finalreportdraft (2).docx

8/10/2019 finalreportdraft (2).docx

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PES INSTITUTE OF TECHNOLOGY

BANGALORE

Project Report

On

DESIGN OF BLADE GEOMETRY FOR

SUPERCRITICAL CARBON DIOXIDE GAS

TURBINE

Submitted in Partial Fulfilment of the requirement for the award of degree

of

Bachelor Engineering In

Mechanical Engineering

BY

Ashutosh Gupta Lokesh Swami

1PI10ME029 1PI10ME062

Under the guidance of

Prof. T.R. SEETHARAM (Chair Professor)

Department of Mechanical Engineering

PES Institute Of Technology

Dr. Pramod Kumar(Assistant Professor)

Department of Mechanical Engineering

Indian Institute of Science


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PES Institute of Technology

Bangalore

eclaration

We hereby declare that the project work entitled Design of Blade Geometry for

Super Critical Carbon Dioxide Gas Turbine submitted to PES Institute of

Technology, is a record of an original work done by us under the guidance of

Prof. T.R. Seetharam, Chair Professor, PES Institute of Technology,

Bangaloreand Dr. Pramod Kumar, Assistant Professor, Indian Institute of

Science, Bangalore .This project work has not performed the basis, for award of

any Degree or Diploma/ Associate ship/ Fellowship and similar project if any.

Ashutosh Gupta Lokesh Swami(1PI10ME029) (IPI10ME062)


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PES INSTITUTE OF TECHNOLOGY

BANGALORE

CERTIFICATE

Certified that the project work entitled Design of Blade Geometry for Super

Critical Carbon Dioxide Gas Turbine is a bona fide work carried out by

Ashutosh Gupta and Lokesh Swami bearing USN 1PI10ME029 and

1PI10ME062 respectively, in a partial fulfilment of award degree of BACHELOR

OF ENGINEERING in MECHANICAL ENGINEERING during the academic year

2013-2014. It is certified that all corrections/suggestions indicated for internal

assessment have been incorporated in the report .The project report has been

approved as it satisfies the academic requirements with respect to project work

prescribed for above mentioned degree

Prof. T.R. Seetharam Prof. K.S. SRIDHAR

CHAIR PROFESSOR HODDEPT. OF MECHANICAL DEPT. OF MECHANICAL

ENGINEERING ENGINEERING

Ashutosh Gupta Lokesh Swami

1PI10ME029 1PI10ME062

Name of examiners Date withsignature

1._________________ 2. _________________

1._________________ 2._________________


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Acknowledgements

We would like to express our sincere thanks to Prof. T.R. Seetharam, Chair

Professor, Mechanical Department ,PES Institute of Technology, Bangalore and

Dr. Pramod Kumar, Assistant Professor, Mechanical Department ,IISC,

Bangalore for his kind and constant support and guidance throughout the course

of this project.

We would like to thank and extend our heartfelt gratitude to Prof. K.N.

Seetharamu ,Chair Professor ,and Prof. K.S. Sridhar,HOD for their valuable

suggestions and directions.

We would also, like to thank Asst. Prof. Saravanan V and Asst. Prof. Mukesh

Patilfor his constant support and technical guidance.

We are at most indebted to our parents for their endless support and

encouragement.


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Abstract

This present study describes the design of gas turbine blades at the mean

blade diameter. The primary objective is to write a program that finds the blade

angles and fluid angles with power output based on the user defined variables.

The program is programmed in Mat lab and is coupled with REFPROP that gives

the blade angles and fluid angles with maximum possible power output. The

program is preloaded with the fluid properties found from the literature review.

This fluid is the best to use according to the respective authors. The result is

generated with the main code of the program. Also a graphical user interface has

been written to be coupled with the main program.

The program generates all design parameters as output when primary design

point specifications are feed as input. Also program returns the velocity triangles

for given turbine stage at mean blade diameter.


