DE2250563A1 - Turbine rotor - using solder material and a volatile material ie polyvinyl alcohol to line hub slits - Google Patents
Turbine rotor - using solder material and a volatile material ie polyvinyl alcohol to line hub slitsInfo
- Publication number
- DE2250563A1 DE2250563A1 DE2250563A DE2250563A DE2250563A1 DE 2250563 A1 DE2250563 A1 DE 2250563A1 DE 2250563 A DE2250563 A DE 2250563A DE 2250563 A DE2250563 A DE 2250563A DE 2250563 A1 DE2250563 A1 DE 2250563A1
- Authority
- DE
- Germany
- Prior art keywords
- hub
- polyvinyl alcohol
- turbine rotor
- volatile material
- slots
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3084—Fixing blades to rotors; Blade roots ; Blade spacers the blades being made of ceramics
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Ceramic Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Turbinen - Rotor. Turbines - rotor.
Die Erfindung betrifft die Herstellung zusammengesetzter Turbinen-Rotoren mit getrennten Flügeln aus keramischem Material, die um eine metallische Wabe befestigt sind. The invention relates to the manufacture of composite turbine rotors with separate wings made of ceramic material, which are attached to a metallic honeycomb are.
Normalerweise werden derartige getrennte Flügel befestigt, indem auf einfache Weise an den Flügelwurzeln, z.B. einem achsialen Zylinder, muldenförmige Ausbildungen in entsprechenden Schlitzen an der Nabe angeordnet werden. Typically, such separate wings are attached by in a simple way at the wing roots, e.g. an axial cylinder, trough-shaped Formations are arranged in corresponding slots on the hub.
Die Flügel können kreisförmig-befestigt werden, und zwar durch passende benachbarte Flächen an Jedem Flügel, und achsial durch Verschlußringe, die in Ausnehmungen in der Nabe eingepaßt sind. Diese Befestigungsweise besitzt den Nachteil, daß bei Auftreten selbst geringfügiger Ungenauigkeiten in den Abmessungen, und zwar sowohl in der Flügelwurzel wie auch in den Schlitzen der Nabe lokale Spannungskonzentrationen an bestimmten Stellen her-vorgerufen werden, dien den Keramikflügeln nicht toleriert werden.The wings can be attached in a circle, using suitable ones Adjacent surfaces on each wing, and axially by locking rings that are in recesses are fitted in the hub. This method of attachment has the disadvantage that at Occurrence of even minor inaccuracies in the dimensions, both local in the wing root as well as in the slots of the hub Stress concentrations are produced at certain points that are not tolerated by the ceramic wings will.
Die Erfindung schlägt ein Verfahren zur Herstellung eines zusammengesetzten Turbinen-Rotors mit getrennten Flügeln aus keramischem Material vor, wobei die Flügel um eine Metallnabe derart befestigt sind, daß muldenförmige Ausbildungen an den Flügelwurzeln in korrespondierende Schlitze in der Nabe angeordnet sind, das dadurch gekennzeichnet ist, daß die Schlitze in der Nabe absichtlich übergroß gemacht sind, und daß die so entstehende Lücke zwischen Jeder Flügelwurzel und ihrem Schlitz mit einem Material ausgefüllt wird, das weicher ist als das Material der Nabe.The invention proposes a method for producing a composite Turbine rotor with separate blades made of ceramic material in front, the blades are attached to a metal hub so that trough-shaped formations on the Wing roots are arranged in corresponding slots in the hub, which thereby it is indicated that the slots in the hub are intentionally made oversized, and that the resulting gap between each wing root and its slit with a material is filled that is softer than the material of the hub.
Weitere wichtige Merkmale der Erfindung werden in dem nachfolgenden Ausführungsbeispiel näher erläutert. Es zeigt: Fig. 1 eine schematische Darstellung der Anwendung der Erfindung auf die Herstellung eins zusammengesetzten Turbinen-Rotors mit Flügeln aus Keramik; Fig. 2 schematisch eine vergrößerte teilweise Endansicht des Flügel-Rotors.Other important features of the invention are set out below Embodiment explained in more detail. It shows: FIG. 1 a schematic representation the application of the invention to the manufacture of a composite turbine rotor with wings made of ceramic; Fig. 2 schematically shows an enlarged partial end view of the wing rotor.
Ein zusammengesetzter Turbinen-Rotor 1 besitzt getrennte Flügel 2 aus Keramik, die um eine Netallnabe 3 durch muldenförmige, hinterschnittene Ausbildungen 4 an der Wurzel 5 jedes Flügels befestigt sind, und zwar durch Einpassen in entsprechende Schlitze 6 in der Nabe 3. Die Schlitze 6 sind gemäß der Erfindung absichtlich übergroß ausgebildet, und die entstehende Lücke zwischen jeder Flügelwurzel 5 und ihrem Schlitz 6 ist mit einem Material gefüllt, das weicher ist, als das Material der Nabe 3.A composite turbine rotor 1 has separate blades 2 Made of ceramic, around a metal hub 3 by trough-shaped, undercut formations 4 are attached to the root 5 of each wing by fitting into corresponding ones Slots 6 in the hub 3. The slots 6 are intentionally oversized according to the invention formed, and the resulting gap between each wing root 5 and its slot 6 is filled with a material that is softer than the material of the hub 3.
