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Aerotecnica Missili & Spazio

, Volume 96, Issue 1, pp 56–62 | Cite as

Numerical investigation of the internal and external thermal fields for a nacelle in pusher configuration

  • A. Carozza
  • G. Mingione
  • G. Pezzella
  • G. Serino
Article
  • 1 Downloads

Abstract

The ESPOSA project “Efficient Systems and PrOpulsion for Small Aircraft” is funded by the European Commission within the 7th Framework Programm. It is coordinated by PBS from the Chezk Repubblic and it involves several partners among European industries, research centers and universities. The project has the objective to develop and integrate novel design and manufacture technologies for small gas turbine engines up to 1000 kW, thus providing aircraft manufacturers with better choice of modern propulsion units. Several aircrafts and engines have been selected as test beds for the study. One of this was the EM-1 ORKA aircraft that will be equipped with the 180 kW TP 100 turboprop engines from Czech company PBS Velká Bíteš. An aeronautical engine is a complex machine composed of different components operating at different temperatures that in conjunction with the nacelle creates a crowded region with the coupled heat transfer mechanisms to be covered by the nacelle cooling/ventilation system. Therefore, the engine/nacelle thermo-fluid dynamics analysis represents a critical design issue since conductive, convective and rediative heat transfer mechanisms must be addressed. In this framework, the present research effort reports on a high fidelity, fully coupled, aero-thermal design procedure that has been set-up and tested to evaluate the nacelle skin temperature and to check that it remains under the critical temperature for the material device.

Nomenclature

GTE

Gas Turbine Engine

ESPOSA

Efficient Systems and Propulsion for Small Aircraft

L

reference length [m]

a

absorbing coefficient

σS

scattering coefficient

velocity vector \(\left[ {\frac{m}{s}} \right]\)

ρ

density \(\left[ {\frac{{kg}}{{{m^3}}}} \right]\)

μ

dynamic viscosity [Pa · s]

α

thermal diffusivity \(\left[ {\frac{{{m^2}}}{s}} \right]\)

κ

thermal conductivity \(\left[ {\frac{W}{{mK}}} \right]\)

source term vector [Pa]

gravity acceleration vector \(\left[ {\frac{m}{{{s^2}}}} \right]\)

τ̿

stress tensor [Pa]

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Copyright information

© AIDAA Associazione Italiana di Aeronautica e Astronautica 2017

Authors and Affiliations

  • A. Carozza
    • 1
  • G. Mingione
    • 1
  • G. Pezzella
    • 2
  • G. Serino
    • 1
  1. 1.Dipartimento di Fluidodinamica, Laboratorio di Tecnologie Aerodinamiche e GhiaccioCIRA, “Centro Italiano Ricerche Aerospaziali”Italy
  2. 2.Laboratorio di Analisi ed Estrapolazione al VoloCIRA, “Centro Italiano Ricerche Aerospaziali”Italy

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