EP1012445B1 - Schaufel für eine strömungsmaschine sowie dampfturbine - Google Patents
Schaufel für eine strömungsmaschine sowie dampfturbine Download PDFInfo
- Publication number
- EP1012445B1 EP1012445B1 EP98951240A EP98951240A EP1012445B1 EP 1012445 B1 EP1012445 B1 EP 1012445B1 EP 98951240 A EP98951240 A EP 98951240A EP 98951240 A EP98951240 A EP 98951240A EP 1012445 B1 EP1012445 B1 EP 1012445B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- vane
- cross
- axis
- region
- 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
- 230000003247 decreasing effect Effects 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 description 4
- 230000005484 gravity Effects 0.000 description 4
- 238000005452 bending Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 210000002435 tendon Anatomy 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000003716 rejuvenation Effects 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
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
- 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
-
- 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
-
- 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
Definitions
- the invention relates to a blade for a turbomachine, wherein the blade is directed along a blade axis and along this blade axis a foot end area, a head end portion and one in between Middle area and a cross-sectional area perpendicular to Has blade axis.
- the invention further relates to a Steam turbine, in particular a high-pressure or medium-pressure steam turbine.
- EP-A-0 704 602 deals with the design of a Turbine guide vane in an intermediate stator along one a turbine axis directed steam turbine.
- the shovel extends here along a radially directed Blade axis and has a pressure side and a suction side as well as an entry edge and an exit edge.
- there the blade is designed along the radial direction in such a way that the pressure side of a blade root area too one along the blade axis the blade root area opposite vane head area a convex Has curvature behavior.
- the Curvature achieved in that with radially successive, spaced cross-sectional profiles a corresponding rotation of the cross-sectional profiles around the fixed common trailing edge of the setting angle (bit angular angle) parabolic with respect to the turbine axis is varied.
- the channel width for the steam can thus be in the Bucket head area and in the blade root area reduced and increased in an intermediate bucket center area become. This leads to a relocation of part of the Steam mass flow, away from the two lossy ones Edge areas of the turbine guide vane.
- Such cylindrical Buckets have pressure and parallel to the bucket axis Suction sides and thus have neither a twist nor a Tilt up.
- As another alternative to the three-dimensional designed turbine blades are so-called twisted turbine blades described which an increasing over their height Twist and have a changing blade profile.
- German Auslegeschrift 28 41 616 is a guide vane ring described for an axial turbine with guide vanes, the guide vanes between an inner and an outer ring are arranged and the profile thickness of the airfoil proportional to the blade pitch changes.
- the change in the blade profile takes place via the Height of the guide vane in that no change in shape the leading edge (pressure side) takes place, but the protrusion on the trailing edge in size over that Height gradually increases as thickness increases the guide vane.
- the profile change is carried out here that the thickness of the vane increases as its Chord length remains the same.
- Such a vane ring is applicable to steam turbines, gas turbines and compressors.
- Inclined turbine blades for a steam turbine are also in the article "Development of three-dimensional stage viscous time marching method for optimization of short height stages "by G. Singh, P.J. Walker, B.R. Haller, in: "VDI Reports No. 1185, 1995, pp. 157-179.
- the object of the invention is a scoop with low To specify flow losses for a turbomachine.
- a Another object of the invention is a steam turbine to be indicated with low flow losses.
- a blade for a turbomachine directed task by such a shovel solved which is directed along a blade axis and along this blade axis a foot end area, a Head end area and in between a middle area and a has a cross-sectional profile perpendicular to the blade axis, being axially spaced apart in the direction of the blade axis
- Direction are offset from each other and being in the foot end area and / or axially spaced apart in the head end region
- Cross-sectional profiles against each other by a difference angle are twisted.
- the axially spaced cross-sectional areas are preferably in the foot end area and in the head end area for Center area rotated in the same direction. This is about the entire height of the bucket from the head end to At the foot end, the twisting is withdrawn.
