EP1911934A1 - Bewegliche Laufradschaufel einer Strömungsmaschine - Google Patents

Bewegliche Laufradschaufel einer Strömungsmaschine Download PDF

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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
Application number
EP07118256A
Other languages
English (en)
French (fr)
Other versions
EP1911934B1 (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
Priority date (The priority date 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 date listed.)
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
Anticipated expiration legal-status Critical

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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.
  • 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.

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

Family

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Family Applications (1)

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EP07118256A Active EP1911934B1 (de) 2006-10-13 2007-10-11 Bewegliche Laufradschaufel einer Strömungsmaschine

Country Status (7)

Country Link
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)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102678189A (zh) * 2011-12-13 2012-09-19 河南科技大学 一种具有叶顶防泄漏结构的涡轮冷却叶片
EP2666967A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
EP2666968A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
WO2013180797A2 (en) 2012-03-14 2013-12-05 United Technologies Corporation Shark-bite tip shelf cooling configuration
WO2017085387A1 (fr) * 2015-11-16 2017-05-26 Safran Aircraft Engines Aube de turbine de turbomachine, turbine et turbomachine associées
EP3216983A1 (de) * 2016-03-08 2017-09-13 Siemens Aktiengesellschaft Laufschaufel für eine gasturbine mit gekühlter anstreifkante
WO2019035800A1 (en) * 2017-08-14 2019-02-21 Siemens Aktiengesellschaft AUBES OF TURBINE
EP3882436A1 (de) * 2020-03-20 2021-09-22 General Electric Company Laufschaufel für eine strömungsmaschine und zugehörige strömungsmaschine
EP4130429A3 (de) * 2021-08-06 2023-04-12 Raytheon Technologies Corporation Schaufelspitzenanordnung für ein gasturbinentriebwerk

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GB0813556D0 (en) * 2008-07-24 2008-09-03 Rolls Royce Plc A blade for a rotor
US8777567B2 (en) 2010-09-22 2014-07-15 Honeywell International Inc. Turbine blades, turbine assemblies, and methods of manufacturing turbine blades
GB201100957D0 (en) * 2011-01-20 2011-03-02 Rolls Royce Plc Rotor blade
US9322280B2 (en) * 2011-08-12 2016-04-26 United Technologies Corporation Method of measuring turbine blade tip erosion
FR2982903B1 (fr) * 2011-11-17 2014-02-21 Snecma Aube de turbine a gaz a decalage vers l'intrados des sections de tete et a canaux de refroidissement
US9470096B2 (en) * 2012-07-26 2016-10-18 General Electric Company Turbine bucket with notched squealer tip
RU2529273C1 (ru) * 2013-09-11 2014-09-27 Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" Рабочая лопатка турбины газотурбинного двигателя
US9856739B2 (en) * 2013-09-18 2018-01-02 Honeywell International Inc. Turbine blades with tip portions having converging cooling holes
US9879544B2 (en) 2013-10-16 2018-01-30 Honeywell International Inc. Turbine rotor blades with improved tip portion cooling holes
US9816389B2 (en) 2013-10-16 2017-11-14 Honeywell International Inc. Turbine rotor blades with tip portion parapet wall cavities
US20150110617A1 (en) * 2013-10-23 2015-04-23 General Electric Company Turbine airfoil including tip fillet
US9670784B2 (en) 2013-10-23 2017-06-06 General Electric Company Turbine bucket base having serpentine cooling passage with leading edge cooling
US9551226B2 (en) 2013-10-23 2017-01-24 General Electric Company Turbine bucket with endwall contour and airfoil profile
US9528379B2 (en) 2013-10-23 2016-12-27 General Electric Company Turbine bucket having serpentine core
US9797258B2 (en) 2013-10-23 2017-10-24 General Electric Company Turbine bucket including cooling passage with turn
US9638041B2 (en) 2013-10-23 2017-05-02 General Electric Company Turbine bucket having non-axisymmetric base contour
US20170145827A1 (en) * 2015-11-23 2017-05-25 United Technologies Corporation Turbine blade with airfoil tip vortex control
US10677066B2 (en) 2015-11-23 2020-06-09 United Technologies Corporation Turbine blade with airfoil tip vortex control
US10253637B2 (en) * 2015-12-11 2019-04-09 General Electric Company Method and system for improving turbine blade performance
US10436037B2 (en) * 2016-07-22 2019-10-08 General Electric Company Blade with parallel corrugated surfaces on inner and outer surfaces
US10465525B2 (en) * 2016-07-22 2019-11-05 General Electric Company Blade with internal rib having corrugated surface(s)
US10450868B2 (en) * 2016-07-22 2019-10-22 General Electric Company Turbine rotor blade with coupon having corrugated surface(s)
US10443399B2 (en) * 2016-07-22 2019-10-15 General Electric Company Turbine vane with coupon having corrugated surface(s)
US10465520B2 (en) 2016-07-22 2019-11-05 General Electric Company Blade with corrugated outer surface(s)
EP3361056A1 (de) 2017-02-10 2018-08-15 Siemens Aktiengesellschaft Leitschaufel für eine strömungsmaschine
EP3669054B1 (de) * 2017-08-14 2022-02-09 Siemens Energy Global GmbH & Co. KG Turbinenschaufel und entsprechendes wartungsverfahren
US10787932B2 (en) 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
BE1026579B1 (fr) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa Aube a protuberance pour compresseur de turbomachine
US11773726B2 (en) * 2019-10-16 2023-10-03 Rtx Corporation Angled tip rods

