US20020182081A1 - Device for fastening a moving blade to the rotor of a turbomachine - Google Patents
Device for fastening a moving blade to the rotor of a turbomachine Download PDFInfo
- Publication number
- US20020182081A1 US20020182081A1 US10/124,428 US12442802A US2002182081A1 US 20020182081 A1 US20020182081 A1 US 20020182081A1 US 12442802 A US12442802 A US 12442802A US 2002182081 A1 US2002182081 A1 US 2002182081A1
- Authority
- US
- United States
- Prior art keywords
- blade
- rotor
- moving blades
- blade root
- circumferential groove
- 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.)
- Abandoned
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
-
- 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
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
Definitions
- the invention relates to a device for fastening a moving blade to the rotor of a thermal turbomachine according to the preamble of claim 1.
- Moving blades which are fastened in circumferential grooves on rotors of turbomachines are to be positioned in a suitable way as a function of the respective flow conditions, but, in particular, are to be secured reliably against coming loose from the circumferential groove completely while the turbomachines are in operation as a result of maladjustments which may possibly occur.
- the blade roots of the individual moving blades or the platforms provided, as a rule, between the blade roots and blade leaves are designed to be contoured obliquely in such a way that two adjacent moving blades come into contact via oblique bearing faces oriented with respect to the rotor axis, the abovementioned thermally induced mechanical constraints lead, within the bearing faces oriented obliquely to the rotor axis, to additional axial forces which lead to a distortion of the rotor and consequently to vibrations.
- U.S. Pat. No. 4,684,325 describes generic turbine moving blades which, in a multiplicity lined up with one another along the circumferential groove, are directly contiguous with one another via the side flanks of rhombically designed platforms.
- the rhombic design of the platforms is due to the oblique position of the respective turbine leaf in relation to the throughflow direction and, on the other hand, is motivated by an increase in the packing density of moving blades to be arranged along the circumferential groove.
- the object on which the invention is based is to develop a device for fastening a moving blade of the generic type described above, in such a way that axial forces on the rotor which occur due to thermal distortions within the moving blades are to be avoided completely. Care is to be taken, at the same time, to show that a coming loose of individual moving blades on account of gap interspaces which may possibly be formed can be ruled out completely.
- the measures to be taken are not to require any structurally complicated work or precautions and, in particular, are to allow retrofitting in the case of already existing rotor arrangements.
- the device for fastening a moving blade according to the preamble of claim 1 is designed such that, in the region of the blade root extending into the circumferential groove, bearing faces are provided which are actively connected to said blade root and are oriented parallel to the rotor axis, and adjacently inserted moving blades come into a loose force-exposed connection directly or indirectly with one another, in each case within the circumferential groove, via the bearing faces oriented parallel to the rotor axis.
- a shim which is introduced radially between the blade root and the rotor within the circumferential groove and which makes at least one releasably firm active connection with the respective blade root.
- the shim has bearing faces which are oriented parallel to the rotor axis and which project beyond the side flanks of the platform of the moving blade in the circumferential direction of the rotor. What is achieved thereby is that two adjacent moving blades butt against one another solely via the bearing faces, assigned to them, of the respective shims, said bearing faces being oriented parallel to the rotor axis.
- the releasably firm active connection between the individual moving-blade roots and the shims assigned to them is made from the sides of the shim preferably by means of a force-exposed bolt, preferably a spring-force-exposed bolt, which engages into a corresponding recess within the blade root, as a result of which, on the one hand, movement-free fixing of the moving blade in the circumferential direction is ensured, but, on the other hand, there is sufficient play between the rotor and the blade root, so that the blade root can thermally expand essentially freely within the circumferential groove. Thermal distortions within the blade root seated in the circumferential groove can thereby be largely avoided.
- FIG. 1 shows a top view of a moving blade inserted into a circumferential groove, with two adjacently arranged shims
- FIG. 2 shows a cross-sectional illustration along the sectional line in FIG. 1,
- FIG. 3 shows an illustration of a detail regarding the connection between shim and blade root.
- FIG. 1 shows a top view of the circumferential groove 1 of a rotor 2 of a thermal turbomachine, such as a compressor or a gas or steam turbine.
- a thermal turbomachine such as a compressor or a gas or steam turbine.
- the side flanks 33 , 34 of the platform 31 are directed essentially parallel to one another and form the same angle of incidence ⁇ with respect to the coparallel, marked by broken lines, to the axis of rotation 4 .