Die Flügel 2 aus Keramik sind in den Schlitzen 6 durch Aufspannvorrichtungen befestigt, die sie in der genauen Relativposition halten. Lötmaterial 7 in Form eines gewundenen Bandes wird in die Lücken zwischen den Wurzeln 5 und den Nabenschlitzen 6 gefüllt. Die Anordnung wird in inerter Atmosphäre auf Löt- bzw-t Hartlöttemperatur erwärmt. Nach dem Abkühlen--werden die Flügel 2 durch die zusammengezogene Nabe 3 und das Füllmaterial- in der richti--; gen Position gehalten. Da das Material 7 weicher ist als das Material der Nabe 3, werden die Stellen mit hoher Spannungskonzentration an der Berührungsfläche der Flügelwurzeln 5 und dem Material 7 verringert.The wings 2 made of ceramic are in the slots 6 by jigs attached, which hold them in the exact relative position. Solder material 7 in the form a twisted ribbon is inserted into the gaps between the roots 5 and the hub slots 6 filled. The arrangement is made in an inert atmosphere on soldering or -t brazing temperature heated. After cooling - the wings 2 are through the contracted hub 3 and the filling material- in the correct-; held in position. Since the material 7 is softer than the material of the hub 3, the places with high stress concentration at the contact surface of the wing roots 5 and the Material 7 decreased.
Es ist möglich, weitere lokale Spannungskonzentrationen an der Flügelwurzel 5 zu verringern, in dem der Elastizitätsmodul des Füllmaterials 7 verändert wird. Beispielsweise besitzt ein herkömmliches Lötmaterial einen E-Modul von 20 x 10 6 psi (= 1,4 x 10-6 Kp/mm2) bei der Lauftemperatur der Turbine. Dieser Modul kann jedoch beträchtlich gesenkt werden, und zwar durch Hinzufügen eines flüchtigen Materials, um das spezifische Gewicht des Füllmaterials zu verringern. Ein derartiges flüchtiges Material kann z.B. Ammoniumchlorid, Ammoniumjodid, Polyvinylalkohol und Methylzellulose sein.It is possible to have more local stress concentrations at the wing root 5, in which the modulus of elasticity of the filler material 7 is changed. For example, a conventional soldering material has a modulus of elasticity of 20 × 10 6 psi (= 1.4 x 10-6 Kp / mm2) at the running temperature of the turbine. This module can but can be reduced considerably by adding a volatile material, to reduce the specific weight of the filler material. Such a fleeting one Material can be, for example, ammonium chloride, ammonium iodide, polyvinyl alcohol, and methyl cellulose be.
- Ansprüche- Expectations
Claims (4)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB5100371 | 1971-11-03 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE2250563A1 true DE2250563A1 (en) | 1973-05-10 |
Family
ID=10458259
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE2250563A Pending DE2250563A1 (en) | 1971-11-03 | 1972-10-14 | Turbine rotor - using solder material and a volatile material ie polyvinyl alcohol to line hub slits |
Country Status (3)
Country | Link |
---|---|
JP (1) | JPS4853107A (en) |
DE (1) | DE2250563A1 (en) |
IT (1) | IT969483B (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2822627A1 (en) * | 1978-05-24 | 1979-11-29 | Volkswagenwerk Ag | CERANOX COMPOUND AND METHOD OF MANUFACTURING IT |
US4207029A (en) * | 1978-06-12 | 1980-06-10 | Avco Corporation | Turbine rotor assembly of ceramic blades to metallic disc |
EP0072909A2 (en) * | 1981-08-21 | 1983-03-02 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Method for manufacturing a metal intermediate layer |
US4417854A (en) * | 1980-03-21 | 1983-11-29 | Rockwell International Corporation | Compliant interface for ceramic turbine blades |
US4743166A (en) * | 1984-12-20 | 1988-05-10 | General Electric Company | Blade root seal |
EP1840337A1 (en) * | 2006-03-31 | 2007-10-03 | Siemens Aktiengesellschaft | Tongue and groove connection between two components of a turbine |
EP2832957A1 (en) * | 2013-07-31 | 2015-02-04 | ALSTOM Technology Ltd | Rotor with groove having a compliant layer |
-
1972
- 1972-10-14 DE DE2250563A patent/DE2250563A1/en active Pending
- 1972-10-16 IT IT7253411A patent/IT969483B/en active
- 1972-11-02 JP JP47109570A patent/JPS4853107A/ja active Pending
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2822627A1 (en) * | 1978-05-24 | 1979-11-29 | Volkswagenwerk Ag | CERANOX COMPOUND AND METHOD OF MANUFACTURING IT |
US4335998A (en) * | 1978-05-24 | 1982-06-22 | Volkswagenwerk Aktiengesellschaft | Ceramic-metal assembly |
US4207029A (en) * | 1978-06-12 | 1980-06-10 | Avco Corporation | Turbine rotor assembly of ceramic blades to metallic disc |
US4417854A (en) * | 1980-03-21 | 1983-11-29 | Rockwell International Corporation | Compliant interface for ceramic turbine blades |
EP0072909A2 (en) * | 1981-08-21 | 1983-03-02 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Method for manufacturing a metal intermediate layer |
EP0072909A3 (en) * | 1981-08-21 | 1983-06-15 | Mtu Muenchen Gmbh | Metal intermediate layer and manufacturing method therefor |
US4743166A (en) * | 1984-12-20 | 1988-05-10 | General Electric Company | Blade root seal |
EP1840337A1 (en) * | 2006-03-31 | 2007-10-03 | Siemens Aktiengesellschaft | Tongue and groove connection between two components of a turbine |
EP2832957A1 (en) * | 2013-07-31 | 2015-02-04 | ALSTOM Technology Ltd | Rotor with groove having a compliant layer |
Also Published As
Publication number | Publication date |
---|---|
IT969483B (en) | 1974-03-30 |
JPS4853107A (en) | 1973-07-26 |
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