DE1956886A1 - Bucket for flow machines - Google Patents
Bucket for flow machinesInfo
- Publication number
- DE1956886A1 DE1956886A1 DE19691956886 DE1956886A DE1956886A1 DE 1956886 A1 DE1956886 A1 DE 1956886A1 DE 19691956886 DE19691956886 DE 19691956886 DE 1956886 A DE1956886 A DE 1956886A DE 1956886 A1 DE1956886 A1 DE 1956886A1
- Authority
- DE
- Germany
- Prior art keywords
- blade
- tip
- shovel according
- convex surface
- rest
- 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.)
- Pending
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
- F01D5/16—Form or construction for counteracting blade vibration
-
- 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
- F01D5/20—Specially-shaped blade tips to seal space between tips and stator
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)
- Turbine Rotor Nozzle Sealing (AREA)
Description
FATFNTANWKLTcFATFNTANWKLTc
blPL.-ING. GÜNTHER KOCH 1956886blPL.-ING. GÜNTHER KOCH 1956886
8 München 2, 12. November 19698 Munich 2, 12 . November 1969
Rolls-Royce Limited, Derby, Derbyshire, England. Schaufel für StrömungsmaschinenRolls-Royce Limited, Derby, Derbyshire, England. Blade for flow machines
Die Erfindung bezieht sich auf eine stromlinienförmig gestaltete Schaufel für Strömungsmaschinen insbesondere für Gasturbinentriebwerke, wo sie in Gestalt einer Rotor- oder Statorschaufel im Kompressor oder der Turbine Anwendung finden kann.The invention relates to a streamlined blade for turbo machines, in particular for gas turbine engines, where it can be used in the form of a rotor or stator blade in the compressor or turbine.
Der Erfindung liegt die Aufgabe zugrunde, eine Schaufel zu schaffen, bei der die Frequenzen der verschiedenen Vibrationsarten an der Schaufelspitze über dem Triebwerkslaufbereich liegen. Wenn zur Lösung dieser Aufgabe die Schaufelspitze verdickt würde, dann könnten Gewicht und aerodynamische Blockierung übermäßig groß werden oder die Vibrationsfrequenzen der Hauptbiege- und Torsionsarten könnten so niedrig werden, daß sie in den Triebwerkslaufbereich hineingeraten je nach dem Grad der Verjüngung längs der Schaufel.The invention is based on the object of creating a shovel, at which the frequencies of the various types of vibration at the blade tip are above the engine running area. if to solve this problem the blade tip would then be thickened weight and aerodynamic blockage could become excessive or the vibration frequencies of the main bending and torsion types could get so low that they get into the engine running area depending on the degree of taper along the Shovel.
Gemäß der Erfindung wird diese Aufgabe ohne Verdickung des Profils dadurch gelöst, daß die Ebene des in Spannrichtung verlaufenden Abschnitts der Schaufelspitze gegenüber der in Spannrichtung verlaufenden Ebene der restlichen Schaufel geneigt ist. . .'■_ / According to the invention, this object is achieved without thickening the profile in that the plane of the section of the blade tip extending in the tensioning direction is inclined with respect to the plane of the rest of the blade extending in the tensioning direction. . . '■ _ /
•A• A
009821/1529009821/1529
■ ■■ β—. . ·■ ■■ β—. . ·
Der Spitzenabschnitt kann so geneigt werden, daß vorzugsweise die konvexe Oberfläche der Spitze nach der konvexen Oberfläche der übrigen Schaufel hin geneigt ist. Der Winkel zwischen Spitze und restlicher Schaufel liegt zweckmäßigerweise zwischen 0 und 30°.The tip portion can be inclined so that preferably the convex surface of the tip after the convex surface the rest of the blade is inclined. The angle between the tip and the rest of the blade is expediently between 0 and 30 °.
Die Schaufel kann die Gestalt einer Rotorschaufel oder einer Statorschaufel beim Kompressor oder der Turbine eines Gasturbinentriebwerks sein. Stattdessen kann die Schaufel auch als Gebläseschaufel oder als Propeller ausgebildet sein. The blade can be in the form of a rotor blade or a stator blade be at the compressor or the turbine of a gas turbine engine. Instead, the blade can also be designed as a fan blade or as a propeller.
Nachstehend wird ein Ausführungsbeispiel der Erfindung anhand der Zeichnung beschrieben. In der Zeichnung zeigen:An exemplary embodiment of the invention is described below with reference to the drawing. In the drawing show:
Fig. 1 eine schematische teilweise aufgebrochene Ansicht eines Gas turbi nenstrahltriebwerks,Fig. 1 is a schematic, partially broken away view of a Gas turbine jet engine,
Fig. 2 einen in Spannrichtung verlaufenden Teilschnitt einer Schaufel nach der Erfindung zur Benutzung in einem Gasturbinentriebwerk nach Fig.l. 2 shows a partial section of a running in the tensioning direction Blade according to the invention for use in a gas turbine engine according to Fig.l.
