EP0661413B1 - Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten - Google Patents
Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten Download PDFInfo
- Publication number
- EP0661413B1 EP0661413B1 EP19940119705 EP94119705A EP0661413B1 EP 0661413 B1 EP0661413 B1 EP 0661413B1 EP 19940119705 EP19940119705 EP 19940119705 EP 94119705 A EP94119705 A EP 94119705A EP 0661413 B1 EP0661413 B1 EP 0661413B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- cascade
- blades
- gravity
- rotor
- 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
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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
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- 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
Definitions
- the invention relates to an axial vane grille according to the preamble of claim 1.
- the object is characterized by the characteristic features of claim 1 solved.
- the design according to the invention has the advantage that the straight, swept course in addition to that from the prior art Technology known effect, influencing the secondary flow Blade grilles, the radial pressure gradient over the blades in the limit area can be influenced, so that the unwanted The formation of horseshoe vertebrae on the side wall is at least reduced becomes. Since the improvement in step efficiency that can be achieved in this way not solely on influencing the rotor blades of The centrifugal secondary flow is based on how this is done the state of the art is known, the invention in running and Guide vane grilles for compressor and turbine blades Be made use of.
- Flow-favorable positive arrow angles ⁇ G and ⁇ N between the Blade leading edge and a solder on the radially inner or radial The outer boundary of the ring channel is between 5 ° and 45 °. Allow negative arrow angles ⁇ G and ⁇ N between -10 ° and 0 ° even with structurally difficult conditions with the sweep related benefits.
- the transition area is designed with a constant curvature and low stress will.
- the curved section following the straight section up to starting from a relative distance of 25% of the associated bucket height from the respective limit into the interior of the blade.
- the rotor blades In the case of a design of the rotor blade as a hollow blade to avoid a high bending moment stress under the influence of centrifugal force standing rotor blading of rotor blade grids the rotor blades have cavities that at least overlap extend part of the blade length, the extension of the Cavities are so distributed over the blade profile depth that the The focus of the profile cuts is on a common level. In turbine blades, the cavities can be used as cooling channels be trained.
- the axial offset allows the individual profile cuts have a favorable influence on the bending moment stress of the airfoil are exerted, the offset can be chosen such that the blade center of gravity in the The line of gravity of the disc comes to rest.
- the center of gravity is also on the common level. Strength-reducing tensions in the blade root area are thus avoided.
- the focal points of the blades are such Blade grid and the center of gravity of the shroud so axially spaced from the center of gravity of the vane grille that the center of gravity the disk receiving the rotor blades on the center of gravity of the Blade grid is located. This in turn results in a low bending stress Design in the area of the blade feet.
- Blade trailing edges result in constant or even Increase or decrease of the airfoil depth over the airfoil length.
- FIG. 1a to 4b show representations in the z-r plane.
- the one in figure 1a schematically shown upper half of a two-stage axial turbine has guide and rotor blade grilles arranged axially one after the other in pairs 2 or 3 with concave against the direction of flow S curved guide or blades 4,5 are equipped.
- the Blades 6 of the guide and moving blades 4.5 extend radially concentric in a to the machine longitudinal axis A of the axial turbine 1 arranged ring channel 7.
- the axially concentric hub and housing side walls form the radially inner and radially outer channel boundary 8 or 9 of the ring channel 7 and give this one with respect to the flow direction S divergent course.
- the rotor blade grids 3 are of disc construction, i.e.
- the blades 5 are each grid-wise on a disk 10 appropriate.
- 1b shows an axial turbine designed according to the prior art 1 'whose guide and rotor blade grille 2' or 3 'with non-curved Guide and rotor blades 4 'or 5' is equipped.
- Threading means the positioning of individual profile cuts Pn of an airfoil 6 with respect to a reference line perpendicular to the machine longitudinal axis A, called threading axis F. which, in the case of rotor blades 5, generally runs through the blade center of gravity SP L, is to be understood for the profiling of an airfoil 6.
