A Computational Model of a Centrifugal Compressor Stage for Aircraft Engines

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F14%3A00221397" target="_blank" >RIV/68407700:21220/14:00221397 - isvavai.cz</a>

Result on the web

<a href="http://stc.fs.cvut.cz/proceedings.html" target="_blank" >http://stc.fs.cvut.cz/proceedings.html</a>

DOI - Digital Object Identifier

—

Result language

angličtina

Original language name

A Computational Model of a Centrifugal Compressor Stage for Aircraft Engines

Original language description

This paper presents the ongoing first steps of development of an innovative centrifugal compressor stage designed for use in turboprop aircraft engines. The so-called tandem impeller blading concept shall be compared to the conventional blading design bymeans of numerical simulation and optimized to achieve the best possible parameters. In this paper, validation of a conventional stage computational model using experimental data is described.

Czech name

—

Czech description

—

Type

D - Article in proceedings

CEP classification

JU - Aeronautics, aerodynamics, aeroplanes

OECD FORD branch

—

Project

—

Continuities

S - Specificky vyzkum na vysokych skolach

Publication year

2014

Confidentiality

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

Article name in the collection

Studentská tvůrčí činnost 2014

ISBN

978-80-01-05484-0

ISSN

—

e-ISSN

—

Number of pages

15

Pages from-to

—

Publisher name

České vysoké učení technické v Praze, Fakulta strojní

Place of publication

Praha

Event location

Praha

Event date

Apr 8, 2014

Type of event by nationality

EUR - Evropská akce

UT code for WoS article

—