EP2083148A3 - Gas turbine with a compressor with run-in coating and method of lapping the free extremities of compressor blades in a gas turbine - Google Patents
Gas turbine with a compressor with run-in coating and method of lapping the free extremities of compressor blades in a gas turbine Download PDFInfo
- Publication number
- EP2083148A3 EP2083148A3 EP09000952A EP09000952A EP2083148A3 EP 2083148 A3 EP2083148 A3 EP 2083148A3 EP 09000952 A EP09000952 A EP 09000952A EP 09000952 A EP09000952 A EP 09000952A EP 2083148 A3 EP2083148 A3 EP 2083148A3
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- compressor
- blades
- lapping
- run
- 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.)
- Withdrawn
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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- 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
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0238—Details or means for fluid reinjection
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/222—Silicon
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Gasturbine mit einem Verdichter (101), welcher zumindest eine Reihe von Schaufeln (102) umfasst, wobei die Schaufeln jeweils mit einem freien Ende (103) versehen sind, wobei angrenzend an das freie Ende der Schaufel an einem ringförmigen Gehäusebereich (104) und/oder an einem ringförmigen Trommelbereich eine Einlaufschicht (106) ausgebildet ist, wobei die Einlaufschicht selbstheilend ist; und Verfahren zum Einlaufen von freien Endbereichen (103) von Schaufeln (102) einer Verdichten (101) einer Gasturbine. A gas turbine having a compressor (101) comprising at least one row of blades (102), the blades each being provided with a free end (103) adjacent to the free end of the blade at an annular housing portion (104) and / or an inlet layer (106) is formed on an annular drum area, the inlet layer being self-healing; and method for entering free end regions (103) of blades (102) of a compressor (101) of a gas turbine.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008005482A DE102008005482A1 (en) | 2008-01-23 | 2008-01-23 | Gas turbine has compressor, which has set of shovels and running-in layer, which is connected with fluid supply device and provided with liquid flow through opening, where upper layer of running-in layer is made of liquid-tight material |
DE102008005479A DE102008005479A1 (en) | 2008-01-23 | 2008-01-23 | Gas turbine has compressor with set of blades, where blades are provided with free end in each case, and adjacent intake layer is formed on free end of blades at circular housing area |
DE200810005480 DE102008005480A1 (en) | 2008-01-23 | 2008-01-23 | Gas turbine, has running-in layer connected with material feeder, which contains air-hardening material, where running-in layer is provided with material openings that are formed by pores of material of running-in layer |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2083148A2 EP2083148A2 (en) | 2009-07-29 |
EP2083148A3 true EP2083148A3 (en) | 2012-06-06 |
Family
ID=40469804
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09000952A Withdrawn EP2083148A3 (en) | 2008-01-23 | 2009-01-23 | Gas turbine with a compressor with run-in coating and method of lapping the free extremities of compressor blades in a gas turbine |
Country Status (2)
Country | Link |
---|---|
US (1) | US8257016B2 (en) |
EP (1) | EP2083148A3 (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9068507B2 (en) * | 2011-11-16 | 2015-06-30 | General Electric Company | Compressor having purge circuit and method of purging |
EP2886804B1 (en) * | 2013-12-20 | 2017-08-16 | Safran Aero Boosters SA | Sealing device for a compressor of a turbomachine |
BE1024735B1 (en) * | 2016-11-15 | 2018-06-19 | Safran Aero Boosters Sa | AXIAL TURBOMACHINE COMPRESSOR ANTI-FOGGER VIROLE |
CN108412761B (en) * | 2018-04-12 | 2024-03-01 | 河北昊方新能源科技有限公司 | Spray liquid cooling vortex air compressor |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0751280A1 (en) * | 1995-05-31 | 1997-01-02 | United Technologies Corporation | Flow aligned plenum endwall treatment for compressor blades |
