EP0536575A1 - Bande de recouvrement pour roue de turbine axiale - Google Patents
Bande de recouvrement pour roue de turbine axiale Download PDFInfo
- Publication number
- EP0536575A1 EP0536575A1 EP92116009A EP92116009A EP0536575A1 EP 0536575 A1 EP0536575 A1 EP 0536575A1 EP 92116009 A EP92116009 A EP 92116009A EP 92116009 A EP92116009 A EP 92116009A EP 0536575 A1 EP0536575 A1 EP 0536575A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- housing
- gap
- cover plates
- cover plate
- blade end
- 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
Images
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
-
- 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
-
- 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
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Definitions
- the invention relates to a device for sealing the gap between the rotor blades and the housing of a turbomachine which is designed with a conical contour, the rotor blades being provided with circumferential cover plates which seal against the housing with prongs to form radial gaps.
- Such devices are known. They essentially consist of cover plates with tines running in the circumferential direction, which seal against the housing or against a honeycomb arrangement (honeycomb). They form a smooth or a stepped labyrinth with pure radial gaps. As a rule, these cover plates extend over the entire blade width.
- a known seal which has two sealing prongs, is shown in FIG. 1 to be described later with reference to the rotor blade of the first stage.
- the object of the invention is to ensure clean guidance of the main flow in the case of blades of the type mentioned at the beginning and to provide a shroud which, in addition to good sealing action, is also accessible to good cooling.
- the cover plate arranged at the blade end has four throttling points against the housing, the throttling point on the inlet side forming a diagonal gap in the stationary operating state.
- the outlet-side throttle point preferably forms a radial gap.
- the advantage of the invention can be seen, inter alia, in the fact that only small amounts of gap occur in the new seal. As a result, high efficiencies can be achieved. In addition, a good introduction of the gap flow into the main flow is achieved.
- cover plates are rotationally symmetrical and if the parting lines between adjacent cover plates run in the direction of the chord. With this design, the inevitable leakage flow between the cover plates is deflected in the direction of the main flow.
- the parting line is provided with four steps, the steps running in the axial plane of the three throttling points.
- the blades come into contact between adjacent cover plates when the blades are unwinding. This creates the necessary damping effect.
- the inlet-side blade end advantageously has a lower inclination than the housing contour.
- This inclination should be such that there is a positive offset at the blade end, which has its greatest value in the area of the blade leading edge and which, together with the associated cover plate part, projects into a gap relief chamber arranged in the housing. With this gap relief, a reduction in the leakage flow through the shroud is achieved by pushing the main flow near the gap.
- the housing is provided with honeycomb arrangements at the four throttling points, no damage to the highly sensitive cover tape is to be expected if it is touched; These honeycomb seals also ensure that the heat generated when touching remains as low as possible. The strength properties of the highly stressed elements involved remain intact.
- the teeth of the cover plates which form the throttling points are preferably tapered in the circumferential direction on the cover plate overhangs.
- the three-stage gas turbine in FIG. 1 essentially consists of the bladed rotor 1 and the blade carrier 2 equipped with guide blades.
- the blade carrier which has a strongly conical channel contour of 40 °, is suspended in a turbine housing (not shown).
- the term blade carrier is synonymous with the term housing.
- the working medium enters the turbine from the outlet of the combustion chamber 3.
- the channel through which it flows opens into the exhaust gas housing, of which only the inner walls 4 of the diffuser are shown.
- the blading consists of three guide rows 5a, 5b and 5c and three run rows 6a, 6b and 6c.
- the blades of the guide rows seal against the rotor 1 by means of cover strips 7.
- the blades of the first rotor row 6a are provided with the cover plate seal 8 known per se, mentioned at the beginning.
- the actual seal consists of tines running in the circumferential direction, which run against a honeycomb arrangement (honeycomb) 9.
- honeycomb honeycomb arrangement
- the cover plates which extend across the entire blade width, form a classified labyrinth with pure radial gaps.