- the profile cuts P n coincide with lines of the same relative blade height h in the zr plane.
- the associated blade height h in turn results from the distance to be measured perpendicular to the longitudinal axis A of the machine between the inner and outer channel boundaries 8 and 9.
- the blade leading edge 11 has a rectilinear section B G and B N in the rz plane.
- the arrow angle . ⁇ .G or ⁇ .N to be measured relative to a perpendicular L to the respective channel boundary 8.9 is 25 ° within the sections B G and B N on the housing side and 45 ° on the hub side.
- the blade leading edge 11 each has a curved extending section Ü G or Ü N , which corresponds to a second-order or higher-order polynomial.
- the blade edge 11 is again designed to be straight in the rz plane.
- the transitions from curved to rectilinear course in the blade leading edge 11 are formed continuously.
- the shape of the trailing edge 12 of the blade results from the specification of the blade depth t (h), which decreases linearly here with increasing duct height h.
- the rotor blade grille shown in FIG. 3 in the r-z plane 3 is of disk construction, the rotor blades 5 About their molded blade feet 13 positively in evenly in the circumferential direction ⁇ . spaced-apart disk grooves 14 the disc 10 are attached.
- the centers of gravity SP G and SP S of the rotor blade grille 3 and the disk 10 lying on the machine longitudinal axis A coincide.
- the focal points SP L of the moving blades 5 lie on a common plane E by corresponding threading of the profile cuts P, which is perpendicular to the machine axis A and runs through the common focal point SPS and SPG of the disk 10 or of the moving blade grid 3.
- the rotor blade grille 3 is to avoid pressure losses and to improve the flow quality with a in the circumferential direction.
- segmented shroud 15 provided which includes the blades at the radially outer end. By balancing the shroud segments in the z direction, the centers of gravity SP D of the shroud segments 15 are also on the plane E, whereby bending stresses in the blades 5 are avoided or reduced.
- Fig. 4 shows an alternative embodiment of a blade 5 to avoid bending stresses in the blade 5 due to unbalanced centers of gravity SP P of the profile cuts P n .
- the interior of the airfoil 6 has a cavity 16 which extends over the channel height h and whose extension over the airfoil depth t (h) is designed such that the centers of gravity SP P of the profile cuts P n lie in an r-common plane.
- FIG. 5 shows an additional concave with respect to the blade suction side 18, Blade 6 curved in the circumferential direction.
- This additional Curvature can advantageously influence the radial Pressure gradients in the outflow plane of a guide or rotor blade 4.5 to take. Due to the circumferential bend, the profile cuts close to the limit aerodynamically relieved. With higher loads at the same time of the center area of the blade 4.5, which makes a total of Blade 4.5 a more efficient efficiency can be achieved.
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Chain Conveyers (AREA)
Description
- Fig. 1 a
- einen Längsschnitt durch die Niederdruckturbine eines Strahltriebwerkes mit gekrümmten Turbinenschaufeln,
- Fig. 1 b
- einen Längsschnitt durch die Niederdruckturbine eines Strahltriebwerkes mit geradlinig verlaufenden Turbinenschaufeln,
- Fig. 2
- einen vergrößerten Ausschnitt eines gekrümmten Schaufelblattes gemäß Fig. 1a,
- Fig. 3
- einen teilweisen Längsschnitt eines Laufschaufelgitters mit Scheibe und Deckband,
- Fig. 4
- einen Schnitt durch die Skelettfläche einer Laufschaufel mit hohlem Schaufelblatt und
- Fig. 5
- eine Ansicht eines Laufschaufelblattes mit Krümmung in Umfangsrichtung
Claims (14)
- Schaufelgitter (2, 3) für Axial-Strömungsmaschinen mit Ringkanal (7), wobei die Schaufelvorderkanten (11) der Schaufeln (4, 5) des im Ringkanal (7) angeordneten Schaufelgitters (2, 3) in randnahen Bereichen der radial inneren und/oder radial äußeren Kanalbegrenzung (8 bzw. 9) des Ringkanals (7) in axialer Richtung gepfeilt sind, dadurch gekennzeichnet, daß die Schaufelvorderkanten (11) in den randnahen Bereichen einen geradlinig verlaufenden Abschnitt (BG bzw. BN) und im Anschluß an diesen Abschnitt, in Übergangsbereichen einen gekrümmt verlaufenden Abschnitt (ÜG bzw. ÜN) aufweisen.
