EP1911934A1 - Mobile blade of a turbomachine - Google Patents
Mobile blade of a turbomachine Download PDFInfo
- Publication number
- EP1911934A1 EP1911934A1 EP07118256A EP07118256A EP1911934A1 EP 1911934 A1 EP1911934 A1 EP 1911934A1 EP 07118256 A EP07118256 A EP 07118256A EP 07118256 A EP07118256 A EP 07118256A EP 1911934 A1 EP1911934 A1 EP 1911934A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- face
- edge
- turbomachine
- underside
- 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
- 239000012530 fluid Substances 0.000 claims abstract description 7
- 238000001816 cooling Methods 0.000 claims description 14
- 238000000926 separation method Methods 0.000 claims description 7
- 230000004907 flux Effects 0.000 abstract description 7
- 230000032798 delamination Effects 0.000 description 5
- 238000012935 Averaging Methods 0.000 description 1
- 239000011324 bead Substances 0.000 description 1
- 238000005553 drilling Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
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- 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
- F05D2240/55—Seals
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- 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
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
-
- 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
- F05D2250/60—Structure; Surface texture
- F05D2250/61—Structure; Surface texture corrugated
- F05D2250/611—Structure; Surface texture corrugated undulated
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- 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
Definitions
- the invention relates to a mobile turbine engine blade. It is intended for any type of turbomachine: turbojet, turboprop, gas turbine land ...
- the invention relates to a blade without a heel.
- a dawn is said without a heel when it does not have a platform at its upper end.
- Figures 1 to 3 show a blade without a bead, known type, mounted on the rotor disc of a turbine (or a compressor) turbojet.
- This known blade 8 comprises a fixing foot 10 surmounted by a blade 12, this blade having an end face 14 and side faces of the lower surface 16 and the upper surface 18, the fixing foot 10 and the said face of the blade.
- end 14 being respectively located at the lower and upper ends of the blade, opposite in the main direction A of the blade, the blade 12 having on its upper edge of a lower surface, a projecting edge 20 defined between a portion 24 of its face 14 and an upper portion 22 of its intrados face 16, these portions 22, 24 forming between them an average edge angle B.
- This average edge angle is calculated by averaging the edge angles measured at different points of the edge, between the parts 22, 24, each angle being measured in a plane perpendicular to the tangent to the edge at the point considered. In FIG. 2, for the sake of simplification, it was considered that the edge angle between the parts 22 and 24, measured in the plane of FIG. 2, was equal to the average edge angle B.
- the turbojet engine comprises a rotor disk 26 with a rotation axis R, the blades 8 are distributed circumferentially around the disk 26 and extend radially outwardly from this disk.
- the main direction A of each blade 8 corresponds to a direction radial with respect to the axis R.
- the blades 8 are surrounded externally by a housing ring 28, a gap I (see FIG. 2) remaining between the end face 14 of dawn and this ring 28.
- F1 and F2 are the respective components of the flux F in a plane perpendicular to the main direction A, such as the section plane III-III of Figure 3, and in a plane parallel to the main direction A, as the section plane II-II of Figure 2.
- a zone of turbulence C is created in the flow F (see FIG. 2).
- the flow F to cross the gap I must bypass the edge 20 and the turbulence zone C. To qualify this phenomenon, it is called detachment of the flux F at the edge.
- the invention aims to further promote the detachment of the flux at the edge.
- the subject of the invention is a turbomachine mobile blade, without heel, comprising a fixing foot surmounted by a blade, this blade having an end face and lateral faces of the lower and upper surfaces.
- the fixing foot and said end face being respectively located at the lower and upper ends of the blade, opposite along the main axis of the blade, the blade having on its upper edge of a lower surface, a defined projecting edge between a portion of its end face and an upper portion of its underside face, these portions forming between them an average edge angle strictly less than 90 °, so as to promote delamination, at the edge , of the flow of fluid passing through the turbomachine, characterized in that the upper part of the intrados face is corrugated and follows, in any plane section perpendicular to the main direction of the blade, a contour line fo rmée by a succession of curves alternately concave and convex.
- a curve is considered concave when its curved portion is oriented towards the upper surface of the blade. Conversely, a curve is considered convex when its curved portion is oriented opposite the extrados face of the blade.
- said intrados face has curved zones defined by the stacking of said convex curves along the main direction of the blade, and recessed zones defined by the stacking of said concave curves along the main direction of the blade.
- said contour line has an alternation of weakly and strongly inclined segments with respect to the components of the fluid flow in said section plane (under normal operating conditions of the turbomachine), and said upper part of the intrados wall. dawn has weakly and strongly inclined zones with respect to the flow, these zones being defined by the stacking of said weakly and strongly inclined segments, along the main direction of the blade.
