US3290004A - Device for damping vibration of long steam-turbine blades - Google Patents
Device for damping vibration of long steam-turbine blades Download PDFInfo
- Publication number
- US3290004A US3290004A US540973A US54097366A US3290004A US 3290004 A US3290004 A US 3290004A US 540973 A US540973 A US 540973A US 54097366 A US54097366 A US 54097366A US 3290004 A US3290004 A US 3290004A
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- US
- United States
- Prior art keywords
- blade
- shroud
- turbine blades
- steam
- blades
- 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.)
- Expired - Lifetime
Links
- 238000013016 damping Methods 0.000 title description 11
- 230000000694 effects Effects 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 1
- 238000013017 mechanical damping Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
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
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
- Y10S416/50—Vibration damping features
Definitions
- This invention relates to the vibration damping of steam-turbine blades and more particularly of long shrouded type blades and has for its object to minimize the stress caused in the material of long blades by vibration to which they are subjected thereby to prevent their otherwise occurring failure.
- the present invention is intended to cope with the above situation and proposes to design long turbine blades and particularly the extreme end portions thereof relative to the shrouding structure so as to obtain a large mechanical damping effect thereby to minimize the vibrational stress caused in the material of the blades.
- such damping characteristic is obtained by utilizing the drain formed on the turbine blades and previously regarded as entirely useless and harmful by introducing it as a damping fluid into a space provided between the blade end and the adjacent shroud portion.
- FIG. 1 is a fragmentary sketch of the tip portion of a typical conventional steam-turbine blade
- FIG. 2 is a cross-sectional view taken along the line AA in FIG. 1;
- FIGS. 3 to 7 illustrate one preferred embodiment of the present invention
- FIG. 3 is a fragmentary sketch of the blade tip
- FIG. 4 is a fragmentary transverse crosssectional view of the shrouded blade assembly
- FIG. 5 is a fragmentary perspective view of the blade tip, showing recessed grooves for drain separation and small drain apertures formed in the blade
- FIG. 6 is a cross-sectional view taken along the line B-B' in FIG. 5
- FIG. 7 is an explanatory cross-sectional view of the blade assembly lustrating the flow of drain therein.
- the shroud 3 is usually aflixed to the blade 1 by upsetting tenons 2 formed thereon, as shown in FIG. 2.
- Such tenon structure involves a disadvantage that heavy stresses inevitably evolve in the tenons 2 under centrifugal forces since they cannot be made with any satisfactorily large cross-sectional area. If the tenons were designed large enough, the adjacent portions of the shroud would be undesirably reduced in effective crosssectional area.
- the shroud ring is partly formed integral with the blade 8, as indicated at 4 in FIG. 3, by machining.
- the shroud section 4 can obviously be designed to have a large strength compared with the conventional tenon structure.
- Formed in the shroud section 4 is a number of small apertures, some of 3,290,004 Patented Dec. 6, 1966 which are shown in FIG. 3 at 5, to serve as passageways for directing the drain formed on the blade and collected through grooves 6 formed therein into gaps between the flanged blade end or shroud section 4 and the remainder of the shroud structure.
- FIG. 4 fragmentarily illustrates a typical shrouded blade system employing shroud sections 4 formed integral with respective blades 8, in cross section at right angles to the turbine shaft.
- the main shroud ring structure in this case is composed of shroud sections 9 and an annular plate 10, which are fixedly joined together by rivets 11, as shown, or alternately by screw or spot-welding means.
- the shroud structure is so designed that, when assembled together with the flanged blades 8, a fine circumferentially extending space or gap 12 is formed between the end face of each of the blades or the shroud section 4 thereon and the adjacent inner surface of the annular plate 10 and fine radially extending spaces or gaps 13 and 14 are formed between the flanged tip of each blade 8 or the shroud section 4 integral therewith and the two adjacent shroud sections 9 joined to the annular plate 10.
