Návrh odstředivého kompresoru s tandemovým lopatkováním rotoru

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21260%2F05%3A06146286" target="_blank" >RIV/68407700:21260/05:06146286 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/68407700:21260/05:06148413

Výsledek na webu

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DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

TANDEM BLADE CENTRIFUGAL COMPRESSOR IMPELLER DESIGN

Popis výsledku v původním jazyce

In the article an innovative design of the centrifugal compressor rotor tandem cascade is described. The new design approach is based on the analysis of the flow characteristics in the rotating working channels within the turbo-machines as one of the results of the arising from previous systematical research of the flow phenomena in the curved channels of turbo-machines carried out at the of Aerospace Research Center. The new design of the impeller flow passage geometry has been made in the form of re-engineering of the existing newly designed centrifugal compressor stage in the Walter Engines a. s. The rotor tandem blade concept lies in the separation of the impeller blades into two parts. First part is formed by the axial-diagonal flow inducer section of the rotor. This flow part is designed as a highly aerodynamic loaded axial flow compressor cascade. The second part of the impeller cascade is designed with double number of blades as in the first part of the impeller.

Název v anglickém jazyce

TANDEM BLADE CENTRIFUGAL COMPRESSOR IMPELLER DESIGN

Popis výsledku anglicky

In the article an innovative design of the centrifugal compressor rotor tandem cascade is described. The new design approach is based on the analysis of the flow characteristics in the rotating working channels within the turbo-machines as one of the results of the arising from previous systematical research of the flow phenomena in the curved channels of turbo-machines carried out at the of Aerospace Research Center. The new design of the impeller flow passage geometry has been made in the form of re-engineering of the existing newly designed centrifugal compressor stage in the Walter Engines a. s. The rotor tandem blade concept lies in the separation of the impeller blades into two parts. First part is formed by the axial-diagonal flow inducer section of the rotor. This flow part is designed as a highly aerodynamic loaded axial flow compressor cascade. The second part of the impeller cascade is designed with double number of blades as in the first part of the impeller.

Druh

J_x - Nezařazeno - Článek v odborném periodiku (Jimp, Jsc a Jost)

CEP obor

JU - Aeronautika, aerodynamika, letadla

OECD FORD obor

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Projekt

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Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2005

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

Letecký zpravodaj

ISSN

1211-877X

e-ISSN

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Svazek periodika

2005

Číslo periodika v rámci svazku

-

Stát vydavatele periodika

CZ - Česká republika

Počet stran výsledku

1

Strana od-do

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Kód UT WoS článku

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EID výsledku v databázi Scopus

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