EP0906514A1 - Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor - Google Patents
Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotorInfo
- Publication number
- EP0906514A1 EP0906514A1 EP97928110A EP97928110A EP0906514A1 EP 0906514 A1 EP0906514 A1 EP 0906514A1 EP 97928110 A EP97928110 A EP 97928110A EP 97928110 A EP97928110 A EP 97928110A EP 0906514 A1 EP0906514 A1 EP 0906514A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- blade root
- blade
- groove
- turbomachine
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
Definitions
- Rotor for a turbo machine with blades which can be fitted in grooves and blade for a rotor
- the present invention relates to a rotor for a turbomachine with blades which can be fitted in grooves, the grooves being arranged obliquely to the axis of rotation of the rotor, and a blade for a rotor.
- the object of the present invention is now to reduce the strength problems occurring during the operation of a rotor and to specify a suitable combination of blade root and groove.
- a rotor for a turbomachine with the features of claim 1 and a blade with the features of claim 6 serve to achieve this object.
- Advantageous features and combinations result from the features disclosed in the respective dependent claims.
- a rotor according to the invention with blades which can be fitted in grooves, in which the grooves are inclined to the axis of rotation of the rotor are attached, has at least a part of its blades a blade root with at least two areas with different stiffness, which are adapted, preferably adjusted, to different areas of the stiffness of the groove into which the blade root can be attached.
- a preferred embodiment provides that a correspondingly adapted region of the blade root and a region of the groove that is stiffer in comparison lie opposite or opposite one another. This ensures that the corresponding stiffness of the groove and
- Blade root correspond so that there is an overall equalization of the stresses that occur.
- the flow of force during the transmission of force from the blade root into the groove can be designed inexpensively with a corresponding adaptation. It is also expedient if there is a region of reduced stiffness of the blade root in the groove area of the highest occurring stress, in general in particular in the area of the pointed corners of the groove in the rotor, so that no stresses occur during operation of the turbomachine which could destroy or Material fatigue leads to prolonged operation of the turbomachine.
- FIG. 1 shows a cross section of a rotor with blades adapted and used according to the invention
- FIG. 2 shows the rotor from FIG. 1 in a top view without inserted blades
- FIG. 3 shows a blade root according to the invention
- FIG. 4 shows the blade root from FIG. 3 used in a rotor disk
- FIG. 5 shows another foot used according to the invention.
- the rotor 1 of the turbomachine is preferably formed from rotor disks 1 which are arranged axially one behind the other and are toothed together (Hirth toothing) and are connected to one another by a tie rod, not shown.
- FIG. 1 shows a section of a rotor disk 1 with blades 3 inserted in grooves 2.
- Each blade 3 has areas with different stiffness.
- a recess 5 is made in the blade root 4 in such a way that the groove 2, which has an unevenly high rigidity over its groove depth, is opposite an adapted rigidity of the blade root 4. Since, in particular at the sharp corner 6 (see FIG. 2) of a groove 2, which lies at the end of the groove, increased voltages occur during operation of the gas turbine compressor, in this area the blade root 4 has the recess 5 in such a way that it is connected to it Body is slightly compliant.
- An advantageous embodiment of the recess 5 provides this in the form of a cutout, which runs obliquely downwards on the end face 8 of the blade root 4.
- FIG. 2 shows the rotor disk 1 from FIG. 1 in a top view.
- the grooves 2 are made at an installation angle ⁇ to the axis of rotation of the rotor disk 1, which can be much larger than conventional installation angles due to the adapted blade feet 4. This is particularly important for gas turbines and their compressors with a low mass flow. There larger blade angles and thus larger installation angles ß may be required. This leads in turn to increased local stresses in the groove 2, since there are reduced stiffnesses in particular in the pointed corners 6 due to the increased angles.
- the pointed corners 6 are places of local high tension. They are shown as the ends of the groove width D indicated in dashed lines and lying inside the rotor disk 1. Seen over the groove length L, it has different ranges of different stresses not only in its depth but also in its extent, which therefore have a different influence on the strength when the blade root 4 is installed and the operation of the turbomachine.