- grooves 6 formed in the blade adjacent to its extreme end and in the vicinity of the steam inlet side of the blade extend substantially radially or along the axis of the blade to serve the purpose of drain separation, and the drain formed in the flow of steam is mostly collected in such grooves, as indicated by the dotted arrows 7 in FIG. 6.
- the device of the present invention has a high vibration-damping effect and is highly valuable in the industry.
- a device for damping vibration of shrouded long steam-turbine blades comprising a spacing provided between the extreme end portion of the blade and the associated shroud structure and means for directing steam drain into said spacing.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
Dec. 6, 1966 EllCHl ISHIBASHI DEVICE FOR DAMPING VIBRATION OF LONG STEAM-TURBINE BLADES Filed April 7, 1966 ATTORNEY United States Patent 3,290,004 DEVICE FOR DAMPING VIBRATION 0F LONG STEAM-TURBINE BLADES Eiichi Ishibashi, Hitachi-shi, Japan, assignor to Hitachi, Ltd., Tokyo, Japan, a corporation of Japan Filed Apr. 7, 1966, Ser. No. 540,973 Claims priority, application Japan, Apr. 9, 1965, 40/ 20,544 1 Claim. (Cl. 253-77) This invention relates to the vibration damping of steam-turbine blades and more particularly of long shrouded type blades and has for its object to minimize the stress caused in the material of long blades by vibration to which they are subjected thereby to prevent their otherwise occurring failure.
In recent years, with increase in the output of steam turbines, the length of blades in low-pressure stages has been increased markedly, making it necessary to impart to such blades a sufficient strength to withstand huge centrifugal forces While allowing them to vibrate only in modes outside the normal range of turbine speed.
The present invention is intended to cope with the above situation and proposes to design long turbine blades and particularly the extreme end portions thereof relative to the shrouding structure so as to obtain a large mechanical damping effect thereby to minimize the vibrational stress caused in the material of the blades.
According to the present invention, such damping characteristic is obtained by utilizing the drain formed on the turbine blades and previously regarded as entirely useless and harmful by introducing it as a damping fluid into a space provided between the blade end and the adjacent shroud portion.
The foregoing and other objects, features and advantages of the present invention will become apparent from the following description when taken in conjunction with the accompanying drawings, in which:
FIG. 1 is a fragmentary sketch of the tip portion of a typical conventional steam-turbine blade;
FIG. 2 is a cross-sectional view taken along the line AA in FIG. 1; and
FIGS. 3 to 7 illustrate one preferred embodiment of the present invention; FIG. 3 is a fragmentary sketch of the blade tip; FIG. 4 is a fragmentary transverse crosssectional view of the shrouded blade assembly; FIG. 5 is a fragmentary perspective view of the blade tip, showing recessed grooves for drain separation and small drain apertures formed in the blade; FIG. 6 is a cross-sectional view taken along the line B-B' in FIG. 5 and FIG. 7 is an explanatory cross-sectional view of the blade assembly lustrating the flow of drain therein.
In cases where long turbine blades are shrouded, the shroud 3 is usually aflixed to the blade 1 by upsetting tenons 2 formed thereon, as shown in FIG. 2. Such tenon structure, however, involves a disadvantage that heavy stresses inevitably evolve in the tenons 2 under centrifugal forces since they cannot be made with any satisfactorily large cross-sectional area. If the tenons were designed large enough, the adjacent portions of the shroud would be undesirably reduced in effective crosssectional area.
According to the present invention, the shroud ring is partly formed integral with the blade 8, as indicated at 4 in FIG. 3, by machining. The shroud section 4 can obviously be designed to have a large strength compared with the conventional tenon structure. Formed in the shroud section 4 is a number of small apertures, some of 3,290,004 Patented Dec. 6, 1966 which are shown in FIG. 3 at 5, to serve as passageways for directing the drain formed on the blade and collected through grooves 6 formed therein into gaps between the flanged blade end or shroud section 4 and the remainder of the shroud structure.