- the blade leaf 32 has a wrenched design in its radial extent, that is to say the blade tip 35 has a larger angle of incidence ⁇ than the blade-leaf region near the platform 31 .
- the blade root not illustrated, which is completely covered by the platform 31 in the illustration of a top view according to FIG. 1, is in engagement with a holding contour which is incorporated within the circumferential groove 1 and may be gathered in detail from the cross-sectional illustration according to the FIG. 2, which will also be dealt with in detail.
- connection means 6 is connected such that the moving blade 3 is fixed securely in the circumferential direction longitudinally in relation to the circumferential groove 1 .
- a special design of the connection means 4 will be dealt with below in FIG. 3.
- the shims 5 connectable in each case to a moving blade 3 are designed preferably in the manner of an obliquely set “H” and have a middle connecting web 51 , in which the corresponding connection means 6 can be integrated.
- the side limbs directed in the circumferential direction in relation to the circumferential groove 1 terminate in each case in the regions having the bearing faces 52 which are oriented parallel to the rotor axis 4 and which all project beyond the moving blade 3 in radial projection, thus ensuring that two moving blades arranged adjacently in the circumferential groove 1 are in force-exposed contact preferably solely in each case via the bearing faces 52 .
- FIG. 2 illustrates a sectional diagram along the sectional line A-A according to FIG. 1.
- This shim 5 assigned to the moving blade 3 is located in an intermediate gap 7 between the blade root 36 and the rotor 2 .
- the platform 31 the top side of which is flush with the rotor top side, may likewise be gathered from the cross-sectional illustration according to FIG. 2.
- a spring-force-exposed bolt 7 by means of which the moving blade 3 is fixed in relation to the shim 5 , is provided centrally in relation to the blade root 36 as a connection means 6 .
- FIG. 3 illustrates a corresponding cross-sectional illustration of the connection means 6 .
- the shim 5 has a press fit by means of a sleeve 62 , within which is provided a spring element 63 which can drive a bolt 61 vertically upwards.
- the bolt 61 and the sleeve 62 project, in association with the moving blade 3 , into a corresponding recess 64 within the blade root 36 .
- At least one intermediate piece 8 may be inserted within the circumferential groove 1 between two moving blades 3 , as a spacer piece which has a blade root as fastening element and also a platform which is flush with the rotor 2 and with the platforms 31 of two adjacent moving blades 3 .
- the measure according to the invention is suitable in a particularly advantageous way as a retrofit set in the case of turbomachines which are already in operation. It is expedient merely to enlarge the axial and, if appropriate, circumferential play in the region of the blade roots by remachining, for example by regrinding, in order to provide sufficient space for inserting the shims.
- List of reference symbols 1 Circumferential groove 2 Rotor 3 Moving blade 31 Platform 32 Blade leaf 33, 34 Side flanks 35 Blade leaf tip 36 Blade root 4 Rotor axis 5 Shim 51 Connecting web 52 Bearing faces 6 Connection means 61 Bolt 62 Sleeve 63 Spring element 64 Recess 7 Intermediate gap 8 Intermediate piece
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- The invention relates to a device for fastening a moving blade to the rotor of a thermal turbomachine according to the preamble of
claim 1. - Moving blades which are fastened in circumferential grooves on rotors of turbomachines are to be positioned in a suitable way as a function of the respective flow conditions, but, in particular, are to be secured reliably against coming loose from the circumferential groove completely while the turbomachines are in operation as a result of maladjustments which may possibly occur.
- There is the risk of individual moving blades coming loose completely from the respective fastening measures when the moving blades inserted within the circumferential grooves and fastened in a way known per se are capable of being displaced unevenly along the circumferential groove on the rotor in the circumferential direction within the respective assembly play. Owing to peripheral maladjustments of this kind in the case of a multiplicity of moving blades inserted along the circumferential groove, a considerable gap may be established between two adjacent moving blades, such a gap being sufficiently large for a moving blade to be capable of coming loose from the circumferential groove as a result of radial twisting, thus causing considerable damage to the entire turbomachine plant.
- Securing measures, known per se, against individual moving blades coming loose independently from the circumferential groove are concerned, in general, with reducing the play between two adjacent blade roots within the circumferential groove in the circumferential direction. Use is made, for this purpose, of special intermediate pieces which can fill the play which has remained in a circumferential direction from assembly, the intermediate pieces having to be installed very closely together in the remaining intermediate gap.
