EP1254301A2 - Ensemble aubes de turbine - Google Patents

Ensemble aubes de turbine

Info

Publication number
EP1254301A2
EP1254301A2 EP01905702A EP01905702A EP1254301A2 EP 1254301 A2 EP1254301 A2 EP 1254301A2 EP 01905702 A EP01905702 A EP 01905702A EP 01905702 A EP01905702 A EP 01905702A EP 1254301 A2 EP1254301 A2 EP 1254301A2
Authority
EP
European Patent Office
Prior art keywords
holding
turbine
rail
platform
partner
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Withdrawn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
EP01905702A
Other languages
German (de)
English (en)
Inventor
Peter Tiemann
Michael Strassberger
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP01905702A priority Critical patent/EP1254301A2/fr
Publication of EP1254301A2 publication Critical patent/EP1254301A2/fr
Withdrawn legal-status Critical Current

Links

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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • the invention relates to a turbine blade vane with blades arranged at predetermined distances over an outer periphery of a turbine disk, each having a blade root that is radially form-fitting in each groove of the outer periphery of the turbine disk, and each having a blade profile that is attached to a blade - the end area on the side has a platform.
  • the blade profiles of the Turbmenla ⁇ fscna ⁇ u.- are usually lengthened in order to achieve a better utilization of the pre-flowing hot working fluid or e, l v performance. This extension of the scraper prof is limited by several parameters.
  • the object is achieved in that at least a part of the platform is connected to the turbine disk by means of a holder which is independent of the blade root.
  • the load redistribution mg thus initiates the turbo screed evenly and the feet of the blades and the grooves into which the feet are inserted are relieved of excessive stresses which impair the strength of the areas, which is particularly important in the area of the foot section which is intended as a circle around the hub and runs through the lowest groove areas, since m
  • the narrow design also results in a further weight saving.
  • the profiles of the blades can thus be extended without or - depending on the strength of the request - with only a slight increase in the local loads on the disk grooves or blade feet. So the efficiency of the turbine, can be increased without adversely affecting the strength of the disc and blades.
  • the blades with the blade profiles and the separately attached platform parts are not so easily exposed to critical vibrations for the blade attachment or the vibrations are more easily vaporized than in the case of a one-piece design of the blade.
  • the shovel and the platform part can be produced separately with much less effort.
  • the manufacture of the casting mold and the exact casting execution are simplified, since the turbine blade has almost no cantilever component without the molded platform.
  • the isolated platform part has a simple geometric shape, generally plate-shaped and can therefore be produced with little effort.
  • different materials can be used for the bucket and the platform part become. This can save weight, material and processing costs if a lighter alloy is used.
  • a uniform distribution of the attacking centrifugal forces over the circumference of the turbine disk is achieved in that an integral platform part is used as the platform part of two adjacent rotor blades and the holder is arranged approximately in the middle between the two adjacent rotor blades.
  • the stress peaks which arise in particular below the lowest toothing of the groove ⁇ urcn d_e rche centrifugal force loading, are thereby reduced to a greater extent.
  • the largest possible proportion of the area of the platform part is achieved in that the platform part is inserted between the end regions of two adjacent blade profiles in such a way that it virtually completely replaces the platforms. Almost all of the platform masses are thus carried by the holder and do not strain the feet or the grooves in which the feet are inserted. An optimal mass distribution on the foot and holder is thus achieved.
