initial commit / add all books

8 files changed, 126 insertions, 0 deletions

diff --git a/2223/CH7/EX7.1/Ex7_1.sav b/2223/CH7/EX7.1/Ex7_1.sav
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diff --git a/2223/CH7/EX7.1/Ex7_1.sce b/2223/CH7/EX7.1/Ex7_1.sce
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+// scilab Code Exa 7.1 Calculation for the specific speed

+funcprot(0)

+//part(a)specific speed of gas turbine

+P=2e3; // Gas Turbine Power Output in kW

+N=16e3; // Speed in RPM

+T1=1e3;  // Entry Temperature in Kelvin

+p1=50; //  Entry Pressure in bar

+p2=25; //  Exit Pressure in bar

+cp=1.15e3; // Specific Heat at Constant Pressure in J/(kgK)

+gamma_g=1.3;

+omega=%pi*2*N/60;

+ro=p1*1e5/(((gamma_g-1)/gamma_g)*cp*T1);

+pr=p2/p1; //  pressure ratio

+T2s=T1*(pr^((gamma_g-1)/gamma_g));

+delh_s=cp*(T1-T2s);

+NS=omega*sqrt(P*10e2/ro)*delh_s^(-5/4)

+disp(NS,"(a)the specific speed of gas turbine is")

+

+// part(b)the specific speed of a centrifugal compressor

+pr_b=2; // Compressor pressure ratio

+N_b=24e3; // Speed in RPM

+m=1.5; //  in kg/s

+cp_a=1.005e3; // Specific Heat of air at Constant Pressure in kJ/(kgK)

+R=0.287;

+gamma=1.4;

+T1_b=300;  // Entry Temperature in Kelvin

+p1_b=1; //  Entry Pressure in bar

+ro_b=p1_b*1e2/(R*T1_b);

+omega_b=%pi*2*N_b/60;

+Q=m/ro_b;

+T2=T1_b*(pr_b^((gamma-1)/gamma));

+delh_s_b=cp_a*(T2-T1_b);

+NS_b=omega_b*sqrt(Q)*delh_s_b^(-3/4);

+disp(NS_b,"(b)the specific speed of a centrifugal compressor is")

+

+// part(c)the specific speed of an axial compressor

+pr_c=1.4; // Compressor pressure ratio

+N_c=6e3; // Speed in RPM

+m_c=15; //  in kg/s

+omega_c=%pi*2*N_c/60;

+Q_c=m_c/ro_b;

+T2_c=T1_b*(pr_c^((gamma-1)/gamma));

+delh_s_c=cp_a*(T2_c-T1_b);

+NS_c=omega_c*sqrt(Q_c)*delh_s_c^(-3/4)

+disp(NS_c,"(c)the specific speed of an axial compressor is")

diff --git a/2223/CH7/EX7.2/Ex7_2.sav b/2223/CH7/EX7.2/Ex7_2.sav
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index 000000000..42652ec8c
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+++ b/2223/CH7/EX7.2/Ex7_2.sav
diff --git a/2223/CH7/EX7.2/Ex7_2.sce b/2223/CH7/EX7.2/Ex7_2.sce
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+

+// scilab Code Exa 7.2 Calculating the discharge of a geometrically similar blower and specific speed of the fan

+pr=2; // Compressor pressure ratio

+N1=1.47e3; // fan Speed in RPM

+N2=0.36e3; // blower Speed in RPM

+Q1=2; // discharge in m3/s

+h=10e-3; // in m W.G.