- The use of specially shaped intermediate pieces, which reduce the assembly-related play in the circumferential direction to an amount which is very much smaller than would be necessary for the free thermal expansion of the individual moving blades along the circumferential groove, gives rise, when the turbomachine is in operation, to thermally induced constraints which are brought about at least longitudinally in the circumferential direction between the individual adjacent moving blades. If the blade roots of the individual moving blades or the platforms provided, as a rule, between the blade roots and blade leaves are designed to be contoured obliquely in such a way that two adjacent moving blades come into contact via oblique bearing faces oriented with respect to the rotor axis, the abovementioned thermally induced mechanical constraints lead, within the bearing faces oriented obliquely to the rotor axis, to additional axial forces which lead to a distortion of the rotor and consequently to vibrations.
- Irrespective of the design of the platforms of respective moving blades, it is also conceivable that two blade roots arranged adjacently within the circumferential groove have blade-root flanks running obliquely to the rotor axis and are contiguous with one another, the vibration phenomena explained above occurring in the same way.
- U.S. Pat. No. 4,684,325 describes generic turbine moving blades which, in a multiplicity lined up with one another along the circumferential groove, are directly contiguous with one another via the side flanks of rhombically designed platforms. The rhombic design of the platforms, on the one hand, is due to the oblique position of the respective turbine leaf in relation to the throughflow direction and, on the other hand, is motivated by an increase in the packing density of moving blades to be arranged along the circumferential groove. If, then, due to the operating conditions prevailing in a turbomachine, turbine moving blades designed in this way come into force-exposed active connection via the bearing faces not oriented parallel to the axis of rotation, the axial forces arising along the individual bearing faces between the adjacent moving blades lead to unavoidable vibrations within the rotor arrangement, due to which corresponding bearings supporting the rotor arrangement are subjected to considerable load. It is expedient to counteract effectively this very situation by means of appropriate measures.
- The object on which the invention is based is to develop a device for fastening a moving blade of the generic type described above, in such a way that axial forces on the rotor which occur due to thermal distortions within the moving blades are to be avoided completely. Care is to be taken, at the same time, to show that a coming loose of individual moving blades on account of gap interspaces which may possibly be formed can be ruled out completely. The measures to be taken are not to require any structurally complicated work or precautions and, in particular, are to allow retrofitting in the case of already existing rotor arrangements.
- According to the invention, the device for fastening a moving blade according to the preamble of
claim 1 is designed such that, in the region of the blade root extending into the circumferential groove, bearing faces are provided which are actively connected to said blade root and are oriented parallel to the rotor axis, and adjacently inserted moving blades come into a loose force-exposed connection directly or indirectly with one another, in each case within the circumferential groove, via the bearing faces oriented parallel to the rotor axis. - The idea, on which the invention is based, of avoiding axial forces occurring on the rotor due to bearing faces set obliquely to the rotor axis between two adjacent moving blades is the avoidance of those very oblique bearing faces. The idea of the invention is therefore of particular importance especially in the case of moving blades with a large angle of incidence in relation to the throughflow direction in turbomachines, especially since the platforms of moving blades of this kind have, not least for reasons of space and weight, obliquely running side flanks, via which the directly adjacent moving blades or similarly configured intermediate pieces, inserted, as a rule, within the circumferential groove, are contiguous with one another.
- To avoid those very contact faces oriented obliquely to the rotor axis, there is in a particularly advantageous way, for each individual moving blade, a shim which is introduced radially between the blade root and the rotor within the circumferential groove and which makes at least one releasably firm active connection with the respective blade root. The shim has bearing faces which are oriented parallel to the rotor axis and which project beyond the side flanks of the platform of the moving blade in the circumferential direction of the rotor. What is achieved thereby is that two adjacent moving blades butt against one another solely via the bearing faces, assigned to them, of the respective shims, said bearing faces being oriented parallel to the rotor axis. By virtue of the geometric design of the shims, during operation, only stresses in the circumferential direction occur on account of differences in thermal expansion between the rotor and the shims arranged in the circumferential direction within the circumferential groove, but said stresses are entirely uncritical for the rotational behavior of the rotor. Any axial forces directed onto the rotor can be avoided because of the axial or parallel orientation of the bearing faces in relation to the rotor axis.
