EP1621735A3 - Gas turbine rotor - Google Patents
Gas turbine rotor Download PDFInfo
- Publication number
- EP1621735A3 EP1621735A3 EP05106088A EP05106088A EP1621735A3 EP 1621735 A3 EP1621735 A3 EP 1621735A3 EP 05106088 A EP05106088 A EP 05106088A EP 05106088 A EP05106088 A EP 05106088A EP 1621735 A3 EP1621735 A3 EP 1621735A3
- Authority
- EP
- European Patent Office
- Prior art keywords
- turbine rotor
- blades
- gas turbine
- gap
- side surfaces
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- 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
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
- F01D11/04—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
-
- 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
- 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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Bei einem Gasturbinenrotor mit innenraumgekühlten Schaufelblättern (4) der Turbinenlaufschaufeln und einem mechanischen Dichtungs- und Dämpfungselement zwischen den einander gegenüberliegenden Seitenflächen (6) der benachbarten Schaufelplattformen (7) wird der Spalt gegenüber dem Heißgasstrom zusätzlich aerodynamisch abgedichtet, und zwar mit Kühlluft, die über einen Kühlkanal (9) aus einem Hohlraum (5) der Schaufelblätter in den Spalt zwischen den Seitenflächen (6) geleitet wird. In a gas turbine rotor with internally cooled blades (4) of the turbine blades and a mechanical sealing and damping element between the opposite side surfaces (6) of the adjacent blade platforms (7), the gap is additionally aerodynamically sealed with respect to the hot gas flow, with cooling air flowing over one Cooling passage (9) from a cavity (5) of the blades is guided into the gap between the side surfaces (6).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102004037331A DE102004037331A1 (en) | 2004-07-28 | 2004-07-28 | Gas turbine rotor |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1621735A2 EP1621735A2 (en) | 2006-02-01 |
EP1621735A3 true EP1621735A3 (en) | 2008-12-17 |
EP1621735B1 EP1621735B1 (en) | 2010-02-24 |
Family
ID=34981327
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP05106088A Expired - Fee Related EP1621735B1 (en) | 2004-07-28 | 2005-07-05 | Gas turbine rotor |
Country Status (3)
Country | Link |
---|---|
US (1) | US7874803B2 (en) |
EP (1) | EP1621735B1 (en) |
DE (2) | DE102004037331A1 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8540486B2 (en) * | 2010-03-22 | 2013-09-24 | General Electric Company | Apparatus for cooling a bucket assembly |
KR101232609B1 (en) * | 2010-12-21 | 2013-02-13 | 두산중공업 주식회사 | Gas turbine engine pre-swirl rotating-disk apparatus |
US11021976B2 (en) * | 2014-12-22 | 2021-06-01 | Raytheon Technologies Corporation | Hardware geometry for increasing part overlap and maintaining clearance |
US10030582B2 (en) | 2015-02-09 | 2018-07-24 | United Technologies Corporation | Orientation feature for swirler tube |
JP5905631B1 (en) * | 2015-09-15 | 2016-04-20 | 三菱日立パワーシステムズ株式会社 | Rotor blade, gas turbine provided with the same, and method of manufacturing rotor blade |
US10655489B2 (en) | 2018-01-04 | 2020-05-19 | General Electric Company | Systems and methods for assembling flow path components |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0856641A1 (en) * | 1997-01-30 | 1998-08-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Cooling system for the shroud of rotor blades |
EP0902167A1 (en) * | 1997-09-15 | 1999-03-17 | Asea Brown Boveri AG | Cooling device for gas turbine components |