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Table of contents

Acknowledgements ............................................................................................04

Abstract.................................................................................. .............................05

List of tables........................................................................................................08

List of figures .......................................................................................................09

Nomenclature......................................................................................................10

Subscript..............................................................................................................11

CHAPTER

1 Introduction

1.1 Super Critical Carbon dioxide........................................................12

1.2 Motivation for Super critical CO2as working fluid.........................12

1.3 Objective and scope.......................................................................13

2 Literature Review

2.1 Derivation of Euler's Turbine Equation...........................................14

2.2 Analytical Calculations....................................................................16

2.2.1 Input Parameters...................................................................16

2.2.2 Theoretical results.................................................................16

3 Design Procedure

3.1 Overall Procedure...........................................................................17

3.2 Design Basics.................................................................................18

3.3 Design Considerations....................................................................19


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4 Mat Lab Programming

4.1 Code..................................................................................................20

4.2 Input GUI Window.............................................................................31

4.3 Output GUI Window...........................................................................31

5 Conclusion and Future work

5.1 Conclusion..................32

5.2 Future work..32

7 References....33


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List of Tables

Table Page

2.1 Various velocity components and their effect............................................15

2.2 Various input Parameters for Blade profile Calculation ............................16

2.3 Output by analytical Calculations..............................................................16

4.1 Properties of nozzle wall............................................................................17

4.2 Variation of maximum temperature of steel wall and heat flux with

varying, constant ablative thicknesses......................................................17

5.1 Relationship for varying ablative thickness against nozzle length..19

5.2 Comparison of ablative thickness and steel wall temperature along

the nozzle length21


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List of Figures

Figure Page

1.2 Comparison of Super critical CO2 cycle with other cycles.13

2.1 Velocity Triangle at Inlet and Outlet of Rotor....14

3.1 Section of Turbine....................18

3.3 XY plot of mach number15

4.1 Nozzle profile incorporated with constant thickness solid wall...16

4.2 Residual plot of iteration process with conjugate wall condition..17

4.3 Contour plot of static temperature with conjugate wall condition18

4.4 XY plot of static temperature along the steel wall of nozzle18

5.1 Graph of relationship for optimum wall thickness at different sections of.19

5.2 Comparison of temperature along steel wall for different conditions20

5.3 Comparison of temperature along st

eel wall for different conditions20


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Torque exerted on shaft

Angular velocity of the shaft

Mass flow rate

ix Unit vector in axial direction

iu Unit vector in whirl direction

ird Unit vector in radial direction

p Power

Subscript

1 Inlet of stator

2 Outlet of stator and Inlet of rotor

3 Outlet of rotor


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Chapter 1

Introduction

1.1 Super Critical Carbon Dioxide

Super critical carbon dioxide is a fluid state of carbon dioxide where it is held at or

above its critical temperature and critical pressure.In critical state, carbondioxide adopts the properties midway between a gas and a liquid. It can effuse

through solids like gas and dissolve materials like liquids[1]. At close to the critical

point small changes in temperature and pressure result in large changes in

density allowing many of its properties to be fine tuned. The advantages of

supercritical fluid extraction (compared with liquid extraction) are that it is

relatively rapid because of the low viscosities and high diffusivities associated

with supercritical fluids. The extraction can be selective to some extent by

controlling the density of the medium and the extracted material is easily

recovered by simply depressurizing, allowing the supercritical fluid to return to

gas phase and evaporate leaving little or no solvent residues.

1.2 Motivation for supercritical CO2 as Working Fluid

Supercritical carbon dioxide can be used in a closed cycle gas turbine near

temperature range of 550C and 20 Mpa. It can be used for bulk thermal and

nuclear generation of electricity as it will enable high thermal efficiency of 45

percent, hence increasing the electrical power produced per unit of fuel by 40

percent. The environmental impact of increased cycle efficiency would be

significant.[2]
http://en.wikipedia.org/wiki/Supercritical_fluid_extractionhttp://en.wikipedia.org/wiki/Supercritical_fluid_extraction


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1.3 Objectives and Scope

The objective of the project is to perform analytical calculation of blade geometry

for single stage axial flow gas turbine. The analytical calculations are then coded

in MAT LAB with the help of REFPROP using given design parameters and live

feed of fluid properties to obtain a complete blade geometry along with

efficiencies. The mat lab code will not only give the theoretical values but also will

yield graphical results by variation of various design parameters. Hence the aim

of the project is to design the blade for turbine with supercritical carbon dioxide

gas as the working fluid . This will extend to making a user interface which will be

assisting in giving theoretical outputs for the user defined inputs.


