Modeling the flow and combustion in an aircraft gas turbine combustor

Result code in IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F00%3A00000025" target="_blank" >RIV/00216305:26210/00:00000025 - 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

Modeling the flow and combustion in an aircraft gas turbine combustor

Original language description

The presented paper describes a numerical investigation of the performance of a can type combustor of the aircraft gas turbine with a commercial code STAR-CD. The flow is considered as incompressible computed by Navier-Stokes equations closed by k-epsiloModeling of swirler by momentum source coding is introduced and it is shown as a good approximation of a swirler. Modeling of gas fuel combustion is compared with experiment where kerosene fuel is used. Presumed pdf model with an equilibrium scheme and Eddy Break-Up (EDBR) models of combustion are compared. It is shown that the mean values of temperature and velocity at the outlet are very close to experimental results Patterns of velocity and temperature fields on the outlet are, however different.

Czech name

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Czech description

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Type

J_x - Unclassified - Peer-reviewed scientific article (Jimp, Jsc and Jost)

CEP classification

JT - Propulsion, engines and fuels

OECD FORD branch

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Project

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Continuities

Z - Vyzkumny zamer (s odkazem do CEZ)

Publication year

2000

Confidentiality

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

Name of the periodical

Inženýrská mechanika

ISSN

1210-2717

e-ISSN

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Volume of the periodical

7

Issue of the periodical within the volume

3

Country of publishing house

US - UNITED STATES

Number of pages

12

Pages from-to

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UT code for WoS article

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EID of the result in the Scopus database

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