  • a lot of material and thus weight is saved compared to a one-piece design, since it is no longer necessary to absorb the lever forces that occur due to the large platform part.
  • a large saving of material is also possible by the fact that the edges of the platform part adjacent to the scoop profiles are shaped to match the curvature of the scoop profiles.
  • the production is simplified since a slim shape of the blade is now also in the transition area between see foot and profile is present, which is much easier to cast.
  • a stable and flexible adaptation of the holder to the platform part and the turbine disk is provided in that the holder consists of at least a pair of mutually engaging holding partners, at least one connecting element having a holding partner being formed separately from the platform part and from the turbine disk.
  • the platform part can be attached to the turbine disc by the separate design of the holding partner with different methods and easily replaceable.
  • different material combinations are possible in this way between the parts.
  • the Mate can rial a separately formed member and the platform ⁇ sepa rat formed hold Partners, as well as the Turoinenscneibe and the blade may be different requirements and taking into account the respective Au and strains are selected cost-optimized.
  • the bracket can be easily removed and also removed in the event of a possible corrosion attack with little effort if the holding partner is connected to the platform part and the turbine disk with play.
  • the holder is better suited to react flexibly and to adjust the corresponding force more easily, thereby avoiding damage to the holder and the associated positive locking means as well as the platform part and the turbine disk.
  • a simple attachment is provided in that em holding partners em ⁇ clutch Long proceeds in a straight line and having ei ⁇ NEN rail-like cross-section and the other holding a partner of the pairing straight proceeds In parallel to the first holding partner and having a rail-like cross-section of the first holding Partners comprehensive under positive engagement cross-section ,
  • By the rail-like design of the holding part ⁇ ner over the entire clutch Long great support and contact surfaces are given and thus a good force distribution over the entire range of the coupling. Local stress peaks due to the attacking centrifugal forces are thus reduced.
  • the platform part is curved, the platform part sits very reliably on the turbine disk due to the rail-like holding partner.
  • a secure hold is given when a rail-like holding partner is connected to the platform part and a rail-like holding partner is connected to the turbine disk and both holding partners are connected by a connecting element to two holding partners, the connecting element having an H-shaped cross-section encompassing the rail-shaped cross sections ,
  • the holding partners are on a large area. positively connected.
  • the connection is simple to make and easy to loosen again. Due to the rail-like configurations of the holding partners, the connecting element with the H-shaped cross section can be easily inserted and pulled out between the platform part and the turbine disk. Since no holding partner has a complex shape, they can be produced with little effort and at low cost.
  • a very stable support is given when it is constructed so that the turbine wheel has a rail-like holding partner and the platform member comprises a scnienenumfas- send holding partner and the two are dung element connected by e Verbm ⁇ , which has a rail comprising holding partner and a rail-like holding partner.
  • exemplary embodiments of the invention are gege ⁇ ben. Show it:
  • FIG. 1 shows a perspective, schematic view of a turbine blade arrangement with a holder, FIG. 2 em connecting element,
  • FIG. 3 shows a side view of a holder
  • FIG. 4 shows a schematic distribution of forces, shown in a side view of the turbine blade arrangement.
  • Fig.l shows a perspective view of a turbo-blade arrangement.
