EP1478828B1 - Rezirkulationsstruktur für turboverdichter - Google Patents

Rezirkulationsstruktur für turboverdichter Download PDF

Info

Publication number
EP1478828B1
EP1478828B1 EP03718608A EP03718608A EP1478828B1 EP 1478828 B1 EP1478828 B1 EP 1478828B1 EP 03718608 A EP03718608 A EP 03718608A EP 03718608 A EP03718608 A EP 03718608A EP 1478828 B1 EP1478828 B1 EP 1478828B1
Authority
EP
European Patent Office
Prior art keywords
guide elements
annular chamber
recirculation
recirculation structure
area
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
Application number
EP03718608A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1478828A1 (de
Inventor
Peter Seitz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1478828A1 publication Critical patent/EP1478828A1/de
Application granted granted Critical
Publication of EP1478828B1 publication Critical patent/EP1478828B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • 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
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • 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
    • Y10S415/00—Rotary kinetic fluid motors or pumps
    • Y10S415/914—Device to control boundary layer

Definitions

  • the invention relates to a recirculation structure for turbocompressors, according to the preamble of claim 1, as well as an aircraft engine and a stationary gas turbine.
  • Document US 3,620,640 A protects a shroud with a recirculation structure for a propeller or fan.
  • the recirculation structure comprises a ring chamber (toroidal cavity 2) which is circular in cross-section and in which profiled partitions 5 can be arranged.
  • the adjacent to the main flow channel side of the annular chamber (2) is open over its axial length and over its circumference to the main flow channel.
  • the axial center of the annular chamber (2) coincides relatively accurately with the axial center of the propeller blades (propeller blades 3) with the open side of the annular chamber extending upstream and downstream of the blades (3).
  • the guide elements (5) reach only at their downstream, rear end to the contour of the main flow channel, ie to the inner contour of the shell (shroud 1), zoom. In the upstream direction, the free edges of the guide elements (5) more and more away from the main flow channel and the blade tips (see the forward obliquely rising edge profile of the guide elements (5) in Fig. 2 and 3).
  • the object of the invention is to provide a recirculation structure for turbocompressors, which allows a significant increase in the surge line and thus a significant increase in the stable operating range without relevant deterioration of the compressor efficiency.
  • the essence of the invention is that the annular chamber, which is completely open to the main flow channel over its axial length and circumference, lies with its axial center upstream of the axial center of the free blade end, and that the free edges of the guide elements are at or near their axial length lie the contour of the main flow channel. Ring-like elements with squish coverings, etc. omitted.
  • the abovementioned patents show that experts have hitherto attempted to carry out recirculation structures to the main flow channel, ie to the so-called annular space over as large an axial area as possible, with little gap and closed, in order to maximize flow-favorable and low-loss extension of the contour of the
  • the recirculation structure 1 according to FIG. 1 is integrated into the housing 5 of a turbocompressor and thus to be referred to as a "casing treatment".
  • the flow direction in the bladed main flow channel 9 is indicated on the left with an arrow, so it runs from left to right.
  • the flow strikes in the area shown first on a vane ring 13, then on a blade ring 20 and finally back on a vane ring 14.
  • the radially outer contour 11 of the main flow channel 9 corresponds to the inner contour of the housing 5 and is to illustrate the left and right of the actual representation continued with dot-dash lines.
  • the static recirculation structure 1 cooperates with the blade ring 20 and is located largely axially before this, ie upstream.
  • the free edges 41 of the guide elements 37 lie on or close to the contour 11 of the main flow channel 9, ie they are at least approximately aligned with the housing inner contour.
  • the guide elements 37 may consist of a metal, such as a Ni-based alloy, or of a light metal, such as Al, or of a plastic, such as thermoplastics, thermosets or elastomers.
  • the front wall 33 and the rear wall 34 of the annular chamber 29 are inclined forwardly from their radially inner edges 35, 36 to be flow-favorable for the recirculation indicated by a small arrow.
