DE102008005480A1 - 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 - Google Patents
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 Download PDFInfo
- Publication number
- DE102008005480A1 DE102008005480A1 DE200810005480 DE102008005480A DE102008005480A1 DE 102008005480 A1 DE102008005480 A1 DE 102008005480A1 DE 200810005480 DE200810005480 DE 200810005480 DE 102008005480 A DE102008005480 A DE 102008005480A DE 102008005480 A1 DE102008005480 A1 DE 102008005480A1
- Authority
- DE
- Germany
- Prior art keywords
- layer
- gas turbine
- running
- air
- 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.)
- Withdrawn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
- F01D11/127—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
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
-
- 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
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/44—Free-space packings
- F16J15/445—Free-space packings with means for adjusting the clearance
-
- 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
-
- 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
Abstract
Description
Die Erfindung bezieht sich auf eine Gasturbine gemäß den Merkmalen des Oberbegriffs des Anspruchs 1.The The invention relates to a gas turbine according to the Features of the preamble of claim 1.
Im Einzelnen bezieht sich die Erfindung auf eine Gasturbine mit einem Verdichter, welcher zumindest eine Reihe von Schaufeln umfasst, wobei die Schaufeln jeweils mit einem freien Ende versehen sind, wobei angrenzend an das freie Ende der Schaufel an einem ringförmigen Gehäusebereich und/oder an einem ringförmigen Trommelbereich eine Einlaufschicht ausgebildet ist.in the More specifically, the invention relates to a gas turbine with a Compressor comprising at least one row of blades, wherein the blades are each provided with a free end, wherein adjacent to the free end of the blade on an annular Housing area and / or on an annular Drum area is formed an inlet layer.
Heutige Axialkompressoren (Verdichter) bestehen aus einem Rotor mit mindestens einer Laufschaufelreihe und einem Gehäuse. Diese Laufschaufelreihe soll zu dem Gehäuse einen möglichst kleinen Abstand haben, um Wirkungsgradverluste zu vermeiden. Um im Falle eines Anstreifens der Laufschaufeln Schäden zu vermeiden, sind im Gehäuse Einlaufbeläge eingebracht. Im Falle des Anstreifens werden Bereiche des Einlaufbelages abgetragen.today Axial compressors (compressors) consist of a rotor with at least a blade row and a housing. This blade row should be the smallest possible distance to the housing have to avoid loss of efficiency. In case of painting the blades to avoid damage are in the housing Inlet linings introduced. In the case of painting, areas become removed the inlet lining.
Es
sind verschiedenste Lösungen vorbekannt, die das Spaltverhalten
zu optimieren versuchen. Oftmals wird versucht, mittels Luftströmungen das
thermische Verhalten der Gehäuse dem des Rotors anzupassen,
wie z. B.
Der Laufspalt zwischen den Rotorschaufeln und dem Gehäuse wird durch verschiedene Faktoren beeinflusst:
- 1. Zentrifugallasten durch den Rotor und die Schaufeln,
- 2. Thermische Bewegungen, wobei das Gehäuse meistens thermisch schneller reagiert, als der Rotor,
- 3. Elastische Dehnungen der Rotoren und Gehäuse durch Flugmanöver,
- 4. Thermische Dehnungen von Rotoren und Gehäusen nach dem Abschalten des Triebwerkes.
- 1. Centrifugal loads through the rotor and the blades,
- 2. Thermal movements, where the housing mostly reacts thermally faster than the rotor,
- 3. Elastic stretching of the rotors and housings by flight maneuvers,
- 4. Thermal expansions of rotors and housings after switching off the engine.
Der letztgenannte Faktor ist schwer zu kontrollieren.Of the The latter factor is difficult to control.
