DE2002348B2 - Blade ring for an axial flow turbine - Google Patents
Blade ring for an axial flow turbineInfo
- Publication number
- DE2002348B2 DE2002348B2 DE2002348A DE2002348A DE2002348B2 DE 2002348 B2 DE2002348 B2 DE 2002348B2 DE 2002348 A DE2002348 A DE 2002348A DE 2002348 A DE2002348 A DE 2002348A DE 2002348 B2 DE2002348 B2 DE 2002348B2
- Authority
- DE
- Germany
- Prior art keywords
- blade
- blades
- suction side
- pressure
- supersonic
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
tisch und besitzt ein Verhältnis Md, das der folgenden Bedingung genügt:table and has a ratio Md that satisfies the following condition:
Von dem Punkt der größten Dicke d verengt sich die Schaufel zum Hals 11 am Anfang des mittleren Teils 4 der Schaufel, Die Saugseite ist in diesem sich verengenden Querschnitt leicht konkav gewölbt, wie es bei 12 angedeutet ist.From the point of greatest thickness d , the shovel narrows towards the neck 11 at the beginning of the middle part 4 of the shovel. The suction side is slightly concave in this narrowing cross section, as indicated at 12.
Das Mittelteil 4 der Schaufel ist sowohl auf der Druck- als auch auf der Saugseite nahezu flach ausgebildet. Die flachen Druck- und Saugseiten divergieren von dem relativ engen Hals 11 am Anfang des mittleren Teiles 4 bis zu einem relativ dicken »Halsteil«, das an seiner dicksten Stelle mit »i« bezeichnet ist. Das Halsteil t befindet sich etwa bei dreiviertel der Profiltiefe entlang der Schaufel und ist deshalb so bezeichnet, weil es dem dicksten Nasenteü d einer benachbarten Schaufel gegenüberliegt, um mit ihm zwischen den Schaufeln 1 und 2 einen Düsenhals einer konvergenten - divergenten Düse zu bilden.The middle part 4 of the blade is designed to be almost flat on both the pressure side and the suction side. The flat pressure and suction sides diverge from the relatively narrow neck 11 at the beginning of the middle part 4 to a relatively thick "neck part", which is labeled "i" at its thickest point. The neck part t is located about three quarters of the profile depth along the blade and is so named because it is opposite the thickest nose part of an adjacent blade in order to form a nozzle neck of a convergent - divergent nozzle with it between the blades 1 and 2.
In einigen Fällen kann die Dicke d des Nasenteils 3 geringfügig größer als t sein, und in anderen Fällen kann die Halsdicke t geringfügig größer als d sein. In jedem Fall jedoch sind die beiden Größen angenähert gleich.In some cases, the thickness d of the nose part 3 can be slightly larger than t , and in other cases the neck thickness t can be slightly larger than d . In each case, however, the two sizes are approximately the same.
Das Endteil 5 des Schaufelprofils besitzt eine relativ flache Saugseite, die eine Fortsetzung der davor angeordneten flachen Saugseite über dem Mittelteil der Schaufel darstellt. Auf der Druckseite ist die Kiirvenform der Schaufel nach dem Durchlaufen des Halsteils t umgekehrt und wölbt sich leicht in Richtung der Hinterkante 9, so daß sich eine leicht konkave Oberfläche auf der Druckseite ergibt.The end part 5 of the blade profile has a relatively flat suction side, which is a continuation of the flat suction side arranged in front of the middle part of the blade. On the pressure side, the vane shape of the blade is reversed after it has passed through the neck part t and curves slightly in the direction of the rear edge 9, so that a slightly concave surface results on the pressure side.
