Computational investigation of rotorcraft avionics bay cooling system

Download

index.pdf

Date

2019

Author

Akın, Altuğ

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

92
views

36
downloads

Computational investigation of a rotorcraft avionics bay cooling system is performed. Within the introduced system, the ambient air is supplied to the avionics-bay by a fan and exhausted back into the ambient after cooling the equipment inside. Depending on the fan and exhaust locations, hot zones may form around some of the equipment. The fan must provide a sufficiently high mass flow rate to keep the temperatures of the avionics equipment below the limits, while avoiding excessive amount of cooling to reduce power consumption. In this study, the effects of the fan and exhaust locations on the required mass flow rate are investigated. Prediction functions with Gaussian Process Regression and Artificial Neural Network methods are built to predict avionics surface temperatures using the results from a series of Computational Fluid Dynamics (CFD) analyses. The first method is selected over the latter as it yields more accurate results. The selected prediction function is used in conjunction with an optimization algorithm to determine the optimum fan and exhaust locations that minimize the required mass flow rate. It is found out that the required mass flow rate significantly depends on the fan location, while, the exhaust location has a relatively lessened effect. The required mass flow rate could be reduced to around half of its value with an even more significant reduction in power consumption. Additionally, the CFD analysis for the optimum fan and exhaust locations are repeated with different turbulence models to evaluate the effect of the selected model on the results.

Subject Keywords

Rotors, Keywords: Avionics Cooling, Design of Experiment, Computational Fluid Dynamics, Optimization, Gaussian Process Regression, Artificial Neural Networks, Turbulence Model.

URI

http://etd.lib.metu.edu.tr/upload/12624314/index.pdf
https://hdl.handle.net/11511/44150

Collections

Graduate School of Natural and Applied Sciences, Thesis

Suggestions

OpenMETU
Core

An optimization study for rotorcraft avionics bay cooling Akin, Altug; Kahveci, Harika Senem (2019-07-01) In this paper, a computational investigation of a rotorcraft avionics-bay cooling system is carried out. The introduced avionics cooling system utilizes a forced-convection method in which the ambient air is supplied to the avionics bay by a fan and then exhausted back into the ambient after cooling the equipment inside. The aim of this system is to keep the air temperature in the vicinity of the avionics equipment below the operational temperature limits. Depending on the locations of the fan and exhaust, ...
Numerical simulation of wave-induced scour and backfilling processes beneath submarine pipelines Fuhrman, David R; Baykal, Cüneyt; Sumer, B Mutlu; Jacobsen, Niels G; Fredsoe, Jorgen (2014-12-01) A fully-coupled hydrodynamic/morphodynamic numerical model is presented and utilized for the simulation of wave-induced scour and backfilling processes beneath submarine pipelines. The model is based on solutions to Reynolds-averaged Navier-Stokes equations, coupled with k - omega turbulence closure, with additional bed and suspended load descriptions forming the basis for sea bed morphology. The morphological evolution is updated continuously, rather than being based e.g. on period- or other time-averaging...
Improved combustion model of boron particles for ducted rocket combustion chambers Kalpakli, Bora; Acar, Emir Bedig; Ulaş, Abdullah (Elsevier BV, 2017-5) A combustion model of boron particles for detailed Computational Fluid Dynamics (CFD) based simulations of ducted rocket combustion chambers is studied. It is aimed to construct a model for combustion of boron containing gas mixtures ejected from a solid propellant gas generator. This model includes all main physical processes required to define an accurate particle combustion simulation. The reaction rate modeling in similar, previous studies are improved for ramjet combustion chambers and this model provi...
Numerical analysis of regenerative cooling in liquid propellant rocket engines Ulaş, Abdullah (2013-01-01) High combustion temperatures and long operation durations require the use of cooling techniques in liquid propellant rocket engines (LPRE). For high-pressure and high-thrust rocket engines, regenerative cooling is the most preferred cooling method. Traditionally, approximately square cross sectional cooling channels have been used. However, recent studies have shown that by increasing the coolant channel height-to-width aspect ratio and changing the cross sectional area in non-critical regions for heat flux...
3 D time accurate CFD simulations of wind turbine rotor flow fields Tonkal, Ozan Çağrı; Pehlivan, Sercan; Sezer Uzol, Nilay; İşler, Veysi (American Institute of Aeronautics and Astronautics Inc.(AIAA); 2006-01-12) This paper presents the results of three-dimensional and time-accurate Computational Fluid Dynamics (CFD) simulations of the flow field around the National Renewable Energy Laboratory (NREL) Phase VI horizontal axis wind turbine rotor. The 3-D, unsteady, parallel, finite volume flow solver, PUMA2, is used for the simulations. The solutions are obtained using unstructured moving grids rotating with the turbine blades. Three different flow cases with different wind speeds and wind yaw angles are investigated:...

Citation Formats

A. Akın, “Computational investigation of rotorcraft avionics bay cooling system,” Thesis (M.S.) -- Graduate School of Natural and Applied Sciences. Aerospace Engineering., Middle East Technical University, 2019.