EP0940561A1 (en) * | 1998-03-03 | 1999-09-08 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade platform |
EP1074695A2 (en) * | 1999-08-02 | 2001-02-07 | United Technologies Corporation | Method for forming a cooling passage in a turbine vane |
EP1221539A2 (en) * | 2001-01-09 | 2002-07-10 | Mitsubishi Heavy Industries, Ltd. | Sealing for shrouds of a gas turbine |
US6561764B1 (en) * | 1999-03-19 | 2003-05-13 | Siemens Aktiengesellschaft | Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1822762U (en) | 1959-07-31 | 1960-12-01 | Entwicklungsbau Pirna Veb | HYDRODYNAMIC SEAL FOR FAST ROTATING SHAFTS. |
BE621931A (en) | 1961-08-30 | |||
GB1284596A (en) | 1969-12-20 | 1972-08-09 | Rolls Royce | Improvements in or relating to hydraulic seals |
US4101245A (en) * | 1976-12-27 | 1978-07-18 | United Technologies Corporation | Interblade damper and seal for turbomachinery rotor |
GB2125118A (en) | 1982-08-03 | 1984-02-29 | Rolls Royce | Hydraulic seal |
JP3040660B2 (en) * | 1994-06-06 | 2000-05-15 | 三菱重工業株式会社 | Gas Turbine Blade Platform Cooling Mechanism |
KR100364183B1 (en) * | 1994-10-31 | 2003-02-19 | 웨스팅하우스 일렉트릭 코포레이션 | Gas turbine blade with a cooled platform |
JP3462695B2 (en) * | 1997-03-12 | 2003-11-05 | 三菱重工業株式会社 | Gas turbine blade seal plate |
GB9801561D0 (en) | 1998-01-27 | 1998-03-25 | Rolls Royce Plc | Hydraulic seal |
CA2262064C (en) * | 1998-02-23 | 2002-09-03 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade platform |
DE19916803A1 (en) | 1999-04-14 | 2000-10-19 | Rolls Royce Deutschland | Hydraulic sealing arrangement, in particular on a gas turbine |
US6241467B1 (en) * | 1999-08-02 | 2001-06-05 | United Technologies Corporation | Stator vane for a rotary machine |
US6402471B1 (en) * | 2000-11-03 | 2002-06-11 | General Electric Company | Turbine blade for gas turbine engine and method of cooling same |
DE10064265A1 (en) * | 2000-12-22 | 2002-07-04 | Alstom Switzerland Ltd | Device and method for cooling a platform of a turbine blade |
US6945749B2 (en) * | 2003-09-12 | 2005-09-20 | Siemens Westinghouse Power Corporation | Turbine blade platform cooling system |
-
2004
- 2004-07-28 DE DE102004037331A patent/DE102004037331A1/en not_active Withdrawn
-
2005
- 2005-07-05 DE DE502005009070T patent/DE502005009070D1/en active Active
- 2005-07-05 EP EP05106088A patent/EP1621735B1/en not_active Expired - Fee Related
- 2005-07-27 US US11/189,771 patent/US7874803B2/en not_active Expired - Fee Related
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0856641A1 (en) * | 1997-01-30 | 1998-08-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Cooling system for the shroud of rotor blades |
EP0902167A1 (en) * | 1997-09-15 | 1999-03-17 | Asea Brown Boveri AG | Cooling device for gas turbine components |
EP0940561A1 (en) * | 1998-03-03 | 1999-09-08 | Mitsubishi Heavy Industries, Ltd. | Gas turbine moving blade platform |
US6561764B1 (en) * | 1999-03-19 | 2003-05-13 | Siemens Aktiengesellschaft | Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms |
EP1074695A2 (en) * | 1999-08-02 | 2001-02-07 | United Technologies Corporation | Method for forming a cooling passage in a turbine vane |
EP1221539A2 (en) * | 2001-01-09 | 2002-07-10 | Mitsubishi Heavy Industries, Ltd. | Sealing for shrouds of a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
DE502005009070D1 (en) | 2010-04-08 |
EP1621735B1 (en) | 2010-02-24 |
US7874803B2 (en) | 2011-01-25 |
US20060024166A1 (en) | 2006-02-02 |
EP1621735A2 (en) | 2006-02-01 |
DE102004037331A1 (en) | 2006-03-23 |
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