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Chapter 2

Literature Review

2.1 Derivation of Eulers Turbine Equation

Assumptions:

The fluid flow through the rotor is assumed to be steady over a long period

of time i.e. mass flow rate is constant, rate of energy transfer at rotor is

constant and state of fluid at any given point is time invariant.

Losses due to leakage are assumed to be negligible.

Uniform of velocity profiles at inlet and exit.

Considering the entry and the exit of the rotor, it is evident that the forces on the

rotor are caused by changes in absolute velocity components in three directions.


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Change Result

Axial velocity component Axial thrust

Radial velocity component Tends to bend the rotor shaft

Tangential velocity component Tends to rotate the shaft

The torque exerted on the rotor due to change in angular momentum of flowing

fluid is given as:

On writing the component of the vector r and V in cylindrical polar coordinate

Then , is the component to tilt the shaft in the bearings . The component of

the moment causing the torque about the axis of the shaft is .

Assuming that is constant over the inlet section and outlet section, the

magnitude of the net torque on the rotor, considering the fluid at entry and exit is :

Where the subscript 2 and 3 refers to rotor inlet and outlet respectively. Taking

the axial component of torque only

is useful in transmitting power . The power transmitted is :

Where is angular speed of rotation.

Since at a point the tangential rotation speed

( )d

m r vdt

( ) ( )rd rd rd u u x x u x x ur v ri v i v i v i rv i rv i

xrv

urv

urv

23 3 3 2 2 2 2 3 3w x x ax u um i r v r v i r v r v

23 2 2 3 3ax u ui r v r v

23 23 2 2 3 3. .ax u up i m r v r v

u r


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Therefore

This is referred to as Eulers turbine equation.The Eulers equation may be used

for the flow of fluids like water, steam, air and combustion products, since their

viscosities are reasonably small. For the fluids of very large viscosity like heavy

oils or petroleum products, errors in the calculated torque and power output may

result due to

1. Non uniformity of velocity profiles at inlet and exit.

2. The boundary layer near the housing and stator surface.

2.2 Analytical Calculations

2.2.1 Input Parameters[3]

Mass Flow() 20kg/s

Isentropic Efficiency() 0.9

Inlet Temperature(T) 1100K

Temperature Drop(T-T) 145K

Pressure ratio(p/p) 1.873

Inlet Pressure(p) 4 bar

Rotational speed(N) 250

Mean blade speed(U) 4bar

2.2.2 Theoretical Results

R

2.8799 .8 .28 60.9448 0 28.8089 51.3402

2 2 3 3u up m u v u v


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Chapter 3

Design Procedure

3.1 Overall Procedure[4]

Assumption:

We are neglecting radial velocity component making it a two dimensional

flow.

The Primary Design Pointspecifications include:

1. Mass Flow Rate

2. Isentropic Efficiency

3. Inlet Temperature

4. Temperature Drop

5. Pressure Ratio

6. Inlet Pressure

7. Mean Blade Speed

8. Rotational Speed

Blade and fluid angles are calculated at the inlet and outlet of the rotor.

Velocity triangle is constructed at mean diameter.

Number of blades are calculated.

Centrifugal and fluid bending stresses are calculated for the turbine blades

so produced


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3.2 Design Basics

1. Spacing between two adjacent blades along the periphery of disk is called

thepi tch. The pitch increases in radial direction from hub of rotor to its

casing. The nominal value of the pitch is at mean radius.

