WO2008061856A1 - Schaufelanordnung - Google Patents
Schaufelanordnung Download PDFInfo
- Publication number
- WO2008061856A1 WO2008061856A1 PCT/EP2007/061469 EP2007061469W WO2008061856A1 WO 2008061856 A1 WO2008061856 A1 WO 2008061856A1 EP 2007061469 W EP2007061469 W EP 2007061469W WO 2008061856 A1 WO2008061856 A1 WO 2008061856A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- damping elements
- rotor
- contact
- damping
- blades
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
- F01D11/006—Sealing the gap between rotor blades or blades and rotor
- F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
-
- 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
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/231—Three-dimensional prismatic cylindrical
-
- 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
- the invention relates to a blade arrangement, comprising a rotor and a plurality of blades arranged on the circumference of the rotor in a ring, wherein between two immediately adjacent blades at least two damping elements in the circumferential direction of the rotor are arranged one behind the other, and wherein acting through a radially
- Centrifugal force in a rotation of the rotor about a rotor axis adjacent damping elements contact each other and contact one of the two damping elements with one of the two blades and the other of the two damping elements with the other of the two blades in contact.
- a blade arrangement in which at least two damping elements are arranged between adjacent blades in the circumferential direction of the rotor one behind the other, in order to achieve an effective damping of the entire blade arrangement.
- the damping elements disclosed in this document are designed in divergent form in order to be able to damp as many different vibration modes as possible.
- contact areas can be converted to vibration damping by friction effect vibration energy in heat energy.
- the contact areas formed between the individual damping elements only have the form of a line contact with which only a slightly pronounced damping effect is associated.
- the invention has for its object to provide a Schaufelanord- tion with damping elements, with the unwanted vibrations can be attenuated more effectively.
- the position of the damping elements is neither underdetermined nor overdetermined.
- the best possible damping in a split damper can be achieved.
- the contact areas of adjacent damping elements which form during rotor rotation are designed in the form of a planar contact. In this way, the entire provided friction surface between the damping elements is significantly increased compared to known blade arrangements, in which the damping elements only come into contact with one another in the form of a line contact. The increase of the invention
- Friction surface causes a very effective vibration damping of the entire blade assembly. Also different vibration modes can be effectively damped. Overall, the blade arrangement according to the invention enables a reduction of the vibration amplitudes and stresses by additional friction damping.
- the contact between one of the two damping elements and one of the two blades is a flat contact and the contact of the other damping element and the other blade is a line-like contact.
- the single line contact could also be provided between the damping elements.
- the damping elements differ in their geometric shape. According to the invention can thus with suitably shaped damping elements Vibration modes are effectively damped, which can not be effectively damped with the same design of all damping elements.
- the damping elements can also differ in their masses in order to effectively dampen the greatest possible number of different vibration modes by combination with suitable geometric shapes.
- the friction conditions coefficient of friction, roughness
- the friction conditions in the contact areas can be influenced, in order to enable targeted damping of several modes, even in increased frequency ranges.
- damping elements are preferably of rod-shaped design.
- two damping elements are arranged one behind the other in the circumferential direction of the rotor, wherein the damping elements are preferably rod-shaped and one damping element has a cross section of the shape of a wedge and the other damping element has a cross section of the shape of a quarter circle ,
- the damping elements are preferably rod-shaped and one damping element has a cross section of the shape of a wedge and the other damping element has a cross section of the shape of a quarter circle
- three damping elements are arranged one behind the other in the circumferential direction of the rotor.
- a further damping element which preferably has a different geometric shape than the other damping elements, optionally further disturbing vibration modes can be effectively damped.
- the two outer damping elements arranged one after the other in the circumferential direction of the rotor come into contact with the blades of the pair of vanes via friction surfaces which are formed on the vanes of the pair of vanes.
- the damping elements are made of steel or ceramic, ie materials, with which an effective damping can be realized.
- FIG. 1 schematically shows a section of a blade arrangement according to the invention in a sectional plane perpendicular to the rotor axis and FIG
- FIG. 2 schematically shows the arrangement of two damping element groups over the axial extent of a blade.
- FIG. 1 shows a schematic section of the blade arrangement 1 according to the invention in a sectional plane perpendicular to the rotor axis.
- the detail shows two blade platforms 3 of adjacent blades of the blade arrangement 1 according to the invention.
- the blades are suspended from the rotor disk of the blade arrangement 1 and are at a small distance from one another.
- two damping elements 5 and 7 are arranged loosely. Both damping elements 5, 7 form a damper group and are rod-shaped in the axial direction, wherein the damping element 7 has a quarter-circle-shaped cross section and the damping element 5 has a wedge-shaped cross section.
- the undersides of the two blade platforms 3 form friction surfaces 9, 11. against these friction surfaces 9, 11, the two damping elements 5, 7 upon rotation of the rotor (not shown) by the action of the centrifugal pressed force.
- the friction surfaces 9, 11 are here inclined at certain angles ⁇ and ⁇ to the plane which is spanned by the radial direction R and the rotor axis, so that they together form a V-shaped guide, in which the damping elements 5, 7 through the Centrifugal force are pressed.
