WO2001059263A2 - Turbinenschaufelanordnung - Google Patents
Turbinenschaufelanordnung Download PDFInfo
- Publication number
- WO2001059263A2 WO2001059263A2 PCT/EP2001/000932 EP0100932W WO0159263A2 WO 2001059263 A2 WO2001059263 A2 WO 2001059263A2 EP 0100932 W EP0100932 W EP 0100932W WO 0159263 A2 WO0159263 A2 WO 0159263A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- holding
- turbine
- rail
- platform
- partner
- Prior art date
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
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP01905702A EP1254301A2 (de) | 2000-02-09 | 2001-01-29 | Turbinenschaufelanordnung |
US10/203,388 US6726452B2 (en) | 2000-02-09 | 2001-01-29 | Turbine blade arrangement |
JP2001558580A JP2003522872A (ja) | 2000-02-09 | 2001-01-29 | タービン翼配置構造 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00102717A EP1124038A1 (de) | 2000-02-09 | 2000-02-09 | Turbinenschaufelanordnung |
EP00102717.6 | 2000-02-09 |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2001059263A2 true WO2001059263A2 (de) | 2001-08-16 |
WO2001059263A3 WO2001059263A3 (de) | 2002-09-19 |
Family
ID=8167814
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2001/000932 WO2001059263A2 (de) | 2000-02-09 | 2001-01-29 | Turbinenschaufelanordnung |
Country Status (5)
Country | Link |
---|---|
US (1) | US6726452B2 (de) |
EP (2) | EP1124038A1 (de) |
JP (1) | JP2003522872A (de) |
CN (1) | CN1289789C (de) |
WO (1) | WO2001059263A2 (de) |
Cited By (1)
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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 |
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DE10134611A1 (de) * | 2000-12-16 | 2002-06-27 | Alstom Switzerland Ltd | Fixiervorrichtung für eine Beschaufelung einer Strömungsmaschine |
EP1319805A1 (de) * | 2001-12-17 | 2003-06-18 | Techspace aero | Rotor oder Rototelement für Turbokompressoren |
US7284958B2 (en) * | 2003-03-22 | 2007-10-23 | Allison Advanced Development Company | Separable blade platform |
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 |
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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 |
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US8545184B2 (en) * | 2010-01-05 | 2013-10-01 | General Electric Company | Locking spacer assembly |
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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 |
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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 |
WO2015076900A2 (en) * | 2013-10-11 | 2015-05-28 | 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 |
JP6222876B2 (ja) * | 2014-04-03 | 2017-11-01 | 三菱日立パワーシステムズ株式会社 | 翼列、ガスタービン |
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 (de) * | 2016-09-07 | 2021-04-14 | Ansaldo Energia IP UK Limited | Turbomotor-beschaufelungselement und verfahren zum herstellen solches elements |
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 |
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-
2000
- 2000-02-09 EP EP00102717A patent/EP1124038A1/de not_active Withdrawn
-
2001
- 2001-01-29 EP EP01905702A patent/EP1254301A2/de not_active Withdrawn
- 2001-01-29 US US10/203,388 patent/US6726452B2/en not_active Expired - Fee Related
- 2001-01-29 WO PCT/EP2001/000932 patent/WO2001059263A2/de not_active Application Discontinuation
- 2001-01-29 JP JP2001558580A patent/JP2003522872A/ja active Pending
- 2001-01-29 CN CN01804795.5A patent/CN1289789C/zh not_active Expired - Fee Related
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Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
CN101233299B (zh) * | 2005-07-25 | 2011-06-15 | 西门子公司 | 燃气透平叶片环 |
Also Published As
Publication number | Publication date |
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CN1398322A (zh) | 2003-02-19 |
JP2003522872A (ja) | 2003-07-29 |
US6726452B2 (en) | 2004-04-27 |
CN1289789C (zh) | 2006-12-13 |
EP1254301A2 (de) | 2002-11-06 |
US20030012654A1 (en) | 2003-01-16 |
EP1124038A1 (de) | 2001-08-16 |
WO2001059263A3 (de) | 2002-09-19 |
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