Unter normalen Betriebsbedingungen und mit herkömmlichen Einlaufbelägen wird der Spalt so eingestellt, dass die Rotorschaufeln nur sehr leicht oder gar nicht in dieser Einlaufschicht einlaufen. So wird sichergestellt, dass bei normalen Bedingungen ein kleiner Spalt existiert. Unter extremen Betriebsbedingungen kann das Rotorblatt in diese Einlaufschichten stärker einlaufen und dort Material abnehmen.Under normal operating conditions and conventional inlet coverings the gap is adjusted so that the rotor blades only very run in easily or not at all in this running-in layer. So will ensured that under normal conditions a small gap exist. Under extreme operating conditions, the rotor blade can enter into these inlet layers stronger and there material lose weight.
Nachteilig ist dabei, dass auch bei normalen Betriebsbedingungen ein größerer Spalt zwischen den Rotorschaufeln und der Einlaufschicht vorhanden ist, was einen negativen Einfluss auf die Pumpgrenze und den Wirkungsgrad hat.adversely is that even under normal operating conditions a larger Gap between the rotor blades and the inlet layer present is what has a negative impact on the surge line and the efficiency Has.
Der Erfindung liegt die Aufgabe zugrunde, eine Gasturbine sowie ein Verfahren zum Einlaufen von Schaufeln zu schaffen, welche bei einfachem Aufbau und einfacher, betriebssicherer Wirksamkeit die Nachteile des Standes der Technik vermeiden und ein hohes Maß an Betriebssicherheit aufweist.Of the Invention is based on the object, a gas turbine and a To provide a method of running in blades, which in a simple structure and simple, reliable operation the disadvantages of the state avoid technology and a high degree of operational safety having.
Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination der unabhängigen Ansprüche gelöst, die jeweiligen Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the task by the feature combination of the independent Claims solved, the respective subclaims show further advantageous embodiments of the invention.
Erfindungsgemäß ist somit vorgesehen, dass die Einlaufschicht porös ausgebildet ist und mit einem luftaushärtenden Material beaufschlagt werden kann.According to the invention thus provided that the inlet layer formed porous is and subjected to an air-hardening material can be.
Das luftaushärtbare oder luftaushärtende Material ist in einer ringförmigen Vorratskammer oder in einem ringförmigen Vorratsbehälter bevorratet. Bei Berührung der Oberfläche des ringförmigen Gehäusebereichs oder des Trommelbereichs durch die freien Schaufelenden der Verdichterschaufeln wird das luftaushärtende Material freigesetzt und durch die Einlaufschicht geleitet. Durch diese dringt es bis in den Luftstrom des Ringkanals des Rotors (Verdichters) und härtet aus.The air-hardenable or air-hardening material is in an annular storage chamber or in an annular reservoir stored. When touching the surface of the annular Housing area or the drum area through the free Blade ends of the compressor blades becomes the air-hardening Material released and passed through the inlet layer. By this penetrates it into the air flow of the annular channel of the rotor (compressor) and hardens.
Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:in the The invention is based on an embodiment described in conjunction with the drawing. Showing:
Die
Freie
Schaufelenden
Bei
der Erfindung ist nunmehr folgendes vorgesehen:
Erfindungsgemäß wird
bevorzugterweise ein bei Luft aushärtendes (luftaushärtbares)
Material
According to the invention is preferably an air-curing (air-curable) material
Auf
einem Einlaufschichtträger
Erfindungsgemäß besteht
die Grundschicht der Einlaufschicht
Ein
Spalt zwischen den Rotorschaufeln
Nun
setzt der erfindungsgemäß vorgesehene Selbstheilungsprozess
ein. Das luftaushärtende Material (Aushärtmasse)
wird an der beschädigten Stelle durch die Einlaufschicht
Das Spaltverhalten eines Triebwerkes ist schwer zu kontrollieren. Die Erfindung erlaubt es, dass sich die Einlaufschicht selbst regeneriert und der Laufspalt wenigstens teilweise wieder hergestellt wird.The Splitting behavior of an engine is difficult to control. The Invention allows the run-in layer to regenerate itself and the running gap is at least partially restored.