- the said slightly inclined zones guide the flow towards the strongly inclined zones. In this way, the flow passes mainly by the strongly inclined zones, before crossing said edge.
- the edge angle to be crossed ie the stop angle "seen” from the flow
- the edge angle to be crossed is lower than if said upper part was smooth (ie without ripples).
- the delamination is all the more important as the edge angle to be crossed by the flow is small, better delamination is obtained with said corrugated upper part than with a smooth part. This reduces the losses of flow in the interstice I.
- said slightly inclined segments are oriented according to the components of the flow in the section plane (under normal operating conditions of the turbomachine), so that they form with these components an angle close to 0 °.
- the flow does not pass through the slightly inclined zones before crossing said ridge (it does not "see” them) and passes almost exclusively through the highly inclined zones.
- said strongly inclined segments are oriented transversely with respect to the components of the flow in the section plane (under normal operating conditions of the turbomachine), so that they form with these components an angle close to 90 °. It is according to this orientation that the edge angle to be crossed by the flow is the lowest and therefore that the separation of the flow in the gap is the most important. In other words, the delamination is most important when the steeply inclined areas face the components of the fluid flow in said section plane.
- FIGS. 4 to 6 a first example of blade 108 according to the invention will be described. Similar elements between this blade 108 and that of Figures 1 to 3 are identified by the same numerical references increased by 100.
- the blade 108 differs from the blade 8 with respect to the upper portion 122 of its intrados wall 116.
- the blade 108 comprises a fixing foot 110 surmounted by a blade 112, this blade having an end face 114 and side faces of the lower surface 116 and the upper surface 118.
- the attachment foot 110 and the face of the blade end 114 are respectively located at the lower and upper ends of the blade 108, opposite in the main direction A of the blade.
- the blade 112 has on its upper edge of a lower surface a protruding edge 120 defined between a portion 124 of the end face 114 and an upper portion 122 of the intrados face 116.
- the portions 122 and 124 form an angle between them. of average edge B strictly less than 90 °.
- the upper part 122 of the intrados face is corrugated so that it follows, in any plane section perpendicular to the main direction A of the blade and, in particular, in the section plane VI-VI, a contour line 130 formed by a succession of alternately concave curves 129 and convex 131.
- this contour line 130 has an alternation of weakly 130a and strongly 130b segments inclined relative to the F1 components of the stream F in the plane of section considered, here the plane VI-VI.
- Slightly inclined segments 130b are rather oriented along the F1 components of the flow in the section plane VI-VI, whereas the strongly inclined segments 130a are oriented transversely with respect to the F1 components of the flow in this plane. In this way, the stream F passes almost exclusively along the steep segments 130a before crossing the gap I. As the strongly inclined segments 130a face the flow F (more precisely the F1 components of this flow), the separation of the flux F at the edge 120 is improved, compared with the separation obtained in the example of FIGS. 3.
- the blade 108 comprises at its upper end an open cavity 132 delimited by a bottom wall 134, a lower edge 136 and an extrados edge 138.
- Said projecting edge 120 is formed on the underside flange 136 between the end face of this flange (which corresponds to said end face portion 114) and the underside face of this flange (which belongs to said upper portion 122 of the face of intrados 116).
- the blade comprises an internal cooling passage 142 and at least one cooling channel 140 communicating with this cooling passage 142.
- the channel 140 opens on said end-face portion 124, at the level of the curved undulating zones of the upper part 122 of the intrados face, that is to say at the level of the convex curves 131 of the contour line 130 (see Figure 6). It is indeed in these curved areas that there is the most material and it is therefore easier to achieve (for example by drilling) the channel 140.
- FIG. 7 a second example of blade 208 according to the invention will now be described.
- the analogous elements between this blade 208 and that of FIGS. 4 to 6 are identified by the same numerical references increased by 100.
- the blade 208 of FIG. 7 differs from that of FIGS. 4 to 6 with respect to the corrugated upper portion 222 of the intrados face 216. This upper portion 222 starts sufficiently far from the leading edge of the blade.
- Zone J covers a quarter of the dovetail face, starting from the leading edge, while Zone K covers the remaining three quarters.
- FIGS. 4 to 6 we will now describe a third example of blade 308 according to the invention.
- the analogous elements between this blade 308 and that of FIGS. 4 to 6 are identified by the same numerical references increased by 200.
- FIG. 8 differs from the example of FIGS. 4 to 6 in that the blade 308 does not have an open cavity at its upper end and, consequently, has no flange of intrados or flange. upper surface.
- FIG. 9 we will describe a fourth example of blade 408 according to the invention.
- the analogous elements between this blade 408 and that of FIGS. 4 to 6 are identified by the same numerical references increased by 300.
- the blade 408 of FIG. 9 differs from the example of FIGS. 4 to 6 in that its intrados flange 436 is set back relative to the remainder of the intrados face.
