Heat Transfer in Aerospace Applications

258 Pages·2016·10.95 MB·English

by  Bengt Sundén and Juan Fu (Auth.)

HEAT TRANSFER IN
AEROSPACE
APPLICATIONS
BENGT SUNDÉN
JUAN FU
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PREFACE
The requirements of thermal management in aerospace applications
are continuously growing, whereas the allotments on weight and volume
remainconstantorshrink.Tomeetthehighheatfluxremovalrequirements,
compact, high-performance, and lightweight heat transfer equipment are
needed. Heat exchangers based on microchannels are very suitable, as they
offeropportunitiesforhighheatfluxremovalbecauseoftheir goodthermal
performance and extremely compact size. However, aerospace challenges
include reduced gravity or microgravity, low or no atmospheric pressure,
extremetemperatures,aerodynamicheating,dynamicvibration,shockloads,
and extended duration of operations. Also alternative power sources are
needed for aerospace vehicles, e.g., fuel cells. As hydrogen is the common
fuel,effortshavebeenspentonitsproduction,transportation,storage,system
design, and safe and effective handling. Heat transfer issues are also
demandingchallengesforaerospacepropulsion.Itisimportanttoprotectthe
propulsion surfaces from the hostile thermal environment. One way to
achieve this is to develop materials capable of withstanding the hostile
environment and offering an adiabatic surface that will not melt or lose its
structural integrity. Another approach is to immediately cool the exposed
surfaces. Heat transfer issues in hypersonic flights include very high aero-
dynamic loads, laminareturbulent transition, shock/shock and shock/
boundary layer interactions, film cooling and skin friction reduction,
advancedcompositematerials,combinedthermal/structuralanalysis,real-gas
effects, and wall catalysis, as well as thermal management of the integrated
engineeairframeenvironment.Heatpipesarepotentialcandidatesforpassive
cooling of structures exposed to very high heat flux levels. It is obvious that
heat transfer engineering and thermal sciences are important for the design
and development in aerospace applications.
Theideatowritethisbookwascreatedaftertheseniorauthorpresented
a short lecture series on aerospace heat transfer issues at the National
University of Defense Technology, Changsha, Hunan, China in 2013.
During the preparation stages, it was found that the textbook treated the
topics of heat transfer in aerospace applications sufficiently well.
ix
x Preface
Some coworkers were quite helpful in the writing of this book and
preparation of figures, as well as searching published literature. They are
Dr. Zan Wu, Dr. Chenglong Wang, Dr. Luan Huibao, and Dr. Daniel
Eriksson.Ms.CarrieBolgerandMs.MohanaNatarajanatElsevierwerealso
quite helpful in bringing this book to completion.
Lund and Beijing, July 2016
Bengt Sundén and Juan Fu
NOMENCLATURE
A Area (m2)
A Reaction activation energy
a Velocity of sound (m/s)
Bo Bond number
b Thickness (m)
C Specific heat matrix
C Convective flux (kg/s)
f
c Specific heat constant pressure [J/(kg K)]
p
c Specific heat constant volume [J/(kg K)]
v
c Specific heat [J/(kg K)]
c Drag coefficient
D
D Diameter (m)
D Diffusive flux (kg/s)
f
d Distance (m)
d Deviatoric stress tensor (N/m2)
ij
_
E,E Energy rate (W)
E Young’s modulus (Pa)
e Internal energy (J/kg)
e Rate of strain tensor (1/s)
ij
F Fill level
!
F, F Body force (N/m3)
i
F View factor
12
f Accommodation coefficient
s
f Velocity function
Gr Grashof number
G Solar radiation (W/m2)
s
g Gravity acceleration (m/s2)
H Enthalpy [J/(kgK)]
h Heat transfer coefficient [W/(m2K)]
h Enthalpy (J/kg)
K Permeability
Ka Kapitza number
K Conductivity matrix
c
Kn Knudsen number
k Thermal conductivity [W/(mK)]
k Boltzmann constant
L Length (m)
L Latent heat (J/kg)
H
l Characteristic length (m)
Ma Mach number, U/a
m_ Phase change mass flow rate (kg/s)
xi
xii Nomenclature
N Mesh number
Nu Nusselt number
n Integer
n Number of molecules per unit volume
n Normal vector
Pr Prandtl number
p, P Pressure (Pa)
p Width (m)
_
Q,Q Heat transfer rate (W)
Q Heat flow vector
Q Latent heat (J/kg)
L
q Heat flux (W/m2)
R Gas constant [J/(kg K)]
Ra Rayleigh number
Re Reynolds number
r Recovery factor
