% Clear variables
clear all;
% Set gas temperature and wall heat transfer coefficients at
% boundaries of the blade. Note: Tcool(i) and hcool(i) are the
% values of Tcool and hcool for the ith boundary which are numbered
% as follows:
%
% 1 = 1st internal cooling passage (from leading edge)
% 2 = 2nd internal cooling passage
% 3 = 3rd internal cooling passage (including trailing edge slot)
Tcool = [600, 600, 600]; % ( K )
hcool = [1500, 1500, 1500]; % ( W/(K m^2) )
% Set blade material properties
kblade = 30; % ( W/( K m) )
% Set blade chord
chord = 0.04; % (m)
% Load in the grid file
fname = input('Enter gridfile name: ','s');
load(fname);
fprintf('Number of nodes = %i\n',Nv);
fprintf('Number of elements = %i\n',Nt);
% NOTE: after loading a gridfile using the load(fname) command,
% three important grid variables and data arrays exist. These are:
%
% Nt: Number of triangles (i.e. elements) in mesh
%
% Nv: Number of nodes (i.e. vertices) in mesh
%
% Nbc: Number of edges which lie on a boundary of the computational
% domain.
%
% tri2nod(3,Nt): list of the 3 node numbers which form the current
% triangle. Thus, tri2nod(1,i) is the 1st node of
% the i'th triangle, tri2nod(2,i) is the 2nd node
% of the i'th triangle, etc.
%
% xy(2,Nv): list of the x and y locations of each node. Thus,
% xy(1,i) is the x-location of the i'th node, xy(2,i)
% is the y-location of the i'th node, etc.
%
% bedge(3,Nbc): For each boundary edge, bedge(1,i) and bedge(2,i)
% are the node numbers for the nodes at the end
% points of the i'th boundary edge. bedge(3,i) is an
% integer which identifies which boundary the edge is
% on. In this solver, the third value has the
% following meaning:
%
% bedge(3,i) = 0: edge is on the airfoil surface
% bedge(3,i) = 1: edge is on the first cooling passage
% bedge(3,i) = 2: edge is on the second cooling passage
% bedge(3,i) = 3: edge is on the third cooling passage
%
% Re-scale xy location because they currently have unit chord.
xy = chord*xy;
% Zero stiffness matrix and b vector
K = sparse(Nv, Nv);
b = zeros(Nv, 1);
% Loop over elements and calculate residual and stiffness matrix
for ii = 1:Nt,
kn(1) = tri2nod(1,ii);
kn(2) = tri2nod(2,ii);
kn(3) = tri2nod(3,ii);
xe(1) = xy(1,kn(1));
xe(2) = xy(1,kn(2));
xe(3) = xy(1,kn(3));
ye(1) = xy(2,kn(1));
ye(2) = xy(2,kn(2));
ye(3) = xy(2,kn(3));
% Calculate all of the necessary shape function derivatives, the
% Jacobian of the element, etc.
% Derivatives of node 1's interpolant
dNdxi(1,1) = -1.0; % with respect to xi1
dNdxi(1,2) = -1.0; % with respect to xi2
% Derivatives of node 2's interpolant
dNdxi(2,1) = 1.0; % with respect to xi1
dNdxi(2,2) = 0.0; % with respect to xi2
% Derivatives of node 3's interpolant
dNdxi(3,1) = 0.0; % with respect to xi1
dNdxi(3,2) = 1.0; % with respect to xi2
% Sum these to find dxdxi (note: these are constant within an element)
dxdxi = zeros(2,2);
for nn = 1:3,
dxdxi(1,:) = dxdxi(1,:) + xe(nn)*dNdxi(nn,:);
dxdxi(2,:) = dxdxi(2,:) + ye(nn)*dNdxi(nn,:);
end
% Calculate determinant for area weighting
J = abs(dxdxi(1,1)*dxdxi(2,2) - dxdxi(1,2)*dxdxi(2,1));
% Invert dxdxi to find dxidx using inversion rule for a 2x2 matrix
dxidx = [ dxdxi(2,2)/J, -dxdxi(1,2)/J; ...