- the upper part 422 of the intrados face 416 corresponds to the intrados face of the intrados flange 436.
- the upper portion 122, 222, 322 of the intrados face 116, 216, 316 protruded from the rest of the intrados face of the blade
- the upper portion 422 of the intrados face 416 is set back relative to the remainder of the underside face of the blade.
- the upper portion 422 forms with the portion 424 of the end face of the blade, an average edge angle B strictly less than 90 °.
- the intrados flange 436 throughout its width is corrugated and inclined towards the intrados (thus, even the extrados wall 423 of the flange 436 is corrugated).
- the intrados flange 436 may be corrugated along its entire length, that is from the leading edge to the trailing edge of the blade, or only over part of its length.
- the blade example of FIG. 9 comprises an internal cooling passage 440 and cooling channels 442 communicating with this passage.
- the cooling channels 440 do not open on the part 424 of the end face of the blade, but at the base of the intrados flange 436, at the hollow corrugation zones of this rim, c that is, at the concave curves 429 of the contour line 430. Indeed, it is easier to realize the cooling channels 440 there.
- the cooling air supplied by the channels 440 rises along the upper portion 422 of the intrados wall (and thus allows the wall to cool) before reaching the gap I.
- FIG. 11 a fifth example of blade 508 according to the invention will be described.
- the analogous elements between this blade 508 and that of FIGS. 4 to 6 are identified by the same numerical references increased by 400.
- the blade 508 of FIG. 11 differs from the blade of FIGS. 9 and 10 in that the extrados rim 538 of this blade is corrugated and inclined towards the underside, in the manner of the intrados flange 536.
- another projecting edge 550 is defined between the end face 554 and the lower surface face 556 of the extrados rim 538.
- the intrados face 556 of the extrados rim 538 is corrugated and follows, in any plane section perpendicular to the main axis A of the dawn, a contour line formed by a succession of alternately concave and convex curves, so that this contour line has an alternation of weakly and strongly inclined segments with respect to the F1 components of the flux F in this section plane.
Abstract
Description
L'invention concerne une aube mobile de turbomachine. Elle se destine à tout type de turbomachine : turboréacteur, turbopropulseur, turbine à gaz terrestre...The invention relates to a mobile turbine engine blade. It is intended for any type of turbomachine: turbojet, turboprop, gas turbine land ...
Plus particulièrement, l'invention concerne une aube mobile sans talon. Une aube est dite sans talon lorsqu'elle ne porte pas de plateforme à son extrémité supérieure.More particularly, the invention relates to a blade without a heel. A dawn is said without a heel when it does not have a platform at its upper end.
Les figures 1 à 3 représentent une aube mobile sans talon, de type connu, montée sur le disque de rotor d'une turbine (ou d'un compresseur) de turboréacteur.Figures 1 to 3 show a blade without a bead, known type, mounted on the rotor disc of a turbine (or a compressor) turbojet.
Cette aube 8 connue comprend un pied de fixation 10 surmonté d'une pale 12, cette pale présentant une face d'extrémité 14 et des faces latérales d'intrados 16 et d'extrados 18, le pied de fixation 10 et ladite face d'extrémité 14 étant respectivement situés aux extrémités inférieure et supérieure de l'aube, opposées suivant la direction principale A de l'aube, la pale 12 présentant sur son bord supérieur d'intrados, une arête saillante 20 définie entre une partie 24 de sa face d'extrémité 14 et une partie supérieure 22 de sa face d'intrados 16, ces parties 22, 24 formant entre elles un angle d'arête moyen B. Cet angle d'arête moyen est calculé en faisant la moyenne des angles d'arête mesurés en différents points de l'arête, entre les parties 22, 24, chaque angle étant mesuré dans un plan perpendiculaire à la tangente à l'arête au point considéré. Sur la figure 2, par soucis de simplification, on a considéré que l'angle d'arête entre les parties 22 et 24, mesuré dans le plan de la figure 2, était égal à l'angle d'arête moyen B.This known
Le turboréacteur comprend un disque de rotor 26 d'axe de rotation R, les aubes 8 sont réparties circonférentiellement autour du disque 26 et s'étendent radialement vers l'extérieur de ce disque. La direction principale A de chaque aube 8 correspond à une direction radiale par rapport à l'axe R. Les aubes 8 sont entourées extérieurement par un anneau de carter 28, un interstice I (voir figure 2) subsistant entre la face d'extrémité 14 de l'aube et cet anneau 28.The turbojet engine comprises a
L'amont et l'aval sont définis dans la présente demande par rapport au sens d'écoulement du flux F d'air traversant le turboréacteur. On appelle F1 et F2 les composantes respectives du flux F dans un plan perpendiculaire à la direction principale A, comme le plan de section III-III de la figure 3, et dans un plan parallèle à la direction principale A, comme le plan de section II-II de la figure 2.Upstream and downstream are defined in the present application with respect to the flow direction of the air flow F flowing through the turbojet engine. F1 and F2 are the respective components of the flux F in a plane perpendicular to the main direction A, such as the section plane III-III of Figure 3, and in a plane parallel to the main direction A, as the section plane II-II of Figure 2.
