EP2653658A1 - Stator pour une turbomachine axiale et procédé de dimensionnement du stator - Google Patents

Stator pour une turbomachine axiale et procédé de dimensionnement du stator Download PDF

Info

Publication number
EP2653658A1
EP2653658A1 EP12164299.5A EP12164299A EP2653658A1 EP 2653658 A1 EP2653658 A1 EP 2653658A1 EP 12164299 A EP12164299 A EP 12164299A EP 2653658 A1 EP2653658 A1 EP 2653658A1
Authority
EP
European Patent Office
Prior art keywords
axial flow
flow machine
vane
blades
guide
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.)
Withdrawn
Application number
EP12164299.5A
Other languages
German (de)
English (en)
Inventor
Christoph Hermann Dr. Richter
Heinrich Dr. Stüer
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP12164299.5A priority Critical patent/EP2653658A1/fr
Priority to CN201380020389.XA priority patent/CN104246137B/zh
Priority to US14/391,876 priority patent/US9951648B2/en
Priority to JP2015506171A priority patent/JP6165841B2/ja
Priority to EP13717223.5A priority patent/EP2805017B1/fr
Priority to PL13717223T priority patent/PL2805017T3/pl
Priority to IN7604DEN2014 priority patent/IN2014DN07604A/en
Priority to PCT/EP2013/057170 priority patent/WO2013156322A1/fr
Publication of EP2653658A1 publication Critical patent/EP2653658A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/10—Anti- vibration means
    • 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
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F05D2230/00—Manufacture
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a vane ring for an axial flow machine, the axial flow machine and a method for laying out the vane ring.
  • the steam turbine has a plurality of stages, each stage having a stator vane having a plurality of vanes and a rotor having a plurality of blades.
  • the blades are mounted on the shaft of the steam turbine and rotate during operation of the steam turbine, the vanes are mounted on the housing of the steam turbine and are fixed.
  • the blades can be excited to vibrate during operation of the steam turbine.
  • the oscillation is characterized in that a vibration node is arranged at the blade roots of the blades. The stress caused by the vibration is high, in particular at the blade roots, so that material fatigue can occur at the blade roots, which necessitates a cost-intensive replacement of the guide blades.
  • a flow channel is formed through which the steam flows during operation of the steam turbine.
  • the velocity distribution of the flow downstream of the vane ring has local velocity minima in the region of the trailing edges of the guide vanes, which are referred to as trailing dents.
  • the follower dents can excite the blades disposed downstream of the vane ring to vibrate.
  • the invention has the object of providing a stage for an axial turbomachine, the axial turbomachine with the stage and to provide a method of laying out the step, wherein the above problems are overcome and the blades of the stage have a long life.
  • Each vane is composed of the profile sections, each profile section being assigned a threading point and all profile sections having their threading points "threaded" onto a threading line. According to the invention, there is a displacement of the at least one profile section, so that the threading point of the at least one profile section no longer lies on the original threading line.
  • the pitch angle is the angle between two connecting lines that extend from a common point on the axis of the axial flow machine and are perpendicular to the axis and terminate at corresponding points on the surfaces of the two adjacent vanes.
  • the two corresponding points are two points that are the same radial distance from the axis of the Axialströmungsmaschine have and in each case at the same points of the guide vanes, that is, for example, a point either on the pressure side, on the suction side, on the leading edge or on the trailing edge of the respective vane, are arranged.
  • the pitch angle is the nominal pitch angle 2 * II / n, with the circle number ⁇ and n of the number of vanes arranged in the vane ring.
  • the blades may be exposed to two different vibrational excitation mechanisms, namely, flutter and forced-response.
  • Fluttering is a self-excited vibration in which energy is transferred from the flow to the vibrations of the blades.
  • the flutter is excited by small blade vibrations, which may be self-energizing, so that the blade vibrates more with each successive oscillation period. This can lead to a demolition of the blades.
  • By varying the pitch angle, with two adjacent channels another flow deflection angle results, whereby the inflow from the blade ring to the blade ring is irregular over the circumference of the axial flow machine. As a result, the load on the blades changes during one revolution, whereby the flutter is advantageously reduced.
  • the forced oscillation results from periodic excitation of the blades.
  • a channel is respectively arranged, through which a fluid of the axial flow machine can be flowed.
  • the trailing shafts assigned to the two channels have a different shape and circumferential position as a result of the changing pitch angle.
  • the downstream blades submerge in the trailing shafts, whereby the blades undergo a transient flow, which leads to a vibration excitation of Can guide blades. Due to the fact that the trailing shafts are inhomogenized over the circumference, the oscillation excitation takes place unperiodically, as a result of which the forced vibrations of the rotor blades are likewise advantageously weak.
  • the displacement of the at least one profile section is preferably carried out on a displacement path, which amounts to a maximum of 10% of the extent of the channel between the two guide vanes in the circumferential direction for each of the two adjacently arranged guide vanes.
  • the profile cuts are preferably shifted in such a way that the guide blade is inclined against a guide blade arranged adjacent to it. In this case, the pitch angle varies linearly over the blade height.
  • the profile sections are preferably displaced in such a way that at least one of two adjacently arranged guide vanes is curved.
  • the pitch angle varies non-linearly over the blade height.
  • the guide vanes, in which profile sections are shifted, are preferably arranged distributed symmetrically about the axis of the axial flow machine. Thus, the downstream flow from the vane ring is symmetrical.