- Schaufelgitter nach Anspruch 1, dadurch gekennzeichnet, daß die geradlinig verlaufenden Abschnitte (BG bzw. BN) sich um einen Abstand von der Schaufelblattspitze (17) bzw. von dem Nabenschnitt PN des Schaufelblattes (6) von bis zu 30% der zugehörigen Schaufelhöhe (h) erstrecken.
- Schaufelgitter nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß positive Pfeilungswinkel (δG bzw. δN) jeweils gemessen in einem Längsschnitt zwischen einem geradlinig verlaufenden Abschnitt (BG bzw. BN) einer Schaufelvorderkante (11) und einer Lotrechten (L) auf eine radial äußere bzw. radial innere Begrenzung (9,8) des Ringkanals (7) im Schnittpunkt mit der Schaufelvorderkante (11) zwischen 5° und 45° betragen.
- Schaufelgitter nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß der gekrümmte Verlauf der Schaufelvorderkanten (11) in den Übergangsbereichen Polynomen zweiter oder höherer Ordnung entsprechen.
- Schaufelgitter nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Schaufelvorderkanten (11) im Anschluß an die Übergangsbereiche im Mittenbereich der Schaufelblätter (6) einen geradlinig verlaufenden Abschnitt (M) aufweisen.
- Schaufelgitter nach Anspruch 5, dadurch gekennzeichnet, daß die gekrümmt verlaufenden Abschnitte (ÜG bzw. ÜN) bis zu 50% der zugehörigen Schaufelhöhe einnehmen.
- Schaufelgitter nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Schaufelblätter (6) zusätzlich zur Pfeilung in Umfangsrichtung gekrümmt sind.
- Schaufelgitter nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß das Schaufelgitter ein Laufschaufelgitter (3) mit Laufschaufeln (5) ist.
- Schaufelgitter nach Anspruch 7, dadurch gekennzeichnet, daß die Laufschaufeln (5) Hohlräume (16) aufweisen, die sich zumindest über einen Teil der Schaufellänge erstrecken, wobei die Ausdehnung der Hohlräume (16) derart über die Schaufelprofiltiefe (t) verteilt sind, daß die Schwerpunkte der Profilschnitte (Pn) auf einer gemeinsamen Ebene (E) senkrecht zur Maschinenlängsachse (A) liegen.
- Schaufelgitter nach Anspruch 9, dadurch gekennzeichnet, daß die Hohlräume (16) Kühlkanäle sind.
- Schaufelgitter nach einem der Ansprüche 8 bis 10, dadurch gekennzeichnet, daß das Laufschaufelgitter (3) eine die Laufschaufeln (5) aufnehmende Scheibe (10) aufweist, deren Schwerpunkt (SPs) auf der gemeinsamen Ebene (E) liegt.
- Schaufelgitter nach einem der Ansprüche 8 bis 11, dadurch gekennzeichnet, daß das Laufschaufelgitter (3) ein Deckband (15) und eine, die Laufschaufeln (5) aufnehmende Scheibe (10) aufweist, wobei die Schwerpunkte (SPL) der Laufschaufeln (5) und der Schwerpunkte (SPD) des Deckbandes (15) derart axial vom Schwerpunkt (SPG) des Laufschaufelgitters (3) beabstandet sind, daß der Schwerpunkt (SPs) der Scheibe (10) auf dem Schwerpunkt (SPG) des Laufschaufelgitters (3) liegt.