  • the angle of inclination of the front wall is denoted by ⁇ , it may be the same or different in relation to the angle of the rear wall 34.
  • ⁇ The angle of inclination of the front wall
  • the guide elements 37 and the rear wall 34 recesses 45, 46 are provided which allow flow processes within the annular chamber in the circumferential direction, in addition to the predominantly axially extending recirculation.
  • 25 the free blade ends of the blade ring 20 are designated, in the area flow disturbances most likely to occur.
  • FIG. 2 shows a recirculation structure 2 integrated in a rotating hub 8. From left to right, a blade ring 21, a vane ring 15 with radially inner, free blade ends 26 and a blade ring 22 are identified in the main flow channel 10 Arrangement of a recirculation structure would consequently be referred to as "stroke treatment”.
  • the recirculation structure consisting of annular chamber 30 and guide elements 38 2 with front and rear recesses 47, 48 cooperates with a largely downstream vane ring 15. Since the "Hub Treatment" rotates here and the vane ring 15 is stationary, the rotor speed fully acts as a differential speed.
  • the mode of action differs in principle not from that of a "Casing Treatments” In a turbo compressor, "Casing Treatment” and “Hub Treatment” can also be combined and used in several stages.
  • the radially inner contour 12 of the main flow passage corresponds here to the outer contour of the hub 8.
  • FIG. 3 shows in cross-section a detail from FIG. 1.
  • the guide elements 37 are inclined at an angle ⁇ to the radial such that the blade ends 25 of the rotor blade ring 20 convey the recirculation flow into the annular chamber 29 without major losses, the direction of rotation (see arrow). is to be noted.
  • the angle of inclination ⁇ can decrease from radially inward to outward to the value "zero" given correspondingly curved guide elements.
  • a radial arrangement of the vanes, i. ⁇ 0 ° is possible, but should be less aerodynamic.
  • FIG. 4 to Figure 3 shows the blade profile of the blade ring 20 in conjunction with its direction of rotation (arrow) and gives a good idea of the flow-favorable profiling and curvature of the guide elements 37.
  • the skilled person can recognize that the recirculation outlet in the upstream Edge 35 of the annular chamber 29 in relation to the blade ring 20 should be done here with counter-rotation.
  • the downstream edge of the annular chamber is designated.
  • the guide elements 37 in simpler embodiments may also consist of flat or curved "sheets".
  • the recirculation structure 3 according to FIG. 5 is a "casing treatment" with an annular chamber 31 integrated in a housing 6.
  • the guide elements 39 extend as far as the front wall of the annular chamber 31, recesses 49 are present in the rear area, in the immediate vicinity of the blade ends 27 of FIG Blade ring 23.
  • the recirculation structure 4 in FIG. 6 with annular chamber 32 and guide elements 40 is likewise a "casing treatment", which is integrated in a housing 7 and cooperates with a rotor blade rim 24.
  • the guide elements 40 In contrast to Figure 5 rich here the guide elements 40 to the rear wall of the annular chamber 32. Recesses 50 are provided here in the front area. Since the free edges 44 of the guide elements 40 extend into the rotation range of the blade ends 28, they are offset radially outward in the rear area in order to reliably avoid contact with the blades. Of course, the edges can be offset accordingly throughout.
  • the free edges 41 to 44 of the guide elements 37 to 40 need not be offset radially outward when the guide elements are made of a soft light metal or plastic, because a contact with the blade ends allowed 25 to 28 can be done without damaging the blades.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Filling Or Discharging Of Gas Storage Vessels (AREA)
  • Catalysts (AREA)
  • Immobilizing And Processing Of Enzymes And Microorganisms (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP03718608A 2002-02-28 2003-02-26 Rezirkulationsstruktur für turboverdichter Expired - Lifetime EP1478828B1 (de)

Applications Claiming Priority (5)

Application Number Priority Date Filing Date Title
ZA200201688 2002-02-28
ZA200201688 2002-02-28
DE10238837 2002-08-23
DE10238837 2002-08-23
PCT/DE2003/000623 WO2003072910A1 (de) 2002-02-28 2003-02-26 Rezirkulationsstruktur für turboverdichter

Publications (2)

Publication Number Publication Date
EP1478828A1 EP1478828A1 (de) 2004-11-24
EP1478828B1 true EP1478828B1 (de) 2006-12-20