- FIG. 3 shows a blade root 4 according to the invention with an indicated extension of the blade leaf 7 of the blade 3.
- This has a recess 5, starting at both end faces 8, which run out of the blade root 4 at an angle downwards.
- This reduction in material in the blade root 4 leads to a reduced stiffness in areas of the end faces 8 and also in adjacent areas of the blade root 4. Areas adapted in this way have greater elasticity, so that deformations occurring during operation, in particular also at the pointed corners 6, are more favorable to be caught.
- FIG. 4 shows the blade 3 from FIG. 3 in the installed state.
- the reduction in material 5 in the blade root 4 leads to the fact that lines of force in the blade root 4 are interrupted and at these points the blade root 4 with respect to loads which arise due to the effective blade forces on the blade blade 7, via the adapted blade root 4 in the central region of the groove length L deflected and received there via the groove 2.
- FIG. 5 shows a further embodiment of the invention.
- the built-in blade root 4 has a recess 5 in a rather elongated shape, which pulls downwards out of the blade root 4 towards the center of the groove depth.
- This recess can not only be achieved by milling, but also by means of a hole or similar machining methods.
- recesses 5 are to be understood as adaptations to the rigidity of regions of the blade root 4.
- all measures that change the rigidity of a blade root in at least one area can be used.
- the invention creates a reduction of local stresses of 30% and more, depending on the size of the recess and the inclination of the installation angle.
- the advantage of the invention is its low cost, its effectiveness and also the subsequent rigidity adjustment of blade bases in turbo machines that have already been put into operation.
- Another advantage of the invention is the interchangeability of the blades. In this way, blade feet with and without material reduction can also be mounted together in one rotor disk.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Applications Claiming Priority (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19624924 | 1996-06-21 | ||
DE19624924 | 1996-06-21 | ||
DE19642537 | 1996-10-15 | ||
DE19642537 | 1996-10-15 | ||
PCT/DE1997/001159 WO1997049921A1 (fr) | 1996-06-21 | 1997-06-09 | Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0906514A1 true EP0906514A1 (fr) | 1999-04-07 |
EP0906514B1 EP0906514B1 (fr) | 2001-10-24 |
Family
ID=26026814
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97928110A Expired - Lifetime EP0906514B1 (fr) | 1996-06-21 | 1997-06-09 | Rotor pour une turbomachine avec des pales a monter dans des rainures et pales pour un rotor |
Country Status (6)
Country | Link |
---|---|
US (1) | US6065938A (fr) |
EP (1) | EP0906514B1 (fr) |
JP (1) | JP2000512707A (fr) |
KR (1) | KR20000022064A (fr) |
DE (1) | DE59705094D1 (fr) |
WO (1) | WO1997049921A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1136654A1 (fr) * | 2000-03-21 | 2001-09-26 | Siemens Aktiengesellschaft | Aube rotorique de turbine |
FR3087479A1 (fr) * | 2018-10-23 | 2020-04-24 | Safran Aircraft Engines | Aube de turbomachine |
Families Citing this family (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6439851B1 (en) * | 2000-12-21 | 2002-08-27 | United Technologies Corporation | Reduced stress rotor blade and disk assembly |