- the highly loaded blades 6 of the outlet row 6c are each provided with a cover plate 30 arranged centrally at the blade end, which forms three throttle points against the blade carrier 2.
- the blades of the middle row of races are provided with cover plates 11 which, according to FIG. 2, counter four throttling points form the blade carrier 2.
- the plates are provided with circumferential serrations 12, 13, 14 and 15 in four different radial planes.
- the outlet-side prongs 15, together with a honeycomb arrangement 25 inserted in the blade carrier 2, form a radial gap 16.
- the middle prongs 13 and 14 likewise form radial gaps 17 and 28 with the opposite honeycomb arrangements 27 and 28. 18.
- the entry-side prong 12 runs diagonally and forms a diagonal gap 19 together with a suitably configured honeycomb arrangement 26.
- the operating position is thus shown in FIG. 2, that is to say the position in which the diagonal gap 19 represents the operating play.
- the axial expansion is thus used to create a throttle gap.
- the four prongs enclose three vortex chambers 20, 21, 22, the radial displacement of the throttle points not influencing one another.
- the new type of seal at the outlet by means of a radial gap results in a cleanly guided outflow into the channel through which the previous free vortex spaces exist, as is contained in the cover plate seal 8 in the first row 5b.
- the wall 29 of the channel through which the honeycomb arrangement 25 adjoins is initially rounded off slightly before it changes into the slope of the channel contour. With this measure, a deflecting Coanda effect is exerted on the gap stream emerging from the radial gap 16, so that the main flow is impaired as little as possible.
- the blade end is provided with a positive offset 10 on the inlet side.
- This offset is formed in that the blade tip has a smaller value than the taper 32 of the channel contour.
- the offset 10 projects together with the cover plate part belonging to it a gap relief chamber 31 arranged in the blade carrier 2.
- the inner contour of the gap relief chamber is adapted to the taper of the blade tip. This results in an aerodynamic relief of the blade gap. The pressure difference across the blade gap drops and the deflection is improved. This reduces the so-called gap losses overall.
- Fig. 3 it can be seen that the cover plates 11 are rotationally symmetrical.
- the parting lines 23 between adjacent cover plates run in the direction of the chord.
- the circumferential sides of the cover plates are provided with four steps 24. These steps run in the axial plane of the four sealing teeth to ensure a continuous seal on the sealing surfaces. In addition, these stages take over the mechanical coupling of the cover plates to one another in order to achieve the damping effect.
- the teeth 12, 13, 14 and 15 are tapered in the circumferential direction on the two overhangs of each cover plate. These tapers 12a, 13a, 14a and 15a contribute significantly to the weight saving of the cover plates.
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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH296591 | 1991-10-08 | ||
CH2965/91 | 1991-10-08 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0536575A1 true EP0536575A1 (fr) | 1993-04-14 |
EP0536575B1 EP0536575B1 (fr) | 1995-04-05 |
Family
ID=4245626
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP92116009A Expired - Lifetime EP0536575B1 (fr) | 1991-10-08 | 1992-09-18 | Bande de recouvrement pour roue de turbine axiale |