  • the blades are preferably designed such that none of the natural frequencies of the blades match the rotational frequency of the axial flow machine or a multiple of the rotational frequency up to and including eight times the rotational frequency.
  • the coupling can lead to an increase in an energy input from the flow into the vibrations.
  • the profile sections on a cylindrical surface or a conical surface whose axes coincide with the axis of the axial flow machine are preferably located on an S 1 flow area or in a tangential plane of the axial flow machine.
  • the S 1 flow area extends in the circumferential direction and in the axial direction of the axial flow machine and describes a surface that follows an idealized flow.
  • the method preferably has the step of: adapting the at least one profile section to the aerodynamic boundary conditions changed after shifting.
  • the stage according to the invention is designed with the method according to the invention.
  • the axial flow machine according to the invention comprises the step, in particular as the last, downstream stage of the axial flow machine.
  • the blades in the last stage of the axial flow machine are the blades with the longest radial extensions in the axial flow machine and are thus particularly susceptible to vibration excitation. An unperiodic vibration excitation of the blades is thus advantageous, especially in the last stage.
  • an axial flow machine 1 has a vane ring 2 and a housing 7.
  • the vane ring 2 has a plurality of guide vanes 3, 4, wherein each of the guide vanes 3, 4 has a blade root 5, a blade tip 6, a pressure side 9 and a suction side 10.
  • Each of the vanes 3, 4 is with its blade tip 6 on the housing and with her Blade foot 5 fixedly attached to a hub ring 8.
  • a channel 14 is formed, in which a working fluid is flowable. Is shown in FIGS. 1 to 3 in each case the trailing edge of the guide vanes 3, 4.
  • FIG. 3 For example, a pitch angle 13 of the axial flow machine 1 is shown.
  • a surface point 15 is respectively shown on the trailing edges of the guide vanes 3, 4.
  • the two surface points 15 have the same distance from the axis 11 of the axial flow machine 1
  • FIG. 3 two connecting lines 16 are shown, each starting from the two surface points 15, perpendicular to the axis 11 of the axial flow machine 1 and each end at the same point on the axis 11 of the axial flow machine 1.
  • the two connecting lines 16 include the pitch angle 13.
  • FIGS. 1 to 3 the vane ring 2 is shown prior to a displacement of at least one profile section and after moving the at least one profile section. Shown are in the FIGS. 1 to 3 Guide vanes 3 before moving (solid lines) and vanes 4 after moving (dashed lines).
  • the vanes 3 are characterized in that they have the same pitch angle 13 for each vane 3 and for each surface point 15, namely the nominal pitch angle 12.
  • the nominal pitch angle 12 is 2 * ⁇ / n, where n is the number of vanes 3 in FIG the vane ring 2 and ⁇ is the circle number.
  • the profile sections are shifted in such a way that the guide vanes 4 are inclined in comparison to the guide vanes 3.
  • the guide vane ring 2 after shifting each have the same pairs of adjacently arranged guide vanes 4.
  • the pairs are characterized in that the blade root 5 of the one vane 4 of the pair in a circumferential direction of the vane ring 2 and the blade tip 6 is displaced in the other circumferential direction, which is directed counter to a circumferential direction.
  • the other vane 4 of the pair is inclined against the one vane 4 of the pair, ie the vane root 5 of the other vane 4 of the pair is displaced in the other circumferential direction and the vane tip 6 of the other vane 4 is displaced in the one circumferential direction.
  • the vane ring 2 off FIG. 2 also has pairs of vanes 4.
  • the vanes 4 of the pairs are curved such that the vanes 4 have a belly.
  • a guide vane 4 of the pair has a belly in one circumferential direction and the other vane 4 of the pair has a belly in the other circumferential direction.
  • the guide vanes 4 have a plurality of bellies, which are arranged either on the same side of the guide vanes 3 in the circumferential direction or on both sides of the guide vanes 4 in the circumferential direction.
  • the pitch angle 13 varies non-linearly across the blade height.
  • the vane ring 2 completely formed from the pairs and also here it is conceivable that between two pairs one or a plurality of Guide vanes 3 is arranged. It is also conceivable that alternately a curved running vane 4 and a stator blade 3 are arranged.
  • every other of the vanes 3, 4 in the vane ring 2 is inclined relative to the respective vanes 3.
  • the thus inclined guide vanes 4 are alternately shifted with their blade roots 5 in the one circumferential direction respectively in the other circumferential direction and with their blade tips 6 alternately in the other circumferential direction respectively in the one circumferential direction.
  • the deviations of the guide vanes 4 relative to the guide vanes 3 a maximum of 10% of the available extent of the channels 14 in the circumferential direction.
  • the deviations are obtained by displacing profile sections of the guide vanes 3 in the circumferential direction.
  • the profile sections of the guide vanes 3 can lie on a cylinder surface or conical surface symmetrical about the axis 11, in a tangential plane of the axial flow machine 1 or on an S 1 flow surface.
  • FIG. 4 a longitudinal section through the axial flow machine 1 with a main flow direction 21 and with the stage 22 according to the invention is shown.
  • the step 22 includes the vane ring 2 and a blade ring 20 disposed downstream of the vane ring 2. Shown are each a vane 18 and a blade 19. Also shown is a hub 17 which rotates about the axis 11 during operation of the axial flow machine 1. The vane 18 is attached to the housing 7, the blade 19 to the hub 17.
  • a flow with an inhomogeneous velocity distribution is formed downstream of the vane ring 2.
  • the load of the blades 19 changes during one revolution, whereby a flutter of the blades 19 is advantageously reduced.
  • the method for laying out a step 22 for an axial flow machine 1 comprising a vane ring 2 and a rotor blade 20 arranged downstream of the vane ring 2 is preferably carried out as follows:

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12164299.5A 2012-04-16 2012-04-16 Stator pour une turbomachine axiale et procédé de dimensionnement du stator Withdrawn EP2653658A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP12164299.5A EP2653658A1 (fr) 2012-04-16 2012-04-16 Stator pour une turbomachine axiale et procédé de dimensionnement du stator
CN201380020389.XA CN104246137B (zh) 2012-04-16 2013-04-05 用于轴流式流体机械的导向叶片环和用于设计导向叶片环的方法
US14/391,876 US9951648B2 (en) 2012-04-16 2013-04-05 Guide blade ring for an axial turbomachine and method for designing the guide blade ring
JP2015506171A JP6165841B2 (ja) 2012-04-16 2013-04-05 軸流流体機械のための静翼リングおよび静翼リングの設計法
EP13717223.5A EP2805017B1 (fr) 2012-04-16 2013-04-05 Stator pour une turbomachine axiale et procédé de dimensionnement du stator
PL13717223T PL2805017T3 (pl) 2012-04-16 2013-04-05 Wieniec łopatek kierowniczych do osiowej maszyny przepływowej i sposób wykonania wieńca łopatek kierowniczych
IN7604DEN2014 IN2014DN07604A (fr) 2012-04-16 2013-04-05
PCT/EP2013/057170 WO2013156322A1 (fr) 2012-04-16 2013-04-05 Couronne d'aubes directrices destinée à une turbomachine axiale et procédé de conception de la couronne d'aubes directrices