- The releasably firm active connection between the individual moving-blade roots and the shims assigned to them is made from the sides of the shim preferably by means of a force-exposed bolt, preferably a spring-force-exposed bolt, which engages into a corresponding recess within the blade root, as a result of which, on the one hand, movement-free fixing of the moving blade in the circumferential direction is ensured, but, on the other hand, there is sufficient play between the rotor and the blade root, so that the blade root can thermally expand essentially freely within the circumferential groove. Thermal distortions within the blade root seated in the circumferential groove can thereby be largely avoided.
- The invention is described by way of example below, without the general idea of the invention being restricted, by means of exemplary embodiments, with reference to the drawings in which:
- FIG. 1 shows a top view of a moving blade inserted into a circumferential groove, with two adjacently arranged shims,
- FIG. 2 shows a cross-sectional illustration along the sectional line in FIG. 1, and
- FIG. 3 shows an illustration of a detail regarding the connection between shim and blade root.
- Only the elements essential for the invention are illustrated. Like elements are designated identically in the various figures.
- FIG. 1 shows a top view of the
circumferential groove 1 of arotor 2 of a thermal turbomachine, such as a compressor or a gas or steam turbine. For the sake of greater clarity in the illustration, only one moving blade 3 (middle position) with a rhombically designedplatform 31 and with ablade leaf 32 set at an angle α is illustrated within thecircumferential groove 2. In the exemplary embodiment illustrated, theside flanks platform 31 are directed essentially parallel to one another and form the same angle of incidence α with respect to the coparallel, marked by broken lines, to the axis ofrotation 4. It may be pointed out, merely for the sake of completeness, that theblade leaf 32 has a wrenched design in its radial extent, that is to say theblade tip 35 has a larger angle of incidence α than the blade-leaf region near theplatform 31. - Furthermore, the blade root, not illustrated, which is completely covered by the
platform 31 in the illustration of a top view according to FIG. 1, is in engagement with a holding contour which is incorporated within thecircumferential groove 1 and may be gathered in detail from the cross-sectional illustration according to the FIG. 2, which will also be dealt with in detail. - Provided radially below the moving
blade 3, within thecircumferential groove 1, is ashim 5, a multiplicity of which are arranged, distributed in the circumferential direction, in each case directly contiguously with one another. Theshims 5 have in each case bearingfaces 52 oriented parallel to therotor axis 4. For the sake of clearer illustration, the associated movingblade 3 is depicted merely in terms of themiddle shim 5 in FIG. 1, said moving blade being connected via a connection means at least releasably firmly to theshim 5 associated with it. The connection means 6 is connected such that the movingblade 3 is fixed securely in the circumferential direction longitudinally in relation to thecircumferential groove 1. A special design of the connection means 4 will be dealt with below in FIG. 3. - In the exemplary embodiment according to FIG. 1, the
shims 5 connectable in each case to a movingblade 3 are designed preferably in the manner of an obliquely set “H” and have amiddle connecting web 51, in which the corresponding connection means 6 can be integrated. The side limbs directed in the circumferential direction in relation to thecircumferential groove 1 terminate in each case in the regions having thebearing faces 52 which are oriented parallel to therotor axis 4 and which all project beyond the movingblade 3 in radial projection, thus ensuring that two moving blades arranged adjacently in thecircumferential groove 1 are in force-exposed contact preferably solely in each case via thebearing faces 52. In particular, as a result of the very high temperatures prevailing when a turbomachine is in operation, even theshims 5 expand in relation to the rotor material, thus giving rise, however, to only mechanical constraints in the circumferential direction between theindividual shims 5, whereas any axial forces on the rotor are avoided owing to the parallel orientation of the bearing faces in relation to the rotor axis. - The idea, on which the invention is based, of avoiding axial forces occurring on the
rotor 2 due to bearing faces set obliquely to therotor axis 4 between two adjacent movingblades 3 is, in general, that adjacent movingblades 3 meet only at axially orientedbearing faces 52, irrespective of whether these bearingfaces 52 are fastened to ashim 5 or directly to theblade root 36 or are connected in another active way to theblade root 36. The bearing faces is oriented parallel to the rotor axis project beyond theside flanks platform 31 of themoving blade 3 in the circumferential direction of the rotor for the inventive purpose. - FIG. 2 illustrates a sectional diagram along the sectional line A-A according to FIG. 1. This
shim 5 assigned to themoving blade 3 is located in anintermediate gap 7 between theblade root 36 and therotor 2. Theplatform 31, the top side of which is flush with the rotor top side, may likewise be gathered from the cross-sectional illustration according to FIG. 2. A spring-force-exposedbolt 7, by means of which the movingblade 3 is fixed in relation to theshim 5, is provided centrally in relation to theblade root 36 as a connection means 6. - FIG. 3 illustrates a corresponding cross-sectional illustration of the connection means6. Here, the
shim 5 has a press fit by means of asleeve 62, within which is provided aspring element 63 which can drive a bolt 61 vertically upwards. The bolt 61 and thesleeve 62 project, in association with themoving blade 3, into acorresponding recess 64 within theblade root 36. - As indicated diagrammatically in FIG. 1 below the
moving blade 3, at least oneintermediate piece 8 may be inserted within thecircumferential groove 1 between two movingblades 3, as a spacer piece which has a blade root as fastening element and also a platform which is flush with therotor 2 and with theplatforms 31 of two adjacent movingblades 3. - The measure according to the invention is suitable in a particularly advantageous way as a retrofit set in the case of turbomachines which are already in operation. It is expedient merely to enlarge the axial and, if appropriate, circumferential play in the region of the blade roots by remachining, for example by regrinding, in order to provide sufficient space for inserting the shims.
