AT74422B - Flexible storage of rotating machine parts that are supported against one another. z. B. turbine wheels, on the shaft to compensate for various thermal expansion. - Google Patents

Flexible storage of rotating machine parts that are supported against one another. z. B. turbine wheels, on the shaft to compensate for various thermal expansion.

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Publication number
AT74422B
AT74422B AT74422DA AT74422B AT 74422 B AT74422 B AT 74422B AT 74422D A AT74422D A AT 74422DA AT 74422 B AT74422 B AT 74422B
Authority
AT
Austria
Prior art keywords
another
shaft
machine parts
compensate
rotating machine
Prior art date
Application number
Other languages
German (de)
Original Assignee
Ver Dampfturbinen Ges Mit Besc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Ver Dampfturbinen Ges Mit Besc filed Critical Ver Dampfturbinen Ges Mit Besc
Application granted granted Critical
Publication of AT74422B publication Critical patent/AT74422B/en

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Description

  

   <Desc/Clms Page number 1> 
 
 EMI1.1 
 



   Die Erfindung betrifft eine nachgiebige Lagerung von gegeneinander abgestützten umlaufenden Maschinenteilen,   z. B. Dampfturbinenradern,   welche   Wärmeeinnüssen   in stärkerem Masse unterworfen sind als ihn zugehörige Welle. Sie besteht darin, dass diese gemeinsam hintereinander eingespannten Maschinenteile einzeln oder gruppenweise derart gegeneinander nachgiebig sind, dass sich bei   Erwärmung   jeder Teil bzw. jede Gruppe für sich ausdehnen kann, ohne die   ursprüngliche Lage wesentlich   zu ändern. 



   Die Zeichnung zeigt mehrere Ausführungsbeispiele des Erfindungsgegenstandes an einer Dampfturbine, und zwar zeigt Fig. 1 die Laufradanordnung einer Dampfturbine im Schnitt, 
 EMI1.2 
 
Hiebei bezeichnet a eine Turbinenwelle, auf welcher zwischen dem Wellenbund b und der Mutter c die Laufräder angeordnet sind, von denen die mit d, e, f, g bezeichneten Laufräder verschiedene Ausführungsformen zeigen. Die Laufräder d besitzen die allgemein übliche Form. 



  Um nun eine Ausdehnung ihrer starren Radnaben bei Wärmeeinwirkung zu ermöglichen, sind zwischen ihnen   federnde Scheiben A1 vorgesehen.   Die übrigen Laufräder liegen unmittelbar mit ihren Naben aneinander und sind an ihren   Berührungsstellen   selbst federnd ausgebildet. Dies wird bei   deu   Laufrädern e dadurch erreicht, dass deren Naben in einzelne Sektoren unterteilt sind, von denen die mit t bezeichneten federnd und die mit k bezeichneten starr ausgebildet sind. Die federnden Sektoren i ragen etwas über die starren Sektoren k hervor, so dass wie bei der ersten, oben beschriebenen Ausführungsform eine   Ausdehnungsmöglichkeit   des starren Nabenteils   gewährleistet   ist. Bei den   mit bezeichneten Laufrädern   sind die Naben voll ausgebildet. 



  Hier wird eine Ausdehnung des Nabenkörpers bei dessen Erwärmung dadurch ermöglicht, dass derselbe auf einer Seite mit nachgiebigen   Vorsprüngen     l   versehen ist. welche sich gegen die Naben der anliegenden Räder anlegen. 



   PATENT-ANSPRÜCHE :
1. Nachgiebige Lagerung von gegeneinander abgestützten, umlaufenden Maschinenteilen z. B. Turbinenlaufrädern, auf der Welle, zum Ausgleich verschiedener Wärmeausdehnung, dadurch gekennzeichnet, dass die gemeinsam hintereinander eingespannten Maschinenteile (d, e, f, g) einzeln oder gruppenweise derart gegeneinander nachgiebig sind, dass sich bei Erwärmung jeder Teil bzw. jede Gruppe für sich ausdehnen kann, ohne die ursprüngliche Lage wesentlich zu   ändern.   

**WARNUNG** Ende DESC Feld kannt Anfang CLMS uberlappen**.



   <Desc / Clms Page number 1>
 
 EMI1.1
 



   The invention relates to a resilient mounting of rotating machine parts supported against one another, e.g. B. Steam turbine wheels, which are subjected to heat inuences to a greater extent than its associated shaft. It consists in the fact that these machine parts clamped together one behind the other are individually or in groups flexible to one another in such a way that when heated, each part or group can expand independently without changing the original position significantly.



   The drawing shows several exemplary embodiments of the subject matter of the invention on a steam turbine, specifically FIG. 1 shows the impeller arrangement of a steam turbine in section,
 EMI1.2
 
Here, a designates a turbine shaft on which the impellers are arranged between the shaft collar b and the nut c, of which the impellers labeled d, e, f, g show different embodiments. The impellers d have the generally customary shape.



