WO2003102378A1 - Aube mobile de turbine - Google Patents
Aube mobile de turbine Download PDFInfo
- Publication number
- WO2003102378A1 WO2003102378A1 PCT/JP2003/006879 JP0306879W WO03102378A1 WO 2003102378 A1 WO2003102378 A1 WO 2003102378A1 JP 0306879 W JP0306879 W JP 0306879W WO 03102378 A1 WO03102378 A1 WO 03102378A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- blade
- contact
- effective
- turbine rotor
- turbine
- Prior art date
Links
- 230000003187 abdominal effect Effects 0.000 claims description 5
- 239000012530 fluid Substances 0.000 claims description 5
- 230000000694 effects Effects 0.000 description 14
- 238000013016 damping Methods 0.000 description 10
- 239000007943 implant Substances 0.000 description 9
- 230000013011 mating Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 241001417534 Lutjanidae Species 0.000 description 2
- 241000779819 Syncarpia glomulifera Species 0.000 description 2
- 210000001015 abdomen Anatomy 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000001739 pinus spp. Substances 0.000 description 2
- 230000001629 suppression Effects 0.000 description 2
- 229940036248 turpentine Drugs 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 241000196324 Embryophyta Species 0.000 description 1
- 241000120551 Heliconiinae Species 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 230000012447 hatching Effects 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
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
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
Definitions
- the present invention relates to an evening bin rotor blade, and more particularly, to a snubber cover (integral cover) formed by integrally shaping a wing tip from an effective wing portion and integrally joining the tip portion of the effective wing portion by a manufacturing or metallurgical method.
- the present invention relates to a turbine blade provided with: Background art
- the tip of the blade is required to prevent the excitation force based on the steam jet flowing through the effective portion of the blade during operation and the reduction of blade efficiency due to steam leakage from the blade tip.
- a snubber cover integrated cover
- Such a structure provided at the top of the wing to form a group wing structure or a one-group structure around the entire circumference is called a snubber force par (integral cover).
- Snatsubakaba -A contact surface is provided at the back and ventral sides of the moving blade so that the contact surface of the snubber force bar of one wing comes into contact with the contact surface of the snubber cover of the other wing. Thing has a high damping effect by friction at this contact surface.
- the snubber covers can all be made to have the same shape (structure), there are advantages that the stresses on all the blades are uniform and that the vibration modes generated during design can be easily limited.
- FIG. 7 shows such a configuration.
- the turbine rotor blade has a blade effective portion 1 for turning the steam flow toward the next paragraph, a blade implant portion 2 provided at the root side of the blade effective portion 1 and implanted in the rotor wheel 4, and a blade effective portion. It has a snubber cover (integral cover) 3 provided at the top of part 1.
- the wing effective part 1, wing implant part 2, and snubber force bar 3 are cut out from the wing body and integrally manufactured, or the wing effective part 1, wing implant part 2 is cut out, and a separately manufactured snubber cover 3 is integrally joined to the tip of the effective blade portion 1 by a metallurgical method such as welding.
- a rotor blade body is implanted in a row in the circumferential direction of a rotor wheel 4 provided at a turpentine opening (not shown) with the blade implant portion 2 as a turbine rotor blade structure. I have.
- the snubber cover 3 is formed from a crank-shaped notch surface 7 a and two abutting surfaces 6 a 1, 6 a 2 on the respective surfaces located on the wing back side and the wing abdomen side of the wing effective portion 1. . Then, by contacting the notched surfaces 7a and 7b and the butted surfaces 6a1, 6bl, 6a2 and 6b2 of the adjacent wings with each other, the frictional force is used to control the vibration. Power is increasing.
- Such a snubber rotor blade has a cutout surface 7a on both the ventral side and the rear side of the effective blade portion 1, so that the frictional force can be used effectively, and the rotor wheel 4
- the same effect can be obtained for all circumferential group wings arranged in a row in the circumferential direction, so that the damping effect of vibration suppression is further enhanced.
- the magnitude of the contact surface pressure has an effect on the vibration damping effect. Therefore, it is effective for long wings that are twisted back during operation.