Das Gasturbinentriebwerk 10 gemäß Fig.l besitzt einen Kompressor 12, eine Verbrennungs einrichtung 14 und eine Turbine 16. Der Kompressor 12 besitzt eine Anzahl von Rotorschaufeln 18 bzw. Statorschaufeln 20.The gas turbine engine 10 according to Fig.l has a compressor 12, a combustion device 14 and a turbine 16. The compressor 12 has a number of rotor blades 18 or stator blades 20.
Fig.2 zeigt einen Schnitt einer Rotorschaufel 18 und diese besitzt einen Schaufelfuß 22 mit Plattform 24 und einen nicht-dargestellten Veranteefcungsansatz sowie eine Schaufelspitze 26. Ein Abschnitt 28 der Spitze ist in einem Winkel zwischen 0° und 30° gegenüber der Spannrichtung der Schaufel so geneigt, daß die konvexe Oberfläche der Spitze nach der konvexen Oberfläche der übrigen Schaufel hin geneigt ist.2 shows a section of a rotor blade 18 and this has a blade root 22 with platform 24 and one not shown Veranteefcungsansatz as well as a blade tip 26. A section 28 the tip is at an angle between 0 ° and 30 ° with respect to the Clamping direction of the blade inclined so that the convex surface the tip is inclined towards the convex surface of the remainder of the blade.
0 0 982 1 /Ί5 290 0 982 1 / Ί5 29
Die Frequenz der "tramline"-Vibration ist proportional dem
Radius von Gyration/Sehne für einen gegebenen Stromlinienquerschnitt und die Biegung der Spitze erhöht den Radius
der Gyration und erhöht dadurch die Frequenz, bei der diese
Vibrationen auftreten.The frequency of the "tramline" vibration is proportional to the radius of gyration / tendon for a given streamline cross section, and the curvature of the tip increases the radius
gyration, thereby increasing the frequency at which these vibrations occur.
Die Erfindung ist in gleicher Weise anwendbar für Statorschaufeln und für Schaufeln von Gebläsen und für Propeller.The invention can be used in the same way for stator blades and for blades of fans and for propellers.
009821 /1529009821/1529
Claims (4)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5428768 | 1968-11-15 | ||
FR6939779A FR2030647A5 (en) | 1968-11-15 | 1969-11-19 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE1956886A1 true DE1956886A1 (en) | 1970-05-21 |
Family
ID=26215380
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE19691956886 Pending DE1956886A1 (en) | 1968-11-15 | 1969-11-12 | Bucket for flow machines |
Country Status (3)
Country | Link |
---|---|
DE (1) | DE1956886A1 (en) |
FR (1) | FR2030647A5 (en) |
GB (1) | GB1231424A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1996014494A2 (en) * | 1994-11-04 | 1996-05-17 | United Technologies Corporation | Rotor airfoils to control tip leakage flows |
EP1953344A1 (en) | 2007-02-05 | 2008-08-06 | Siemens Aktiengesellschaft | Turbine blade |
WO2012025359A1 (en) | 2010-08-23 | 2012-03-01 | Rolls-Royce Plc | Method of damping aerofoil structure vibrations and corresponding aerofoil structure |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS52115409A (en) * | 1976-03-24 | 1977-09-28 | Dowa Co | Axiallflow fan wheels |
GB2139294A (en) * | 1983-02-18 | 1984-11-07 | Pioneer Dharma Ventures Limite | Omni-directional rotor |
FR2556409B1 (en) * | 1983-12-12 | 1991-07-12 | Gen Electric | IMPROVED BLADE FOR A GAS TURBINE ENGINE AND MANUFACTURING METHOD |
US6290465B1 (en) * | 1999-07-30 | 2001-09-18 | General Electric Company | Rotor blade |
US9845683B2 (en) | 2013-01-08 | 2017-12-19 | United Technology Corporation | Gas turbine engine rotor blade |
US10947851B2 (en) * | 2018-12-19 | 2021-03-16 | Raytheon Technologies Corporation | Local pressure side blade tip lean |
-
1968
- 1968-11-15 GB GB5428768A patent/GB1231424A/en not_active Expired
-
1969
- 1969-11-12 DE DE19691956886 patent/DE1956886A1/en active Pending
- 1969-11-19 FR FR6939779A patent/FR2030647A5/fr not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1996014494A2 (en) * | 1994-11-04 | 1996-05-17 | United Technologies Corporation | Rotor airfoils to control tip leakage flows |
WO1996014494A3 (en) * | 1994-11-04 | 1997-02-13 | United Technologies Corp | Rotor airfoils to control tip leakage flows |
EP1953344A1 (en) | 2007-02-05 | 2008-08-06 | Siemens Aktiengesellschaft | Turbine blade |
WO2012025359A1 (en) | 2010-08-23 | 2012-03-01 | Rolls-Royce Plc | Method of damping aerofoil structure vibrations and corresponding aerofoil structure |
Also Published As
Publication number | Publication date |
---|---|
FR2030647A5 (en) | 1970-11-13 |
GB1231424A (en) | 1971-05-12 |
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