Development of a Novel 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%3A00220451" target="_blank" >RIV/68407700:21220/14:00220451 - isvavai.cz</a>

Alternative codes found

RIV/68407700:21260/14:00220451

Result on the web

—

DOI - Digital Object Identifier

—

Result language

angličtina

Original language name

Development of a Novel 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<br>I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Publication year

2014

Confidentiality

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

Article name in the collection

New Trends in Civil Aviation 2014

ISBN

978-80-7204-891-5

ISSN

—

e-ISSN

—

Number of pages

7

Pages from-to

8-14

Publisher name

Akademické nakladatelství CERM

Place of publication

Brno

Event location

Vyšší Brod - Herbertov

Event date

May 18, 2014

Type of event by nationality

EUR - Evropská akce

UT code for WoS article

—