- the turbine blade of the snubber structure has one centrifugal force generated during operation even if one snubber cover 3a and the adjacent snubber cover 3b, 3b are in close contact with each other.
- the snubber cover 3a floats up, or there is a gap between the cutout surfaces 7a and 7b due to the centrifugal force and the difference in thermal expansion of the material, creating a clearance between the snubber covers 3b, 3a, and 3b, and frictional force.
- the snubber covers 3 a, 3 b, 3 b in which the butting surfaces 6 a 1 (6 a 2) and 6 b 1 (6 b 2) are formed in a wedge shape require a lot of time for machining and assembly work.
- part of the centrifugal force generated during operation acts not only on the snubber cover 3a on which it acts but also on the snubber covers 3b, 3b adjacent to it, and based on this, the adjacent blade implants
- the centrifugal stress generated in the sample increased.
- another turbine blade having a snubber structure has a notch between one snubber cover 3a and the adjacent snubber cover 3b, as shown in FIG. 9, for example.
- the planes 7a and 7b are parallel to the rotation direction of the wing effective part 1. Proposed.
- Turbine blades with such a snapper structure do not lift the snubber cover 3a due to centrifugal force, nor do the clearances of the notched surfaces 7a and 7b due to the centrifugal force and the difference in thermal expansion of the material. It appears that the damping effect is seemingly high.
- the notch surfaces 7a and 7b of the notch 5 between the snubber cover 3a and the adjacent snubber cover 3b are parallel to the rotation direction of the blade effective portion 1. Therefore, the vibration damping effect during operation is effective for vibration in the direction different from the rotation direction, but the suppression of vibration that occurs in parallel to the rotation direction is limited by the frictional force acting on this parallel surface. As a result, it was not possible to secure a sufficient frictional force, and the damping effect was reduced accordingly.
- the present invention has been made in view of such circumstances, and with the simplification of the structure, the mating surface between one snubber cover and the adjacent snubber covers keeps the contact state constantly during operation. It is another object of the present invention to provide an evening bin rotor blade capable of sufficiently suppressing the vibration in the rotational direction of the effective blade portion. Disclosure of the invention
- a turbine rotor blade according to the present invention includes at least one end face of a snubber cover provided on a top of an effective blade portion and a snubber cover provided on a top of an adjacent effective blade portion. Wherein the end face has a predetermined inclination angle with respect to the direction of rotation of the blade effective portion.
- the blade effective portion rotation direction of the snubber cover The front and rear end surfaces are formed in a crank shape composed of two abutting surfaces and one contact end surface.
- the contact end face is formed in a rotation direction of the blade effective portion, and forms a predetermined inclination angle with the rotation direction.
- a turbine rotor blade according to the present invention includes an implant portion, an effective blade portion continuous with the implant portion, and an effective blade portion to achieve the above object.
- the snubber cover integrally provided at the end of the snubber cover and the snubber cover having the evening bin moving blade are viewed from the radial direction of the tarpin opening where the evening pin moving blade is planted.
- a contact surface formed substantially perpendicular to the rotation direction of the turbine rotor blade and at a position on the back side of the blade effective portion and on the opposite side of the blade effective portion to contact the adjacent rotor blade; And a fluid end face formed substantially at right angles to the contact surface or substantially parallel to the rotation direction of the turbine rotor blade and formed on the leading edge side and the trailing edge side of the blade effective portion, respectively.
- the contact surface has a predetermined distance It also consists of three consecutive surfaces consisting of a contact leading surface and a contact trailing surface that are parallel to each other and one contact friction surface that connects these two surfaces.
- the contact friction surface has a predetermined positive angle with respect to the rotation direction of the turbine moving blade.
- the turbine rotor blade according to the present invention includes, among the turbine rotor blades, a contact friction surface on the back side of the blade effective portion of one of the turbine rotor blades and the turbine rotor blade.
- the contact friction surface on the blade effective portion abdominal side of the other turbine rotor blade adjacent to the rotation direction side is fitted, and the contact friction surface on the blade effective portion abdominal side of the one turbine rotor blade and the tarpin
- the other circumference of the turbine blade adjacent to the rotor in the anti-rotational direction is fitted with the contact friction surface on the back side of the blade effective portion, and the entire circumference of the turbine pin blade that is planted at the evening bin opening are linked.