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EP1650404A2 (de) * 2004-10-21 2006-04-26 General Electric Company Wiederherstellungsverfahren einer Turbinenschaufelspitze

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US20040096328A1 (en) * 2002-11-20 2004-05-20 Mitsubishi Heavy Industries Ltd. Turbine blade and gas turbine
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EP1650404A2 (de) * 2004-10-21 2006-04-26 General Electric Company Wiederherstellungsverfahren einer Turbinenschaufelspitze

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102678189A (zh) * 2011-12-13 2012-09-19 河南科技大学 一种具有叶顶防泄漏结构的涡轮冷却叶片
WO2013180797A2 (en) 2012-03-14 2013-12-05 United Technologies Corporation Shark-bite tip shelf cooling configuration
EP2825733A4 (de) * 2012-03-14 2015-11-11 United Technologies Corp Dreieckige schaufelspitzenkühlungskonfiguration
EP2666967A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
EP2666968A1 (de) * 2012-05-24 2013-11-27 General Electric Company Turbinenlaufschaufel
US9188012B2 (en) 2012-05-24 2015-11-17 General Electric Company Cooling structures in the tips of turbine rotor blades
GB2560124A (en) * 2015-11-16 2018-08-29 Safran Aircraft Engines Turbine engine turbine vane, and related turbine and turbine engine
WO2017085387A1 (fr) * 2015-11-16 2017-05-26 Safran Aircraft Engines Aube de turbine de turbomachine, turbine et turbomachine associées
US10753215B2 (en) 2015-11-16 2020-08-25 Safran Aircraft Engines Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region
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
EP3216983A1 (de) * 2016-03-08 2017-09-13 Siemens Aktiengesellschaft Laufschaufel für eine gasturbine mit gekühlter anstreifkante
US11136892B2 (en) 2016-03-08 2021-10-05 Siemens Energy Global GmbH & Co. KG Rotor blade for a gas turbine with a cooled sweep edge
WO2019035800A1 (en) * 2017-08-14 2019-02-21 Siemens Aktiengesellschaft AUBES OF TURBINE
EP3882436A1 (de) * 2020-03-20 2021-09-22 General Electric Company Laufschaufel für eine strömungsmaschine und zugehörige strömungsmaschine
EP4130429A3 (de) * 2021-08-06 2023-04-12 Raytheon Technologies Corporation Schaufelspitzenanordnung für ein gasturbinentriebwerk
US11913353B2 (en) 2021-08-06 2024-02-27 Rtx Corporation Airfoil tip arrangement for gas turbine engine

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Publication number Publication date
JP4889123B2 (ja) 2012-03-07
RU2457335C2 (ru) 2012-07-27
CA2606072A1 (fr) 2008-04-13
DE602007001652D1 (de) 2009-09-03
RU2007138000A (ru) 2009-04-20
JP2008095695A (ja) 2008-04-24
CA2606072C (fr) 2015-03-31
FR2907157A1 (fr) 2008-04-18
US20080175716A1 (en) 2008-07-24
US7972115B2 (en) 2011-07-05
EP1911934B1 (de) 2009-07-22

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