ίο Die Arbeitsweise des beschriebenen Ausführungsbeispiels der Erfindung ist nun folgendermaßen. Das dickste Nasenteil d der Schaufel 2 liegt dem dicksten Halsteil t der Schaufel 1 gegenüber, und diese beiden Teile bilden zusammen eine konvergente — divergenteίο The operation of the described embodiment of the invention is now as follows. The thickest nose part d of the blade 2 lies opposite the thickest neck part t of the blade 1, and these two parts together form a convergent - divergent one
Düse für transsonische Strömungsbedingungen in der zwischen gestrichelten Linien angedeuteten Zone I. Neben der Zone I befindet sich die Zone II für eine Oberschallströmung und Zone ΙΠ für eine Überschallströmung mit nahezu konstanter Geschwindig-Nozzle for transonic flow conditions in the Zone I indicated between dashed lines. Next to Zone I is Zone II for a Upper sonic flow and zone ΙΠ for a supersonic flow with almost constant speed
keit. Der Krümmungsradius der konkaven Saugseite 12 der Schaufel 2 und der Krümmungsradius der konkaven Druckseite 10 der Schaufel 1, Ana beide berechnet, und zwar vorzugsweise nach dem bekannten Kennlinienverfahren, um optimale Strömungsbedingungen zu erreichen.speed. The radius of curvature of the concave suction side 12 of the blade 2 and the radius of curvature of the concave pressure side 10 of the blade 1, Ana are both calculated, preferably according to the known characteristic curve method, in order to achieve optimal flow conditions.
Claims (1)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US79383169A | 1969-01-24 | 1969-01-24 |
Publications (3)
Publication Number | Publication Date |
---|---|
DE2002348A1 DE2002348A1 (en) | 1970-07-30 |
DE2002348B2 true DE2002348B2 (en) | 1979-06-13 |
DE2002348C3 DE2002348C3 (en) | 1984-09-06 |
Family
ID=25160924
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE2002348A Expired DE2002348C3 (en) | 1969-01-24 | 1970-01-20 | Blade ring for an axial flow turbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US3565548A (en) |
JP (1) | JPS5612681B1 (en) |
CH (1) | CH515412A (en) |
DE (1) | DE2002348C3 (en) |
FR (1) | FR2029035A1 (en) |
GB (1) | GB1270156A (en) |
SE (1) | SE358438B (en) |
Families Citing this family (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3697193A (en) * | 1970-12-10 | 1972-10-10 | Adrian Phillips | Fluidfoil section |
DE2524250A1 (en) * | 1975-05-31 | 1976-12-02 | Maschf Augsburg Nuernberg Ag | LARGE CIRCLING SPEED FOR THERMAL, AXIAL-FLOW TURBO MACHINES |
US4240952A (en) * | 1979-01-15 | 1980-12-23 | Clarence E. Hulbert, Jr. | Method of making concrete from fly ash |
US4333088A (en) * | 1980-11-03 | 1982-06-01 | Exxon Research & Engineering Co. | Disposable peristaltic pump assembly for facsimile printer |
US4616975A (en) * | 1984-07-30 | 1986-10-14 | General Electric Company | Diaphragm for a steam turbine |
US4643645A (en) * | 1984-07-30 | 1987-02-17 | General Electric Company | Stage for a steam turbine |
US4900230A (en) * | 1989-04-27 | 1990-02-13 | Westinghouse Electric Corp. | Low pressure end blade for a low pressure steam turbine |
US5197854A (en) * | 1991-09-05 | 1993-03-30 | Industrial Design Laboratories, Inc. | Axial flow fan |
US5588804A (en) * | 1994-11-18 | 1996-12-31 | Itt Automotive Electrical Systems, Inc. | High-lift airfoil with bulbous leading edge |
FR2728618B1 (en) * | 1994-12-27 | 1997-03-14 | Europ Propulsion | SUPERSONIC DISTRIBUTOR OF TURBOMACHINE INPUT STAGE |