-dxdxi(2,1)/J, dxdxi(1,1)/J];
% Calculate dNdx
dNdx = dNdxi*dxidx;
% Add contributions to stiffness matrix for node 1 weighted residual
K(kn(1), kn(1)) = K(kn(1), kn(1)) - 0.5*kblade*(dNdx(1,1)*dNdx(1,1) + dNdx(1,2)*dNdx(1,2))*J;
K(kn(1), kn(2)) = K(kn(1), kn(2)) - 0.5*kblade*(dNdx(1,1)*dNdx(2,1) + dNdx(1,2)*dNdx(2,2))*J;
K(kn(1), kn(3)) = K(kn(1), kn(3)) - 0.5*kblade*(dNdx(1,1)*dNdx(3,1) + dNdx(1,2)*dNdx(3,2))*J;
% Add contributions to stiffness matrix for node 2 weighted residual
K(kn(2), kn(1)) = K(kn(2), kn(1)) - 0.5*kblade*(dNdx(2,1)*dNdx(1,1) + dNdx(2,2)*dNdx(1,2))*J;
K(kn(2), kn(2)) = K(kn(2), kn(2)) - 0.5*kblade*(dNdx(2,1)*dNdx(2,1) + dNdx(2,2)*dNdx(2,2))*J;
K(kn(2), kn(3)) = K(kn(2), kn(3)) - 0.5*kblade*(dNdx(2,1)*dNdx(3,1) + dNdx(2,2)*dNdx(3,2))*J;
% Add contributions to stiffness matrix for node 3 weighted residual
K(kn(3), kn(1)) = K(kn(3), kn(1)) - 0.5*kblade*(dNdx(3,1)*dNdx(1,1) + dNdx(3,2)*dNdx(1,2))*J;
K(kn(3), kn(2)) = K(kn(3), kn(2)) - 0.5*kblade*(dNdx(3,1)*dNdx(2,1) + dNdx(3,2)*dNdx(2,2))*J;
K(kn(3), kn(3)) = K(kn(3), kn(3)) - 0.5*kblade*(dNdx(3,1)*dNdx(3,1) + dNdx(3,2)*dNdx(3,2))*J;
end
% Loop over boundary edges and account for bc's
% Note: the bc's are all convective heat transfer coefficient bc's
% so they are of 'Robin' form. This requires modification of the
% stiffness matrix as well as b.
for ii = 1:Nbc,
% Get node numbers on edge
kn(1) = bedge(1,ii);
kn(2) = bedge(2,ii);
% Get node coordinates
xe(1) = xy(1,kn(1));
xe(2) = xy(1,kn(2));
ye(1) = xy(2,kn(1));
ye(2) = xy(2,kn(2));
% Calculate edge length
ds = sqrt((xe(1)-xe(2))^2 + (ye(1)-ye(2))^2);
% Determine the boundary number
bnum = bedge(3,ii);
if (bnum == 0), % Blade surface
[Text, hext] = Thgas( 0.5*(xe(1)+xe(2)), 0.5*(ye(1)+ye(2)), chord );
else, % cooling passage
Text = Tcool(bnum);
hext = hcool(bnum);
end
% Based on boundary number, set heat transfer bc
K(kn(1), kn(1)) = K(kn(1), kn(1)) - hext*ds*(1/3);
K(kn(1), kn(2)) = K(kn(1), kn(2)) - hext*ds*(1/6);
b(kn(1)) = b(kn(1)) + hext*ds*0.5*Text;
K(kn(2), kn(1)) = K(kn(2), kn(1)) - hext*ds*(1/6);
K(kn(2), kn(2)) = K(kn(2), kn(2)) - hext*ds*(1/3);
b(kn(2)) = b(kn(2)) + hext*ds*0.5*Text;
end
% Solve for temperature
T = -K\b;
% Plot solution
bladeplot;
% Report outputs
Tmax = max(T);
Tmin = min(T);
fprintf('Tmin = %7.2f, Tmax = %7.2f\n',Tmin,Tmax);