- the blade is preferably for arrangement in a blade ring designed which has a circumferential direction, where the cross-sectional direction is local to the circumferential direction coincides. This takes place in the edge zones of the blade a circumferential bend with a simultaneous one Rotation (angle adjustment) in the end areas of the blade, thereby reducing flow losses and thus an increase in the efficiency of a turbomachine can be achieved is. This is particularly the case with steam turbines on the one hand an increase in the mechanical exit energy with the same thermal energy input and on the other hand a reduction in the use of thermal energy and thus the Environmental pollution due to pollutant emissions with the same Exit energy compared to pure cylindrical or pure inclined or curved blades.
- the cross-sectional profiles are preferably one turn with respect to their center of area or with respect to the blade axis (if different, e.g. due to inhomogeneous mass distribution) turned.
- the angle of rotation that occurs is in following as a stagger angle and performing the rotation referred to as a change in stagger angle.
- Cross-sectional profile preferably along the blade axis the same everywhere.
- the cross-sectional profile changes accordingly not about the height of the bucket.
- the cross-sectional area of the cross-sectional profiles is also constant.
- the blade preferably has a combination a circumferential deflection of the center of gravity of the cross-sectional profiles (Bend in the circumferential direction) and a staggering of the Cross-sectional profiles (without changing the profile) in Head end and foot end area (hub and housing area).
- the blade in the middle area preferably cylindrical.
- the pages (printed page, Suction side) of the blade therefore run parallel to the Blade axis.
- the blade is preferably a guide blade or a moving blade a steam turbine, in particular a high pressure or Medium pressure steam turbine executed.
- the Shovel a small length to width ratio on how it is particularly with blades for a high pressure steam turbine the case is.
- the task aimed at a steam turbine is for a Steam turbine, which is directed along a turbine axis is and an inflow area, an outflow area and a Blading area arranged between them in terms of flow has, solved in that in the blading area one directed along a blade axis Blade is arranged, which is a via the blade axis Inclination and a twist, each of one Increase foot end area to a middle area and from that Remove the central area from a head end area.
- the bucket with increasing and decreasing inclination and twisting is preferably assigned to the inflow area. It is therefore preferably in the first stage and / or the subsequent ones Stages arranged. This applies to both levels comprehensively a blade ring made of moving blades or guide blades.
- Stage losses secondary losses particularly high in the hub and housing area is (e.g. up to 30% of the total losses) and by the specified Blade shape is reduced, this can be a noticeable Increased efficiency can be achieved.
- the outflow area is preferably a twisted blade, i.e. a scoop with increasing twist along its length and changing the cross-sectional profile and / or the cross-sectional area, arranged.
- a twisted blade i.e. a scoop with increasing twist along its length and changing the cross-sectional profile and / or the cross-sectional area, arranged.
- a pure one cylindrical blade i.e. with parallel to the blade axis Side walls, provided.
- FIG. 1 is a turbomachine, a high pressure steam turbine 11, shown in a longitudinal section along a turbine axis 17 is directed.
- the steam turbine 11 has a turbine shaft directed along the turbine axis 17 20, which are surrounded by a turbine housing 18 is.
- the steam turbine 11 points along the turbine axis 17 an inflow area 12 for action fluid, superheated steam, and an outflow area 13 for the superheated steam.
- Axially between Inflow area 12 and outflow area 13 is a blading area 14 provided.
- In the blading area 14 follow each other alternately in the axial direction summarized in a corresponding blade ring 21 Guide vanes 9 and blades 8.
- Each blade 8 and each guide vane 9 points along a vane axis 2 (see FIG.
- a foot end area 3 a head end area 4 and arranged axially in between in the direction of the blade axis 2 a central area 10.
- the inflow area 12 closest blades 8 and / or guide blades 9 are each designed as a blade 1, which in the Foot end area 3 and in the head end area 4 inclined and twisted is.
- Blade 8 closest to outflow area 13 and guide blades 9 are each twisted blades 19 with increasing rotation over the blade axis 2 and itself changing cross-sectional profile.
- the suction and pressure side are each parallel to the blade axis 2.
- FIG. 2 shows a section of a blade ring 21, in the blades 1 arranged side by side in the circumferential direction 6a are.
- the blade ring is 21 unwound along the circumferential direction 6a and with only two blades 1 shown.
