EP1911934B1 - Bewegliche Laufradschaufel einer Strömungsmaschine - Google Patents

Bewegliche Laufradschaufel einer Strömungsmaschine Download PDF

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Publication number
EP1911934B1
EP1911934B1 EP07118256A EP07118256A EP1911934B1 EP 1911934 B1 EP1911934 B1 EP 1911934B1 EP 07118256 A EP07118256 A EP 07118256A EP 07118256 A EP07118256 A EP 07118256A EP 1911934 B1 EP1911934 B1 EP 1911934B1
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EP
European Patent Office
Prior art keywords
blade
pressure
face
turbomachine
edge
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.)
Active
Application number
EP07118256A
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English (en)
French (fr)
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EP1911934A1 (de
Inventor
Thomas Potier
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1911934A1 publication Critical patent/EP1911934A1/de
Application granted granted Critical
Publication of EP1911934B1 publication Critical patent/EP1911934B1/de
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • 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
    • 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
    • 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.
  • the Figures 1 to 3 represent a mobile blade without heel, of 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. On the figure 2 for the sake of simplification, it was considered that the edge angle between the parts 22 and 24, measured in the plane of the figure 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, an interstice I (see figure 2 ) remaining between the end face 14 of the blade 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 the figure 3 , and in a plane parallel to the main direction A, as the section plane II-II of the figure 2 .
  • 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.
  • 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 the Figures 1 to 3 .
  • the blade 108 comprises at its upper end an open cavity 132 defined by a bottom wall 134, a lower edge 136 and an extrados edge 138.
  • Said protruding edge 120 is formed on the underside flange 136 between the end face of this flange (which corresponds to said end face portion 124) and the underside face of this rim (which belongs to said upper portion 122 of the intrados face 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.
  • Dawn 208 of the figure 7 differs from that of Figures 4 to 6 as regards the corrugated upper portion 222 of the intrados face 216. This upper portion 222 starts far enough from the leading edge of the blade.
  • zone J 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. Indeed, with reference to the figure 7 it is roughly estimated that 20% of the flow passes through gap I at zone J and thus the remaining 80% of flow passes through gap I at zone K. Therefore, the presence of corrugations according to the invention (ie the succession of alternately concave curves 229 and convex curves 231 along the contour line 230) is particularly useful in zone K. Approximately, Zone J covers a quarter of the dovetail face, starting from the leading edge, while Zone K covers the remaining three quarters.
  • the example of figure 8 differs from the example of Figures 4 to 6 in that the blade 308 does not have an open cavity at its upper end and, consequently, has no underside or extrados rim.
  • Dawn 408 of the figure 9 differs from the example of Figures 4 to 6 in that its intrados flange 436 is set back from the rest 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 dawn example of the figure 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.
  • Dawn 508 of the figure 11 differs from the dawn of Figures 9 and 10 in that the extrados rim 538 of this blade is corrugated and inclined towards the lower surface, in the manner of the lower flange 536.
  • another projecting edge 550 is defined between the end face 554 and the face These portions form between them an angle of average edge G strictly less than 90 ° so as to promote the separation of the flow F of fluid passing through the turbomachine at the edge 550.
