AT212969B - Multi-stage axial compressor - Google Patents

Multi-stage axial compressor

Info

Publication number
AT212969B
AT212969B AT574158A AT574158A AT212969B AT 212969 B AT212969 B AT 212969B AT 574158 A AT574158 A AT 574158A AT 574158 A AT574158 A AT 574158A AT 212969 B AT212969 B AT 212969B
Authority
AT
Austria
Prior art keywords
compressor
radius
stage axial
axial compressor
flow
Prior art date
Application number
AT574158A
Other languages
German (de)
Inventor
Werner Held
Original Assignee
Entwicklungsbau Pirna Veb
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 Entwicklungsbau Pirna Veb filed Critical Entwicklungsbau Pirna Veb
Application granted granted Critical
Publication of AT212969B publication Critical patent/AT212969B/en

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Description

  

   <Desc/Clms Page number 1> 
 



  Mehrstufiger Axialverdichter 
 EMI1.1 
 
 EMI1.2 
 Berichtigung der Patentschrift Nr. 212969
Ausgegeben am 12. Juni   1961.   
 EMI1.3 
 
 EMI1.4 
 

 <Desc/Clms Page number 2> 

 
 EMI2.1 
 Drallverteilung um gewisse Beträge von der mittleren Kanalströmung abweichen. Der Verlauf des mittle-   ren Durchmessers des Strömungskanals   kann ohne Krümmungssprung stetig ab-oder zunehmen bzw. erst abund dann wieder zunehmen, je nachdem, ob grössere   Schaufelhöhen (besserer   Wirkungsgrad) oder grössere Förderhöhen erwünscht sind. Der im Meridianschnitt gekrümmte   Strömungskanal   kann auch stetig auf einen unendlich grossen Krümmungsradius übergehen, falls der gewünschte Effekt nur in bestimmten Stufen erreicht werden soll. 



   In der Zeichnung ist ein Ausführungsbeispiel der Erfindung schematisch dargestellt. 



   Die Schaufeln 1 des Verdichters sind in einem im Meridianschnitt stetig gekrümmten Strömungskanal 2 angeordnet. Der mittlere Durchmesser des Strömungskanals 2 nimmt anfangs stetig ab und steigt ohne Krümmungssprung danach wieder stetig an. Hiedurch ist ein günstiger Kompromiss zwischen genügend grossen Schaufelhöhen und entsprechend grosser Förderhöhe erreicht. Der Krümmungsradius Rm des Strö-   mungskanals   liegt innerhalb des durch die Beziehung 
 EMI2.2 
 gegebenen Bereichs. 



   Die Filehkräfte F1 der Meridianströmung sind zur Verdichterachse gerichtet, so dass die durch den gekrümmten Strömungskanal 2 erzeugten Fliehkräfte F   1 der MeridianstrÏmung den,   von   der Dral1strÏmung   erzeugten Fliehkräften F entgegenwirken und die Schaufeln 1 voll ausgelastet sind. 



   Die Erfindung eignet sich besonders für PTL-Triebwerke und Verdichter stationärer Gasturbinenanlagen : sie ist aber grundsätzlich bei jedem Verdichter anwendbar.



   <Desc / Clms Page number 1>
 



  Multi-stage axial compressor
 EMI1.1
 
 EMI1.2
 Correction of patent specification No. 212969
Issued June 12, 1961.
 EMI1.3
 
 EMI1.4
 

 <Desc / Clms Page number 2>

 
 EMI2.1
 The swirl distribution deviates from the mean channel flow by certain amounts. The course of the mean diameter of the flow channel can steadily decrease or increase without a jump in curvature or only decrease and then increase again, depending on whether larger blade heights (better efficiency) or larger delivery heights are desired. The flow channel, which is curved in the meridional section, can also transition continuously to an infinitely large radius of curvature if the desired effect is to be achieved only in certain stages.



   An exemplary embodiment of the invention is shown schematically in the drawing.



   The blades 1 of the compressor are arranged in a flow channel 2 which is continuously curved in the meridional section. The mean diameter of the flow channel 2 initially decreases steadily and then increases again continuously without a jump in curvature. This results in a favorable compromise between sufficiently large blade heights and a correspondingly large delivery head. The radius of curvature Rm of the flow channel lies within the relationship
 EMI2.2
 given area.



   The axial forces F1 of the meridional flow are directed towards the compressor axis, so that the centrifugal forces F 1 of the meridional flow generated by the curved flow channel 2 counteract the centrifugal forces F generated by the twisting flow and the blades 1 are fully utilized.



   The invention is particularly suitable for PTL engines and compressors in stationary gas turbine systems: however, it can in principle be used with any compressor.

Claims (1)

PATENTANSPRUCH : Mehrstufiger Axialverdichter, dadurch gekennzeichnet, dass die Schaufeln in oder unmittelbar nach einem im Meridianschnitt-derart gekrümmten Strömungskanal angeordnet sind, dass die Fliehkräfte der Meridianströmung zur Verdichterachse gerichtet sind, wobei der mittlere Krümmungsradius Rm innerhalb EMI2.3 EMI2.4 EMI2.5 EMI2.6 EMI2.7 r ein beliebiger Radius zwischen dem Innenradius ri und dem Aussenradius ra der Schaufeln, bezogen auf die Verdichterachse, ist. PATENT CLAIM: Multi-stage axial compressor, characterized in that the blades are arranged in or immediately after a flow channel curved in the meridional section in such a way that the centrifugal forces of the meridional flow are directed towards the compressor axis, the mean radius of curvature Rm within EMI2.3 EMI2.4 EMI2.5 EMI2.6 EMI2.7 r any radius between the inner radius ri and the outer radius ra der Blades, based on the compressor axis.
AT574158A 1958-06-19 1958-08-16 Multi-stage axial compressor AT212969B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE212969X 1958-06-19

Publications (1)

Publication Number Publication Date
AT212969B true AT212969B (en) 1961-01-10

Family

ID=5810852

Family Applications (1)

Application Number Title Priority Date Filing Date
AT574158A AT212969B (en) 1958-06-19 1958-08-16 Multi-stage axial compressor

Country Status (1)

Country Link
AT (1) AT212969B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3143334A (en) * 1962-08-06 1964-08-04 Gen Electric Flow path design

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3143334A (en) * 1962-08-06 1964-08-04 Gen Electric Flow path design

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