- the circumferential direction 6a corresponds to the circumference of the turbine shaft 20 in one section perpendicular to the turbine axis 17.
- the main flow direction 22 of the steam flowing in the steam turbine 11 is vertical to the circumferential direction 6a of the blade ring 21.
- FIG. 3 shows the aerofoil area in a spatial representation 23 one directed along a blade axis 2 Shovel 1 shown.
- the airfoil area 23 has a foot end area 3, a head end area 4 and in between a central area 10.
- an adjoining the foot end area 3 Fastening area with which the door window shovel 1 in the turbine shaft 20 or the turbine housing 18 attached is.
- the cover band adjoining the head end region 4 is not shown.
- the turbine blade 1 in a cross-sectional direction 6 the preferably the circumferential direction 6a of the blade ring 21 corresponds, inclined, and in the axial direction by a difference angle ⁇ (see Figures 4 and 5) rotated.
- the one in the foot end area 3 enlarging towards the central region 10 Corresponds to twisting and increasing circumferential bending the same twist and circumferential bend as in the head end area 4.
- About the height of the middle area 10 remains the degree of displacement and twisting constant.
- the size of the back turn and back shift over the head end area 4 is preferably as large as the displacement and rotation in the foot end area 3.
- the circumferential bend here means a displacement of the Cross-sectional profile 5, 5a in the direction of a cross-sectional direction 6, which preferably in the circumferential direction 6a Blade ring 21 corresponds.
- a rotation of the blade 1 takes place by changing the stagger angle, i.e. a change of the angle ⁇ according to FIG. 4 and FIG. 5 by rotation of the cross-sectional profile 5 about the blade axis 2, which is preferably coincides with the gravity axis of the bucket 1.
- Mass distribution also corresponds to a rotation around the center of gravity 7 (center of mass 7) of the cross-section profile 5, 5a.
- the cross-sectional profile 5, 5a, 5b is over the entire height of the airfoil area 23 for everyone Cross-section the same, i.e. especially that cross-sectional shape and area are constant.
- the shown in Figure 5 Cross-sectional profile 5b is compared to that shown in Figure 4 Cross-sectional profile 5a rotated by the difference angle ⁇ and shifted by the shift value ⁇ U. This matches with a change in the stagger angle ⁇ to the value of the Stagger angle ⁇ '( Figure 5).
- the edge losses i.e. the fluid mechanics Losses in the vicinity of the turbine shaft and the turbine housing, can be up to about 30% of the total losses, leads to a reduction of these edge losses due to the twisting and peripheral bending of the blade in a steam turbine to increase efficiency.
- the degree of twist and circumferential bend is in each case related to the fluidic Ratios in a steam turbine adaptable, the Twist and circumferential bend also over the entire May extend mid-range. It is also possible that the central area is purely cylindrical, i.e. the suction side and the pressure side of the blade parallel to the blade axis are directed.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Description
- FIG 1
- einen Längsschnitt durch eine Hochdruck-Dampfturbine,
- FIG 2
- einen Querschnitt eines Ausschnitts durch einen Schaufelkranz,
- FIG 3
- eine räumliche Darstellung des Schaufelblattbereichs einer Schaufel,
- FIG 4
- einen Querschnitt durch den Schaufelblattbereich der Schaufel gemäß Figur 3 und
- FIG 5
- einen weiteren Querschnitt durch die Schaufel gemäß Figur 3 axial in Richtung der Schaufelachse beabstandet von dem Querschnitt gemäß Figur 4.