Family

ID=27766709

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03718608A Expired - Lifetime EP1478828B1 (de) 2002-02-28 2003-02-26 Rezirkulationsstruktur für turboverdichter

Country Status (11)

Country Link
US (1) US6935833B2 (ja)
EP (1) EP1478828B1 (ja)
JP (1) JP4527403B2 (ja)
CN (1) CN100395432C (ja)
AT (1) ATE348943T1 (ja)
AU (1) AU2003222718A1 (ja)
CA (1) CA2495186C (ja)
DE (2) DE10390754D2 (ja)
RU (1) RU2293221C2 (ja)
UA (1) UA76596C2 (ja)
WO (1) WO2003072910A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2818724A1 (de) 2013-06-27 2014-12-31 MTU Aero Engines GmbH Strömungsmaschine, Zirkulationsstruktur und Verfahren

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ATE325939T1 (de) 2002-08-23 2006-06-15 Mtu Aero Engines Gmbh Rezirkulationsstruktur für turboverdichter
DE102004032978A1 (de) * 2004-07-08 2006-02-09 Mtu Aero Engines Gmbh Strömungsstruktur für einen Turboverdichter
DE102008010283A1 (de) * 2008-02-21 2009-08-27 Mtu Aero Engines Gmbh Zirkulationsstruktur für einen Turboverdichter
FR2940374B1 (fr) * 2008-12-23 2015-02-20 Snecma Carter de compresseur a cavites optimisees.
US8337146B2 (en) * 2009-06-03 2012-12-25 Pratt & Whitney Canada Corp. Rotor casing treatment with recessed baffles
FR2949518B1 (fr) * 2009-08-31 2011-10-21 Snecma Compresseur de turbomachine ayant des injecteurs d'air
US8616838B2 (en) * 2009-12-31 2013-12-31 General Electric Company Systems and apparatus relating to compressor operation in turbine engines
FR2961564B1 (fr) 2010-06-17 2016-03-04 Snecma Compresseur et turbomachine a rendement optimise
FR2988146B1 (fr) * 2012-03-15 2014-04-11 Snecma Carter pour roue a aubes de turbomachine ameliore et turbomachine equipee dudit carter
FR2989744B1 (fr) * 2012-04-19 2014-06-13 Snecma Carter de compresseur a cavites au calage optimise
US9181877B2 (en) 2012-09-27 2015-11-10 United Technologies Corporation Seal hook mount structure with overlapped coating
US9783309B2 (en) 2013-07-16 2017-10-10 The Boeing Company Methods and device for mixing airflows in environmental control systems
EP2927503B1 (de) 2014-04-03 2023-05-17 MTU Aero Engines AG Gasturbinenverdichter, Flugtriebwerk und Auslegungsverfahren
US10041500B2 (en) * 2015-12-08 2018-08-07 General Electric Company Venturi effect endwall treatment
CN105465047A (zh) * 2015-12-14 2016-04-06 中国北方发动机研究所(天津) 一种改善压气机失速和喘振的机匣处理装置
US10106246B2 (en) 2016-06-10 2018-10-23 Coflow Jet, LLC Fluid systems that include a co-flow jet
US10315754B2 (en) 2016-06-10 2019-06-11 Coflow Jet, LLC Fluid systems that include a co-flow jet
CN106151112B (zh) * 2016-08-29 2020-02-18 中国能源建设集团广东省电力设计研究院有限公司 轴流风机的防失速装置及其控制方法
RU2645100C1 (ru) * 2016-09-28 2018-02-15 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Периферийное устройство для снижения утечек теплоносителя
CN106382260B (zh) * 2016-10-14 2018-08-10 中国科学院工程热物理研究所 一种压气机弦向凹槽导流片式机匣处理方法及装置
CN109209980B (zh) * 2017-06-30 2020-06-05 中国航发商用航空发动机有限责任公司 一种用于轴流压气机的导流板
US10465539B2 (en) * 2017-08-04 2019-11-05 Pratt & Whitney Canada Corp. Rotor casing
US10683076B2 (en) 2017-10-31 2020-06-16 Coflow Jet, LLC Fluid systems that include a co-flow jet
US11293293B2 (en) 2018-01-22 2022-04-05 Coflow Jet, LLC Turbomachines that include a casing treatment
DE102018203304A1 (de) 2018-03-06 2019-09-12 MTU Aero Engines AG Gasturbinenverdichter
US11111025B2 (en) 2018-06-22 2021-09-07 Coflow Jet, LLC Fluid systems that prevent the formation of ice
US10876549B2 (en) 2019-04-05 2020-12-29 Pratt & Whitney Canada Corp. Tandem stators with flow recirculation conduit
CN110374688B (zh) * 2019-07-16 2022-02-22 中国航发沈阳发动机研究所 一种多腔静子结构及气流吸附系统
GB2600584B (en) 2019-07-23 2024-03-06 Coflow Jet Llc Fluid systems and methods that address flow separation
US11702945B2 (en) * 2021-12-22 2023-07-18 Rolls-Royce North American Technologies Inc. Turbine engine fan case with tip injection air recirculation passage
US20230265862A1 (en) * 2022-02-21 2023-08-24 General Electric Company Turbofan engine having angled inlet pre-swirl vanes
US11970985B1 (en) 2023-08-16 2024-04-30 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine

Family Cites Families (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1155958A (fr) * 1956-03-28 1958-05-12 Perfectionnements aux turbines à fluide compressible
JPS5018603B1 (ja) * 1968-08-13 1975-07-01
NL7004146A (ja) * 1969-03-27 1970-09-29
SE451873B (sv) 1982-07-29 1987-11-02 Do G Pk I Experiment Axialflekt
SE451620B (sv) 1983-03-18 1987-10-19 Flaekt Ab Forfarande for framstellning av ledskenekrans for aterstromningskanal vid axialflektar
GB2245312B (en) * 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
JPS6331293U (ja) * 1986-08-13 1988-02-29
KR100198721B1 (ko) * 1991-01-30 1999-06-15 레비스 스테픈 이 개선된 케이스를 갖는 가스 터어빈 엔진
US5282718A (en) * 1991-01-30 1994-02-01 United Technologies Corporation Case treatment for compressor blades
JP3004474B2 (ja) * 1992-06-12 2000-01-31 三菱重工業株式会社 軸流回転機械
RU2034175C1 (ru) * 1993-03-11 1995-04-30 Центральный институт авиационного моторостроения им.П.И.Баранова Турбокомпрессор
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
GB9400254D0 (en) 1994-01-07 1994-03-02 Britisch Technology Group Limi Improvements in or relating to housings for axial flow fans
US5562404A (en) * 1994-12-23 1996-10-08 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US5607284A (en) * 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
US5586859A (en) * 1995-05-31 1996-12-24 United Technologies Corporation Flow aligned plenum endwall treatment for compressor blades
JPH09291897A (ja) * 1996-04-26 1997-11-11 Toshiba Corp 軸流圧縮機
CN2374683Y (zh) * 1999-06-18 2000-04-19 张坤林 微型泵气体导流改进结构
US6302640B1 (en) * 1999-11-10 2001-10-16 Alliedsignal Inc. Axial fan skip-stall
JP3841391B2 (ja) * 2000-03-17 2006-11-01 株式会社 日立インダストリイズ ターボ機械
DE10105456A1 (de) 2001-02-07 2002-08-08 Daimler Chrysler Ag Verdichter, insbesondere für eine Brennkraftmaschine
US6585479B2 (en) * 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2818724A1 (de) 2013-06-27 2014-12-31 MTU Aero Engines GmbH Strömungsmaschine, Zirkulationsstruktur und Verfahren
US10151206B2 (en) 2013-06-27 2018-12-11 MTU Aero Engines AG Turbomachine, circulation structure and method