r Radial coordinate (m)
r Adjustable coefficient
r , r Principal radii of curvature (m)
1 2
S Molecular velocity ratio
S Source term energy equation (W/m3)
h
St Stanton number
s Pitch (m)
T Temperature ((cid:2)C, K)
T Adiabatic wall temperature ((cid:2)C, K)
aw
T* Reference temperature ((cid:2)C, K)
t Temperature ((cid:2)C)
t , t , t Thicknesses (m)
B w T
U Velocity (m/s)
u Velocity (m/s)
V Average or absolute velocity (m/s)
V Vapor volume (m3)
g
V Tank volume (m3)
t
!
Velocity vector (m/s)
V
v Molecular mean velocity (m/s)
u, v, w Local velocity (m/s)
n , n , n Molecular velocity component (m/s)
1 2 3
_
W,W Work rate (W)
We Weber number
X Thickness (m)
x, y, z Coordinates (m)
Nomenclature xiii
Greek
a Heat transfer coefficient (W/(m2K)]
a Thermal diffusivity (m2/s)
a Thermal expansion coefficient (1/K)
a Volume fraction
a Absorptance
s
a Accommodation coefficient
s
b Inclination angle
b Thermal expansion coefficient
D Rate of expansion (1/s)
Dp Pressure drop (Pa)
d Boundary layer thickness (m)
d Depth (m)
d Kronecker’s delta
ij
ε Emissivity
ε Porosity
f Arbitrary variable
z Dimensionless parameter
g c /c
p v
k Curvature (1/m)
h Dimensionless coordinate
q Dimensionless temperature
q Polar angle, angle
q Temperature difference
w Dimensionless temperature
l Mean free path (m)
l Dimensionless parameter
m Dynamic viscosity [kg/(ms)]
m Poisson’s ratio
n Kinematic viscosity (m2/s)
n Dimensionless parameter
r Density (kg/m3)
s Surface tension (N/m)
s StefaneBoltzmann constant [W/(m2K4)]
s Accommodation coefficient
s
s Time (s)
j Stream function (m2/s)
j Angle
U Dimensionless parameter
u Length
xiv Nomenclature
Indices
a Adiabatic
aw Adiabatic wall
b Bulk
c Continuum
eff Effective
fm Free molecule
l Liquid
lv Liquidevapor
tj Temperature jump
v Vapor
vol Volume
w Wall
N Free stream
Abbreviations
ACC Advanced carbon-carbon
BEM Boundary element method
CAD Computer-aided design
CFD Computational fluid dynamics
CMC Ceramic matrix composites
CMG Compression mass gauge
CVFEM Control volume finite element method
CO Carbon dioxide
2
DNS Direct numerical simulation
DSMC Direct simulation Monte Carlo
ECS Environmental control system
FEM Finite element method
FVM Finite volume method
H Hydrogen
2
H O Hydrogen peroxide
2 2
Ir Iridium
LH Liquid hydrogen
2
LOX Liquid oxygen
MMC Metallic matrix composites
mHEX Micro heat exchanger
NaBH Sodium borohydride
4
NB Neighbor
O Oxygen
2
PCHE Printed circuit heat exchanger
PFHE Plate-fin heat exchanger
Nomenclature xv
PISO Pressure implicit splitting operators
QUICK Quadratic upstream interpolation for convective kinetics
RANS Reynolds-averaged NaviereStokes
RSM Reynolds stress method
SiC Silicon carbide
SIMPLE Semi-implicit method for pressure-linked equations
SIMPLEX SIMPLE extended
SIMPLER SIMPLE revised
SiO Silicon oxide
SST Shear stress transport
TDMA Tridiagonal matrix algorithm
TPS Thermal protection system
VOF Volume of fluid
Zr Zirconium
CHAPTER 1
Introduction
1.1 HEAT TRANSFER IN GENERAL
Heat is a form of energy that is always transferred from the hot part to the
cold part in a substance or from a body at a high temperature to another
bodyatalowertemperature.Thebodiesdonotneedtobeincontactbuta
difference in temperature must exist.
In some cases the amount of heat transferred can be determined simply
by applying basic relations or the laws of thermodynamics and fluid me-
chanics. In other cases in which the mechanisms of heat transport are not
completely known, methods of analogy or empirical methods based on
experiments are applied.
Heat can be transferred by three different means, namely, heat con-
duction, convection, and thermal radiation, as illustrated in Fig. 1.1. Many
textbooks are available on general heat transfer, see, e.g., Refs. [1e3].
Heat conduction is a process in which energy transfer from a high
temperature region to a low-temperature region is governed by the mo-
lecularmotion,asinsolidbodiesandfluids(gasesandliquids)atrest,andby
the movement of electrons, as for metals.
Figure 1.1 Heat transfer by (a) heat conduction, (b) convection, and (c) thermal
radiation.
HeatTransferinAerospaceApplications
ISBN978-0-12-809760-1 ©2017ElsevierLtd.
http://dx.doi.org/10.1016/B978-0-12-809760-1.00001-6 Allrightsreserved. 1