En aval de l'arête saillante 20 il se crée une zone de turbulences C dans le flux F (voir figure 2). Le flux F pour traverser l'interstice I doit donc contourner l'arête 20 et la zone de turbulence C. Pour qualifier ce phénomène, on parle de décollement du flux F au niveau de l'arête.Downstream of the projecting
On cherche généralement à favoriser le plus possible le décollement du flux F dans l'interstice I car plus ce décollement est important plus la section de passage effective du flux F dans l'interstice I est réduite et, donc, plus la proportion du flux F traversant l'interstice est réduite. Or, le flux F traversant l'interstice I ne participe pas au rendement du turboréacteur. En favorisant le décollement on améliore donc le rendement du turboréacteur et, par voie de conséquence, on diminue la consommation en carburant de ce dernier.It is generally sought to promote as much as possible the detachment of the flux F in the gap I because the more this separation is important, the greater the effective cross section of the flow F in the gap I is reduced and therefore the proportion of the flow F crossing the gap is reduced. However, the flow F crossing the gap I does not participate in the performance of the turbojet engine. By favoring the separation, the efficiency of the turbojet engine is improved and, consequently, the fuel consumption of the latter is reduced.
Pour favoriser le décollement, il est connu de choisir l'angle d'arête moyen B strictement inférieur à 90°, comme représenté sur les figures 1 à 3 ou dans des exemples d'aubes connus et décrits dans
L'invention a pour but de favoriser encore plus le décollement du flux au niveau de l'arête.The invention aims to further promote the detachment of the flux at the edge.
Pour atteindre ce but, l'invention a pour objet une aube mobile de turbomachine, sans talon, comprenant un pied de fixation surmonté d'une pale, cette pale présentant une face d'extrémité et des faces latérales d'intrados et d'extrados, le pied de fixation et ladite face d'extrémité étant respectivement situés aux extrémités inférieure et supérieure de l'aube, opposées suivant l'axe principal de l'aube, la pale présentant sur son bord supérieur d'intrados, une arête saillante définie entre une partie de sa face d'extrémité et une partie supérieure de sa face d'intrados, ces parties formant entre elles un angle d'arête moyen strictement inférieur à 90°, de manière à favoriser le décollement, au niveau de l'arête, du flux de fluide traversant la turbomachine, caractérisée en ce que la partie supérieure de la face d'intrados est ondulée et suit, dans un quelconque plan de section perpendiculaire à la direction principale de l'aube, une ligne de contour formée par une succession de courbes alternativement concaves et convexes.To achieve this object, the subject of the invention is a turbomachine mobile blade, without heel, comprising a fixing foot surmounted by a blade, this blade having an end face and lateral faces of the lower and upper surfaces. , the fixing foot and said end face being respectively located at the lower and upper ends of the blade, opposite along the main axis of the blade, the blade having on its upper edge of a lower surface, a defined projecting edge between a portion of its end face and an upper portion of its underside face, these portions forming between them an average edge angle strictly less than 90 °, so as to promote delamination, at the edge , of the flow of fluid passing through the turbomachine, characterized in that the upper part of the intrados face is corrugated and follows, in any plane section perpendicular to the main direction of the blade, a contour line fo rmée by a succession of curves alternately concave and convex.
Dans la présente demande, une courbe est considérée comme concave lorsque sa partie bombée est orientée vers la face d'extrados de l'aube. Inversement, une courbe est considérée comme convexe lorsque sa partie bombée est orientée à l'opposé de la face d'extrados de l'aube.In the present application, a curve is considered concave when its curved portion is oriented towards the upper surface of the blade. Conversely, a curve is considered convex when its curved portion is oriented opposite the extrados face of the blade.
Ainsi, ladite face d'intrados présente des zones bombées définies par l'empilement desdites courbes convexes suivant la direction principale de l'aube, et des zones en creux définies par l'empilement desdites courbes concaves suivant la direction principale de l'aube.Thus, said intrados face has curved zones defined by the stacking of said convex curves along the main direction of the blade, and recessed zones defined by the stacking of said concave curves along the main direction of the blade.