Also Published As

Publication number Publication date
JP4527403B2 (ja) 2010-08-18
CN1646790A (zh) 2005-07-27
RU2004129277A (ru) 2005-08-27
WO2003072910A1 (de) 2003-09-04
DE50306028D1 (de) 2007-02-01
US6935833B2 (en) 2005-08-30
CA2495186A1 (en) 2003-09-04
US20040156714A1 (en) 2004-08-12
CA2495186C (en) 2010-04-27
RU2293221C2 (ru) 2007-02-10
CN100395432C (zh) 2008-06-18
ATE348943T1 (de) 2007-01-15
EP1478828A1 (de) 2004-11-24
AU2003222718A1 (en) 2003-09-09
DE10390754D2 (de) 2005-05-12
UA76596C2 (uk) 2006-08-15
JP2006505730A (ja) 2006-02-16

Similar Documents

Publication Publication Date Title
EP1478828B1 (de) Rezirkulationsstruktur für turboverdichter
EP1530670B1 (de) Rezirkulationsstruktur für turboverdichter
DE10330084B4 (de) Rezirkulationsstruktur für Turboverdichter
EP1614863B1 (de) Strömungsstruktur für einen Turboverdichter
EP2725194B1 (de) Turbinenrotorschaufel einer Gasturbine
EP2802780B1 (de) Axial- oder diagonallüfter mit stolperkante auf der laufschaufel-saugseite
EP2242931B1 (de) Zirkulationsstruktur für einen turboverdichter
EP1609999B1 (de) Strömungsarbeitsmaschine
EP0903468B1 (de) Vorrichtung zur Spaltdichtung
DE60320537T2 (de) Kompressor mit schaufelspitzeneinrichtung
DE60124572T2 (de) Halbaxial- und kreiselverdichter für ein gasturbinentriebwerk
DE102006048933A1 (de) Anordnung zur Strömungsbeeinflussung
DE102015120127A1 (de) Axialverdichterendwandeinrichtung zur steuerung der leckage in dieser
DE1428191A1 (de) Kreiselgeblaese
EP2025946A2 (de) Schaufeldeckband mit Sperrstrahlerzeugung
DE3031553A1 (de) Gasturbinenlaufrad.
EP3431708A1 (de) Umströmungsanordnung, zugehörige strömungsmaschine und verwendung
WO2010142287A1 (de) Verdichterlaufrad
DE102018206601A1 (de) Schaufel, Schaufelsegment und Baugruppe für eine Turbomaschine und Turbomaschine
DE102014226341A1 (de) Verdichter, Abgasturbolader und Brennkraftmaschine
DE102012021400A1 (de) Turbinenrotorschaufel einer Gasturbine
WO2018060068A1 (de) Schaufeln mit in strömungsrichtung s-förmigem verlauf für laufräder radialer bauart
WO2021037296A1 (de) Verdichter-laufschaufel
DE102011013677B4 (de) Lüfterrad
DE102020202258A1 (de) Mehrstufiger zentrifugalkompressor

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

17P Request for examination filed

Effective date: 20040821

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT SE SI SK TR

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

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: 20061220

Ref country code: SI

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: 20061220

Ref country code: IE

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: 20061220

Ref country code: FI

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: 20061220

Ref country code: CZ

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: 20061220

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: 20061220

Ref country code: DK

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: 20061220

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 50306028

Country of ref document: DE

Date of ref document: 20070201

Kind code of ref document: P

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20070124

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070228

Ref country code: MC

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070228

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

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: 20070320

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

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: 20070331

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: PT

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: 20070424

NLV1 Nl: lapsed or annulled due to failure to fulfill the requirements of art. 29p and 29m of the patents act
ET Fr: translation filed
REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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

Effective date: 20070921

BERE Be: lapsed

Owner name: MTU AERO ENGINES G.M.B.H.

Effective date: 20070228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

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: 20070321

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070226

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

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: 20061220

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20070226

Ref country code: CY

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: 20061220

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

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: 20070621

Ref country code: TR

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: 20061220

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20180222

Year of fee payment: 16

Ref country code: IT

Payment date: 20180221

Year of fee payment: 16

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20190227

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 NON-PAYMENT OF DUE FEES

Effective date: 20190226

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20210217

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20210223

Year of fee payment: 19

Ref country code: GB

Payment date: 20210222

Year of fee payment: 19

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 50306028

Country of ref document: DE

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20220226

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220228

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220226

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20220901