Country Status (5)
Country | Link |
---|---|
US (1) | US5290144A (fr) |
EP (1) | EP0536575B1 (fr) |
JP (1) | JP3307692B2 (fr) |
DE (1) | DE59201833D1 (fr) |
PL (1) | PL296074A1 (fr) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0903468A1 (fr) * | 1997-09-19 | 1999-03-24 | Asea Brown Boveri AG | Bandage annulaire pour turbine axiale |
EP1267042A2 (fr) * | 2001-06-14 | 2002-12-18 | Mitsubishi Heavy Industries, Ltd. | Aube de turbine à gaz avec bande de recouvrement |
WO2009138057A2 (fr) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Carénage pour aubes mobiles d'une turbomachine, et turbomachine correspondante |
EP2551460A1 (fr) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Groupe d'aubes |
CN103184900A (zh) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | 用于涡轮护罩的向前台阶蜂巢式密封件 |
EP3399152A3 (fr) * | 2017-05-01 | 2018-11-14 | General Electric Company | Interface buse vers déflecteur de turbine |
KR20200126773A (ko) * | 2019-04-30 | 2020-11-09 | 두산중공업 주식회사 | 터빈의 실링 모듈 및 이를 포함하는 발전용 터빈 장치 |
Families Citing this family (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5632598A (en) * | 1995-01-17 | 1997-05-27 | Dresser-Rand | Shrouded axial flow turbo machine utilizing multiple labrinth seals |
JP3477347B2 (ja) * | 1997-07-30 | 2003-12-10 | 三菱重工業株式会社 | ガスタービン段間部シール装置 |
US6231301B1 (en) | 1998-12-10 | 2001-05-15 | United Technologies Corporation | Casing treatment for a fluid compressor |
RU2150627C1 (ru) * | 1999-03-31 | 2000-06-10 | Государственное научно-производственное предприятие "Мотор" | Сотовое уплотнение, преимущественно для паровой турбины |
US6896483B2 (en) | 2001-07-02 | 2005-05-24 | Allison Advanced Development Company | Blade track assembly |
GB0218060D0 (en) * | 2002-08-03 | 2002-09-11 | Alstom Switzerland Ltd | Sealing arrangements |
US6910854B2 (en) | 2002-10-08 | 2005-06-28 | United Technologies Corporation | Leak resistant vane cluster |
US6805530B1 (en) * | 2003-04-18 | 2004-10-19 | General Electric Company | Center-located cutter teeth on shrouded turbine blades |
US6893216B2 (en) * | 2003-07-17 | 2005-05-17 | General Electric Company | Turbine bucket tip shroud edge profile |
DE102004025321A1 (de) * | 2004-05-19 | 2005-12-08 | Alstom Technology Ltd | Strömungsmaschinenschaufel |
US7234918B2 (en) * | 2004-12-16 | 2007-06-26 | Siemens Power Generation, Inc. | Gap control system for turbine engines |
US7861823B2 (en) * | 2005-11-04 | 2011-01-04 | United Technologies Corporation | Duct for reducing shock related noise |
US20070273104A1 (en) * | 2006-05-26 | 2007-11-29 | Siemens Power Generation, Inc. | Abradable labyrinth tooth seal |
EP1995413B1 (fr) * | 2007-04-05 | 2010-04-28 | ALSTOM Technology Ltd | Joint d'étanchéité pour le jeu d'aubes d'une turbomachine |
DE102008061800A1 (de) * | 2008-12-11 | 2010-06-17 | Rolls-Royce Deutschland Ltd & Co Kg | Segmentierte Dichtlippen für Labyrinthdichtungsringe |
EP2218918A1 (fr) * | 2009-02-13 | 2010-08-18 | Siemens Aktiengesellschaft | Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites |
US8317465B2 (en) * | 2009-07-02 | 2012-11-27 | General Electric Company | Systems and apparatus relating to turbine engines and seals for turbine engines |
US20110070072A1 (en) * | 2009-09-23 | 2011-03-24 | General Electric Company | Rotary machine tip clearance control mechanism |
US8608424B2 (en) * | 2009-10-09 | 2013-12-17 | General Electric Company | Contoured honeycomb seal for a turbomachine |
US8333557B2 (en) * | 2009-10-14 | 2012-12-18 | General Electric Company | Vortex chambers for clearance flow control |