List of reference symbols 1 Circumferential groove 2 Rotor 3 Moving blade 31 Platform 32 Blade leaf 33, 34 Side flanks 35 Blade leaf tip 36 Blade root 4 Rotor axis 5 Shim 51 Connecting web 52 Bearing faces 6 Connection means 61 Bolt 62 Sleeve 63 Spring element 64 Recess 7 Intermediate gap 8 Intermediate piece
Claims (10)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10120532.5 | 2001-04-26 | ||
DE10120532A DE10120532A1 (en) | 2001-04-26 | 2001-04-26 | Device and method for fastening a rotor blade along a circumferential groove running within a rotor of an axially flowed through turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
US20020182081A1 true US20020182081A1 (en) | 2002-12-05 |
Family
ID=7682853
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US10/124,428 Abandoned US20020182081A1 (en) | 2001-04-26 | 2002-04-18 | Device for fastening a moving blade to the rotor of a turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20020182081A1 (en) |
EP (1) | EP1253293A3 (en) |
JP (1) | JP2002332802A (en) |
DE (1) | DE10120532A1 (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20060228216A1 (en) * | 2003-12-06 | 2006-10-12 | Rene Bachofner | Rotor for a compressor |
US20060251522A1 (en) * | 2005-05-05 | 2006-11-09 | Matheny Alfred P | Curved blade and vane attachment |
US20110110785A1 (en) * | 2009-11-10 | 2011-05-12 | Alstom Technology Ltd | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
CN103195514A (en) * | 2012-01-05 | 2013-07-10 | 通用电气公司 | Turbine rotor rim seal axial retention assembly |
US20140199172A1 (en) * | 2013-01-11 | 2014-07-17 | General Electric Company | Turbomachine and method of handling turbomachine components |
CN114837993A (en) * | 2022-05-23 | 2022-08-02 | 安徽朗迪叶轮机械有限公司 | Double-layer axial flow fan blade |
US20230212960A1 (en) * | 2022-01-05 | 2023-07-06 | General Electric Company | Turbomachine component retention |
Families Citing this family (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2005273646A (en) | 2004-02-25 | 2005-10-06 | Mitsubishi Heavy Ind Ltd | Moving blade element and rotary machine having the moving blade element |
DE502004006777D1 (en) * | 2004-07-22 | 2008-05-21 | Siemens Ag | Securing device for a arranged on a rotatable rotor blade rotor of a turbomachine, turbomachine and method for assembling and disassembling a blade on a rotor disk of a turbomachine |
EP1892380A1 (en) | 2006-08-25 | 2008-02-27 | Siemens Aktiengesellschaft | Turbine blade retention system |
CH702203A1 (en) * | 2009-11-10 | 2011-05-13 | Alstom Technology Ltd | Rotor for axial flow turbomachine i.e. gas turbine, in combined cycle power plant, has rotating blades inserted into groove, and blade root comprising inverted-T root with hammer head and adapted to base area of groove in radial direction |
DE102012213227B3 (en) * | 2012-07-27 | 2013-09-26 | Siemens Aktiengesellschaft | Blade ring for a turbo machine |
CN109366403B (en) * | 2018-12-10 | 2023-09-22 | 无锡透平叶片有限公司 | Device for simulating assembly of fungus type blade |
CN112855282B (en) * | 2021-03-01 | 2022-04-12 | 杭州汽轮机股份有限公司 | Method for controlling assembly interference of adjusting grade taper pin of industrial steam turbine |
Citations (3)
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US3252687A (en) * | 1965-02-01 | 1966-05-24 | Gen Motors Corp | Rotor blade locking |