- the wedge-shaped damping element 5 has a friction surface 13 whose inclination is adapted to the angle ⁇ in order to provide an effective areal frictional contact between the damping element 5 and the corresponding blade platform 3.
- the angles ⁇ and ⁇ are preferably in the range of 20 ° to 70 °, the range of 40 ° to 60 ° being more preferred.
- the damping elements 5 and 7 are formed and arranged in the circumferential direction of the rotor one behind the other, that the contact in the contact region 15 is a flat contact 15, as well as the contact between the damping element 5 and platform 3.
- the entire provided friction surface between the Dämpfungsele- Menten 5 and 7 compared to known blade arrangements significantly increased, in which the contact area between the damping elements is not formed as a flat contact, but in the form of a line contact (Hertz shear contact).
- there are two planar contacts and only one line contact namely between damping element 7 and platform 3).
- the friction surface additionally provided according to the invention via the flat contact 15 effects a very effective vibration damping of the entire blade arrangement 1.
- the flat contact 15 extends parallel to the radial direction R, but can be inclined by correspondingly selected angles ⁇ and ⁇ also to the radial direction R.
- the angle ⁇ is preferably within a range of 70 ° to 90 ° and the angle ⁇ within a range of 110 ° to 90 ° or vice versa.
- Fig. 2 shows schematically the arrangement of two damping element groups 25, 27.
- the positions of the damping element groups 25 and 27, each comprising a certain number of damping elements are indicated schematically by circles.
- the damping elements extend rod-shaped in the axial direction, wherein the groups along the axial extent of a blade 17 (axial direction 23) are distributed.
- the blade 17 comprises an airfoil 19, a blade platform 3, a blade root 21, a blade leading edge 29 and a blade trailing edge 31.
- Die Flow direction 33 is indicated by an arrow.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Processing Of Stones Or Stones Resemblance Materials (AREA)
- Power Steering Mechanism (AREA)
- Fluid-Damping Devices (AREA)
Abstract
Description
Claims
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2009537583A JP4806075B2 (ja) | 2006-11-23 | 2007-10-25 | 翼配置構造 |
CN2007800436875A CN101542073B (zh) | 2006-11-23 | 2007-10-25 | 叶片装置 |
EP07821832A EP2094946B1 (de) | 2006-11-23 | 2007-10-25 | Schaufelanordnung |
US12/515,845 US8167563B2 (en) | 2006-11-23 | 2007-10-25 | Blade arrangement |
AT07821832T ATE469288T1 (de) | 2006-11-23 | 2007-10-25 | Schaufelanordnung |
DE502007003972T DE502007003972D1 (de) | 2006-11-23 | 2007-10-25 | Schaufelanordnung |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP06024326.8 | 2006-11-23 | ||
EP06024326A EP1925781A1 (de) | 2006-11-23 | 2006-11-23 | Schaufelanordnung |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2008061856A1 true WO2008061856A1 (de) | 2008-05-29 |
Family
ID=37888032
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2007/061469 WO2008061856A1 (de) | 2006-11-23 | 2007-10-25 | Schaufelanordnung |
Country Status (9)
Country | Link |
---|---|
US (1) | US8167563B2 (de) |
EP (2) | EP1925781A1 (de) |
JP (1) | JP4806075B2 (de) |
CN (1) | CN101542073B (de) |
AT (1) | ATE469288T1 (de) |
DE (1) | DE502007003972D1 (de) |
ES (1) | ES2345686T3 (de) |
RU (1) | RU2417323C2 (de) |
WO (1) | WO2008061856A1 (de) |
Families Citing this family (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2418356A1 (de) | 2010-08-10 | 2012-02-15 | Siemens Aktiengesellschaft | Dämpfungselement für ein Turbinenschaufelrad und entsprechend ausgebildete Turbinenschaufel |
EP2434098A1 (de) * | 2010-09-24 | 2012-03-28 | Siemens Aktiengesellschaft | Schaufelanordnung und zugehörige Gasturbine |
US9194238B2 (en) * | 2012-11-28 | 2015-11-24 | General Electric Company | System for damping vibrations in a turbine |
CN104594957B (zh) * | 2014-12-08 | 2016-06-15 | 东方电气集团东方汽轮机有限公司 | 汽轮机调节级动叶片的阻尼结构 |
EP3078808A1 (de) * | 2015-04-07 | 2016-10-12 | Siemens Aktiengesellschaft | Laufschaufelreihe für eine strömungsmaschine |
US10472975B2 (en) * | 2015-09-03 | 2019-11-12 | General Electric Company | Damper pin having elongated bodies for damping adjacent turbine blades |