US6428279B1 (en) * | 2000-12-22 | 2002-08-06 | General Electric Company | Low windage loss, light weight closure bucket design and related method |
US6846159B2 (en) | 2002-04-16 | 2005-01-25 | United Technologies Corporation | Chamfered attachment for a bladed rotor |
US6769877B2 (en) | 2002-10-18 | 2004-08-03 | General Electric Company | Undercut leading edge for compressor blades and related method |
EP1426553A1 (fr) * | 2002-12-03 | 2004-06-09 | Techspace Aero S.A. | Réduction de la masse d'aubes mobiles |
US7121803B2 (en) * | 2002-12-26 | 2006-10-17 | General Electric Company | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
US20040213672A1 (en) * | 2003-04-25 | 2004-10-28 | Gautreau James Charles | Undercut leading edge for compressor blades and related method |
US6902376B2 (en) * | 2002-12-26 | 2005-06-07 | General Electric Company | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
SE526255C2 (sv) * | 2003-03-14 | 2005-08-09 | Sandvik Intellectual Property | Verktyg och indexerbart skär för finsvarvning av rotationssymmetriska spår i arbetsstycken |
DE10357134A1 (de) | 2003-12-06 | 2005-06-30 | Alstom Technology Ltd | Rotor für einen Verdichter |
US7252481B2 (en) * | 2004-05-14 | 2007-08-07 | Pratt & Whitney Canada Corp. | Natural frequency tuning of gas turbine engine blades |
US7156621B2 (en) * | 2004-05-14 | 2007-01-02 | Pratt & Whitney Canada Corp. | Blade fixing relief mismatch |
JP4869616B2 (ja) * | 2005-04-01 | 2012-02-08 | 株式会社日立製作所 | 蒸気タービン動翼と蒸気タービンロータ及びそれを用いた蒸気タービン並びにその発電プラント |
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 |
FR2900989B1 (fr) * | 2006-05-12 | 2008-07-11 | Snecma Sa | Ensemble pour compresseur de moteur d'aeronef comprenant des aubes a attache marteau a pied incline |
FR2903138B1 (fr) * | 2006-06-28 | 2017-10-06 | Snecma | Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque |
FR2905139B1 (fr) * | 2006-08-25 | 2012-09-28 | Snecma | Aube de rotor d'une turbomachine |
FR2911632B1 (fr) | 2007-01-18 | 2009-08-21 | Snecma Sa | Disque de rotor de soufflante de turbomachine |
US8313289B2 (en) | 2007-12-07 | 2012-11-20 | United Technologies Corp. | Gas turbine engine systems involving rotor bayonet coverplates and tools for installing such coverplates |
US8075280B2 (en) * | 2008-09-08 | 2011-12-13 | Siemens Energy, Inc. | Composite blade and method of manufacture |
JP5395455B2 (ja) * | 2009-02-20 | 2014-01-22 | 三菱重工業株式会社 | 軸流圧縮機用動翼 |
EP2282010A1 (fr) | 2009-06-23 | 2011-02-09 | Siemens Aktiengesellschaft | Aube de rotor pour une turbomachine à flux axial |
FR2981132B1 (fr) * | 2011-10-10 | 2013-12-06 | Snecma | Ensemble pour turbomachine a refroidissement de disque |
FR3001646B1 (fr) * | 2013-02-01 | 2015-09-11 | Turbomeca | Broche et procede de brochage d alveoles pour des pieces telles que des disques de rotor de turbine ou des disques de compresseur de turbomachine |
JP2016035209A (ja) * | 2014-08-01 | 2016-03-17 | 三菱日立パワーシステムズ株式会社 | 軸流圧縮機、及び軸流圧縮機を備えたガスタービン |
GB2529681B (en) * | 2014-08-29 | 2019-02-20 | Rolls Royce Plc | Gas turbine engine rotor arrangement |
CN104265377B (zh) * | 2014-09-16 | 2016-01-20 | 上海金通灵动力科技有限公司 | 一种降低纵树型轮毂型线处应力的结构 |
US9896947B2 (en) * | 2014-12-15 | 2018-02-20 | United Technologies Corporation | Turbine airfoil attachment with multi-radial serration profile |