US20050141990A1 (en) * | 2003-11-26 | 2005-06-30 | Volker Guemmer | Turbomachine wtih fluid supply |
WO2005114013A1 (en) * | 2004-05-20 | 2005-12-01 | Rolls-Royce Plc | Sealing arrangement |
DE102004031255A1 (en) * | 2004-06-29 | 2006-01-19 | Mtu Aero Engines Gmbh | inlet lining |
US20060153673A1 (en) * | 2004-11-17 | 2006-07-13 | Volker Guemmer | Turbomachine exerting dynamic influence on the flow |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1061467B (en) | 1956-12-22 | 1959-07-16 | Gen Electric | Sealing between the runner and the housing of a centrifugal compressor, in which the runner scrapes the necessary clearance out of the seal |
DE1913065C3 (en) | 1969-03-14 | 1974-10-10 | General Electric Co., Schenectady, N.Y. (V.St.A.) | Liquid cooling of rotor blades of a gas turbine |
FR2401310A1 (en) | 1977-08-26 | 1979-03-23 | Snecma | REACTION ENGINE TURBINE CASE |
FR2438165A1 (en) | 1978-10-06 | 1980-04-30 | Snecma | TEMPERATURE CONTROL DEVICE FOR GAS TURBINES |
GB2053367B (en) | 1979-07-12 | 1983-01-26 | Rolls Royce | Cooled shroud for a gas turbine engine |
US4269903A (en) * | 1979-09-06 | 1981-05-26 | General Motors Corporation | Abradable ceramic seal and method of making same |
GB2095749B (en) | 1981-03-25 | 1984-12-12 | Rolls Royce | Gas turbine engine having improved resistance for foreign object ingestion damage |
JPS6345402A (en) | 1986-08-11 | 1988-02-26 | Nagasu Hideo | Fluid machine |
US5161942A (en) | 1990-10-24 | 1992-11-10 | Westinghouse Electric Corp. | Moisture drainage of honeycomb seals |
US6196790B1 (en) | 1998-12-17 | 2001-03-06 | United Technologies Corporation | Seal assembly for an intershaft seal in a gas turbine engine |
US6425736B1 (en) | 1999-08-09 | 2002-07-30 | United Technologies Corporation | Stator assembly for a rotary machine and method for making the stator assembly |
EP1245792A1 (en) | 2001-03-30 | 2002-10-02 | Siemens Aktiengesellschaft | Coolable turbine shroud and process of manufacturing the shroud |
GB0117110D0 (en) | 2001-07-13 | 2001-09-05 | Siemens Ag | Coolable segment for a turbomachinery and combustion turbine |
DE10337094A1 (en) | 2003-08-12 | 2005-03-03 | Mtu Aero Engines Gmbh | Inlet lining for gas turbines and method for producing the same |
SE525924C2 (en) * | 2003-09-25 | 2005-05-24 | Gas Turbine Efficiency Ab | Nozzle and method for cleaning gas turbine compressors |
US7086233B2 (en) | 2003-11-26 | 2006-08-08 | Siemens Power Generation, Inc. | Blade tip clearance control |
DE10360164A1 (en) | 2003-12-20 | 2005-07-21 | Mtu Aero Engines Gmbh | Gas turbine component |
MXPA06009305A (en) * | 2004-02-16 | 2007-04-10 | Gas Turbine Efficiency Ab | Method and apparatus for cleaning a turbofan gas turbine engine. |
DE502005010381D1 (en) | 2005-04-28 | 2010-11-25 | Siemens Ag | Method and device for adjusting a radial gap of an axial flow compressor of a turbomachine |
DE102005058324A1 (en) | 2005-12-07 | 2007-06-14 | Mtu Aero Engines Gmbh | Method for producing an inlet lining |
-
2009
- 2009-01-23 US US12/320,368 patent/US8257016B2/en not_active Expired - Fee Related
- 2009-01-23 EP EP09000952A patent/EP2083148A3/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0751280A1 (en) * | 1995-05-31 | 1997-01-02 | United Technologies Corporation | Flow aligned plenum endwall treatment for compressor blades |
US20050141990A1 (en) * | 2003-11-26 | 2005-06-30 | Volker Guemmer | Turbomachine wtih fluid supply |
WO2005114013A1 (en) * | 2004-05-20 | 2005-12-01 | Rolls-Royce Plc | Sealing arrangement |
DE102004031255A1 (en) * | 2004-06-29 | 2006-01-19 | Mtu Aero Engines Gmbh | inlet lining |
US20060153673A1 (en) * | 2004-11-17 | 2006-07-13 | Volker Guemmer | Turbomachine exerting dynamic influence on the flow |
Also Published As
Publication number | Publication date |
---|---|
EP2083148A2 (en) | 2009-07-29 |
US20090196730A1 (en) | 2009-08-06 |
US8257016B2 (en) | 2012-09-04 |
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