Ainsi, ladite ligne de contour présente une alternance de segments faiblement et fortement inclinés par rapport aux composantes du flux de fluide dans ledit plan de section (dans des conditions de fonctionnement normales de la turbomachine), et ladite partie supérieure de la paroi d'intrados de l'aube présente des zones faiblement et fortement inclinées par rapport au flux, ces zones étant définies par l'empilement desdits segments faiblement et fortement inclinés, suivant la direction principale de l'aube.Thus, said contour line has an alternation of weakly and strongly inclined segments with respect to the components of the fluid flow in said section plane (under normal operating conditions of the turbomachine), and said upper part of the intrados wall. dawn has weakly and strongly inclined zones with respect to the flow, these zones being defined by the stacking of said weakly and strongly inclined segments, along the main direction of the blade.
Lesdites zones faiblement inclinées guident le flux vers les zones fortement inclinées. De cette manière, le flux passe majoritairement par les zones fortement inclinées, avant de franchir ladite arête. Or, pour le flux passant par les zones fortement inclinées, l'angle d'arête à franchir (i.e. l'angle d'arrête "vu" depuis le flux) est plus faible que si ladite partie supérieure était lisse (i.e. sans ondulations). Comme le décollement est d'autant plus important que l'angle d'arête à franchir par le flux est faible, on obtient un meilleur décollement avec ladite partie supérieure ondulée qu'avec une partie lisse. On diminue ainsi les pertes de flux dans l'interstice I.The said slightly inclined zones guide the flow towards the strongly inclined zones. In this way, the flow passes mainly by the strongly inclined zones, before crossing said edge. However, for the flow passing through the steeply inclined zones, the edge angle to be crossed (ie the stop angle "seen" from the flow) is lower than if said upper part was smooth (ie without ripples). . As the delamination is all the more important as the edge angle to be crossed by the flow is small, better delamination is obtained with said corrugated upper part than with a smooth part. This reduces the losses of flow in the interstice I.
Avantageusement, lesdits segments faiblement inclinés sont orientés suivant les composantes du flux dans le plan de section (dans des conditions de fonctionnement normales de la turbomachine), de sorte qu'ils forment avec ces composantes un angle voisin de 0°. De cette manière, le flux ne passe pas par les zones faiblement inclinées avant de franchir ladite arête (il ne les "voit" pas) et passe quasi-exclusivement par les zones fortement inclinées.Advantageously, said slightly inclined segments are oriented according to the components of the flow in the section plane (under normal operating conditions of the turbomachine), so that they form with these components an angle close to 0 °. In this way, the flow does not pass through the slightly inclined zones before crossing said ridge (it does not "see" them) and passes almost exclusively through the highly inclined zones.
Avantageusement, lesdits segments fortement inclinés sont orientés transversalement par rapport aux composantes du flux dans le plan de section (dans des conditions de fonctionnement normales de la turbomachine), de sorte qu'ils forment avec ces composantes un angle voisin de 90°. C'est selon cette orientation que l'angle d'arête à franchir par le flux est le plus faible et donc que le décollement du flux dans l'interstice est le plus important. En d'autres termes, le décollement est le plus important lorsque les zones fortement inclinées font face aux composantes du flux de fluide dans ledit plan de section.Advantageously, said strongly inclined segments are oriented transversely with respect to the components of the flow in the section plane (under normal operating conditions of the turbomachine), so that they form with these components an angle close to 90 °. It is according to this orientation that the edge angle to be crossed by the flow is the lowest and therefore that the separation of the flow in the gap is the most important. In other words, the delamination is most important when the steeply inclined areas face the components of the fluid flow in said section plane.
L'invention et ses avantages seront mieux compris à la lecture de la description détaillée qui suit. Cette description fait référence aux figures annexées sur lesquelles :
- la figure 1 est une vue en perspective d'une partie d'un turboréacteur équipé d'une aube de type connu;
- la figure 2 représente l'aube de la figure 1 en section suivant le plan II-II, plan perpendiculaire à la tangente à l'arête de l'aube, passant par le point D;
- la figure 3 représente l'aube de la figure 1 en section suivant le plan III-III, plan perpendiculaire à la direction principale A de l'aube, coupant la partie supérieure de la face d'intrados de l'aube, et passant par le point D;
- la figure 4 est une vue en perspective d'une partie d'un turboréacteur équipé d'un premier exemple d'aube selon l'invention;
- la figure 5 représente l'aube de la figure 4 en section suivant le plan V-V, plan perpendiculaire à la tangente à l'arête de l'aube, passant par le point D;
- la figure 6 représente l'aube de la figure 4 en section suivant le plan VI-VI, plan perpendiculaire à la direction principale A de l'aube, coupant la partie supérieure ondulée de la face d'intrados de l'aube et passant par le point D;
- la figure 7 est une section analogue à celle de la figure 6, représentant un deuxième exemple d'aube selon l'invention;
- la figure 8 est une section analogue à celle de la figure 5, représentant un troisième exemple d'aube selon l'invention;
- la figure 9 est une section analogue à celle de la figure 5, représentant en section suivant le plan IX-IX un quatrième exemple d'aube selon l'invention;
- la figure 10 est une section analogue à celle de la figure 6, et représente en section suivant le plan X-X, l'exemple d'aube de la figure 9; et
- la figure 11 est une section analogue à celle de la figure 5, représentant un cinquième exemple d'aube selon l'invention.