  • a turbo scan or the like 3 With a hot working fluid flowing through the turbine, in particular hot gas in a gas turbine, which flows against a blade profile 5, a turbo scan or the like 3 with a rotary knob 4 is driven in order to rotate and a turbomachine 24.
  • the Laufscnaufein 4 are with fir tree-shaped feet 8 m grooves 9 with a distance 1 in the outer circumference? the Turbmenscneibe 3 inserted by side insertion.
  • the rotor blades 3 are loaded by an outwardly directed centrifugal force due to rotary movements of the turbine disk 3.
  • This centrifugal force is taken by the base 8 of the rotor blade 4 and the claws 25 of the turbine disk 3 by means of various teeth 17, 18, 19, 21, 22, 23, which are shaped like a fir tree on the base 8 and find their corresponding formations on the claw 25, on.
  • the bottom foot teeth 17 on both sides of the foot 8, which are held by the bottom jaw teeth 21 of the claws 25, and middle foot teeth 18 on both sides of the foot 8, which engage behind the corresponding middle jaw teeth 22, and the top foot tooth are shown as examples 19, which are closest to the surface of the turbine disk 3 and engage behind the uppermost claw teeth 23. Starting from the lower foot tooth 17 to the uppermost foot tooth 19 m, the foot 8 becomes increasingly thicker in diameter 26.
  • the centrifugal forces generated by the rotation of the disc 3 and the rotor blades 4 attached to it can be absorbed.
  • the lowermost teeth 17 receiving recesses 17 m of the claw 25, due to the strong local forces acting there, in particular in the area of a root cut 33 along the lowermost ends of the grooves 9, represent a limitation for an enlargement of the rotor blades 4 countered by em 10 part of the platform by a bracket 11 is connected to the turbine disk 3 to resist centrifugal stress.
  • a platform like the platform part 10 present here, is generally used to protect the foot area against emitting zen by flowing Aroeitsfluid, in particular hot gas.
  • the platform part 10 is inserted separately between each two blades 4.
  • the bracket 11 is in this
  • the rail-like holding partners 31 are each on the outer circumference 2 of the turbine disk 3, preferably in the middle between two grooves 9 for the scooping feet 8, almost halfway between 1 and on the platform part 10 on the Turbine disc 3 facing underside 28 attached. Both rail-like holding partners 31 are parallel to one another and aligned one above the other in the radial direction. They are connected by the connection element 32, which has an H-shaped cross section, with holding partners 30, which consist of rounded recesses 13, into which the holding partners 31 are inserted.
  • the elements mentioned can be made from different, coordinated materials, in particular from a different material than the turbomachine 3, for example in order to save costs.
  • the holding partners 30, 31 and the connecting element 32 are preferably formed in one piece, so that the strong attacking forces cannot find a starting point for damage.
  • the turbine disk is made of special, hardened alloys that are only cut to a limited extent. can be machined and machined.
  • an integral production of the linear, rail-like holding partner 31 with the turbine disk 3 is also possible. This improves the hold of the holding partner 31 on the turbine disk 3, thereby reducing points of attack for damage due to the centrifugal load.
  • the platform part 10 has a curvature 15 on its two longer edges 20.
  • the curvatures of the anterior 20 on both sides do not necessarily have to match. They can be selected according to the shape of the turbine blade profile cross section.
  • a corresponding curvature 15 is found on the radius-affecting longitudinal section edges 29 of a cross section of the blade profiles 5 in the end region 6 of the rotor blades 4. In this way, the curved profile of the edges 29 also becomes em with respect to the cross-sectional area of the blade profile 5 in End area 6 optimized area portion of the platform part 10 reached. This significantly relieves the groove area.
  • damping wires 16 are placed on the underside 28 of the platform part.
  • the damping wires 16 are held in a 50 m position by a plurality of fastening knobs, as shown in FIG. 4.