US8708639B2 (en) * | 2010-10-11 | 2014-04-29 | The Coca-Cola Company | Turbine bucket shroud tail |
US20120195742A1 (en) * | 2011-01-28 | 2012-08-02 | Jain Sanjeev Kumar | Turbine bucket for use in gas turbine engines and methods for fabricating the same |
US9291061B2 (en) * | 2012-04-13 | 2016-03-22 | General Electric Company | Turbomachine blade tip shroud with parallel casing configuration |
EP2998517B1 (fr) * | 2014-09-16 | 2019-03-27 | Ansaldo Energia Switzerland AG | Agencement d'étanchéité au niveau de l'interface entre une chambre de combustion et une turbine d'une turbine à gaz et turbine à gaz avec un tel agencement d'étanchéité |
KR101981922B1 (ko) | 2015-04-15 | 2019-08-28 | 로베르트 보쉬 게엠베하 | 프리-팁형 축류 팬 조립체 |
JP7086595B2 (ja) * | 2017-12-28 | 2022-06-20 | 三菱重工航空エンジン株式会社 | 航空機用ガスタービン |
JP2021110291A (ja) * | 2020-01-10 | 2021-08-02 | 三菱重工業株式会社 | 動翼、及び軸流回転機械 |
CN113266431B (zh) * | 2021-06-03 | 2022-08-09 | 西安交通大学 | 向心透平叶尖间隙超声波密封结构 |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB191210179A (en) * | 1911-05-04 | 1912-06-20 | Heinrich Holzer | Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids. |
FR2264964A1 (fr) * | 1974-03-21 | 1975-10-17 | Maschf Augsburg Nuernberg Ag | Procédé pour élever la limite dynamique de puissance des turbines et des compresseurs et moyens pour sa mise en oeuvre |
FR2406074A1 (fr) * | 1977-10-11 | 1979-05-11 | Snecma | Dispositif de securite pour machine tournante axiale |
EP0194957A2 (fr) * | 1985-03-11 | 1986-09-17 | United Technologies Corporation | Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs |
GB2215407A (en) * | 1988-03-05 | 1989-09-20 | Rolls Royce Plc | A bladed rotor assembly |
DE4015206C1 (fr) * | 1990-05-11 | 1991-10-17 | Mtu Muenchen Gmbh |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE485833C (de) * | 1929-11-08 | J A Maffei A G | Verfahren zur Herstellung von Schauflungen fuer Turbomaschinen, insbesondere fuer Dampf- oder Gasturbinen | |
GB804922A (en) * | 1956-01-13 | 1958-11-26 | Rolls Royce | Improvements in or relating to axial-flow fluid machines for example compressors andturbines |
FR1403799A (fr) * | 1964-05-13 | 1965-06-25 | Rateau Soc | Roue de turbine soumise à l'injection partielle |
US3677660A (en) * | 1969-04-08 | 1972-07-18 | Mitsubishi Heavy Ind Ltd | Propeller with kort nozzle |
GB1423833A (en) * | 1972-04-20 | 1976-02-04 | Rolls Royce | Rotor blades for fluid flow machines |
US4370094A (en) * | 1974-03-21 | 1983-01-25 | Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft | Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors |
DE2745130C2 (de) * | 1977-10-07 | 1980-01-03 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Dichtungseinrichtung für die freien Schaufelenden von Axialturbinen |
FR2452601A1 (fr) * | 1979-03-30 | 1980-10-24 | Snecma | Support amovible de revetement d'etancheite pour carter de soufflante de turboreacteur |
US4576551A (en) * | 1982-06-17 | 1986-03-18 | The Garrett Corporation | Turbo machine blading |
FR2552159B1 (fr) * | 1983-09-21 | 1987-07-10 | Snecma | Dispositif de liaison et d'etancheite de secteurs d'aubes de stator de turbine |
JPS6123804A (ja) * | 1984-07-10 | 1986-02-01 | Hitachi Ltd | タ−ビン段落構造 |
US4710102A (en) * | 1984-11-05 | 1987-12-01 | Ortolano Ralph J | Connected turbine shrouding |
-
1992
- 1992-09-18 DE DE59201833T patent/DE59201833D1/de not_active Expired - Lifetime
- 1992-09-18 EP EP92116009A patent/EP0536575B1/fr not_active Expired - Lifetime
- 1992-09-28 PL PL29607492A patent/PL296074A1/xx unknown