US10662784B2 (en) * | 2016-11-28 | 2020-05-26 | Raytheon Technologies Corporation | Damper with varying thickness for a blade |
US10731479B2 (en) | 2017-01-03 | 2020-08-04 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10677073B2 (en) | 2017-01-03 | 2020-06-09 | Raytheon Technologies Corporation | Blade platform with damper restraint |
JP7039355B2 (ja) * | 2018-03-28 | 2022-03-22 | 三菱重工業株式会社 | 回転機械 |
CN114080490A (zh) * | 2019-05-29 | 2022-02-22 | 赛峰飞机发动机公司 | 用于涡轮机的组件 |
CN113803115B (zh) * | 2020-06-16 | 2024-04-05 | 中国航发商用航空发动机有限责任公司 | 涡轮叶片缘板阻尼器、涡轮叶片和航空发动机 |
US11391157B1 (en) | 2021-03-23 | 2022-07-19 | Pratt & Whitney Canada Corp. | Damped rotor assembly |
US11525464B2 (en) | 2021-03-23 | 2022-12-13 | Pratt & Whitney Canada Corp. | Rotor with centrifugally wedged damper |
JP2023093088A (ja) * | 2021-12-22 | 2023-07-04 | 三菱重工業株式会社 | 回転機械 |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2942843A (en) * | 1956-06-15 | 1960-06-28 | Westinghouse Electric Corp | Blade vibration damping structure |
SU1127979A1 (ru) * | 1983-02-23 | 1984-12-07 | Предприятие П/Я Р-6837 | Рабочее колесо турбомашины |
US4580946A (en) * | 1984-11-26 | 1986-04-08 | General Electric Company | Fan blade platform seal |
EP0918139A2 (de) * | 1997-11-25 | 1999-05-26 | ROLLS-ROYCE plc | Reibungsdämpfer |
EP1154125A2 (de) * | 2000-05-08 | 2001-11-14 | ALSTOM Power N.V. | Schaufelanordnung mit Dämpfungselementen |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2310412A (en) * | 1941-03-08 | 1943-02-09 | Westinghouse Electric & Mfg Co | Vibration dampener |
SU128868A1 (ru) | 1959-04-20 | 1959-11-30 | В.С. Осадченко | Демпфер сухого трени дл изменени собственной частоты колебаний бандажированных рабочих лопаток турбин |
GB2223277B (en) * | 1988-09-30 | 1992-08-12 | Rolls Royce Plc | Aerofoil blade damping |
FR2665726B1 (fr) * | 1990-08-08 | 1993-07-02 | Snecma | Soufflante de turbomachine a amortisseur dynamique a cames. |
US5156528A (en) | 1991-04-19 | 1992-10-20 | General Electric Company | Vibration damping of gas turbine engine buckets |
FR2716502B1 (fr) * | 1994-02-23 | 1996-04-05 | Snecma | Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires. |
JP2006125372A (ja) | 2004-11-01 | 2006-05-18 | Mitsubishi Heavy Ind Ltd | 回転機械翼の防振構造および回転機械 |
-
2006
- 2006-11-23 EP EP06024326A patent/EP1925781A1/de not_active Withdrawn
-
2007
- 2007-10-25 AT AT07821832T patent/ATE469288T1/de active
- 2007-10-25 US US12/515,845 patent/US8167563B2/en not_active Expired - Fee Related
- 2007-10-25 RU RU2009123844/06A patent/RU2417323C2/ru not_active IP Right Cessation
- 2007-10-25 JP JP2009537583A patent/JP4806075B2/ja not_active Expired - Fee Related
- 2007-10-25 EP EP07821832A patent/EP2094946B1/de not_active Not-in-force
- 2007-10-25 DE DE502007003972T patent/DE502007003972D1/de active Active
- 2007-10-25 ES ES07821832T patent/ES2345686T3/es active Active
- 2007-10-25 WO PCT/EP2007/061469 patent/WO2008061856A1/de active Application Filing
- 2007-10-25 CN CN2007800436875A patent/CN101542073B/zh not_active Expired - Fee Related
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2942843A (en) * | 1956-06-15 | 1960-06-28 | Westinghouse Electric Corp | Blade vibration damping structure |
SU1127979A1 (ru) * | 1983-02-23 | 1984-12-07 | Предприятие П/Я Р-6837 | Рабочее колесо турбомашины |
US4580946A (en) * | 1984-11-26 | 1986-04-08 | General Electric Company | Fan blade platform seal |
EP0918139A2 (de) * | 1997-11-25 | 1999-05-26 | ROLLS-ROYCE plc | Reibungsdämpfer |
EP1154125A2 (de) * | 2000-05-08 | 2001-11-14 | ALSTOM Power N.V. | Schaufelanordnung mit Dämpfungselementen |
Also Published As
Publication number | Publication date |
---|---|
RU2009123844A (ru) | 2010-12-27 |
US20100021302A1 (en) | 2010-01-28 |
EP1925781A1 (de) | 2008-05-28 |
CN101542073B (zh) | 2013-02-13 |
JP4806075B2 (ja) | 2011-11-02 |
ES2345686T3 (es) | 2010-09-29 |
EP2094946B1 (de) | 2010-05-26 |
US8167563B2 (en) | 2012-05-01 |
EP2094946A1 (de) | 2009-09-02 |
DE502007003972D1 (de) | 2010-07-08 |
ATE469288T1 (de) | 2010-06-15 |
CN101542073A (zh) | 2009-09-23 |
JP2010510436A (ja) | 2010-04-02 |
RU2417323C2 (ru) | 2011-04-27 |
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