+ro_w=10e2;

+ro_a=1.25; // density of air in kg/m3

+omega1=%pi*2*N1/60;

+g=9.81; // in m/s2

+p=ro_w*g*h

+H=p/(ro_a*g);

+delh_s=g*H;

+NS=omega1*sqrt(Q1)*delh_s^(-3/4)

+disp(NS,"the specific speed is")

+// for the same specific speed of two geometrically similar fans

+a=N1/N2;

+Q2=a^2*Q1;

+disp("m3/s",Q2," and the discharge of a geometrically similar blower is")

diff --git a/2223/CH7/EX7.3/Ex7_3.sav b/2223/CH7/EX7.3/Ex7_3.sav
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index 000000000..aa8ba8af8
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+++ b/2223/CH7/EX7.3/Ex7_3.sav
diff --git a/2223/CH7/EX7.3/Ex7_3.sce b/2223/CH7/EX7.3/Ex7_3.sce
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+// scilab Code Exa 7.3 Calculation on a small compressor

+pr=1.6; // Compressor pressure ratio

+N1=54e3; // Speed in RPM

+n_c=0.85; // efficiency

+m_a=1.5778; //  in kg/s

+cp_a=1.009; // Specific Heat of air at Constant Pressure in kJ/(kgK)

+gamma=1.4;

+// part (a) determining the power required to drive the compressor

+T01=300;  // Entry Temperature in Kelvin

+p01=1.008; //  Entry Pressure in bar

+n=(gamma-1)/gamma;

+T2s=T01*(pr^n);

+delh_s=cp_a*(T2s-T01)/n_c;

+P=m_a*delh_s;

+disp("kW",P,"(a)Power required to drive the compressor is")

+

+// part (b) determining the speed, mass flow rate, pressure ratio and power required of a geometrically similar compressor

+// geometrically similar compressor of 3 times the size of small compressor is constructed 

+N2=N1/3;

+disp("rpm",N2,"(b)(i)speed of a geometrically similar compressor is")

+m2=9*m_a;

+disp("kg/s",m2,"(b)(ii)mass flow rate of a geometrically similar compressor is")

+disp(pr,"(b)(iii)pressure ratio of a geometrically similar compressor is")

+P2=9*P;

+disp("kW",P2,"(b)(iv)Power required is")

+

diff --git a/2223/CH7/EX7.4/Ex7_4.sav b/2223/CH7/EX7.4/Ex7_4.sav
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index 000000000..af66304db
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+++ b/2223/CH7/EX7.4/Ex7_4.sav
diff --git a/2223/CH7/EX7.4/Ex7_4.sce b/2223/CH7/EX7.4/Ex7_4.sce
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index 000000000..e654fb602
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+// scilab Code Exa 7.4 Calculation on a single stage gas turbine

+

+gamma_g=1.33;

+gamma=1.4

+R_g=284.1;

+R=287;

+P=1e3; // Power Output in kW

+N1=3e3; // Speed in RPM

+n_t=0.87; // efficiency

+cp_g=1.145; // Specific Heat of gas at Constant Pressure in kJ/(kgK)

+cp_a=1.0045; // Specific Heat of air at Constant Pressure in kJ/(kgK)

+

+// part (a)mass flow rate of the gas through the turbine

+T01=1000;  // Entry Temperature in Kelvin

+p01=2.5; //  Entry Pressure in bar

+T01a=500;  // Entry Temperature of air in Kelvin

+p01a=2; //  Entry Pressure of air in bar

+p02=1; //  Exit Pressure in bar

+pr0=p01/p02;

+T02=T01*(pr0^(-((gamma_g-1)/gamma_g)));

+delh_s1=cp_g*(T01-T02)*n_t;

+m_g=P/delh_s1;

+disp("kg/s",m_g,"(a)mass flow rate of the gas through the turbine is")

+

+// part (b)speed, mass flow rate, pressure ratio and power required 

+N2=sqrt(1/2)*5*N1;

+disp("rpm",N2,"(b)(i)speed of a geometrically similar compressor is")

+a=0.2; // a=D2/D1;

+m2=(a^2)*sqrt(R_g/R)*sqrt(T01/T01a)*(p01a/p01)*m_g;

+disp("kg/s",m2,"(b)(ii)mass flow rate of a geometrically similar turbine is")

+delh_s2=0.5*delh_s1;

+P2=m2*delh_s2;

+disp("kW",P2,"(b)(iii)Power developed is")

+pr=(1-(delh_s2/(cp_a*T01a*n_t)))^(-1/((gamma-1)/gamma));

+disp(pr,"(b)(iv)pressure ratio of a geometrically similar turbine is")