US10400784B2 (en) * | 2015-05-27 | 2019-09-03 | United Technologies Corporation | Fan blade attachment root with improved strain response |
US20180112544A1 (en) | 2016-10-26 | 2018-04-26 | Siemens Aktiengesellschaft | Turbine rotor blade, turbine rotor arrangement and method for manufacturing a turbine rotor blade |
FR3062875B1 (fr) * | 2017-02-10 | 2021-07-02 | Safran Aircraft Engines | Aube mobile de turbomachine comprenant des evidements dans le pied |
JP7031270B2 (ja) * | 2017-12-08 | 2022-03-08 | 株式会社リコー | 検査装置、検査システム及び検査方法 |
US10815799B2 (en) * | 2018-11-15 | 2020-10-27 | General Electric Company | Turbine blade with radial support, shim and related turbine rotor |
JP7385992B2 (ja) * | 2018-12-28 | 2023-11-24 | 川崎重工業株式会社 | 回転体の動翼およびディスク |
CN111412183B (zh) * | 2020-04-24 | 2021-05-18 | 上海应达风机股份有限公司 | 一种风机叶轮及其加工制造工艺 |
KR20230081267A (ko) | 2021-11-30 | 2023-06-07 | 두산에너빌리티 주식회사 | 터빈 블레이드, 이를 포함하는 터빈 및 가스터빈 |
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US2643853A (en) * | 1948-07-26 | 1953-06-30 | Westinghouse Electric Corp | Turbine apparatus |
US4191509A (en) * | 1977-12-27 | 1980-03-04 | United Technologies Corporation | Rotor blade attachment |
WO1991001433A1 (fr) * | 1989-07-25 | 1991-02-07 | Allied-Signal Inc. | Aube de turbine a double alliage |
GB2237846B (en) * | 1989-11-09 | 1993-12-15 | Rolls Royce Plc | Rim parasitic weight reduction |
FR2697051B1 (fr) * | 1992-10-21 | 1994-12-02 | Snecma | Rotor de turbomachine comprenant un disque dont le pourtour est occupé par des alvéoles obliques qui alternent avec des dents de section transversale variable. |
US5372481A (en) * | 1993-11-29 | 1994-12-13 | Solar Turbine Incorporated | Ceramic blade attachment system |
FR2725239B1 (fr) * | 1994-09-30 | 1996-11-22 | Gec Alsthom Electromec | Disposition pour l'ecretement des pointes de contrainte dans l'ancrage d'une ailette de turbine, comportant une racine dite en "pied-sapin" |
US5846054A (en) * | 1994-10-06 | 1998-12-08 | General Electric Company | Laser shock peened dovetails for disks and blades |
-
1997
- 1997-06-09 KR KR1019980710467A patent/KR20000022064A/ko not_active Application Discontinuation
- 1997-06-09 JP JP10502063A patent/JP2000512707A/ja active Pending
- 1997-06-09 EP EP97928110A patent/EP0906514B1/fr not_active Expired - Lifetime
- 1997-06-09 WO PCT/DE1997/001159 patent/WO1997049921A1/fr not_active Application Discontinuation
- 1997-06-09 DE DE59705094T patent/DE59705094D1/de not_active Expired - Lifetime
-
1998
- 1998-12-21 US US09/217,862 patent/US6065938A/en not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
---|
See references of WO9749921A1 * |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1136654A1 (fr) * | 2000-03-21 | 2001-09-26 | Siemens Aktiengesellschaft | Aube rotorique de turbine |
WO2001071166A1 (fr) * | 2000-03-21 | 2001-09-27 | Siemens Aktiengesellschaft | Aube mobile de turbine |
FR3087479A1 (fr) * | 2018-10-23 | 2020-04-24 | Safran Aircraft Engines | Aube de turbomachine |
US11156107B2 (en) | 2018-10-23 | 2021-10-26 | Safran Aircraft Engines | Turbomachine blade |
Also Published As
Publication number | Publication date |
---|---|
WO1997049921A1 (fr) | 1997-12-31 |
US6065938A (en) | 2000-05-23 |
KR20000022064A (ko) | 2000-04-25 |
DE59705094D1 (de) | 2001-11-29 |
JP2000512707A (ja) | 2000-09-26 |
EP0906514B1 (fr) | 2001-10-24 |
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