- Figure 1 is a perspective view of a portion of a turbojet equipped with a blade of known type;
- Figure 2 shows the blade of Figure 1 in section along the plane II-II plane perpendicular to the tangent to the edge of the blade, passing through the point D;
- FIG. 3 represents the blade of FIG. 1 in section along plane III-III, plane perpendicular to the principal direction A of the blade, intersecting the upper part of the intrados face of the blade, and passing through point D;
- FIG. 4 is a perspective view of a portion of a turbojet engine equipped with a first example of a blade according to the invention;
- Figure 5 shows the blade of Figure 4 in section along the plane VV plane perpendicular to the tangent to the edge of the blade, passing through the point D;
- FIG. 6 represents the blade of FIG. 4 in section along the plane VI-VI, plane perpendicular to the principal direction A of the blade, intersecting the undulating upper part of the intrados face of the blade and passing through point D;
- Figure 7 is a section similar to that of Figure 6, showing a second example of blade according to the invention;
- Figure 8 is a section similar to that of Figure 5, showing a third example of blade according to the invention;
- Figure 9 is a section similar to that of Figure 5, showing in section along the IX-IX plane a fourth example of blade according to the invention;
- Figure 10 is a section similar to that of Figure 6, and shows in section along the plane XX, the blade example of Figure 9; and
- Figure 11 is a section similar to that of Figure 5, showing a fifth example of blade according to the invention.
Les figures 1 à 3 ont été décrites plus haut.Figures 1 to 3 have been described above.
En référence aux figures 4 à 6, on va décrire un premier exemple d'aube 108 selon l'invention. Les éléments analogues entre cette aube 108 et celle des figures 1 à 3 sont repérés par les mêmes références numériques augmentées de 100.With reference to FIGS. 4 to 6, a first example of
L'aube 108 diffère de l'aube 8 en ce qui concerne la partie supérieure 122 de sa paroi d'intrados 116.The
L'aube 108 comprend un pied de fixation 110 surmonté d'une pale 112, cette pale présentant une face d'extrémité 114 et des faces latérales d'intrados 116 et d'extrados 118. Le pied de fixation 110 et la face d'extrémité 114 sont respectivement situés aux extrémités inférieure et supérieure de l'aube 108, opposées suivant la direction principale A de l'aube. La pale 112 présente sur son bord supérieur d'intrados une arête saillante 120 définie entre une partie 124 de la face d'extrémité 114 et une partie supérieure 122 de la face d'intrados 116. Les parties 122 et 124 forment entre elles un angle d'arête moyen B strictement inférieur à 90°.The
Conformément à l'invention, la partie supérieure 122 de la face d'intrados est ondulée de sorte qu'elle suit, dans un quelconque plan de section perpendiculaire à la direction principale A de l'aube et, notamment, dans le plan de section VI-VI, une ligne de contour 130 formée par une par une succession de courbes alternativement concaves 129 et convexes 131. Ainsi, cette ligne de contour 130 présente une alternance de segments faiblement 130a et fortement 130b inclinées par rapport aux composantes F1 du flux F dans le plan de section considéré, ici le plan VI-VI.According to the invention, the
Les segments faiblement inclinés 130b sont plutôt orientés suivant les composantes F1 du flux dans le plan de section VI-VI, tandis que les segments fortement inclinés 130a sont plutôt orientés transversalement par rapport aux composantes F1 du flux dans ce plan. De cette manière, le flux F passe quasi exclusivement le long des segments fortement inclinés 130a avant de traverser l'interstice I. Comme les segments fortement inclinés 130a font face au flux F (plus précisément aux composantes F1 de ce flux), le décollement du flux F au niveau de l'arête 120 est amélioré, en comparaison avec le décollement obtenu dans l'exemple des figures 1 à 3.Slightly
Dans l'exemple des figures 4 à 6, l'aube 108 comprend à son extrémité supérieure une cavité ouverte 132 délimitée par une paroi de fond 134, un rebord d'intrados 136 et un rebord d'extrados 138. Ladite arête saillante 120 est formée sur le rebord d'intrados 136 entre la face d'extrémité de ce rebord (qui correspond à ladite partie 124 de face d'extrémité 114) et la face d'intrados de ce rebord (qui appartient à ladite partie supérieure 122 de la face d'intrados 116).In the example of FIGS. 4 to 6, the
On notera également que, selon cet exemple, l'aube comprend un passage de refroidissement interne 142 et au moins un canal de refroidissement 140 communiquant avec ce passage de refroidissement 142.It will also be noted that, according to this example, the blade comprises an