FIG. 4 fragmentarily illustrates a typical shrouded blade system employing shroud sections 4 formed integral with respective blades 8, in cross section at right angles to the turbine shaft. The main shroud ring structure in this case is composed of shroud sections 9 and an annular plate 10, which are fixedly joined together by rivets 11, as shown, or alternately by screw or spot-welding means. In order to attain the object of the present invention, the shroud structure is so designed that, when assembled together with the flanged blades 8, a fine circumferentially extending space or gap 12 is formed between the end face of each of the blades or the shroud section 4 thereon and the adjacent inner surface of the annular plate 10 and fine radially extending spaces or gaps 13 and 14 are formed between the flanged tip of each blade 8 or the shroud section 4 integral therewith and the two adjacent shroud sections 9 joined to the annular plate 10.
Referring next to FIGS. 5 and 6, grooves 6 formed in the blade adjacent to its extreme end and in the vicinity of the steam inlet side of the blade extend substantially radially or along the axis of the blade to serve the purpose of drain separation, and the drain formed in the flow of steam is mostly collected in such grooves, as indicated by the dotted arrows 7 in FIG. 6.
Though, in the past, steam drain collected on turbine blades has been regarded as useless and harmful and removed exteriorly of the turbine casing, it is utilized according to the present invention as a vibration-damping fluid to serve between the flanged blade 8 and the main shroud structure 9-10. For this purpose, small apertures 5 are formed in the end face of the blade 8 or in the shroud section 4 integral therewith to communicate with the drain grooves 6 formed in the side of the blade. Re ferring to FIG. 7, the steam drain collected in the grooves 6, as indicated by the dotted arrows 7, flows radially out wardly along the grooves, as indicated by the arrow a, and through the apertures 5 into the gap 12 between the shroud section 4 and the annular plate 10 and further into gaps 13 and 14, as indicated by the arrows b and c to act upon the blade 8 as a powerful damping fluid. Another important advantage of this arrangement is that the frictional drag acting between the shroud sections 4 and 9 also has a substantial damping effect, as will be readily understood.
It will be appreciated from the foregoing that the device of the present invention has a high vibration-damping effect and is highly valuable in the industry.
What is claimed is:
A device for damping vibration of shrouded long steam-turbine blades comprising a spacing provided between the extreme end portion of the blade and the associated shroud structure and means for directing steam drain into said spacing.
References Cited by the Examiner UNITED STATES PATENTS 1,829,674 10/ 1931 Rosenlocher 25 376 2,221,678 ll/ 1940 Hechman 253-77 2,292,072 8/ 1942 Hanna et a1 25 3-77 2,349,187 5/1944 Meyer 253--77 MARTIN P. SCHWADRON, Primary Examiner.