  • the damping wires 16 seal a space between the platform and the turbine disk against the penetration of hot gases through the gap.
  • the damping wires dampen 16 vibrations in the area of the blade.
  • the damping wires 16 follow the curvature 15 of the platform part 10 and the moving blade 4. To make it easier to insert the damping wires 16, these are pre-bent.
  • the edges 20, 29 preferably have one Corresponding, constant curvature 15 so that the damping wires 16 previously provided with a bending radius corresponding to the curvature 15 can be easily inserted.
  • axial sealing plates 27 are placed on the end faces of the turbine disk 3, which preferably cover almost the largest part of the end disk area from the top edge to the bottom edge of the platform. This prevents working fluid, especially hot gas, from penetrating under the platforms and / or. prevents the platform parts 10 or to the feet, which would otherwise sparkle to stronglogies.
  • Fig.2 shows em connection element 32 with an H-shaped cross section.
  • the holding partners 30 forming the two yards of the H, FIG. 1, preferably run in a straight line and in the form of rounded recesses 13 in the coupling area 14, which simplifies the manufacture of the elements.
  • the connection element 32 has the same shape and dimensions over its entire cross-section. In this way it can be used from both sides of the turbo disk.
  • the platform part 10 has a holding partner 30 encompassing the rail shape
  • the turbine disk 3 as in the first example, has a rail-like holding partner 31.
  • the connecting element 32 now has in each case a rail-like holding partner 31 and a holding partner 30 encompassing the rail. The connecting element 32 can easily be inserted between the platform part 10 and the turbine disk 3.
  • FIG. 4 shows a force distribution that arises due to the internal force load within a turbine disk 3 and the louvre 4 used, in which the mounting technology according to the invention is used.
  • the maximum notch stresses can be seen in the claw area, in particular below the claw tooth 21 in the area of the recesses 17 ' . he Fig.l.
  • a substantial part of the centrifugal force load is passed directly into the turbine disk 3 via the holder 11 and does not load the claw recesses 17 ' .
  • mean tensions and the tension peaks in the narrowest cross-sections or radii of the teeth in the claw area show tension values which are far below the values that were previously achievable.
  • the force distribution is thus smoothed by the load-optimized division of functional areas of the turbine blade arrangement. This allows an overall higher centrifugal force load, which is caused, for example, by lengthening the vane profile to improve the efficiency.
  • This extension can be carried out both outwards together with an enlargement of an outer turbine outlet cross section, and also inwards in the direction of the hub region of the turbine disk.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Ensemble aubes de turbine doté d'aubes mobiles (4) de turbines qui possèdent chacune un pied (8) pouvant être installé radialement par liaison de forme dans une rainure (9) située sur la circonférence externe (2) du disque (3) de turbine et qui possèdent un profil (5) doté latéralement d'une plate-forme dans une zone terminale (6) située côté disque. Selon la présente invention, au moins une partie (10) de la plate-forme est reliée au disque (3) par l'intermédiaire d'un élément de retenue (11) indépendant du pied (8) d'aube, ledit ensemble aubes de turbine étant ainsi conçu qu'il permet un allongement du profil des aubes mobiles.
EP01905702A 2000-02-09 2001-01-29 Ensemble aubes de turbine Withdrawn EP1254301A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP01905702A EP1254301A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP00102717 2000-02-09
EP00102717A EP1124038A1 (fr) 2000-02-09 2000-02-09 Aubage de turbine
EP01905702A EP1254301A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine
PCT/EP2001/000932 WO2001059263A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine

Publications (1)

Publication Number Publication Date
EP1254301A2 true EP1254301A2 (fr) 2002-11-06

Family

ID=8167814

Family Applications (2)

Application Number Title Priority Date Filing Date
EP00102717A Withdrawn EP1124038A1 (fr) 2000-02-09 2000-02-09 Aubage de turbine
EP01905702A Withdrawn EP1254301A2 (fr) 2000-02-09 2001-01-29 Ensemble aubes de turbine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP00102717A Withdrawn EP1124038A1 (fr) 2000-02-09 2000-02-09 Aubage de turbine

Country Status (5)

Country Link
US (1) US6726452B2 (fr)
EP (2) EP1124038A1 (fr)
JP (1) JP2003522872A (fr)
CN (1) CN1289789C (fr)
WO (1) WO2001059263A2 (fr)

Families Citing this family (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10134611A1 (de) * 2000-12-16 2002-06-27 Alstom Switzerland Ltd Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine
EP1319805A1 (fr) * 2001-12-17 2003-06-18 Techspace aero Rotor ou élément rotorique pour turbocompresseur
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US7300253B2 (en) * 2005-07-25 2007-11-27 Siemens Aktiengesellschaft Gas turbine blade or vane and platform element for a gas turbine blade or vane ring of a gas turbine, supporting structure for securing gas turbine blades or vanes arranged in a ring, gas turbine blade or vane ring and the use of a gas turbine blade or vane ring
JP4584102B2 (ja) 2005-09-30 2010-11-17 株式会社日立製作所 タービンロータと逆クリスマスツリー型タービン動翼及びそれを用いた低圧蒸気タービン並びに蒸気タービン発電プラント
US20070134094A1 (en) * 2005-12-08 2007-06-14 Stephen Gregory Rotor apparatus and turbine system incorporating same
EP1898049B1 (fr) 2006-09-11 2012-05-23 Siemens Aktiengesellschaft Aube de turbine
US7762781B1 (en) 2007-03-06 2010-07-27 Florida Turbine Technologies, Inc. Composite blade and platform assembly
FR2913735B1 (fr) * 2007-03-16 2013-04-19 Snecma Disque de rotor d'une turbomachine
FR2913734B1 (fr) * 2007-03-16 2009-05-01 Snecma Sa Soufflante de turbomachine
US7931442B1 (en) 2007-05-31 2011-04-26 Florida Turbine Technologies, Inc. Rotor blade assembly with de-coupled composite platform
GB0802834D0 (en) * 2008-02-18 2008-03-26 Rolls Royce Plc Annulus filler
US9662721B2 (en) * 2008-02-26 2017-05-30 United Technologies Corporation Method of generating a curved blade retention slot in a turbine disk
EP2098687A1 (fr) * 2008-03-07 2009-09-09 Siemens Aktiengesellschaft Rotor pour une turbomachine
GB0814718D0 (en) 2008-08-13 2008-09-17 Rolls Royce Plc Annulus filler
US8257045B2 (en) * 2008-08-15 2012-09-04 United Technologies Corp. Platforms with curved side edges and gas turbine engine systems involving such platforms
EP2157283A1 (fr) * 2008-08-18 2010-02-24 Siemens Aktiengesellschaft Fixation d'aube avec élément d'amortissement pour une turbomachine
GB2463036B (en) * 2008-08-29 2011-04-20 Rolls Royce Plc A blade arrangement
US8277190B2 (en) * 2009-03-27 2012-10-02 General Electric Company Turbomachine rotor assembly and method
GB0908422D0 (en) * 2009-05-18 2009-06-24 Rolls Royce Plc Annulus filler
GB0910752D0 (en) * 2009-06-23 2009-08-05 Rolls Royce Plc An annulus filler for a gas turbine engine
FR2949142B1 (fr) * 2009-08-11 2011-10-14 Snecma Cale amortisseuse de vibrations pour aube de soufflante
GB0914060D0 (en) * 2009-08-12 2009-09-16 Rolls Royce Plc A rotor assembly for a gas turbine
US8231354B2 (en) * 2009-12-15 2012-07-31 Siemens Energy, Inc. Turbine engine airfoil and platform assembly
US8496443B2 (en) * 2009-12-15 2013-07-30 Siemens Energy, Inc. Modular turbine airfoil and platform assembly with independent root teeth
GB0922422D0 (en) * 2009-12-23 2010-02-03 Rolls Royce Plc Annulus Filler Assembly for a Rotor of a Turbomachine