DE19614420C2 (en) * | 1996-04-12 | 2003-05-22 | Aloys Wobben | Rotor blade and wind turbine with a rotor blade |
US6068454A (en) * | 1998-04-06 | 2000-05-30 | Ford Motor Company | Fuel pump with helical impeller |
US6358012B1 (en) * | 2000-05-01 | 2002-03-19 | United Technologies Corporation | High efficiency turbomachinery blade |
US7179058B2 (en) * | 2004-03-21 | 2007-02-20 | Bharat Heavy Electricals Limited | Aerodynamically wide range applicable cylindrical blade profiles |
US7175393B2 (en) * | 2004-03-31 | 2007-02-13 | Bharat Heavy Electricals Limited | Transonic blade profiles |
US8393872B2 (en) * | 2009-10-23 | 2013-03-12 | General Electric Company | Turbine airfoil |
GB201003084D0 (en) | 2010-02-24 | 2010-04-14 | Rolls Royce Plc | An aerofoil |
JP6030853B2 (en) * | 2011-06-29 | 2016-11-24 | 三菱日立パワーシステムズ株式会社 | Turbine blade and axial turbine |
JP6110544B2 (en) * | 2011-06-29 | 2017-04-05 | 三菱日立パワーシステムズ株式会社 | Supersonic turbine blade and axial turbine |
US9340277B2 (en) * | 2012-02-29 | 2016-05-17 | General Electric Company | Airfoils for use in rotary machines |
DE102014200644B4 (en) * | 2014-01-16 | 2017-03-02 | MTU Aero Engines AG | Extruded profile and method for producing a blade of a Nachleitrads, blade of a Nachleitrads, Nachleitrad and turbomachinery with such a Nachleitrad |
JP6081398B2 (en) * | 2014-03-12 | 2017-02-15 | 株式会社東芝 | Turbine blade cascade, turbine stage and steam turbine |
US10358926B2 (en) | 2017-08-11 | 2019-07-23 | General Electric Company | Low-noise airfoil for an open rotor |
GB201719538D0 (en) | 2017-11-24 | 2018-01-10 | Rolls Royce Plc | Gas turbine engine |
GB201719539D0 (en) | 2017-11-24 | 2018-01-10 | Rolls Royce Plc | Gas Turbine Engine |
EP4332346A3 (en) * | 2022-08-09 | 2024-06-19 | RTX Corporation | Fan blade or vane with improved bird impact capability |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE446861A (en) * | 1941-08-29 | |||
US2935246A (en) * | 1949-06-02 | 1960-05-03 | Onera (Off Nat Aerospatiale) | Shock wave compressors, especially for use in connection with continuous flow engines for aircraft |
FR1473721A (en) * | 1965-04-01 | 1967-03-17 | Brown | Movable fins for transonic flow |
CH427851A (en) * | 1965-04-01 | 1967-01-15 | Bbc Brown Boveri & Cie | Blade ring for transonic flow |
US3333817A (en) * | 1965-04-01 | 1967-08-01 | Bbc Brown Boveri & Cie | Blading structure for axial flow turbo-machines |
-
1969
- 1969-01-24 US US793831*A patent/US3565548A/en not_active Expired - Lifetime
- 1969-12-11 GB GB60427/69A patent/GB1270156A/en not_active Expired
- 1969-12-29 SE SE18019/69A patent/SE358438B/xx unknown
-
1970
- 1970-01-20 DE DE2002348A patent/DE2002348C3/en not_active Expired
- 1970-01-21 FR FR7002119A patent/FR2029035A1/fr active Pending
- 1970-01-23 CH CH97270A patent/CH515412A/en not_active IP Right Cessation
- 1970-01-23 JP JP575270A patent/JPS5612681B1/ja active Pending
Also Published As
Publication number | Publication date |
---|---|
GB1270156A (en) | 1972-04-12 |
CH515412A (en) | 1971-11-15 |
JPS5612681B1 (en) | 1981-03-24 |
FR2029035A1 (en) | 1970-10-16 |
SE358438B (en) | 1973-07-30 |
DE2002348C3 (en) | 1984-09-06 |
DE2002348A1 (en) | 1970-07-30 |
US3565548A (en) | 1971-02-23 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
8281 | Inventor (new situation) |
Free format text: FOWLER, JACKSON ESTES, SCHENECTADY, N.Y., US HERZOG, JOSEF, SCOTIA, N.Y., US |
|
C3 | Grant after two publication steps (3rd publication) |