- 1992-09-28 US US07/951,839 patent/US5290144A/en not_active Expired - Lifetime
- 1992-10-07 JP JP26836992A patent/JP3307692B2/ja not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB191210179A (en) * | 1911-05-04 | 1912-06-20 | Heinrich Holzer | Arrangement for Diminishing Clearance Losses in Turbines and Pumps for Liquids and Elastic Fluids. |
FR2264964A1 (fr) * | 1974-03-21 | 1975-10-17 | Maschf Augsburg Nuernberg Ag | Procédé pour élever la limite dynamique de puissance des turbines et des compresseurs et moyens pour sa mise en oeuvre |
FR2406074A1 (fr) * | 1977-10-11 | 1979-05-11 | Snecma | Dispositif de securite pour machine tournante axiale |
EP0194957A2 (fr) * | 1985-03-11 | 1986-09-17 | United Technologies Corporation | Système de réduction des pertes des extrémités des aubes tournants auprès des compresseurs |
GB2215407A (en) * | 1988-03-05 | 1989-09-20 | Rolls Royce Plc | A bladed rotor assembly |
DE4015206C1 (fr) * | 1990-05-11 | 1991-10-17 | Mtu Muenchen Gmbh |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0903468A1 (fr) * | 1997-09-19 | 1999-03-24 | Asea Brown Boveri AG | Bandage annulaire pour turbine axiale |
US6102655A (en) * | 1997-09-19 | 2000-08-15 | Asea Brown Boveri Ag | Shroud band for an axial-flow turbine |
EP1267042A2 (fr) * | 2001-06-14 | 2002-12-18 | Mitsubishi Heavy Industries, Ltd. | Aube de turbine à gaz avec bande de recouvrement |
EP1267042A3 (fr) * | 2001-06-14 | 2009-06-17 | Mitsubishi Heavy Industries, Ltd. | Aube de turbine à gaz avec bande de recouvrement |
EP2280149A1 (fr) * | 2001-06-14 | 2011-02-02 | Mitsubishi Heavy Industries, Ltd. | Aube de turbine à gaz avec bande de recouvrement et virole en morceau |
WO2009138057A2 (fr) * | 2008-05-13 | 2009-11-19 | Mtu Aero Engines Gmbh | Carénage pour aubes mobiles d'une turbomachine, et turbomachine correspondante |
WO2009138057A3 (fr) * | 2008-05-13 | 2010-08-26 | Mtu Aero Engines Gmbh | Carénage pour aubes mobiles d'une turbomachine, et turbomachine correspondante |
EP2551460A1 (fr) * | 2011-07-29 | 2013-01-30 | Siemens Aktiengesellschaft | Groupe d'aubes |
CN103184900A (zh) * | 2012-01-03 | 2013-07-03 | 通用电气公司 | 用于涡轮护罩的向前台阶蜂巢式密封件 |
CN103184900B (zh) * | 2012-01-03 | 2017-10-24 | 通用电气公司 | 用于涡轮护罩的向前台阶蜂巢式密封件 |
EP3399152A3 (fr) * | 2017-05-01 | 2018-11-14 | General Electric Company | Interface buse vers déflecteur de turbine |
KR20200126773A (ko) * | 2019-04-30 | 2020-11-09 | 두산중공업 주식회사 | 터빈의 실링 모듈 및 이를 포함하는 발전용 터빈 장치 |
Also Published As
Publication number | Publication date |
---|---|
US5290144A (en) | 1994-03-01 |
PL296074A1 (en) | 1993-05-17 |
DE59201833D1 (de) | 1995-05-11 |
JPH05195988A (ja) | 1993-08-06 |
EP0536575B1 (fr) | 1995-04-05 |
JP3307692B2 (ja) | 2002-07-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0536575B1 (fr) | Bande de recouvrement pour roue de turbine axiale | |
EP0528138B1 (fr) | Anneau d'aube de turbine axiale | |
DE3534905C2 (de) | Gekühlte hohle Turbinenschaufel | |
DE69718229T2 (de) | Spitzendichtung für Turbinenlaufschaufeln | |
DE2913548C2 (de) | Wellenkühlung für ein Gasturbinentriebwerk | |
DE69831109T2 (de) | Kühlluftzufuhrsystem für die Schaufeln einer Gasturbine | |
DE60320537T2 (de) | Kompressor mit schaufelspitzeneinrichtung | |
DE1476796C3 (de) | Aus einem hochfesten Material integral hergestelltes Bauteil einer Gasturbinenanlage | |
EP1219781B1 (fr) | Dispositif et méthode de refroidissement d'une plate-forme d'une aube de turbine | |
DE69105837T2 (de) | Gekühlte Turbinenschaufel. | |
EP0417433B1 (fr) | Turbine axiale | |