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12164299.5A EP2653658A1 (fr) 2012-04-16 2012-04-16 Stator pour une turbomachine axiale et procédé de dimensionnement du stator

Publications (1)

Publication Number Publication Date
EP2653658A1 true EP2653658A1 (fr) 2013-10-23

Family

ID=48141941

Family Applications (2)

Application Number Title Priority Date Filing Date
EP12164299.5A Withdrawn EP2653658A1 (fr) 2012-04-16 2012-04-16 Stator pour une turbomachine axiale et procédé de dimensionnement du stator
EP13717223.5A Not-in-force EP2805017B1 (fr) 2012-04-16 2013-04-05 Stator pour une turbomachine axiale et procédé de dimensionnement du stator

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP13717223.5A Not-in-force EP2805017B1 (fr) 2012-04-16 2013-04-05 Stator pour une turbomachine axiale et procédé de dimensionnement du stator

Country Status (7)

Country Link
US (1) US9951648B2 (fr)
EP (2) EP2653658A1 (fr)
JP (1) JP6165841B2 (fr)
CN (1) CN104246137B (fr)
IN (1) IN2014DN07604A (fr)
PL (1) PL2805017T3 (fr)
WO (1) WO2013156322A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2775097A3 (fr) * 2013-03-04 2017-06-21 Rolls-Royce plc Rangée d'aubes de stator

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITTO20110728A1 (it) * 2011-08-04 2013-02-05 Avio Spa Segmento palettato statorico di una turbina a gas per motori aeronautici
ITTO20120517A1 (it) * 2012-06-14 2013-12-15 Avio Spa Schiera di profili aerodinamici per un impianto di turbina a gas
US20180094833A1 (en) * 2016-09-30 2018-04-05 Haier Us Appliance Solutions, Inc. Water heater appliance
GB2574493A (en) * 2019-01-22 2019-12-11 Rolls Royce Plc Stacking of rotor blade aerofoil sections to adjust resonant frequencies

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4253800A (en) * 1978-08-12 1981-03-03 Hitachi, Ltd. Wheel or rotor with a plurality of blades
US20020064458A1 (en) * 2000-11-30 2002-05-30 Matthew Montgomery Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability
US20090169371A1 (en) * 2005-11-29 2009-07-02 Ishikawajima-Harima Heavy Industries Co., Ltd. Stator cascade of turbo type fluid machine
US20100247310A1 (en) * 2009-03-26 2010-09-30 Frank Kelly Intentionally mistuned integrally bladed rotor
DE102009033618A1 (de) * 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3883264A (en) * 1971-04-08 1975-05-13 Gadicherla V R Rao Quiet fan with non-radial elements
JPH0126068Y2 (fr) 1980-12-11 1989-08-03
JPH0211802U (fr) 1988-07-04 1990-01-25
JPH02118102U (fr) * 1989-03-09 1990-09-21
US5167489A (en) * 1991-04-15 1992-12-01 General Electric Company Forward swept rotor blade
GB9210421D0 (en) * 1992-05-15 1992-07-01 Gec Alsthom Ltd Turbine blade assembly
JP3132944B2 (ja) * 1993-03-17 2001-02-05 三菱重工業株式会社 ３次元設計タービン翼
JPH0861002A (ja) * 1994-08-24 1996-03-05 Mitsubishi Heavy Ind Ltd 蒸気タービンのダイヤフラム
JPH10184304A (ja) * 1996-12-27 1998-07-14 Toshiba Corp 軸流タービンのタービンノズルおよびタービン動翼
JP2000045704A (ja) 1998-07-31 2000-02-15 Toshiba Corp 蒸気タービン
JP2000328902A (ja) * 1999-05-19 2000-11-28 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンエンジン
JP4373629B2 (ja) 2001-08-31 2009-11-25 株式会社東芝 軸流タービン
JP2004100553A (ja) * 2002-09-09 2004-04-02 Mitsubishi Heavy Ind Ltd 回転機械の静翼構造
CN1828024A (zh) * 2005-03-04 2006-09-06 徐大懋 提高能量转换效率的叶轮机械叶片设计方法
US7758306B2 (en) * 2006-12-22 2010-07-20 General Electric Company Turbine assembly for a gas turbine engine and method of manufacturing the same
US8678752B2 (en) * 2010-10-20 2014-03-25 General Electric Company Rotary machine having non-uniform blade and vane spacing
US20130094942A1 (en) * 2011-10-12 2013-04-18 Raymond Angus MacKay Non-uniform variable vanes
GB201303767D0 (en) * 2013-03-04 2013-04-17 Rolls Royce Plc Stator Vane Row