- FIG. 1 is a partially cutaway perspective view showing a turbine blade according to the present invention.
- FIG. 2 is a plan view showing a snubber cover provided on the top of the turbine rotor blade according to the present invention.
- FIG. 3 is a view of the behavior of the rotating pin rotor according to the present invention during rotation, as viewed from the axial direction of the bin.
- FIG. 4 is a plan view showing a behavior at the time of stationary and rotation when a part of the snubber cover provided at the top of the turbine rotor blade according to the present invention is enlarged.
- FIG. 5 is a plan view showing an assembled state of the snubber cover provided on the top of the turbine blade according to the present invention before operation. '
- FIG. 6 is a plan view showing an assembling state during operation of a snubber cover provided on the blade top of the evening pin rotor blade according to the present invention.
- FIG. 7 is a perspective view showing a conventional tarpin bucket.
- FIG. 8 is a side view showing a conventional turbine blade in which a mating surface between one snubber cover and an adjacent snubber cover is formed in an inclined shape.
- FIG. 9 is a plan view showing an assembled state of a conventional snubber cover before operation.
- FIG. 1 is a partially cutaway perspective view showing an embodiment of a turbine bucket according to the present invention.
- the turbine rotor blade according to the present embodiment has a blade implanted portion 11 implanted in the rotor wheel 10, and a working fluid, for example, a blade effective portion 12 that turns steam and guides it to the next paragraph, A snubber cover 13 (13a, 13b, 13c) provided on the wing effective portion 12 (12a, 12b, 12c) is provided.
- the wing implant 11, effective wing 12, and snubber cover 13 are integrally manufactured from the wing body, or separately manufactured into the wing implant 11, effective wing 12 machined from the wing body. 1 3 at the tip of the effective wing 1 2 It is configured as an integral structure joined by a metallurgical method such as welding.
- the snubber cover 13b provided on the top of the wing effective portion 12b has a contact surface 14bF, 1 at a position substantially perpendicular to the rotation direction of the wing and in the direction of the back and the abdomen of the wing.
- contact surfaces 14b F and 14bB are two surfaces that are substantially perpendicular to the direction of rotation of the wing and are substantially parallel to each other with a predetermined distance from each other, a contact leading surface 15bF l (15 bB 1) It consists of three surfaces, a contact trailing surface 15bF2 (15bB2) and a contact friction surface 16bF (16bB) connecting these two surfaces, and forms a crank-like surface as a whole. I have.
- the snubber cover 13b is provided at a position in the direction of the blade tip and is substantially parallel to the rotation direction thereof, and a fluid inlet end face 17bL connecting the contact leading surfaces 15bF1 and 15bB1 with each other;
- a fluid outlet end face 17bT is provided at a position in the direction of the trailing edge of the blade and is substantially parallel to the rotational direction thereof and connects the contact trailing faces 15bF2 and 15bB2.
- the contact leading surface 15bF1 and the contact trailing surface 15bF2 of the contact surface 14bF are connected to the wing effective portion 12c of the other adjacent wing effective portion 12c.
- the snubber cover has a contact friction surface 16 aF (16 aB) provided on one of the snapper covers 13 a having a predetermined positive value with respect to the rotational direction of the blade effective portion 12 a. It is formed to have an angle ⁇ .
- B is also shaped so as to have a predetermined positive angle with respect to the rotation direction of the wing effective portion 12b. Has been established.
- the contact surface 14bF (14bB) does not necessarily need to be in contact with the contact leading surface 15 bF l (15 bB 1) and the contact trailing surface 15 bF2 (15 bB 2), and has small gaps A and B. May be facing each other.
- the contact friction surface 16 aF (16 aB) and the contact friction surface 16 bF (16 bB) Due to the contact with each other at a positive angle ⁇ with respect to the rotation direction, vibration modes in the same direction as the rotation direction are generated in the effective blade portions 12a and 12b, and the relative distances approach or move away from each other. Contact, the contact is always maintained at the contact point C. As a result, the vibration can be effectively attenuated by the frictional force acting on the contact portion C.