- 11
- Luftaushärtendes/luftaushärtbares MaterialLuftaushärtendes / luftaushärtbares material
- 22
- Vorratsbehälter/MaterialzuführungsvorrichtungReservoir / material feeder
- 33
- Elastische Folie/Kunststofffolieelastic Foil / plastic film
- 44
- EinlaufschichtträgerIncoming substrate
- 55
- Ringkanal des Rotorsannular channel of the rotor
- 66
- Einlaufschichtrunning-in layer
- 77
- Loch/AusnehmungHole / recess
- 88th
- Oberste Schicht/DeckschichtTop Layer / top coat
- 99
- Gehäusecasing
- 1010
- Kammerchamber
- 1111
- Rotorschaufelnrotor blades
- 1212
- Verdichtercompressor
- 1313
- Trommelbereichdrum area
- 1414
- Rotor/TrommelRotor / drum
- 1515
- Ringförmiger Gehäusebereichannular housing area
- 1616
- Freies SchaufelendeFree blade end
- 1717
- Zufuhrrohrsupply pipe
- 1818
- Statorschaufelnstator
ZITATE ENTHALTEN IN DER BESCHREIBUNGQUOTES INCLUDE IN THE DESCRIPTION
Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.
Zitierte PatentliteraturCited patent literature
- - US 7086233 [0004] US 7086233 [0004]
Claims (11)
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 |
EP09000952A 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 |
US12/320,368 US8257016B2 (en) | 2008-01-23 | 2009-01-23 | Gas turbine with a compressor with self-healing abradable coating |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 (1)
Publication Number | Publication Date |
---|---|
DE102008005480A1 true DE102008005480A1 (en) | 2009-07-30 |
Family
ID=40794270
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200810005480 Withdrawn 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 |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE102008005480A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3011033A1 (en) * | 2013-09-25 | 2015-03-27 | Snecma | FIXING ABRADABLE SECTIONS HELD BY SLIDE |
Citations (12)
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 |
US4318666A (en) * | 1979-07-12 | 1982-03-09 | Rolls-Royce Limited | Cooled shroud for a gas turbine engine |
FR2438165B1 (en) * | 1978-10-06 | 1982-11-05 | Snecma | |
DE3209960C2 (en) * | 1981-03-25 | 1984-04-12 | Rolls-Royce Ltd., London | Inner lining for the compressor housing of a gas turbine engine |
US4732531A (en) * | 1986-08-11 | 1988-03-22 | National Aerospace Laboratory of Science and Technoloyg Agency | Air sealed turbine blades |
US5161942A (en) * | 1990-10-24 | 1992-11-10 | Westinghouse Electric Corp. | Moisture drainage of honeycomb seals |
DE10360164A1 (en) * | 2003-12-20 | 2005-07-21 | Mtu Aero Engines Gmbh | Gas turbine component |
DE69926203T2 (en) * | 1998-12-17 | 2006-01-12 | United Technologies Corp., Hartford | Inter-shaft seal assembly for a gas turbine engine |
US7086233B2 (en) | 2003-11-26 | 2006-08-08 | Siemens Power Generation, Inc. | Blade tip clearance control |
DE102005058324A1 (en) * | 2005-12-07 | 2007-06-14 | Mtu Aero Engines Gmbh | Method for producing an inlet lining |
DE60032843T2 (en) * | 1999-08-09 | 2007-06-21 | United Technologies Corp., Hartford | Stator for a turbomachine and method for its production |
US7246993B2 (en) * | 2001-07-13 | 2007-07-24 | Siemens Aktiengesellschaft | Coolable segment for a turbomachine and combustion turbine |
-
2008
- 2008-01-23 DE DE200810005480 patent/DE102008005480A1/en not_active Withdrawn
Patent Citations (12)
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 |
FR2438165B1 (en) * | 1978-10-06 | 1982-11-05 | Snecma | |
US4318666A (en) * | 1979-07-12 | 1982-03-09 | Rolls-Royce Limited | Cooled shroud for a gas turbine engine |
DE3209960C2 (en) * | 1981-03-25 | 1984-04-12 | Rolls-Royce Ltd., London | Inner lining for the compressor housing of a gas turbine engine |
US4732531A (en) * | 1986-08-11 | 1988-03-22 | National Aerospace Laboratory of Science and Technoloyg Agency | Air sealed turbine blades |