Avantageusement, le canal 140 débouche sur ladite partie 124 de face d'extrémité, au niveau des zones d'ondulation bombées de la partie supérieure 122 de la face d'intrados, c'est-à-dire au niveau des courbes convexes 131 de la ligne de contour 130 (voir figure 6). C'est en effet dans ces zones bombées qu'il y a le plus de matière et qu'il est donc plus facile de réaliser (par exemple par perçage) le canal 140.Advantageously, the
En référence à la figure 7, on va maintenant décrire un deuxième exemple d'aube 208 selon l'invention. Les éléments analogues entre cette aube 208 et celle des figures 4 à 6 sont repérés par les mêmes références numériques augmentées de 100.With reference to FIG. 7, a second example of
L'aube 208 de la figure 7 diffère de celle des figures 4 à 6 en ce qui concerne la partie supérieure ondulée 222 de la face d'intrados 216. Cette partie supérieure 222 débute assez loin du bord d'attaque de l'aube.The
Ceci tient compte du fait que seule une petite partie du flux traverse l'interstice I dans la zone J proche du bord d'attaque de l'aube. En effet, en référence à la figure 7, on estime grossièrement que 20 % du flux traverse l'interstice I au niveau de la zone J et donc que les 80 % restants du flux traversent l'interstice I au niveau de la zone K. Par conséquent, la présence d'ondulations selon l'invention (i.e. la succession de courbes alternativement concaves 229 et convexes 231 suivant la ligne de contour 230), se révèle surtout utile dans la zone K. Approximativement, la zone J couvre un quart de la face d'intrados de l'aube, en partant du bord d'attaque, tandis que la zone K couvre les trois quarts restants.This takes into account that only a small portion of the flow passes through gap I in zone J near the leading edge of the blade. With reference to FIG. 7, it is roughly estimated that 20% of the flow passes through gap I at zone J and therefore the remaining 80% of the flow passes through gap I at zone K. Consequently, the presence of corrugations according to the invention (ie the succession of alternately
En référence à la figure 8, nous allons maintenant décrire un troisième exemple d'aube 308 selon l'invention. Les éléments analogues entre cette aube 308 et celle des figures 4 à 6 sont repérés par les mêmes références numériques augmentées de 200.Referring to Figure 8, we will now describe a third example of
L'exemple de la figure 8 diffère de l'exemple des figures 4 à 6 en ce que l'aube 308 ne présente pas une cavité ouverte à son extrémité supérieure et, par conséquent, ne présente ni rebord d'intrados, ni rebord d'extrados.The example of FIG. 8 differs from the example of FIGS. 4 to 6 in that the
En référence à la figure 9, nous allons décrire un quatrième exemple d'aube 408 selon l'invention. Les éléments analogues entre cette aube 408 et celle des figures 4 à 6 sont repérés par les mêmes références numériques augmentées de 300.With reference to FIG. 9, we will describe a fourth example of
L'aube 408 de la figure 9 diffère de l'exemple des figures 4 à 6 en ce que son rebord d'intrados 436 est en retrait par rapport au reste de la face d'intrados. La partie supérieure 422 de la face d'intrados 416 correspond à la face d'intrados du rebord d'intrados 436.The
Ainsi, alors que dans les trois premiers exemples, la partie supérieure 122, 222, 322 de la face d'intrados 116, 216, 316 était en saillie par rapport au reste de la face d'intrados de l'aube, dans ce quatrième exemple, la partie supérieure 422 de la face d'intrados 416 est en retrait par rapport au reste de la face d'intrados de l'aube.Thus, while in the first three examples, the
La partie supérieure 422 forme avec la partie 424 de la face d'extrémité de l'aube, un angle d'arête moyen B strictement inférieur à 90°.The
Par ailleurs, on notera que dans ce quatrième exemple, le rebord d'intrados 436 dans toute sa largeur, est ondulé et incliné vers l'intrados (ainsi, même la paroi d'extrados 423 du rebord 436 est ondulée). Le rebord d'intrados 436 peut être ondulé sur toute sa longueur, c'est-à-dire depuis le bord d'attaque jusqu'au bord de fuite de l'aube, ou seulement sur une partie de sa longueur.Furthermore, it will be noted that in this fourth example, the