E. A. POWELL, ]R., Assistant Examiner.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2054465 | 1965-04-09 |
Publications (1)
Publication Number | Publication Date |
---|---|
US3290004A true US3290004A (en) | 1966-12-06 |
Family
ID=12030081
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US540973A Expired - Lifetime US3290004A (en) | 1965-04-09 | 1966-04-07 | Device for damping vibration of long steam-turbine blades |
Country Status (2)
Country | Link |
---|---|
US (1) | US3290004A (en) |
GB (1) | GB1087514A (en) |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3527544A (en) * | 1968-12-12 | 1970-09-08 | Gen Motors Corp | Cooled blade shroud |
US3973870A (en) * | 1974-11-04 | 1976-08-10 | Westinghouse Electric Corporation | Internal moisture removal scheme for low pressure axial flow steam turbine |
US4050845A (en) * | 1975-09-30 | 1977-09-27 | Kraftwerk Union Aktiengesellschaft | Device for stabilizing the position of rotors of large steam turbines |
US4257742A (en) * | 1978-04-03 | 1981-03-24 | Tokyo Shibaura Denki Kabushiki Kaisha | Device for interconnecting turbine blades |
US5261785A (en) * | 1992-08-04 | 1993-11-16 | General Electric Company | Rotor blade cover adapted to facilitate moisture removal |
AU770671B2 (en) * | 1999-05-07 | 2004-02-26 | Abbvie Deutschland Gmbh & Co Kg | Use of dopamine D3 receptor ligands for producing medicaments for treating kidney disorders |
US20040241003A1 (en) * | 2003-05-29 | 2004-12-02 | Francois Roy | Turbine blade dimple |
US20060263223A1 (en) * | 2005-05-18 | 2006-11-23 | Hartzell Fan, Inc. | Fan blade with ridges |
US20060269401A1 (en) * | 2005-05-31 | 2006-11-30 | General Electric Company | Moisture removal grooves on steam turbine buckets and covers and methods of manufacture |
EP1764479A1 (en) * | 2005-09-15 | 2007-03-21 | ALSTOM Technology Ltd | Coupled shroud plates for a row of blades of a turbomachine |
WO2007031408A1 (en) * | 2005-09-15 | 2007-03-22 | Alstom Technology Ltd | Cover strip comprising a detachable anchoring for a row of blades of a turbomachine |
US20070128035A1 (en) * | 2005-08-26 | 2007-06-07 | Siemens Aktiengesellschaft | Hollow turbine blade |
US20100008785A1 (en) * | 2008-07-14 | 2010-01-14 | Marc Tardif | Dynamically tuned turbine blade growth pocket |
WO2011007506A1 (en) * | 2009-07-14 | 2011-01-20 | 株式会社 東芝 | Steam turbine |
US20140227102A1 (en) * | 2011-06-01 | 2014-08-14 | MTU Aero Engines AG | Rotor blade for a compressor of a turbomachine, compressor, and turbomachine |
US11858615B2 (en) | 2022-01-10 | 2024-01-02 | General Electric Company | Rotating airfoil assembly with opening formed therein to eject or to draw air |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1829674A (en) * | 1928-12-08 | 1931-10-27 | Gen Electric | Elastic fluid turbine and the like |
US2221678A (en) * | 1938-08-30 | 1940-11-12 | Gen Electric | Elastic fluid turbine bucket wheel |
US2292072A (en) * | 1940-01-10 | 1942-08-04 | Westinghouse Electric & Mfg Co | Turbine blade vibration damper |
US2349187A (en) * | 1941-03-08 | 1944-05-16 | Westinghouse Electric & Mfg Co | Vibration dampener |
-
1966
- 1966-04-07 US US540973A patent/US3290004A/en not_active Expired - Lifetime
- 1966-04-07 GB GB15704/66A patent/GB1087514A/en not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1829674A (en) * | 1928-12-08 | 1931-10-27 | Gen Electric | Elastic fluid turbine and the like |
US2221678A (en) * | 1938-08-30 | 1940-11-12 | Gen Electric | Elastic fluid turbine bucket wheel |
US2292072A (en) * | 1940-01-10 | 1942-08-04 | Westinghouse Electric & Mfg Co | Turbine blade vibration damper |