Claims (11)
- Schaufel (1) für eine Strömungsmaschine (11), welche entlang einer Schaufelachse (2) gerichtet ist, mit einem Fußendbereich (3) und einem diesem entlang der Schaufelachse (2) gegenüber angeordneten Kopfendbereich (4) sowie einem dazwischen angeordneten Mittelbereich (10) und mit einem zur Schaufelachse (2) senkrechten Querschnittsprofil (5; 5a, 5b; 15a, 15b), wobei im Kopfendbereich (4) zum Mittelbereich (10) hin axial in Richtung der Schaufelachse (2) voneinander beabstandete Querschnittsprofile (5a, 5b) in einer Querschnittsrichtung (6) durch eine Translation gegeneinander versetzt sind, und im Fußendbereich (3) zum Mitteibereich (10) hin axial voneinander beabstandete Querschnittsprofile (15a, 15b) in derselben Querschnittsrichtung (6) durch eine Translation gegeneinander versetzt sind und wobei im Fußendbereich (3) und/oder im Kopfendbereich (4) axial voneinander beabstandete Querschnittsprofile (15a, 15b; 5a, 5b) um einen jeweiligen Differenzwinkel (Δβ) gegeneinander verdreht sind.
- Schaufel (1) nach Anspruch 1, wobei die axial voneinander beabstandeten Querschnittsprofile (5a, 5b;15a, 15b) im Fußendbereich (3) und im Kopfendbereich (4) zum Mittelbereich (10) hin jeweils gleichgerichtet verdreht sind.
- Schaufel (1) nach einem der vorhergehenden Ansprüche zur Anordnung in einen Schaufelkranz mit einer Umfangsrichtung (6a), wobei die Querschnittsrichtung (6) lokal mit der Umfangsrichtung (6a) zusammenfallt.
- Schaufel (1) nach einem der vorhergehenden Ansprüche, bei der Querschnittsprofile (5a, 5b;15a, 15b) jeweils bezüglich ihres Flächenschwerpunktes (7) gedreht sind.
- Schaufel (1) nach einem der vorhergehenden Ansprüche, bei der das Querschnittsprofil (5a, 5b; 15a, 15b) entlang der Schaufelachse (2) überall gleich ist.
- Schaufel (1) nach einem der vorhergehenden Ansprüche, die im Mittelbereich (10) zylindrisch ausgeführt ist.
- Schaufel (1) nach einem der vorhergehenden Ansprüche, die als Leitschaufel (9) oder Laufschaufel (8) einer Dampfturbine (11), ausgeführt ist.
- Dampfturbine (11), insbesondere Hochdruck- oder Mitteldruckdampfturbine, die entlang einer Turbinenachse (17) gerichtet ist, mit einem Einstrombereich (12), einem Abströmbereich (13) und einem strömungstechnisch dazwischen angeordneten Beschaufelungsbereich (14), wobei in dem Beschaufelungsbereich (14) eine entlang einer Schaufelachse (2) gerichtete Schaufel (1) angeordnet ist, welche Schaufel (1) über die Schaufelachse (2) ein Neigung und eine Verdrehung aufweist, welche jeweils von einem Fußendbereich (3) zu einem Mittelbereich (10) zunehmen und von dem Mittelbereich (10) zu einem Kopfendbereich (4) abnehmen.
- Dampfturbine (11) nach Anspruch 8, bei der die Schaufel (1) mit ab- und zunehmender Neigung und Verdrehung dem Einströmbereich (12) zugeordnet ist.
- Dampfturbine (11) nach Anspruch 9, bei der eine verwundene Schaufel (19) dem Abströmbereich (13) zugeordnet ist.