US8545184B2 (en) * 2010-01-05 2013-10-01 General Electric Company Locking spacer assembly
GB2478918B8 (en) * 2010-03-23 2013-06-19 Rolls Royce Plc Interstage seal
US8066479B2 (en) * 2010-04-05 2011-11-29 Pratt & Whitney Rocketdyne, Inc. Non-integral platform and damper for an airfoil
US8550785B2 (en) 2010-06-11 2013-10-08 Siemens Energy, Inc. Wire seal for metering of turbine blade cooling fluids
US8753090B2 (en) 2010-11-24 2014-06-17 Rolls-Royce Corporation Bladed disk assembly
US20120156045A1 (en) * 2010-12-17 2012-06-21 General Electric Company Methods, systems and apparatus relating to root and platform configurations for turbine rotor blades
KR101250643B1 (ko) * 2010-12-29 2013-04-03 현대중공업 주식회사 복합재료로 이루어진 프로펠러용 블레이드와 프로펠러 보스 연결 구조
CH704825A1 (de) * 2011-03-31 2012-10-15 Alstom Technology Ltd Turbomaschinenrotor.
US8689441B2 (en) 2011-12-07 2014-04-08 United Technologies Corporation Method for machining a slot in a turbine engine rotor disk
FR2987086B1 (fr) * 2012-02-22 2014-03-21 Snecma Joint lineaire de plateforme inter-aubes
FR2991372B1 (fr) * 2012-06-04 2014-05-16 Snecma Roue de turbine dans une turbomachine
US9399922B2 (en) 2012-12-31 2016-07-26 General Electric Company Non-integral fan blade platform
US9845699B2 (en) * 2013-03-15 2017-12-19 Gkn Aerospace Services Structures Corp. Fan spacer having unitary over molded feature
US10590798B2 (en) 2013-03-25 2020-03-17 United Technologies Corporation Non-integral blade and platform segment for rotor
US10539148B2 (en) 2013-10-11 2020-01-21 United Technologies Corporation Fan rotor with integrated platform attachment
GB201322668D0 (en) 2013-12-20 2014-02-05 Rolls Royce Deutschland & Co Kg Vibration Damper
US9856737B2 (en) * 2014-03-27 2018-01-02 United Technologies Corporation Blades and blade dampers for gas turbine engines
KR101833660B1 (ko) * 2014-04-03 2018-02-28 미츠비시 히타치 파워 시스템즈 가부시키가이샤 날개열, 가스터빈
US10156151B2 (en) 2014-10-23 2018-12-18 Rolls-Royce North American Technologies Inc. Composite annulus filler
FR3038344B1 (fr) * 2015-06-30 2017-08-04 Snecma Assemblage aubage utilisant un emboitement
FR3039854B1 (fr) * 2015-08-03 2019-08-16 Safran Aircraft Engines Carter intermediaire de turbomachine comportant des moyens de fixation ameliores
US10584592B2 (en) * 2015-11-23 2020-03-10 United Technologies Corporation Platform for an airfoil having bowed sidewalls
CN105909557A (zh) * 2016-06-21 2016-08-31 中国航空工业集团公司沈阳发动机设计研究所 一种风扇转子叶片安装结构
EP3293354B1 (fr) * 2016-09-07 2021-04-14 Ansaldo Energia IP UK Limited Élément d'aubage de turbomachine et procédé de montage d'un tel élément
US11021984B2 (en) * 2018-03-08 2021-06-01 Raytheon Technologies Corporation Gas turbine engine fan platform
CN109469513B (zh) * 2018-12-13 2020-10-27 西安交通大学 一种汽轮机及其错位排布的枞树型叶根轮缘槽结构
FR3109403B1 (fr) * 2020-04-16 2022-08-12 Safran Aircraft Engines Aube avec organes d’étanchéités améliorés
CN113623020B (zh) * 2021-08-02 2022-07-08 无锡友鹏航空装备科技有限公司 一种密封性高的涡轮导向装置
US12352174B2 (en) * 2023-02-10 2025-07-08 General Electric Company Fan retention member for supporting a blade platform of a fan assembly
US12352175B2 (en) * 2023-07-04 2025-07-08 Rolls-Royce Plc Annulus filler for a gas turbine engine
US12473863B2 (en) 2024-03-13 2025-11-18 General Electric Company Gas turbine engine having composite fan blades
US12510104B2 (en) 2024-06-14 2025-12-30 General Electric Company Gas turbine engine with acoustic spacing of the fan blades and outlet guide vanes
US12546229B1 (en) * 2024-12-30 2026-02-10 Pratt & Whitney Canada Corp. Gas turbine engine rotor stage with seal members