A l'image de l'exemple de la figure 5, l'exemple d'aube de la figure 9 comprend un passage de refroidissement interne 440 et des canaux de refroidissement 442 communiquant avec ce passage. En revanche, les canaux de refroidissement 440 ne débouchent pas sur la partie 424 de la face d'extrémité de l'aube, mais à la base du rebord d'intrados 436, au niveau des zones d'ondulation en creux de ce rebord, c'est-à-dire au niveau des courbes concaves 429 de la ligne de contour 430. En effet, il est plus facile de réaliser les canaux de refroidissement 440 à cet endroit. En outre, l'air de refroidissement amené par les canaux 440 remonte le long de la partie supérieure 422 de paroi d'intrados (et permet ainsi de refroidir cette paroi) avant de gagner l'interstice I.As in the example of FIG. 5, the blade example of FIG. 9 comprises an
En référence à la figure 11, on va décrire un cinquième exemple d'aube 508 selon l'invention. Les éléments analogues entre ce cette aube 508 et celle des figures 4 à 6 sont repérés par les mêmes références numériques augmentées de 400.With reference to FIG. 11, a fifth example of
L'aube 508 de la figure 11 diffère de l'aube des figures 9 et 10 en ce que le rebord d'extrados 538 de cette aube est ondulé et incliné vers l'intrados, à la manière du rebord d'intrados 536. Ainsi, une autre arête saillante 550 est définie entre la face d'extrémité 554 et la face d'intrados 556 du rebord d'extrados 538. Ces parties forment entre elles un angle d'arête moyen G strictement inférieur à 90° de manière à favoriser le décollement du flux F de fluide traversant la turbomachine au niveau de l'arête 550. La face d'intrados 556 du rebord d'extrados 538 est ondulée et suit, dans un quelconque plan de section perpendiculaire à l'axe principal A de l'aube, une ligne de contour formée par une succession de courbes alternativement concaves et convexes, de sorte que cette ligne de contour présente une alternance de segments faiblement et fortement inclinés par rapport aux composantes F1 du flux F dans ce plan de section.The
Dans les exemples précités, on a décrit une aube appartenant à un rotor de turbine de turboréacteur. Néanmoins, il est clair que l'invention peut s'appliquer à d'autres types de turbomachines, les pertes de rendement liées au passage du flux F dans l'interstice I se retrouvant dans d'autres types de turbomachines.In the above examples, a blade belonging to a turbojet turbine rotor has been described. Nevertheless, it is clear that the invention can be applied to other types of turbomachines, the yield losses related to the passage of the flow F in the gap I found in other types of turbomachines.
Claims (9)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0654257A FR2907157A1 (en) | 2006-10-13 | 2006-10-13 | MOBILE AUB OF TURBOMACHINE |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1911934A1 true EP1911934A1 (en) | 2008-04-16 |
EP1911934B1 EP1911934B1 (en) | 2009-07-22 |
Family
ID=38066650
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07118256A Active EP1911934B1 (en) | 2006-10-13 | 2007-10-11 | Blade of a turbomachine |
Country Status (7)
Country | Link |
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US (1) | US7972115B2 (en) |
EP (1) | EP1911934B1 (en) |
JP (1) | JP4889123B2 (en) |
CA (1) | CA2606072C (en) |
DE (1) | DE602007001652D1 (en) |
FR (1) | FR2907157A1 (en) |
RU (1) | RU2457335C2 (en) |
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CN102678189A (en) * | 2011-12-13 | 2012-09-19 | 河南科技大学 | Turbine cooling blade with blade tip leakage prevention structure |
WO2013180797A2 (en) | 2012-03-14 | 2013-12-05 | United Technologies Corporation | Shark-bite tip shelf cooling configuration |
EP2825733A4 (en) * | 2012-03-14 | 2015-11-11 | United Technologies Corp | Shark-bite tip shelf cooling configuration |
EP2666968A1 (en) * | 2012-05-24 | 2013-11-27 | General Electric Company | Turbine rotor blade |
EP2666967A1 (en) * | 2012-05-24 | 2013-11-27 | General Electric Company | Turbine rotor blade |
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GB2560124B (en) * | 2015-11-16 | 2022-04-13 | Safran Aircraft Engines | Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region |
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EP3882436A1 (en) * | 2020-03-20 | 2021-09-22 | General Electric Company | Rotor blade for a turbomachine and corresponding turbomachine |
EP4130429A3 (en) * | 2021-08-06 | 2023-04-12 | Raytheon Technologies Corporation | Airfoil tip arrangement for gas turbine engine |
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Also Published As
Publication number | Publication date |
---|---|
EP1911934B1 (en) | 2009-07-22 |
JP4889123B2 (en) | 2012-03-07 |
CA2606072A1 (en) | 2008-04-13 |
RU2007138000A (en) | 2009-04-20 |
JP2008095695A (en) | 2008-04-24 |
CA2606072C (en) | 2015-03-31 |
US7972115B2 (en) | 2011-07-05 |
US20080175716A1 (en) | 2008-07-24 |
DE602007001652D1 (en) | 2009-09-03 |
RU2457335C2 (en) | 2012-07-27 |
FR2907157A1 (en) | 2008-04-18 |
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