (4)
- An arrangement for clipping stress peaks in the anchoring of a turbine blade (1) including a root (2) that is shaped like a Christmas tree, that includes tangs (3A, 3B. 3C. 3D), and that is received in a correspondingly-shaped groove (6) in a disk (7) so as to anchor said blade thereto. said arrangement being characterized by the fact that the outline of each tang (3), on the extrados side (B) of the blade root (2). is such that the clearance (J) for mounting the root in its groove. on the extrados side, is not uniform but rather it includes at least one zone in which the clearance varies, said zone corresponding to a zone of the tang (3) in question where, if the disk-and-blade assembly were rotating at its rated speed of rotation, there would otherwise occur a stress peak relative to the mean stress (m) along the tang if the blade were mounted with constant clearance along the entire length of said tang, said varying clearance (J2) varying along a said zone with the same sign as said stress peak.
- An arrangement according to claim 1, characterized in that said zone is situated at the trailing edge.
- An arrangement according to claim 1, characterized in that said zone is situated at the leading edge.
- A turbine blade, including a root (2) that is shaped like a Christmas tree, that includes tangs (3A, 3B, 3C, 3D), said blade being characterized in that the outline of each tang (3), on the extrados side (B) of the blade root (2), is such that the clearance (J) for mounting the root in its groove (6), on the extrados side, includes at least one zone in which the clearance varies, said zone corresponding to a zone of the tang (3) in question where, if the disk-and-blade assembly were rotating at its rated speed of rotation, there would otherwise occur a stress peak relative to the mean stress (m) along the tang if the blade were mounted with constant clearance along the entire length of said tang. said varying clearance (J2) varying along a said zone with the same sign as said stress peak.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR9411724A FR2725239B1 (en) | 1994-09-30 | 1994-09-30 | PROVISION FOR THE SHARPING OF STRESS SPIKES IN THE ANCHORAGE OF A TURBINE BLADE, COMPRISING A ROOT CALLED IN "FOOT-FIR" |
| FR9411724 | 1994-09-30 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP0705958A1 EP0705958A1 (en) | 1996-04-10 |
| EP0705958B1 true EP0705958B1 (en) | 1998-10-21 |
Family
ID=9467468
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP95402163A Expired - Lifetime EP0705958B1 (en) | 1994-09-30 | 1995-09-27 | Chamfering of stressed regions in a fir-tree turbine blade root |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US5567116A (en) |
| EP (1) | EP0705958B1 (en) |
| JP (1) | JPH08105301A (en) |
| DE (1) | DE69505479T2 (en) |
| FR (1) | FR2725239B1 (en) |
Families Citing this family (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9606963D0 (en) * | 1996-04-02 | 1996-06-05 | Rolls Royce Plc | A root attachment for a turbomachine blade |
| KR20000022064A (en) * | 1996-06-21 | 2000-04-25 | 칼 하인쯔 호르닝어 | Rotor for turbomachine with blades insertable into grooves and blades for rotor |
| DE19705323A1 (en) * | 1997-02-12 | 1998-08-27 | Siemens Ag | Turbo-machine blade |
| US6439851B1 (en) * | 2000-12-21 | 2002-08-27 | United Technologies Corporation | Reduced stress rotor blade and disk assembly |
| US7007382B2 (en) * | 2003-07-24 | 2006-03-07 | United Technologies Corporation | Slot machining |
| US7156621B2 (en) * | 2004-05-14 | 2007-01-02 | Pratt & Whitney Canada Corp. | Blade fixing relief mismatch |
| US7153102B2 (en) * | 2004-05-14 | 2006-12-26 | Pratt & Whitney Canada Corp. | Bladed disk fixing undercut |
| WO2006124614A2 (en) * | 2005-05-12 | 2006-11-23 | General Electric Company | Blade/disk dovetail backcut for blade/disk stress reduction (9fa+e, stage 2) |
| WO2006124619A2 (en) * | 2005-05-12 | 2006-11-23 | General Electric Company | BLADE/DISK DOVETAIL BACKCUT FOR BLADE/DISK STRESS REDUCTION (7FA+e, STAGE 2) |