- Schaufelgitter nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß die Schaufelblattiefe t(h) zwischen Schaufelvorder- (11) und -hinterkante (12) der Laufschaufel (5) eines Schaufelgitters über die Schaufelhöhe (h) konstant ist oder linear verläuft.
- Schaufelgitter nach einem der vorhergehenden Ansprüche, dadurch gekennzeichnet, daß dem Verlauf der Schaufelvorder- (11) und/oder -hinterkante (12) der Schaufel (5,6) im Bereich der randnahen Profilschnitte (PN bzw. PG) ein Ausrundungsradius (RN bzw. RG) überlagert ist.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE4344189 | 1993-12-23 | ||
DE19934344189 DE4344189C1 (de) | 1993-12-23 | 1993-12-23 | Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0661413A1 EP0661413A1 (de) | 1995-07-05 |
EP0661413B1 true EP0661413B1 (de) | 1998-08-26 |
Family
ID=6506022
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19940119705 Expired - Lifetime EP0661413B1 (de) | 1993-12-23 | 1994-12-14 | Axial-Schaufelgitter mit gepfeilten Schaufelvorderkanten |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0661413B1 (de) |
DE (1) | DE4344189C1 (de) |
ES (1) | ES2123700T3 (de) |
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US7419353B2 (en) | 2005-09-05 | 2008-09-02 | Rolls-Royce Deutschland Ltd & Co Kg | Blade of a turbomachine with block-wise defined profile skeleton line |
US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
US7874802B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
US7878762B2 (en) | 2004-12-01 | 2011-02-01 | United Technologies Corporation | Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor |
US7882694B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Variable fan inlet guide vane assembly for gas turbine engine |
US7887296B2 (en) | 2004-12-01 | 2011-02-15 | United Technologies Corporation | Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine |
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Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB719061A (en) * | 1950-06-21 | 1954-11-24 | United Aircraft Corp | Blade arrangement for improving the performance of a gas turbine plant |
DE2034890A1 (de) * | 1969-07-21 | 1971-02-04 | Rolls Royce Ltd Derby, Derbyshire (Großbritannien) | Schaufel fur Axialstromungsmaschinen |
US4012172A (en) * | 1975-09-10 | 1977-03-15 | Avco Corporation | Low noise blades for axial flow compressors |
JPS5447907A (en) * | 1977-09-26 | 1979-04-16 | Hitachi Ltd | Blading structure for axial-flow fluid machine |
FR2556409B1 (fr) * | 1983-12-12 | 1991-07-12 | Gen Electric | Aube perfectionnee pour moteur a turbine a gaz et procede de fabrication |
GB2164098B (en) * | 1984-09-07 | 1988-12-07 | Rolls Royce | Improvements in or relating to aerofoil section members for turbine engines |
JP2665005B2 (ja) * | 1989-10-24 | 1997-10-22 | 三菱重工業株式会社 | 軸流機械の動翼 |
ES2128357T3 (es) * | 1991-08-30 | 1999-05-16 | Airflow Res & Mfg | Aparato ventilador sesgado hacia adelante con inclinacion. |
-
1993
- 1993-12-23 DE DE19934344189 patent/DE4344189C1/de not_active Expired - Fee Related
-
1994
- 1994-12-14 EP EP19940119705 patent/EP0661413B1/de not_active Expired - Lifetime
- 1994-12-14 ES ES94119705T patent/ES2123700T3/es not_active Expired - Lifetime
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EP3816397B1 (de) * | 2019-10-31 | 2023-05-10 | General Electric Company | Turbinenschaufel mit kontrollierter strömung |
Also Published As
Publication number | Publication date |
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DE4344189C1 (de) | 1995-08-03 |
EP0661413A1 (de) | 1995-07-05 |
ES2123700T3 (es) | 1999-01-16 |
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