EP1013890B1 - Anstreifdichtung für Turbomaschinen - Google Patents
Anstreifdichtung für Turbomaschinen Download PDFInfo
- Publication number
- EP1013890B1 EP1013890B1 EP99124032A EP99124032A EP1013890B1 EP 1013890 B1 EP1013890 B1 EP 1013890B1 EP 99124032 A EP99124032 A EP 99124032A EP 99124032 A EP99124032 A EP 99124032A EP 1013890 B1 EP1013890 B1 EP 1013890B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing
- foamed
- gas turbine
- abradable seal
- seal
- 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
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 7
- 239000000956 alloy Substances 0.000 claims abstract description 7
- 239000011148 porous material Substances 0.000 claims abstract description 6
- 238000005260 corrosion Methods 0.000 claims abstract description 5
- 230000007797 corrosion Effects 0.000 claims abstract description 5
- 238000004519 manufacturing process Methods 0.000 claims description 8
- 239000000463 material Substances 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 239000006260 foam Substances 0.000 abstract description 5
- 229910000679 solder Inorganic materials 0.000 abstract description 4
- 238000005476 soldering Methods 0.000 abstract description 2
- 239000002994 raw material Substances 0.000 abstract 1
- 238000007789 sealing Methods 0.000 description 19
- 239000006262 metallic foam Substances 0.000 description 9
- 239000002184 metal Substances 0.000 description 5
- 238000009413 insulation Methods 0.000 description 4
- 241000792859 Enema Species 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007920 enema Substances 0.000 description 1
- 229940095399 enema Drugs 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000005187 foaming Methods 0.000 description 1
- 238000013012 foaming technology Methods 0.000 description 1
- 229910000856 hastalloy Inorganic materials 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- NLYAJNPCOHFWQQ-UHFFFAOYSA-N kaolin Chemical compound O.O.O=[Al]O[Si](=O)O[Si](=O)O[Al]=O NLYAJNPCOHFWQQ-UHFFFAOYSA-N 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 229910001175 oxide dispersion-strengthened alloy Inorganic materials 0.000 description 1
- 230000035699 permeability Effects 0.000 description 1
- 239000000843 powder Substances 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
- 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
- F01D11/127—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 a deformable or crushable structure, e.g. honeycomb
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/612—Foam
Definitions
- the invention relates to a brush seal between a wall section and the blade tips of a gas turbine.
- the invention further relates to a Method for producing a gas turbine with such a sealing seal.
- DE 32 35 745 C2 the technical environment in particular to EP 0 605 417 B1 and to US 5,388,959 and US 4,392,656.
- Bearing seals from or in gas turbines essentially have two Fulfill tasks, namely firstly a flow around the individual running stages prevent the gas turbine and secondly the housing structure or thermally insulate the hot gas in the gas turbine wall sections or control the heat flow passing into the wall sections in such a way that the thermal expansion of the housing is simultaneous with the thermal expansion of the rotating blades or the disks carrying them.
- the so-called gap between the tips of the turbine blades and the these surrounding wall sections or that on the wall sections The intended sealing seal should namely over the entire operating area the gas turbine should be as small as possible because of any enlargement of the gap dimension a reduction in thrust and thus a reduced Efficiency.
- the invention proposed here replaces the above. known Sealing systems through a metal foam.
- a corrosion-resistant high-temperature alloy such as. Hastalloy X, IN 601, ODS alloys are the ones mentioned Requirements met in an excellent way.
- the one is younger Metal foam technology that is currently up to date for the specialist basically known.
- a suitable metal alloy is used
- the present invention is a metallic corrosion-resistant High temperature alloy - foamed using known methods, so that an essentially fine foam structure is formed, with thin metal walls enclosing a plurality of cavities between them.
- a foaming method for example, a metal powder mixed with a metal hydrite and then extruded, after which this primary material is thermally foamed.
- one is Appropriate manufacture from prefabricated hollow metal spheres possible. In general, this produces a mainly closed-pore foam Structure with high porosity and good thermal insulation properties educated.
- a brush seal between a wall section and the blade tips of a gas turbine combines such a structure with high porosity, favorable running-in properties, high sealing capacity and good thermal insulation in a single material.