US5161942A (en) * | 1990-10-24 | 1992-11-10 | Westinghouse Electric Corp. | Moisture drainage of honeycomb seals |
DE69926203T2 (en) * | 1998-12-17 | 2006-01-12 | United Technologies Corp., Hartford | Inter-shaft seal assembly for a gas turbine engine |
DE60032843T2 (en) * | 1999-08-09 | 2007-06-21 | United Technologies Corp., Hartford | Stator for a turbomachine and method for its production |
US7246993B2 (en) * | 2001-07-13 | 2007-07-24 | Siemens Aktiengesellschaft | Coolable segment for a turbomachine and combustion turbine |
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 |
DE102005058324A1 (en) * | 2005-12-07 | 2007-06-14 | Mtu Aero Engines Gmbh | Method for producing an inlet lining |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3011033A1 (en) * | 2013-09-25 | 2015-03-27 | Snecma | FIXING ABRADABLE SECTIONS HELD BY SLIDE |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2719484B1 (en) | Component for turbomachine | |
DE102012011952B4 (en) | Composite turbine blade | |
DE19817705C2 (en) | Extraction of cooling air from the diffuser part of a compressor in a gas turbine | |
DE3504378A1 (en) | PROFILE BODY CONSTRUCTION AND METHOD FOR PRODUCING THE SAME | |
CH704833A1 (en) | Component for a turbo machine and a method of manufacturing such a component. | |
EP2647795A1 (en) | Seal system for a turbo engine | |
DE102012023682A1 (en) | Liquid separators for use in fuel cell system of vehicle, have guide element arranged in region for distributing mixture on cross section area of droplet separator, and separator body arranged between inflowing region and collection area | |
WO2010018174A1 (en) | Blade arrangement of a gas turbine | |
EP2083148A2 (en) | Gas turbine with a compressor with run-in coating and method of lapping the free extremities of compressor blades in a gas turbine | |
DE102008005480A1 (en) | 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 | |
DE102010005389A1 (en) | Structured surface coating by means of kinetic cold gas spraying | |
EP3078649B1 (en) | Composite ceramic with corrosion protection layer and method for producing same | |
WO2011009433A1 (en) | Abradable coating to be arranged on a gas turbine component | |
DE102008053394A1 (en) | Device for partially covering a component zone | |
DE102007042785A1 (en) | Fuel cell operating method for motor vehicle, involves conducting air flow through fuel cell, and withdrawing water from air flow in dehumidifying region between fuel cell and turbine wheel | |
EP3216554A1 (en) | Component with wear- resistant openings and depressions and method for producing the same | |
DE102015217944A1 (en) | Electrochemical cell and method for producing an electrochemical cell | |
DE102010000816A1 (en) | Drive system for car, has turbine wheel, compressor wheel, rotor, turbine control device and/or cabinet, compressor and/or fan provided with protective coating, and made of aluminum, magnesium, titanium, plastic or ceramic | |
DE102008005482A1 (en) | 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 | |
WO2005038072A1 (en) | Method for coating a component and component | |
EP1625283A1 (en) | Inlet coating for gas turbines | |
DE102010021220A1 (en) | Rotor for turbine engine, has rotor base body and blades arranged on periphery of rotor base body, where cable is provided for receiving centrifugal force | |
DE10019546B4 (en) | Steam turbine with a rotor and / or a stator associated blade carrier | |
DE102008005479A1 (en) | 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 | |
DE102019215223A1 (en) | Thrust gas bearings |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
OM8 | Search report available as to paragraph 43 lit. 1 sentence 1 patent law | ||
R005 | Application deemed withdrawn due to failure to request examination | ||
R005 | Application deemed withdrawn due to failure to request examination |
Effective date: 20150124 |