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE169601C (fr) *
GB811922A (en) * 1955-03-10 1959-04-15 Rolls Royce Improvements relating to bladed rotors of axial flow fluid machines
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
GB2006883B (en) * 1977-10-27 1982-02-24 Rolls Royce Fan or compressor stage for a gas turbine engine
US4621979A (en) * 1979-11-30 1986-11-11 United Technologies Corporation Fan rotor blades of turbofan engines
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines
GB2186639B (en) * 1986-02-19 1989-11-01 Rolls Royce Improvements in or relating to bladed structures for fluid flow propulsion engines
FR2608674B1 (fr) * 1986-12-17 1991-04-19 Snecma Roue de turbine a aubes ceramique
US5156528A (en) * 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
FR2716502B1 (fr) * 1994-02-23 1996-04-05 Snecma Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
GB9602129D0 (en) * 1996-02-02 1996-04-03 Rolls Royce Plc Rotors for gas turbine engines
JP2000008804A (ja) * 1998-06-25 2000-01-11 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンのタービン動翼防振装置

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0159263A3 *

Also Published As

Publication number Publication date
US6726452B2 (en) 2004-04-27
EP1124038A1 (fr) 2001-08-16
US20030012654A1 (en) 2003-01-16
JP2003522872A (ja) 2003-07-29
CN1398322A (zh) 2003-02-19
CN1289789C (zh) 2006-12-13
WO2001059263A3 (fr) 2002-09-19
WO2001059263A2 (fr) 2001-08-16

Similar Documents

Publication Publication Date Title
WO2001059263A2 (fr) Ensemble aubes de turbine
EP0699824B1 (fr) Dispositif pour le verrouillage d'aubes de rotor et pour l'élimination du déséquilibre du rotor de compresseurs ou turbines de turbines à gaz
EP2320030B1 (fr) Rotor et aube de rotor pour une turbomachine axiale
EP0203287B1 (fr) Elément supprimant les vibrations des aubes de turbomachines
EP1944472A1 (fr) Partie axiale d'un rotor de turbine, élément d'étanchéité pour un rotor équipé d'aubes de rotor d'une turbine et rotor de turbine
DE3527122A1 (de) Schaufel und beschaufelte scheibenbaugruppe fuer ein gasturbinentriebwerk
WO2004111392A1 (fr) Turbine à gaz et aube
EP1413712A1 (fr) Virole pour une turbine avec joint d'extrémité
DE1016982B (de) Laeufer mit Kuehleinrichtung fuer mit gasfoermigen Arbeitsmitteln betriebene Stroemungsmaschinen, insbesondere Gasturbinen
DE2841131A1 (de) Rotor fuer gasturbinentriebwerk
DE2514050C2 (de) Verriegelung von am Rotorkörper von Turbomaschinen angebrachten Schaufeln
CN88100914A (zh) 减小汽轮机中叶片抖振的装置和方法
EP2617945B1 (fr) Rotor pour une turbomachine et procédé de fabrication
DE10120532A1 (de) Vorrichtung und Verfahren zur Befestigung einer Laufschaufel längs einer innerhalb eines Rotors einer axial durchströmten Turbomaschine verlaufenden Umfangsnut
EP1215367A2 (fr) Dispositif de fixation des aubes de turbomachine
DE19654471B4 (de) Rotor einer Strömungsmaschine
DE2944987B2 (de) Laufschaufel für Dampfturbinen
DE69525014T2 (de) Abdeckstück zur Abdichtung des Raums zwischen Rotorstufen
DE102009007664A1 (de) Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine
EP2807342A1 (fr) Aube de turbine modulaire à plate-forme
EP1910647A1 (fr) Element de fixation d'aubes mobiles
CH666722A5 (de) Laufschaufelkranz einer axial durchstroemten turbomaschine.
EP1905954A1 (fr) Aube de turbine
DE19823157A1 (de) Einrichtung zur Befestigung der Laufschaufeln axial durchströmter Turbomaschinen
WO2009100795A1 (fr) Aube mobile pour une 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

17P Request for examination filed

Effective date: 20020628

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

RBV Designated contracting states (corrected)

Designated state(s): CH DE FR GB IT LI

17Q First examination report despatched

Effective date: 20040705

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: 20041116