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4253800A (en) * 1978-08-12 1981-03-03 Hitachi, Ltd. Wheel or rotor with a plurality of blades
US20020064458A1 (en) * 2000-11-30 2002-05-30 Matthew Montgomery Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability
US20090169371A1 (en) * 2005-11-29 2009-07-02 Ishikawajima-Harima Heavy Industries Co., Ltd. Stator cascade of turbo type fluid machine
US20100247310A1 (en) * 2009-03-26 2010-09-30 Frank Kelly Intentionally mistuned integrally bladed rotor
DE102009033618A1 (de) * 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2775097A3 (fr) * 2013-03-04 2017-06-21 Rolls-Royce plc Rangée d'aubes de stator

Also Published As

Publication number Publication date
US9951648B2 (en) 2018-04-24
JP6165841B2 (ja) 2017-07-19
EP2805017A1 (fr) 2014-11-26
WO2013156322A1 (fr) 2013-10-24
EP2805017B1 (fr) 2016-06-22
US20150063985A1 (en) 2015-03-05
CN104246137A (zh) 2014-12-24
PL2805017T3 (pl) 2017-04-28
IN2014DN07604A (fr) 2015-05-15
CN104246137B (zh) 2016-07-06
JP2015519501A (ja) 2015-07-09

Similar Documents

Publication Publication Date Title
EP2805017B1 (fr) Stator pour une turbomachine axiale et procédé de dimensionnement du stator
EP2993357B1 (fr) Étage de compresseur radial
DE10359917A1 (de) Verfahren und Vorrichtung zum Abstimmen der Eigenfrequenz von Turbinenlaufschaufeln
DE102007037924A1 (de) Strömungsarbeitsmaschine mit Ringkanalwandausnehmung
WO1998044240A1 (fr) Structure superficielle pour la paroi d'un canal d'ecoulement ou d'une aube de turbine
EP2921716B1 (fr) Groupe de série d'aubes
EP2725193B1 (fr) Méthode pour désaccorder les aubes d'un moteur de turbine à gas et moteur de turbine à gas correspondant.
EP2478186B1 (fr) Rotor de turbomachine
EP2921714A1 (fr) Groupe de série d'aubes
EP3199758B1 (fr) Rotor dans une turbine à gaz de type blisk (disque à aubes) ou bling (bague à aubes)
DE102014114916A1 (de) Turbinenschaufelblatt mit Spitzenausrundung
EP2993356A1 (fr) Étage de compresseur radial
EP3404210A1 (fr) Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés
EP3428393B1 (fr) Roue aubagée d'une turbomachine
EP2746533A1 (fr) Grille d'aube et turbomachine
EP3064706A1 (fr) Rangée d'aubes directrices pour une turbomachine traversée axialement
EP3078804A1 (fr) Agencement virole pour une rangée d'aubes de rotor ou stator et turbine associée
WO2017178203A1 (fr) Aube de turbine, dispositif associé, turbomachine et utilisation
EP3388626B1 (fr) Contournage d'une plate-forme de grille d'aube
EP2410131B1 (fr) Rotor d'une turbomachine
EP2607625A1 (fr) Turbomachine et étage de turbomachine
WO2011026468A2 (fr) Turbomachine et procédé de production d'un revêtement de rodage structuré
EP3498972B1 (fr) Module de turbine pour une turbomachine
DE102014203604A1 (de) Schaufelreihengruppe
WO2018069552A1 (fr) Ensemble turbomachine coulé intégralement et procédé de fabrication d'un ensemble turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20140424