Innovative Design Optimization of Centrifugal Compressor Impeller for Small Turboprop Aero Engines

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F06%3A02132080" target="_blank" >RIV/68407700:21220/06:02132080 - isvavai.cz</a>
Result on the web
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DOI - Digital Object Identifier
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Result language
angličtina
Original language name
Innovative Design Optimization of Centrifugal Compressor Impeller for Small Turboprop Aero Engines
Original language description
In the paper a new innovative approach to the design of the centrifugal compressor impeller blades with the goal to improve the centrifugal compressor stage performance characteristics, namely its efficiency and the range of stable work is described. Thenew design of the impeller flow passage geometry consists of the separation of the impeller blades into two parts. First part is formed by the axial-diagonal flow inducer section of the rotor. The second part of the impeller blade row is designed with double number of blades as in the first part of the impeller. Calculated compressor stage performance characteristics using FLUENT solver show significant improvement of characteristics, particularly in the maximum attainable efficiency and stable workingrange in comparison with standard, but already advanced centrifugal compressor stage of the same size almost the same design working point.
Czech name
Inovativní návrh konstrukce rotoru odstředivého kompresoru pro malé turbovrtulové motory
Czech description
Je popsám návrh rotoru odstředivého kompresoru s inovativní konstrukcí zvyšující účinnost.

Project
<a href="/en/project/1M0501" target="_blank" >1M0501: Aerospace Research Centre</a><br>
Continuities
P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Publication year
2006
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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