WO2003052240A2 (fr) | Systeme de turbine a gaz | |
EP1191189A1 (fr) | Aube de turbine à gaz | |
EP0903468A1 (fr) | Bandage annulaire pour turbine axiale | |
DE4422700A1 (de) | Diffusor für Turbomaschine | |
EP0902164A1 (fr) | Refroidissement de la platte-forme dans les turbines à gas | |
DE3825744A1 (de) | Fluiddichtungs- und gasturbinenanordnung sowie verfahren zum verhindern des entweichens von arbeitsfluid aus einer turbomaschine | |
DE2943464A1 (de) | Dichtungsvorrichtung fuer ein gasturbinentriebwerk | |
EP3121373B1 (fr) | Roue de turbine refroidie, plus particulièrement pour un réacteur | |
EP0798448A2 (fr) | Système et dispositif pour réfroidir une paroi chauffée d'un cÔté par un gaz chaud | |
DE2037407C3 (de) | Strahlrohr mit einem Kernstromkanal und einem Mantelstromkanal | |
EP0916812A1 (fr) | Etage final pour turbine axial | |
EP1848904B1 (fr) | Element d'etancheite s'utilisant dans une turbomachine | |
DE102009040758A1 (de) | Umlenkvorrichtung für einen Leckagestrom in einer Gasturbine und Gasturbine | |
EP0640745B1 (fr) | Procédé de refroidissement d'un composant |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): CH DE FR GB IT LI NL |
|
17P | Request for examination filed |
Effective date: 19930923 |
|
17Q | First examination report despatched |
Effective date: 19940919 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE FR GB IT LI NL |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRE;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED.SCRIBED TIME-LIMIT Effective date: 19950405 Ref country code: NL Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 19950405 |
|
REF | Corresponds to: |
Ref document number: 59201833 Country of ref document: DE Date of ref document: 19950511 |
|
ET | Fr: translation filed | ||
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 19950615 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CH Effective date: 19950930 Ref country code: LI Effective date: 19950930 |
|
NLV1 | Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed | ||
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Ref country code: FR Ref legal event code: CA |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: TP |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20100930 Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20110901 Year of fee payment: 20 Ref country code: GB Payment date: 20110826 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R081 Ref document number: 59201833 Country of ref document: DE Owner name: ALSTOM TECHNOLOGY LTD., CH Free format text: FORMER OWNER: ALSTOM, PARIS, FR Effective date: 20120621 Ref country code: DE Ref legal event code: R082 Ref document number: 59201833 Country of ref document: DE Representative=s name: UWE ROESLER, DE Effective date: 20120621 Ref country code: DE Ref legal event code: R082 Ref document number: 59201833 Country of ref document: DE Representative=s name: ROESLER, UWE, DIPL.-PHYS.UNIV., DE Effective date: 20120621 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: 732E Free format text: REGISTERED BETWEEN 20120802 AND 20120808 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 59201833 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 59201833 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 Expiry date: 20120917 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: TP Owner name: ALSTOM TECHNOLOGY LTD., CH Effective date: 20120918 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20120919 Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20120917 |