  In order to allow their rigid wheel hubs to expand when exposed to heat, resilient washers A1 are provided between them. The other running wheels are directly adjacent to one another with their hubs and are themselves designed to be resilient at their contact points. This is achieved with deu running wheels e in that their hubs are subdivided into individual sectors, of which those labeled t are resilient and those labeled k are rigid. The resilient sectors i protrude somewhat beyond the rigid sectors k, so that, as in the first embodiment described above, the rigid hub part can be expanded. The hubs of the impellers marked with are fully formed.



  Here, the hub body can expand when it is heated in that it is provided with flexible projections 1 on one side. which lie against the hubs of the adjacent wheels.



   PATENT CLAIMS:
1. Flexible storage of mutually supported rotating machine parts z. B. turbine wheels, on the shaft, to compensate for different thermal expansion, characterized in that the machine parts (d, e, f, g) clamped together one behind the other are individually or in groups so flexible that when heated, each part or group for can expand without significantly changing the original position.

** WARNING ** End of DESC field may overlap beginning of CLMS **.

 

Claims (1)

2. Einrichtung nach Anspruch 1, dadurch gekennzeichnet, dass die einzelnen Maschmen teile (e, f, g) unmittelbar aneinanderliegen und an ihren Berührungsstellen federnd ausgebildet sind. **WARNUNG** Ende CLMS Feld Kannt Anfang DESC uberlappen**. 2. Device according to claim 1, characterized in that the individual Maschmen parts (e, f, g) lie directly against one another and are resilient at their points of contact. ** WARNING ** End of CLMS field may overlap beginning of DESC **.
AT74422D 1913-05-31 1914-05-28 Flexible storage of rotating machine parts that are supported against one another. z. B. turbine wheels, on the shaft to compensate for various thermal expansion. AT74422B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE74422X 1913-05-31

Publications (1)

Publication Number Publication Date
AT74422B true AT74422B (en) 1918-07-10

Family

ID=5636781

Family Applications (1)

Application Number Title Priority Date Filing Date
AT74422D AT74422B (en) 1913-05-31 1914-05-28 Flexible storage of rotating machine parts that are supported against one another. z. B. turbine wheels, on the shaft to compensate for various thermal expansion.

Country Status (1)

Country Link
AT (1) AT74422B (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2427614A (en) * 1943-02-09 1947-09-16 Tech Studien Ag Rotor for multistage turbomachines
US2458149A (en) * 1944-08-23 1949-01-04 United Aircraft Corp Rotor construction for turbines
US2458148A (en) * 1944-08-23 1949-01-04 United Aircraft Corp Rotor construction for turbines
US2497151A (en) * 1946-03-04 1950-02-14 Armstrong Siddeley Motors Ltd Multidisk rotor
US2516066A (en) * 1942-04-27 1950-07-18 Power Jets Res & Dev Ltd Rotor assembly
US2553442A (en) * 1946-12-09 1951-05-15 Armstrong Siddeley Motors Ltd Arrangement of labyrinth packing for a rotary type of fluid-pressure apparatus
US2618463A (en) * 1947-02-20 1952-11-18 Rolls Royce Multistage axial compressor and turbine
US4039268A (en) * 1975-02-20 1977-08-02 A/S Kongsberg Vapenfabrik Arrangement for endwise clamping a first gas turbine rotor member to another member of a gas turbine rotor
US4097194A (en) * 1976-03-22 1978-06-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Redundant disc
US4102601A (en) * 1975-07-17 1978-07-25 Robert Bosch Gmbh Forced draft fan blade construction for dynamo electric machines and forced draft automotive alternator

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2516066A (en) * 1942-04-27 1950-07-18 Power Jets Res & Dev Ltd Rotor assembly
US2427614A (en) * 1943-02-09 1947-09-16 Tech Studien Ag Rotor for multistage turbomachines
US2458149A (en) * 1944-08-23 1949-01-04 United Aircraft Corp Rotor construction for turbines
US2458148A (en) * 1944-08-23 1949-01-04 United Aircraft Corp Rotor construction for turbines
US2497151A (en) * 1946-03-04 1950-02-14 Armstrong Siddeley Motors Ltd Multidisk rotor
US2553442A (en) * 1946-12-09 1951-05-15 Armstrong Siddeley Motors Ltd Arrangement of labyrinth packing for a rotary type of fluid-pressure apparatus
US2618463A (en) * 1947-02-20 1952-11-18 Rolls Royce Multistage axial compressor and turbine
US4039268A (en) * 1975-02-20 1977-08-02 A/S Kongsberg Vapenfabrik Arrangement for endwise clamping a first gas turbine rotor member to another member of a gas turbine rotor
US4102601A (en) * 1975-07-17 1978-07-25 Robert Bosch Gmbh Forced draft fan blade construction for dynamo electric machines and forced draft automotive alternator
US4097194A (en) * 1976-03-22 1978-06-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Redundant disc

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