| JP4918806B2 (en) * | 2006-04-06 | 2012-04-18 | 株式会社日立製作所 | Turbine rotor and turbine blade |
| JP2009536994A (en) * | 2006-05-12 | 2009-10-22 | ゼネラル・エレクトリック・カンパニイ | Blade / disk dovetail backcut for stress reduction in blade / disk (6FA + e, 2nd stage) |
| US20090208339A1 (en) * | 2008-02-15 | 2009-08-20 | United Technologies Corporation | Blade root stress relief |
| US9174292B2 (en) * | 2008-04-16 | 2015-11-03 | United Technologies Corporation | Electro chemical grinding (ECG) quill and method to manufacture a rotor blade retention slot |
| CN101285401B (en) * | 2008-06-03 | 2010-06-02 | 东方电气集团东方汽轮机有限公司 | Firtree -type bucket root steam turbine rotor blades and its locking notch vane |
| US7846010B2 (en) * | 2008-09-10 | 2010-12-07 | United Technologies Corporation | Notched grind wheel and method to manufacture a rotor blade retention slot |
| JP5395455B2 (en) * | 2009-02-20 | 2014-01-22 | 三菱重工業株式会社 | Rotor blade for axial compressor |
| US9151167B2 (en) * | 2012-02-10 | 2015-10-06 | General Electric Company | Turbine assembly |
| US8974188B2 (en) | 2012-03-06 | 2015-03-10 | Hamilton Sundstrand Corporation | Blade clip |
| US10072507B2 (en) | 2012-10-25 | 2018-09-11 | United Technologies Corporation | Redundant airfoil attachment |
| WO2014163680A1 (en) * | 2013-03-10 | 2014-10-09 | Rivers Jonathan M | Attachment feature of a gas turbine engine blade having a curved profile |
| WO2015171446A1 (en) | 2014-05-05 | 2015-11-12 | Horton, Inc. | Composite fan |
| CN104018888A (en) * | 2014-06-23 | 2014-09-03 | 中国船舶重工集团公司第七0四研究所 | Wrapping fir type blade root for circumferentially installing blades |
| US10731484B2 (en) | 2014-11-17 | 2020-08-04 | General Electric Company | BLISK rim face undercut |
| US20170074107A1 (en) * | 2015-09-15 | 2017-03-16 | General Electric Company | Blade/disk dovetail backcut for blade disk stress reduction (9e.04, stage 2) |
| US20170356297A1 (en) * | 2016-06-13 | 2017-12-14 | General Electric Company | Lockwire Tab Backcut For Blade Stress Reduction (9E.04) |
| US10895160B1 (en) * | 2017-04-07 | 2021-01-19 | Glenn B. Sinclair | Stress relief via unblended edge radii in blade attachments in gas turbines |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB677142A (en) * | 1949-08-24 | 1952-08-13 | Power Jets Res & Dev Ltd | Improved mounting for turbine and like blades |
| US3986793A (en) * | 1974-10-29 | 1976-10-19 | Westinghouse Electric Corporation | Turbine rotating blade |
| US4621979A (en) * | 1979-11-30 | 1986-11-11 | United Technologies Corporation | Fan rotor blades of turbofan engines |
| GB2238581B (en) * | 1989-11-30 | 1994-01-12 | Rolls Royce Plc | Improved attachment of a gas turbine engine blade to a turbine rotor disc |
| US5141401A (en) * | 1990-09-27 | 1992-08-25 | General Electric Company | Stress-relieved rotor blade attachment slot |
| FR2697051B1 (en) * | 1992-10-21 | 1994-12-02 | Snecma | Turbomachine rotor comprising a disk whose periphery is occupied by oblique cells which alternate with teeth of variable cross section. |
| FR2712631B1 (en) * | 1993-11-19 | 1998-08-21 | Gen Electric | Rotor fin and rotor disc-fin assembly comprising such a fin. |
-
1994
- 1994-09-30 FR FR9411724A patent/FR2725239B1/en not_active Expired - Fee Related
-
1995
- 1995-09-22 US US08/532,103 patent/US5567116A/en not_active Expired - Lifetime
- 1995-09-27 EP EP95402163A patent/EP0705958B1/en not_active Expired - Lifetime
- 1995-09-27 DE DE69505479T patent/DE69505479T2/en not_active Expired - Lifetime
- 1995-09-28 JP JP7250907A patent/JPH08105301A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| JPH08105301A (en) | 1996-04-23 |
| US5567116A (en) | 1996-10-22 |
| DE69505479D1 (en) | 1998-11-26 |
| FR2725239A1 (en) | 1996-04-05 |
| DE69505479T2 (en) | 1999-04-15 |
| EP0705958A1 (en) | 1996-04-10 |
| FR2725239B1 (en) | 1996-11-22 |
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