- Fig. 3 is a view of the rotor blade viewed from the axial direction of the turbine port.
- the solid line shows the position of the moving blades at rest, and is implanted at the pitch P at the rotor blade 10 via the implanted portion 11 at the pitch P.
- the dashed line indicates the portion where the AL extends in the longitudinal direction of the blade due to the centrifugal force and the thermal expansion of the steam caused by the rotation of the blade.
- the pitch P at rest is changed from the pitch P at rest to the pitch P 'increased by ⁇ P due to the effect of ⁇ L.
- FIG. 4 is an enlarged view of the contact friction surfaces 16aF and 16bB of the contact surfaces 14aF and 14bB of the snubber covers 13a and 13b of the present invention.
- the contact leading surface 15aF1 and the other contact trailing surface 15bB1 face each other with a gap B in addition to a certain gap B, and one contact leading surface 15aF2 and the other After the contact with the surface 15 b B 2, it has a certain gap A and ⁇ ⁇ . Further, at this time, since the contact friction surface 16aF and the other contact friction surface 16bB have an angle ⁇ ;, the surfaces overlap each other as shown by hatching in the figure. Actually, the overlapping portion is elastically deformed and acts as a contact surface pressure on each surface. That is, in the contact friction surface of the present invention, if the pitch of the wing is widened, the surface pressure of the contact friction surface increases, and the vibration acts in a direction to attenuate the vibration.
- FIG. 5 and 6 are plan views of applying the snubber cover according to the present invention to a turbine blade.
- Fig. 5 is a plan view from the top of the snubber cover during assembly (or at rest)
- Fig. 6 is a view from the top of the snubber cover during operation (rotation). It is a top view.
- the rotational directions of the blade effective portions 12a and 12b are provided on the contact friction surfaces 16aF and 16bB.
- a predetermined positive angle ⁇ is formed, and by adopting such a structure, during operation, the pitch between the effective blade portions 12a and 12b increases by ⁇ P,
- the gap A between the leading contact surface 15aF1 and the trailing surface 15bB1 and the gap B between the leading contact surface 15aF2 and the trailing surface 15bB2 also increase by the pitch ⁇ ⁇ ⁇ ⁇ .
- the contact portion can always be secured between the contact friction surfaces 16aF and 16bB, even if vibration occurs in the same direction as the rotation direction of the wing effective portions 12a and 12b, the mating end surface C It is possible to sufficiently secure the frictional force and the necessary contact pressure when the contact surface oscillates.
- the vibration can be sufficiently suppressed, and the turbine blade can be operated in a stable state. be able to.
- the snubber cover 13 (13a, 13b) applied to the turbine rotor blade according to the present embodiment can be applied to any of the high-pressure, medium-pressure and low-pressure sections of the turbine. When applied to the section and the medium pressure section, the vibration damping effect is extremely high, which is preferable. Industrial applicability
- the turpentine rotor blade according to the present invention includes a snubber cover provided on the top of one effective blade portion and a snubber cover provided on the top of an adjacent effective blade portion, each of which has a plurality of end faces.