- a sealing gasket can also be manufactured extremely simply, in fact Manufacturing process the porosity of the resulting structure as desired can be controlled. This in turn makes it possible for the enema that Sealing and insulating properties in the desired direction.
- solder does not migrate (as for example in the case of open-pore structures or metal felts) from the joint into the sealing structure due to capillary forces; so that the foam is easy to solder.
- An alternative production method is to connect the unfoamed primary material to the respective wall section or to the housing structure in a first process step and to foam this primary material in a second process step. This is followed by machining, of course, to bring the metal foam or the sealing gasket into the desired shape.
- the use leads from metal foam seals to better sealing behavior while improving the insulation of the housing structure against that in the gas turbine or between the brush seals and the turbine blades led hot gas.
- the relatively simple manufacturing route leads to cost savings.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Sealing Material Composition (AREA)
- Sealing With Elastic Sealing Lips (AREA)
Description
Ein alternativer Herstellweg besteht darin, in einem ersten Prozessschritt das ungeschäumte Vormaterial mit dem jeweiligen Wandabschnitt bzw. mit der Gehäusestruktur zu verbinden und in einem zweiten Prozessschritt dieses Vormaterial zu schäumen. Danach erfolgt selbstverständlich eine spanende Bearbeitung, um den Metallschaum bzw. die Anstreifdichtung in die gewünschte Form zu bringen.
Claims (2)
- Anstreifdichtung zwischen einem Wandabschnitt und den Schaufelspitzen einer Gasturbine, die vollständig aus einer aufgeschäumten, metallischen, korrosionsbeständigen Hochtemperaturlegierung besteht, dadurch gekennzeichnet, dass diese Hochtemperaturlegierung eine geschlossenporige Struktur aufweist.
- Verfahren zum Herstellen einer Gasturbine mit einer Anstreifdichtung nach Anspruch 1,
dadurch gekennzeichnet, dass das nicht aufgeschäumte Vormaterial der Anstreifdichtung zunächst mit den Wandabschnitten verbunden und anschließend daran aufgeschäumt wird.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19858031 | 1998-12-16 | ||
| DE19858031A DE19858031A1 (de) | 1998-12-16 | 1998-12-16 | Anstreifdichtung zwischen einem Wandabschnitt und den Schaufelspitzen einer Gasturbine |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| EP1013890A2 EP1013890A2 (de) | 2000-06-28 |
| EP1013890A3 EP1013890A3 (de) | 2001-11-07 |
| EP1013890B1 true EP1013890B1 (de) | 2004-02-04 |
Family
ID=7891283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP99124032A Expired - Lifetime EP1013890B1 (de) | 1998-12-16 | 1999-12-09 | Anstreifdichtung für Turbomaschinen |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP1013890B1 (de) |
| AT (1) | ATE259027T1 (de) |
| DE (2) | DE19858031A1 (de) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007032707A1 (de) | 2007-07-13 | 2009-01-15 | Mtu Aero Engines Gmbh | Verfahren zum Herstellen eines Einlaufbelags |
| EP2196632A2 (de) | 2008-12-10 | 2010-06-16 | Rolls-Royce plc | Dichtung sowie Verfahren zur Herstellung einer Dichtung in einer Gasturbine |
| DE102009016803A1 (de) | 2009-04-09 | 2010-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Labyrinth-Anstreifdichtung für eine Strömungsmaschine |
| DE102011014292A1 (de) * | 2011-03-17 | 2012-09-20 | Rolls-Royce Deutschland Ltd & Co Kg | Zwischenstufendichtungsring sowie Verfahren zu dessen Herstellung |
| EP2873811A1 (de) | 2013-11-19 | 2015-05-20 | MTU Aero Engines GmbH | Einlaufbelag auf Basis von Metallfasern |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE50211431D1 (de) | 2001-09-25 | 2008-02-07 | Alstom Technology Ltd | Dichtungsanordnung zur dichtspaltreduzierung innerhalb einer strömungsrotationsmaschine |