  • the intrados face 556 of the extrados rim 538 is corrugated and follows, in any sectional plane perpendicular to the main axis A of the blade, 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Ansatzlose Laufschaufel einer Turbomaschine, mit einem Befestigungsfuß (110), auf dem ein Blatt (112) angeordnet ist, wobei dieses Blatt eine Endseite (114) sowie eine vorderseitige Seitenfläche (116) und eine rückseitige Seitenfläche (118) aufweist, wobei der Befestigungsfuß und die Endseite sich am unteren Ende bzw. am oberen Ende der Schaufel befinden, die entlang der Hauptachse (A) der Schaufel einander gegenüberliegen, wobei das Blatt an seinem oberen vorderseitigen Rand eine vorspringende Kante (120) aufweist, die zwischen einem Teil (124) seiner Endseite und einem oberen Teil (122) seiner Vorderseite definiert ist, wobei diese Teile einen mittleren Kantenwinkel (B) streng kleiner als 90° einschließen, um die Ablösung des die Turbomaschine durchströmenden Fluidstroms (F) im Bereich der Kante zu begünstigen, dadurch gekennzeichnet, daß der obere Teil (122) der Vorderseite gewellt ist und in einer beliebigen Schnittebene senkrecht zur Hauptachse der Schaufel einer Umrißlinie (130) folgt, die von einer Folge von abwechselnd konkaven (129) und konvexen (131) Krümmungen gebildet ist.
  2. Turbomaschinenschaufel nach Anspruch 1, bei welcher der obere Teil (122) der Vorderseite gegenüber dem Rest der Vorderseite der Schaufel vorspringt.
  3. Turbomaschinenschaufel nach Anspruch 1 oder 2, die an ihrem oberen Ende einen offenen Hohlraum (132) aufweist, der durch eine bodenseitige Wand (134), einen vorderseitigen Rand (136) und einen rückseitigen Rand (138) begrenzt ist, und bei welcher die vorspringende Kante (120) an dem vorderseitigen Rand zwischen der Endseite und der gewellten Vorderseite des vorderseitigen Randes gebildet ist.
  4. Turbomaschinenschaufel nach einem der Ansprüche 1 bis 3, die einen inneren Kühldurchlaß (142) sowie wenigstens einen mit dem inneren Kühldurchlaß in Verbindung stehenden Kühlkanal (140) aufweist, wobei dieser Kanal an dem Teil (124) der Endseite im Bereich der gewölbten Wellenbereiche des oberen Teils (122) der Vorderseite ausmündet.
  5. Turbomaschinenschaufel nach Anspruch 3, bei welcher der vorderseitige Rand (436) gewellt und zur Vorderseite geneigt ist.
  6. Turbomaschinenschaufel nach Anspruch 5, die einen inneren Kühldurchlaß (442) sowie wenigstens einen mit dem inneren Kühldurchlaß in Verbindung stehenden Kühlkanal (440) aufweist, wobei dieser Kanal an der Basis des vorderseitigen Randes (436) im Bereich der vertieften Wellenbereiche dieses Randes ausmündet.
  7. Turbomaschinenschaufel nach Anspruch 3, bei welcher eine weitere vorspringende Kante (550) zwischen der Endseite und der Vorderseite des rückseitigen Randes (538) definiert ist, wobei diese Teile einen mittleren Kantenwinkel (G) streng kleiner als 90° einschließen, um die Ablösung des die Turbomaschine durchströmenden Fluidstroms (F) im Bereich dieser weiteren Kante zu begünstigen, und bei welcher die Vorderseite des rückseitigen Randes (538) gewellt ist und in einer beliebigen Schnittebene senkrecht zur Hauptachse der Schaufel einer Umrißlinie folgt, die von einer Folge von abwechselnd konkaven und konvexen Krümmungen gebildet ist.
  8. Turbine, die eine Schaufel nach einem der vorhergehenden Ansprüche umfaßt.
  9. Turbomaschine, die eine Turbine nach Anspruch 8 umfaßt.
EP07118256A 2006-10-13 2007-10-11 Bewegliche Laufradschaufel einer Strömungsmaschine Active EP1911934B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0654257A FR2907157A1 (fr) 2006-10-13 2006-10-13 Aube mobile de turbomachine

Publications (2)

Publication Number Publication Date
EP1911934A1 EP1911934A1 (de) 2008-04-16
EP1911934B1 true EP1911934B1 (de) 2009-07-22

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US (1) US7972115B2 (de)
EP (1) EP1911934B1 (de)
JP (1) JP4889123B2 (de)
CA (1) CA2606072C (de)
DE (1) DE602007001652D1 (de)
FR (1) FR2907157A1 (de)
RU (1) RU2457335C2 (de)

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Also Published As

Publication number Publication date
FR2907157A1 (fr) 2008-04-18
EP1911934A1 (de) 2008-04-16
JP2008095695A (ja) 2008-04-24
RU2457335C2 (ru) 2012-07-27
US7972115B2 (en) 2011-07-05
CA2606072A1 (fr) 2008-04-13
JP4889123B2 (ja) 2012-03-07
CA2606072C (fr) 2015-03-31
US20080175716A1 (en) 2008-07-24
RU2007138000A (ru) 2009-04-20
DE602007001652D1 (de) 2009-09-03

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