- the contact friction surface which is one of the crank-shaped contact surfaces, has a positive inclination of 0! With respect to the rotation direction of the wing effective part. Therefore, even during operation, even if the pitch between the effective blade portions becomes large, a contact portion can always be secured, and sufficient measures can be taken even if vibration occurs in the same direction as the rotation direction of the effective blade portion. With a sufficient vibration damping effect, a stable operation state of the tarpin can be ensured.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AU2003241680A AU2003241680B2 (en) | 2002-05-31 | 2003-05-30 | Turbine moving blade |
US10/516,171 US20060002798A1 (en) | 2002-05-31 | 2003-05-30 | Turbine moving blade |
EP03733210A EP1512837B1 (en) | 2002-05-31 | 2003-05-30 | Turbine blade arrangement |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2002160512 | 2002-05-31 | ||
JP2002-160512 | 2002-05-31 | ||
JP2003149770A JP2004052757A (ja) | 2002-05-31 | 2003-05-27 | タービン動翼 |
JP2003-149770 | 2003-05-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2003102378A1 true WO2003102378A1 (fr) | 2003-12-11 |
Family
ID=29714313
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2003/006879 WO2003102378A1 (fr) | 2002-05-31 | 2003-05-30 | Aube mobile de turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20060002798A1 (ja) |
EP (1) | EP1512837B1 (ja) |
JP (1) | JP2004052757A (ja) |
CN (1) | CN100414075C (ja) |
AU (1) | AU2003241680B2 (ja) |
WO (1) | WO2003102378A1 (ja) |
Families Citing this family (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7344359B2 (en) * | 2005-06-02 | 2008-03-18 | General Electric Company | Methods and systems for assembling shrouded turbine bucket and tangential entry dovetail |
JP4673732B2 (ja) * | 2005-12-01 | 2011-04-20 | 株式会社東芝 | タービン動翼および蒸気タービン |
JP2007303440A (ja) * | 2006-05-15 | 2007-11-22 | Toshiba Corp | タービンおよびタービン動翼 |
JP4886735B2 (ja) | 2008-05-26 | 2012-02-29 | 株式会社東芝 | タービン動翼組立体および蒸気タービン |
DE102010041808B4 (de) * | 2010-09-30 | 2014-10-23 | Siemens Aktiengesellschaft | Schaufelkranzsegment, Strömungsmaschine sowie Verfahren zu deren Herstellung |
JP5843482B2 (ja) * | 2011-05-23 | 2016-01-13 | 株式会社東芝 | タービン動翼および蒸気タービン |
US20130209258A1 (en) * | 2012-02-15 | 2013-08-15 | General Electric Company | Tip shrouded blade |
ITTO20120517A1 (it) * | 2012-06-14 | 2013-12-15 | Avio Spa | Schiera di profili aerodinamici per un impianto di turbina a gas |
CN102877892B (zh) * | 2012-10-23 | 2015-02-11 | 湖南航翔燃气轮机有限公司 | 一种涡轮转子叶片及具有其的燃气轮机 |
JP5956365B2 (ja) * | 2013-02-28 | 2016-07-27 | 三菱日立パワーシステムズ株式会社 | タービン動翼列組立体、および蒸気タービン設備 |
EP2792848A1 (de) * | 2013-04-17 | 2014-10-22 | Siemens Aktiengesellschaft | Verfahren zum Wiederherstellen der Deckplattenvorspannung einer Turbinenbeschaufelung |
DE102013212252A1 (de) * | 2013-06-26 | 2014-12-31 | Siemens Aktiengesellschaft | Turbine und Verfahren zur Anstreiferkennung |
JP6066948B2 (ja) | 2014-03-13 | 2017-01-25 | 三菱重工業株式会社 | シュラウド、動翼体、及び回転機械 |
EP3042737A1 (de) * | 2015-01-12 | 2016-07-13 | Siemens Aktiengesellschaft | Verfahren zur montage von laufschaufeln an einer rotorscheibe sowie spannvorrichtung zur durchführung eines solchen verfahrens |
GB2547273A (en) * | 2016-02-15 | 2017-08-16 | Rolls Royce Plc | Stator vane |
KR101874243B1 (ko) * | 2017-03-31 | 2018-07-03 | 두산중공업 주식회사 | 버킷의 진동감쇠구조와 이를 포함하는 버킷 및 터보머신 |
CN113550827A (zh) * | 2021-08-04 | 2021-10-26 | 哈尔滨工业大学 | 一种扇形叶栅叶片及其角度安装方法 |