| DE10360164A1 (de) | 2003-12-20 | 2005-07-21 | Mtu Aero Engines Gmbh | Gasturbinenbauteil |
| DE102008007321A1 (de) | 2008-02-02 | 2009-08-13 | Mtu Aero Engines Gmbh | Vorrichtung mit Rotor, Gehäuse und Anstreifdichtung |
| DE102008019331A1 (de) * | 2008-04-16 | 2009-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Einlaufdichtung für den Kompressor eines Gasturbinentriebwerks |
| GB0912796D0 (en) | 2009-07-23 | 2009-08-26 | Cummins Turbo Tech Ltd | Compressor,turbine and turbocharger |
| DE102013219766A1 (de) | 2013-09-30 | 2015-04-16 | Siemens Aktiengesellschaft | Anstreifdichtung und Dichtungsanordnung |
| KR102720466B1 (ko) * | 2024-01-23 | 2024-10-22 | 터보파워텍(주) | 발전 터빈용 실링 장치 |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4392656A (en) * | 1979-10-26 | 1983-07-12 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Air-cooled sealing rings for the wheels of gas turbines |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4177308A (en) * | 1978-08-10 | 1979-12-04 | The United States Of America As Represented By The Secretary Of The Air Force | Non-combustible high temperature abradable seal material |
| US4433845A (en) | 1981-09-29 | 1984-02-28 | United Technologies Corporation | Insulated honeycomb seal |
| DE3203869C2 (de) * | 1982-02-05 | 1984-05-10 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Turbinenlaufschaufel für Strömungsmaschinen, insbesondere Gasturbinentriebwerke |
| US5350557A (en) * | 1991-09-23 | 1994-09-27 | Technetics Corp. | Impermeable, abradable seal and method for the production thereof |
| DE4241420C1 (de) * | 1992-12-09 | 1993-11-25 | Mtu Muenchen Gmbh | Verfahren zur Herstellung von Bauteilen oder Substraten mit Verbundbeschichtungen und dessen Anwendung |
| US5388959A (en) | 1993-08-23 | 1995-02-14 | General Electric Company | Seal including a non-metallic abradable material |
| DE19750516A1 (de) * | 1997-11-14 | 1999-05-20 | Asea Brown Boveri | Abreibbare Dichtung |
-
1998
- 1998-12-16 DE DE19858031A patent/DE19858031A1/de not_active Withdrawn
-
1999
- 1999-12-09 AT AT99124032T patent/ATE259027T1/de not_active IP Right Cessation
- 1999-12-09 EP EP99124032A patent/EP1013890B1/de not_active Expired - Lifetime
- 1999-12-09 DE DE59908461T patent/DE59908461D1/de not_active Expired - Lifetime
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4392656A (en) * | 1979-10-26 | 1983-07-12 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Air-cooled sealing rings for the wheels of gas turbines |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102007032707A1 (de) | 2007-07-13 | 2009-01-15 | Mtu Aero Engines Gmbh | Verfahren zum Herstellen eines Einlaufbelags |
| EP2196632A2 (de) | 2008-12-10 | 2010-06-16 | Rolls-Royce plc | Dichtung sowie Verfahren zur Herstellung einer Dichtung in einer Gasturbine |
| US8650753B2 (en) | 2008-12-10 | 2014-02-18 | Rolls-Royce, Plc | Seal and a method of manufacturing a seal |
| DE102009016803A1 (de) | 2009-04-09 | 2010-10-14 | Rolls-Royce Deutschland Ltd & Co Kg | Labyrinth-Anstreifdichtung für eine Strömungsmaschine |
| EP2241724A2 (de) | 2009-04-09 | 2010-10-20 | Rolls-Royce Deutschland Ltd & Co KG | Labyrinth-Anstreifdichtung für eine Strömungsmaschine |
| DE102011014292A1 (de) * | 2011-03-17 | 2012-09-20 | Rolls-Royce Deutschland Ltd & Co Kg | Zwischenstufendichtungsring sowie Verfahren zu dessen Herstellung |
| EP2873811A1 (de) | 2013-11-19 | 2015-05-20 | MTU Aero Engines GmbH | Einlaufbelag auf Basis von Metallfasern |
| DE102013223585A1 (de) | 2013-11-19 | 2015-06-03 | MTU Aero Engines AG | Einlaufbelag auf Basis von Metallfasern |
Also Published As
| Publication number | Publication date |
|---|---|
| EP1013890A3 (de) | 2001-11-07 |
| DE19858031A1 (de) | 2000-06-21 |
| DE59908461D1 (de) | 2004-03-11 |
| EP1013890A2 (de) | 2000-06-28 |
| ATE259027T1 (de) | 2004-02-15 |
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