- Dampfturbine (11) nach Anspruch 10, bei der in Richtung der Turbinenachse (17) zwischen der Schaufel (1) und der verwundenen Schaufel (19) eine rein zylindrische Schaufel (16) angeordnet ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19739318 | 1997-09-08 | ||
DE19739318 | 1997-09-08 | ||
PCT/DE1998/002556 WO1999013199A1 (de) | 1997-09-08 | 1998-08-31 | Schaufel für eine strömungsmaschine sowie dampfturbine |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1012445A1 EP1012445A1 (de) | 2000-06-28 |
EP1012445B1 true EP1012445B1 (de) | 2002-10-02 |
EP1012445B2 EP1012445B2 (de) | 2008-01-16 |
Family
ID=7841609
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98951240A Expired - Lifetime EP1012445B2 (de) | 1997-09-08 | 1998-08-31 | Schaufel für eine strömungsmaschine |
Country Status (8)
Country | Link |
---|---|
US (1) | US6354798B1 (de) |
EP (1) | EP1012445B2 (de) |
JP (1) | JP4217000B2 (de) |
KR (1) | KR20010023783A (de) |
CN (1) | CN1100195C (de) |
AT (1) | ATE225460T1 (de) |
DE (1) | DE59805843D1 (de) |
WO (1) | WO1999013199A1 (de) |
Families Citing this family (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10027084C2 (de) * | 2000-05-31 | 2002-07-18 | Honda Motor Co Ltd | Leitschaufel und Leitschaufelkaskade für einen Axialverdichter |
US6682301B2 (en) * | 2001-10-05 | 2004-01-27 | General Electric Company | Reduced shock transonic airfoil |
DE60121968T2 (de) * | 2001-11-22 | 2006-12-07 | Siemens Ag | Verfahren zum Herstellen von Dampfturbinen |
JP2005522629A (ja) | 2002-04-11 | 2005-07-28 | エイ. ハーゼ,リチャード | 水燃焼技術−水素と酸素を燃焼させる方法、プロセス、システム及び装置 |
CA2426892C (en) | 2002-08-16 | 2011-10-25 | The Fuel Genie Corporation | Device and method for changing angular velocity of airflow |
US7262550B2 (en) * | 2003-04-15 | 2007-08-28 | Luminus Devices, Inc. | Light emitting diode utilizing a physical pattern |
EP1710397B1 (de) * | 2005-03-31 | 2014-06-11 | Kabushiki Kaisha Toshiba | Gekrümmte Leitschaufel |
FR2903138B1 (fr) * | 2006-06-28 | 2017-10-06 | Snecma | Aube mobile et disque de rotor de turbomachine, et dispositif d'attache d'une telle aube sur un tel disque |
US8545170B2 (en) * | 2009-10-27 | 2013-10-01 | General Electric Company | Turbo machine efficiency equalizer system |
US8342009B2 (en) | 2011-05-10 | 2013-01-01 | General Electric Company | Method for determining steampath efficiency of a steam turbine section with internal leakage |
ITTO20111009A1 (it) * | 2011-11-03 | 2013-05-04 | Avio Spa | Profilo aerodinamico di una turbina |
US9032733B2 (en) | 2013-04-04 | 2015-05-19 | General Electric Company | Turbomachine system with direct header steam injection, related control system and program product |
CN107489461A (zh) * | 2017-09-15 | 2017-12-19 | 哈尔滨汽轮机厂有限责任公司 | 一种用于汽轮机叶片的高效宽负荷叶型 |
RU191926U1 (ru) * | 2019-02-28 | 2019-08-28 | Публичное Акционерное Общество "Одк-Сатурн" | Сопловой аппарат турбины |
JP7264685B2 (ja) * | 2019-03-26 | 2023-04-25 | 三菱重工航空エンジン株式会社 | タービン静翼、及びタービン |
CN113339325B (zh) * | 2021-08-09 | 2022-01-07 | 中国航发上海商用航空发动机制造有限责任公司 | 用于压气机的进口级叶片组件及包含其的轴流压气机 |
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DE1168599B (de) | 1953-10-29 | 1964-04-23 | United Aircraft Corp | Axialverdichter |
JPS5447907A (en) | 1977-09-26 | 1979-04-16 | Hitachi Ltd | Blading structure for axial-flow fluid machine |
JPS5944482B2 (ja) | 1980-12-12 | 1984-10-30 | 株式会社東芝 | 軸流タ−ビン |
US4682935A (en) * | 1983-12-12 | 1987-07-28 | General Electric Company | Bowed turbine blade |
GB2164098B (en) * | 1984-09-07 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for turbine engines |