US3841792A (en) * | 1973-03-09 | 1974-10-15 | Westinghouse Electric Corp | Turbomachine blade lock and seal device |
US4688992A (en) * | 1985-01-25 | 1987-08-25 | General Electric Company | Blade platform |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
NL252407A (en) * | 1960-05-09 | 1900-01-01 | ||
CH494341A (en) * | 1968-07-26 | 1970-07-31 | Sulzer Ag | Rotor for turbo machinery |
GB2171150B (en) * | 1985-02-12 | 1989-07-26 | Rolls Royce Plc | Bladed rotor assembly for a turbomachine |
FR2616480B1 (en) * | 1987-06-10 | 1989-09-29 | Snecma | DEVICE FOR LOCKING BLADES WITH A HAMMER FOOT ON A TURBOMACHINE DISC AND ASSEMBLY AND DISASSEMBLY METHODS |
FR2776012B1 (en) * | 1998-03-12 | 2000-04-07 | Snecma | SEAL OF A CIRCULAR BLADE STAGE |
-
2001
- 2001-04-26 DE DE10120532A patent/DE10120532A1/en not_active Withdrawn
-
2002
- 2002-04-09 EP EP02405278A patent/EP1253293A3/en not_active Withdrawn
- 2002-04-18 US US10/124,428 patent/US20020182081A1/en not_active Abandoned
- 2002-04-26 JP JP2002127030A patent/JP2002332802A/en not_active Withdrawn
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3252687A (en) * | 1965-02-01 | 1966-05-24 | Gen Motors Corp | Rotor blade locking |
US3841792A (en) * | 1973-03-09 | 1974-10-15 | Westinghouse Electric Corp | Turbomachine blade lock and seal device |
US4688992A (en) * | 1985-01-25 | 1987-08-25 | General Electric Company | Blade platform |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20060228216A1 (en) * | 2003-12-06 | 2006-10-12 | Rene Bachofner | Rotor for a compressor |
US7513747B2 (en) * | 2003-12-06 | 2009-04-07 | Alstom Technology Ltd. | Rotor for a compressor |
US20060251522A1 (en) * | 2005-05-05 | 2006-11-09 | Matheny Alfred P | Curved blade and vane attachment |
US20110110785A1 (en) * | 2009-11-10 | 2011-05-12 | Alstom Technology Ltd | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
CN102121400A (en) * | 2009-11-10 | 2011-07-13 | 阿尔斯托姆科技有限公司 | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
US8770938B2 (en) * | 2009-11-10 | 2014-07-08 | Alstom Technology Ltd | Rotor for an axial-throughflow turbomachine and moving blade for such a rotor |
US20130175230A1 (en) * | 2012-01-05 | 2013-07-11 | General Electric Company | Turbine rotor rim seal axial retention assembly |
CN103195514A (en) * | 2012-01-05 | 2013-07-10 | 通用电气公司 | Turbine rotor rim seal axial retention assembly |
US9890648B2 (en) * | 2012-01-05 | 2018-02-13 | General Electric Company | Turbine rotor rim seal axial retention assembly |
US20140199172A1 (en) * | 2013-01-11 | 2014-07-17 | General Electric Company | Turbomachine and method of handling turbomachine components |
US20230212960A1 (en) * | 2022-01-05 | 2023-07-06 | General Electric Company | Turbomachine component retention |
US11773750B2 (en) * | 2022-01-05 | 2023-10-03 | General Electric Company | Turbomachine component retention |
CN114837993A (en) * | 2022-05-23 | 2022-08-02 | 安徽朗迪叶轮机械有限公司 | Double-layer axial flow fan blade |
Also Published As
Publication number | Publication date |
---|---|
JP2002332802A (en) | 2002-11-22 |
DE10120532A1 (en) | 2002-10-31 |
EP1253293A2 (en) | 2002-10-30 |
EP1253293A3 (en) | 2004-09-29 |
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