JP2023119098A (ja) * | 2022-02-16 | 2023-08-28 | 三菱重工航空エンジン株式会社 | タービン |
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JPS60116002U (ja) * | 1984-01-13 | 1985-08-06 | 株式会社日立製作所 | タ−ビン動翼連結装置 |
US4710102A (en) * | 1984-11-05 | 1987-12-01 | Ortolano Ralph J | Connected turbine shrouding |
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JPH07332003A (ja) | 1994-06-13 | 1995-12-19 | Hitachi Ltd | タービン動翼 |
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JPH0972202A (ja) * | 1995-09-06 | 1997-03-18 | Hitachi Ltd | タービン動翼の連結構造及びその方法 |
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JP2000018002A (ja) | 1998-07-07 | 2000-01-18 | Mitsubishi Heavy Ind Ltd | 蒸気タービンの動翼 |
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GB2251034B (en) * | 1990-12-20 | 1995-05-17 | Rolls Royce Plc | Shrouded aerofoils |
US5482435A (en) * | 1994-10-26 | 1996-01-09 | Westinghouse Electric Corporation | Gas turbine blade having a cooled shroud |
US6827554B2 (en) * | 2003-02-25 | 2004-12-07 | General Electric Company | Axial entry turbine bucket dovetail with integral anti-rotation key |
US7009137B2 (en) * | 2003-03-27 | 2006-03-07 | Honeywell International, Inc. | Laser powder fusion repair of Z-notches with nickel based superalloy powder |
-
2003
- 2003-05-27 JP JP2003149770A patent/JP2004052757A/ja active Pending
- 2003-05-30 AU AU2003241680A patent/AU2003241680B2/en not_active Ceased
- 2003-05-30 WO PCT/JP2003/006879 patent/WO2003102378A1/ja active Application Filing
- 2003-05-30 US US10/516,171 patent/US20060002798A1/en not_active Abandoned
- 2003-05-30 EP EP03733210A patent/EP1512837B1/en not_active Expired - Lifetime
- 2003-05-30 CN CNB038126060A patent/CN100414075C/zh not_active Expired - Fee Related
Patent Citations (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB622019A (en) | 1946-04-06 | 1949-04-26 | United Aircraft Corp | Improvements in or relating to turbine rotors |
GB2072760A (en) * | 1980-03-29 | 1981-10-07 | Rolls Royce | Shrouded turbine rotor blade |
JPS5776208A (en) | 1980-10-30 | 1982-05-13 | Toshiba Corp | Turbine vane |
JPS60116002U (ja) * | 1984-01-13 | 1985-08-06 | 株式会社日立製作所 | タ−ビン動翼連結装置 |
US4710102A (en) * | 1984-11-05 | 1987-12-01 | Ortolano Ralph J | Connected turbine shrouding |
GB2215407A (en) | 1988-03-05 | 1989-09-20 | Rolls Royce Plc | A bladed rotor assembly |
JPH07332003A (ja) | 1994-06-13 | 1995-12-19 | Hitachi Ltd | タービン動翼 |
US5509784A (en) | 1994-07-27 | 1996-04-23 | General Electric Co. | Turbine bucket and wheel assembly with integral bucket shroud |
JPH0972202A (ja) * | 1995-09-06 | 1997-03-18 | Hitachi Ltd | タービン動翼の連結構造及びその方法 |
JPH10103003A (ja) * | 1996-09-26 | 1998-04-21 | Toshiba Corp | タービン動翼及びその組立方法 |
JP2000018002A (ja) | 1998-07-07 | 2000-01-18 | Mitsubishi Heavy Ind Ltd | 蒸気タービンの動翼 |
JP2001152803A (ja) * | 1999-11-30 | 2001-06-05 | Mitsubishi Heavy Ind Ltd | シュラウドコンタクト面のコーティング方法およびシュラウド付き動翼 |
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JP6060563B2 (ja) * | 2012-08-24 | 2017-01-18 | セイコーエプソン株式会社 | 心房細動判定装置、心房細動判定方法およびプログラム |
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Also Published As
Publication number | Publication date |
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CN100414075C (zh) | 2008-08-27 |
EP1512837B1 (en) | 2012-05-23 |
JP2004052757A (ja) | 2004-02-19 |
AU2003241680B2 (en) | 2008-02-07 |
AU2003241680A1 (en) | 2003-12-19 |
EP1512837A1 (en) | 2005-03-09 |
US20060002798A1 (en) | 2006-01-05 |
CN1659361A (zh) | 2005-08-24 |
EP1512837A4 (en) | 2007-08-08 |
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