New Design Concept of Centrifugal Compressor Impellers of Turbojet Engines

Result code in IS VaVaI
<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21260%2F08%3A06148892" target="_blank" >RIV/68407700:21260/08:06148892 - isvavai.cz</a>
Alternative codes found
RIV/68407700:21220/08:02155376
Result on the web
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DOI - Digital Object Identifier
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Result language
angličtina
Original language name
New Design Concept of Centrifugal Compressor Impellers of Turbojet Engines
Original language description
In the paper a new innovative design of the centrifugal compressor impeller blades with the aim to improve the centrifugal compressor stage performance characteristics, namely its efficiency and the range of stable work is described. The new design concept consists in the division of the of the impeller blades into two parts. First part of the rotor blades is formed by highly aerodynamic loaded axial flow cascade. The second part is formed by axial/radial cascade with double blades then the first part.The new design has been applied to the advanced centrifugal compressor stage of Walter Aero Engine Company. Performance characteristics of both stages have been calculated using Fluent code at design speed of the rotor. Results obtained by numerical experiment and based on the relative comparison of the two designs show considerable improvement of performance characteristics of the new centrifugal compressor stage design.
Czech name
Koncept nového designu rotoru odstředivého kompresoru u proudových motorů
Czech description
Koncept nového designu rotoru odstředivého kompresoru u proudových motorů

Project
<a href="/en/project/GA101%2F06%2F1440" target="_blank" >GA101/06/1440: Improvement of the IGCC using brown coal for obtaining maximum thermic efficiency and minimum CO2 emissions</a><br>
Continuities
S - Specificky vyzkum na vysokych skolach

Publication year
2008
Confidentiality
S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

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