US4826400A (en) * | 1986-12-29 | 1989-05-02 | General Electric Company | Curvilinear turbine airfoil |
JP2665005B2 (ja) * | 1989-10-24 | 1997-10-22 | 三菱重工業株式会社 | 軸流機械の動翼 |
US5088892A (en) * | 1990-02-07 | 1992-02-18 | United Technologies Corporation | Bowed airfoil for the compression section of a rotary machine |
US5067876A (en) * | 1990-03-29 | 1991-11-26 | General Electric Company | Gas turbine bladed disk |
US5203676A (en) * | 1992-03-05 | 1993-04-20 | Westinghouse Electric Corp. | Ruggedized tapered twisted integral shroud blade |
DE4228879A1 (de) | 1992-08-29 | 1994-03-03 | Asea Brown Boveri | Axialdurchströmte Turbine |
DE4228870C2 (de) | 1992-08-29 | 1997-01-09 | Inst Halbleiterphysik Gmbh | Verfahren zum Bestimmen geometrischer Abmessungen an dünnen, optisch transparenten Schichten |
DE4344189C1 (de) * | 1993-12-23 | 1995-08-03 | Mtu Muenchen Gmbh | Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten |
GB9417406D0 (en) * | 1994-08-30 | 1994-10-19 | Gec Alsthom Ltd | Turbine blade |
US5525038A (en) * | 1994-11-04 | 1996-06-11 | United Technologies Corporation | Rotor airfoils to control tip leakage flows |
JPH0925897A (ja) * | 1995-07-11 | 1997-01-28 | Mitsubishi Heavy Ind Ltd | 軸流圧縮機の静翼 |
US6071077A (en) * | 1996-04-09 | 2000-06-06 | Rolls-Royce Plc | Swept fan blade |
JP3621216B2 (ja) * | 1996-12-05 | 2005-02-16 | 株式会社東芝 | タービンノズル |
US6195983B1 (en) * | 1999-02-12 | 2001-03-06 | General Electric Company | Leaned and swept fan outlet guide vanes |
-
1998
- 1998-08-31 EP EP98951240A patent/EP1012445B2/de not_active Expired - Lifetime
- 1998-08-31 AT AT98951240T patent/ATE225460T1/de not_active IP Right Cessation
- 1998-08-31 JP JP2000510964A patent/JP4217000B2/ja not_active Expired - Fee Related
- 1998-08-31 WO PCT/DE1998/002556 patent/WO1999013199A1/de not_active Application Discontinuation
- 1998-08-31 KR KR1020007002440A patent/KR20010023783A/ko not_active Application Discontinuation
- 1998-08-31 DE DE59805843T patent/DE59805843D1/de not_active Expired - Lifetime
- 1998-08-31 CN CN98808932A patent/CN1100195C/zh not_active Expired - Fee Related
-
2000
- 2000-03-08 US US09/521,397 patent/US6354798B1/en not_active Expired - Lifetime
Non-Patent Citations (4)
Title |
---|
G. Singh, P: J. Walker, B.R. Hailer, "Development of Three-Dimensional Stage Viscous Time Marching Method for Optimisation of Short Heights Stages", VDI Berichte NR. 1185, 1995. * |
J. I. Cofer, IV, GE Power Generation, "Advances in Steam Path Technology", Journal of Engineering for Gas Turbines and Power, April 1998. Vol. 118, pp. 337-352. * |
K Kobayashi, M Honjo, H Tashiro and I Nagayama, "Verification of flow pattern for three-dimensional-designes blades" C423101 5 ©IMechE 1991. * |
Ueli Wieland, Andreas Kirschner, Said Havakechian, Brendon Scarfin,"Advanced Steam Turbine Blading for Retrofit and Repowering Applications", American Society of Mechanical Engineers: PWR - Vol. 26, Advanced, in Steam Turbine Technology for the Power Generation Industry, Editor W.G. Moore, Book No B0877 - 1994, pp.19-25 * |
Also Published As
Publication number | Publication date |
---|---|
EP1012445A1 (de) | 2000-06-28 |
JP4217000B2 (ja) | 2009-01-28 |
CN1100195C (zh) | 2003-01-29 |
US6354798B1 (en) | 2002-03-12 |
ATE225460T1 (de) | 2002-10-15 |
KR20010023783A (ko) | 2001-03-26 |
JP2001515983A (ja) | 2001-09-25 |
CN1269865A (zh) | 2000-10-11 |
WO1999013199A1 (de) | 1999-03-18 |
EP1012445B2 (de) | 2008-01-16 |
DE59805843D1 (de) | 2002-11-07 |
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