US2349187A (en) * | 1941-03-08 | 1944-05-16 | Westinghouse Electric & Mfg Co | Vibration dampener |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3527544A (en) * | 1968-12-12 | 1970-09-08 | Gen Motors Corp | Cooled blade shroud |
US3973870A (en) * | 1974-11-04 | 1976-08-10 | Westinghouse Electric Corporation | Internal moisture removal scheme for low pressure axial flow steam turbine |
US4050845A (en) * | 1975-09-30 | 1977-09-27 | Kraftwerk Union Aktiengesellschaft | Device for stabilizing the position of rotors of large steam turbines |
US4257742A (en) * | 1978-04-03 | 1981-03-24 | Tokyo Shibaura Denki Kabushiki Kaisha | Device for interconnecting turbine blades |
US5261785A (en) * | 1992-08-04 | 1993-11-16 | General Electric Company | Rotor blade cover adapted to facilitate moisture removal |
AU770671B2 (en) * | 1999-05-07 | 2004-02-26 | Abbvie Deutschland Gmbh & Co Kg | Use of dopamine D3 receptor ligands for producing medicaments for treating kidney disorders |
US20040241003A1 (en) * | 2003-05-29 | 2004-12-02 | Francois Roy | Turbine blade dimple |
US6976826B2 (en) | 2003-05-29 | 2005-12-20 | Pratt & Whitney Canada Corp. | Turbine blade dimple |
US20060263223A1 (en) * | 2005-05-18 | 2006-11-23 | Hartzell Fan, Inc. | Fan blade with ridges |
US7494325B2 (en) * | 2005-05-18 | 2009-02-24 | Hartzell Fan, Inc. | Fan blade with ridges |
US7318699B2 (en) * | 2005-05-31 | 2008-01-15 | General Electric Company | Moisture removal grooves on steam turbine buckets and covers and methods of manufacture |
US20060269401A1 (en) * | 2005-05-31 | 2006-11-30 | General Electric Company | Moisture removal grooves on steam turbine buckets and covers and methods of manufacture |
US20070128035A1 (en) * | 2005-08-26 | 2007-06-07 | Siemens Aktiengesellschaft | Hollow turbine blade |
US7845905B2 (en) * | 2005-08-26 | 2010-12-07 | Siemens Aktiengesellschaft | Hollow turbine blade |
US7874791B2 (en) | 2005-09-15 | 2011-01-25 | Alstom Technology Ltd. | Turbomachine |
US20070212215A1 (en) * | 2005-09-15 | 2007-09-13 | Joergen Ferber | Turbomachine |
EP1764479A1 (en) * | 2005-09-15 | 2007-03-21 | ALSTOM Technology Ltd | Coupled shroud plates for a row of blades of a turbomachine |
WO2007031408A1 (en) * | 2005-09-15 | 2007-03-22 | Alstom Technology Ltd | Cover strip comprising a detachable anchoring for a row of blades of a turbomachine |
US8167572B2 (en) | 2008-07-14 | 2012-05-01 | Pratt & Whitney Canada Corp. | Dynamically tuned turbine blade growth pocket |
US20100008785A1 (en) * | 2008-07-14 | 2010-01-14 | Marc Tardif | Dynamically tuned turbine blade growth pocket |
US8499449B2 (en) | 2008-07-14 | 2013-08-06 | Pratt & Whitney Canada Corp. | Method for manufacturing a turbine blade |
WO2011007506A1 (en) * | 2009-07-14 | 2011-01-20 | 株式会社 東芝 | Steam turbine |
CN102472116A (en) * | 2009-07-14 | 2012-05-23 | 株式会社东芝 | Steam turbine |
JP2011021519A (en) * | 2009-07-14 | 2011-02-03 | Toshiba Corp | Steam turbine |
KR101443988B1 (en) | 2009-07-14 | 2014-09-23 | 가부시끼가이샤 도시바 | Steam turbine |
CN102472116B (en) * | 2009-07-14 | 2014-10-01 | 株式会社东芝 | Steam turbine |
CZ305769B6 (en) * | 2009-07-14 | 2016-03-09 | Kabushiki Kaisha Toshiba | Steam turbine |
US20140227102A1 (en) * | 2011-06-01 | 2014-08-14 | MTU Aero Engines AG | Rotor blade for a compressor of a turbomachine, compressor, and turbomachine |
US11858615B2 (en) | 2022-01-10 | 2024-01-02 | General Electric Company | Rotating airfoil assembly with opening formed therein to eject or to draw air |
Also Published As
Publication number | Publication date |
---|---|
GB1087514A (en) | 1967-10-18 |
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