EP1478828B1 - Rezirkulationsstruktur für turboverdichter - Google Patents
Rezirkulationsstruktur für turboverdichter Download PDFInfo
- 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
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)
- Immobilizing And Processing Of Enzymes And Microorganisms (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Catalysts (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
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 (zh) |
EP (1) | EP1478828B1 (zh) |
JP (1) | JP4527403B2 (zh) |
CN (1) | CN100395432C (zh) |
AT (1) | ATE348943T1 (zh) |
AU (1) | AU2003222718A1 (zh) |
CA (1) | CA2495186C (zh) |
DE (2) | DE50306028D1 (zh) |
RU (1) | RU2293221C2 (zh) |
UA (1) | UA76596C2 (zh) |
WO (1) | WO2003072910A1 (zh) |
Cited By (1)
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 (39)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7186072B2 (en) | 2002-08-23 | 2007-03-06 | Mtu Aero Engines Gmbh | Recirculation structure for a turbocompressor |
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 |
US12085023B2 (en) | 2022-10-03 | 2024-09-10 | General Electric Company | Circumferentially varying fan casing treatments for reducing fan noise effects |
US12092034B2 (en) | 2022-10-03 | 2024-09-17 | General Electric Company | Circumferentially varying fan casing treatments for reducing fan noise effects |
US12078070B1 (en) | 2023-08-16 | 2024-09-03 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with sliding doors for a fan of a gas turbine engine |
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 |
US12066035B1 (en) | 2023-08-16 | 2024-08-20 | Rolls-Royce North American Technologies Inc. | Adjustable depth tip treatment with axial member with pockets for a fan of a gas turbine engine |
US11965528B1 (en) | 2023-08-16 | 2024-04-23 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine |
US12018621B1 (en) | 2023-08-16 | 2024-06-25 | Rolls-Royce North American Technologies Inc. | Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine |
US12085021B1 (en) | 2023-08-16 | 2024-09-10 | Rolls-Royce North American Technologies Inc. | Adjustable air flow plenum with movable closure for a fan of a gas turbine engine |
Family Cites Families (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1155958A (fr) * | 1956-03-28 | 1958-05-12 | Perfectionnements aux turbines à fluide compressible | |
JPS5018603B1 (zh) * | 1968-08-13 | 1975-07-01 | ||
BE747870A (fr) * | 1969-03-27 | 1970-09-24 | Aerospatiale | Perfectionnements apportes aux carenages pour helices ou ventilateurs |
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 (zh) * | 1986-08-13 | 1988-02-29 | ||
US5282718A (en) * | 1991-01-30 | 1994-02-01 | United Technologies Corporation | Case treatment for compressor blades |
KR100198721B1 (ko) * | 1991-01-30 | 1999-06-15 | 레비스 스테픈 이 | 개선된 케이스를 갖는 가스 터어빈 엔진 |
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 |
-
2003
- 2003-02-26 WO PCT/DE2003/000623 patent/WO2003072910A1/de active IP Right Grant
- 2003-02-26 EP EP03718608A patent/EP1478828B1/de not_active Expired - Lifetime
- 2003-02-26 UA UA20040907814A patent/UA76596C2/uk unknown
- 2003-02-26 DE DE50306028T patent/DE50306028D1/de not_active Expired - Lifetime
- 2003-02-26 AU AU2003222718A patent/AU2003222718A1/en not_active Abandoned
- 2003-02-26 US US10/473,152 patent/US6935833B2/en not_active Expired - Lifetime
- 2003-02-26 JP JP2003571571A patent/JP4527403B2/ja not_active Expired - Fee Related
- 2003-02-26 AT AT03718608T patent/ATE348943T1/de not_active IP Right Cessation
- 2003-02-26 CA CA2495186A patent/CA2495186C/en not_active Expired - Fee Related
- 2003-02-26 CN CNB038075032A patent/CN100395432C/zh not_active Expired - Fee Related
- 2003-02-26 DE DE10390754T patent/DE10390754D2/de not_active Expired - Fee Related
- 2003-02-26 RU RU2004129277/06A patent/RU2293221C2/ru not_active IP Right Cessation
Cited By (2)
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 |
---|---|
EP1478828A1 (de) | 2004-11-24 |
UA76596C2 (uk) | 2006-08-15 |
WO2003072910A1 (de) | 2003-09-04 |
RU2004129277A (ru) | 2005-08-27 |
CN1646790A (zh) | 2005-07-27 |
CA2495186A1 (en) | 2003-09-04 |
JP4527403B2 (ja) | 2010-08-18 |
RU2293221C2 (ru) | 2007-02-10 |
US20040156714A1 (en) | 2004-08-12 |
AU2003222718A1 (en) | 2003-09-09 |
US6935833B2 (en) | 2005-08-30 |
DE50306028D1 (de) | 2007-02-01 |
CN100395432C (zh) | 2008-06-18 |
JP2006505730A (ja) | 2006-02-16 |
CA2495186C (en) | 2010-04-27 |
ATE348943T1 (de) | 2007-01-15 |
DE10390754D2 (de) | 2005-05-12 |
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