CFD MODEL OF THE TURBOPROP ENGINE HOT PART - BAY COOLING

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F68407700%3A21220%2F19%3A00340839" target="_blank" >RIV/68407700:21220/19:00340839 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1115/IMECE2018-87066" target="_blank" >https://doi.org/10.1115/IMECE2018-87066</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1115/IMECE2018-87066" target="_blank" >10.1115/IMECE2018-87066</a>

Jazyk výsledku

angličtina

Název v původním jazyce

CFD MODEL OF THE TURBOPROP ENGINE HOT PART - BAY COOLING

Popis výsledku v původním jazyce

The bay cooling of a specific new turboprop engine is investigated in this paper. The new ATP turboprop engine has additional jets with hot air stream close to the PT. This considerably increases the temperature inside the first nacelle compartment in the hot engine part around the engine combustion chamber. In order to achieve the optimal temperature conditions for engine parts inside the nacelle in the critical operating regime (triple red line), a new bay cooling system is proposed. Using the existing standard (National Advisory Committee for Aeronautics) NACA inlet at the front of the nacelle, two additional groups of ribs on rear part of front nacelle compartment and standard nacelle gaps (around exhausts), the temperature in the front part of the nacelle is decreased bellow the critical temperature for installed devices and engine parts (gear box etc.) in this compartments. Using a 3D CFD model of the first compartment of the nacelle is analyzed using the software ANSYS. The boundary conditions for this CFD simulation are obtained from ground testing of the turboprop engine.

Název v anglickém jazyce

CFD MODEL OF THE TURBOPROP ENGINE HOT PART - BAY COOLING

Popis výsledku anglicky

The bay cooling of a specific new turboprop engine is investigated in this paper. The new ATP turboprop engine has additional jets with hot air stream close to the PT. This considerably increases the temperature inside the first nacelle compartment in the hot engine part around the engine combustion chamber. In order to achieve the optimal temperature conditions for engine parts inside the nacelle in the critical operating regime (triple red line), a new bay cooling system is proposed. Using the existing standard (National Advisory Committee for Aeronautics) NACA inlet at the front of the nacelle, two additional groups of ribs on rear part of front nacelle compartment and standard nacelle gaps (around exhausts), the temperature in the front part of the nacelle is decreased bellow the critical temperature for installed devices and engine parts (gear box etc.) in this compartments. Using a 3D CFD model of the first compartment of the nacelle is analyzed using the software ANSYS. The boundary conditions for this CFD simulation are obtained from ground testing of the turboprop engine.

Druh

D - Stať ve sborníku

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

<a href="/cs/project/EF16_019%2F0000826" target="_blank" >EF16_019/0000826: Centrum pokročilých leteckých technologií</a><br>

Návaznosti

P - Projekt vyzkumu a vyvoje financovany z verejnych zdroju (s odkazem do CEP)

Rok uplatnění

2019

Kód důvěrnosti údajů

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

Název statě ve sborníku

PROCEEDINGS OF THE ASME INTERNATIONAL MECHANICAL ENGINEERING CONGRESS AND EXPOSITION

ISBN

978-0-7918-5211-8

ISSN

—

e-ISSN

—

Počet stran výsledku

6

Strana od-do

—

Název nakladatele

American Society of Mechanical Engineers - ASME

Místo vydání

New York

Místo konání akce

Pittsburgh, PA

Datum konání akce

9. 11. 2018

Typ akce podle státní příslušnosti

WRD - Celosvětová akce

Kód UT WoS článku

000465191300005