2. The lateral boundary of the channels is along pressure and suction sides

of the blades and the end wall along hub and casing.

3. The bladechordis the straight distance from leading edge of the blade to

trailing edge. Its projection in the axial direction is axial cho rd.

4. Blade aspect ratio is the ratio of blade height to chord.

5. The distance between rotor blade tip and casing is called t ip clearance.

This is kept small in order to prevent t ip leakage flow in the rotor.


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3.3 Design Considerations[3]

2 3 2 3

The work delivered by a stage is given by

( ) ( ) (3.1)

if is constant across stage, equatio

u u u u

x x

w U V V U W W

v w

2 3 2 3

2

n may be written as

(tan tan ) (tan tan ) (3.2)

Let / denotes a flow coefficient and / a blade-loading coefficient

x x

x

w UV UV

V U w U

2

2 3

.

Then dividing both sides by Euler turbine equation in a nondimensional form as

2 (tan tan ) (

u

2 3 02 03

3.3)

In addition to and , a third non dimensional quantity is degree of reaction

= / (3.R h h h h

2 2 2 2 2 2 2 2 22 3 2 3 2 3 2 3

2 202 03

2 2 22 3

4)

( ) ( ) ( ) (tan tan )1 1 1 1

2 2 2 2

(tan tan ) = 1 (3

2

u uV V V V V V Vx R

h h w u u

R

2 3

2

.5)

using equation (3.3)

(tan tan ) = 1 (3.6)

2

Now is eliminated, again using eq. (3.3)

4(1 ta

R

R

3

2 3

2

n )

equation (3.3) and (3.5), written as

tan tan (3.7)2

tan t

3

3

2 2an (3.8)

when we solved for the unknown angles, gives

/ 2 2(1 )tan

2

R

R

2

(3.9)

/ 2 2(1 )tan (3.1

R

3

2

0)

Also in the same way we can obtain blade angles

/ 2 2tan = (3.11)

/ 2 2tan

R

R (3.12)


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Chapter 4

Mat lab Programming

4.1 Code[5],[6],[7]

%$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$%PROGRAM FOR CALCULATING VARIOUS OUTPUT PARAMETERS BY INTAKING INPUT% INPUT PARAMETERS IN SEQUENCE AS FOLLOWS% MASS FLOW RATE(kg/s) m% ROTATIONAL SPEED(rev/s) n% MEAN BLADE SPEED(m/s) u% ISENTROPIC EFFICIENCY e% INPUT PRESSURE(kpa) pi

% INPUT TEMPERATURE(K) ti% PRESSURE RATIO(kpa) pd% TEMPERATURE DROP(K) td%$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$% OUTPUT PARAMETERS IN SEQUENCE AS FOLLOWS% BLADE-LODING COEFFICIENT si% FLOW COEFFICIENT phi% DEGREE OF REACTION r% all the angle are measured from axial direction% DIRECTION OF ABSOLUTE VELOCITY AT INLET OF ROTOR atwo% DIRECTION OF ABSOLUTE VELOCITY AT OUTLET OF ROTOR athree% BLADE ANGLE(relative velocity) AT INLET btwo% BLADE ANGLE(relative velocity) AT OUTLET bthree

% power output(watt) p%$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$function varargout = axialguitrial2(varargin)% AXIALGUITRIAL2 M-file for axialguitrial2.fig% AXIALGUITRIAL2, by itself, creates a new AXIALGUITRIAL2 or raisesthe existing% singleton*.%% H = AXIALGUITRIAL2 returns the handle to a new AXIALGUITRIAL2 orthe handle to% the existing singleton*.%% AXIALGUITRIAL2('CALLBACK',hObject,eventData,handles,...) callsthe local% function named CALLBACK in AXIALGUITRIAL2.M with the given inputarguments.%% AXIALGUITRIAL2('Property','Value',...) creates a newAXIALGUITRIAL2 or raises the% existing singleton*. Starting from the left, property valuepairs are% applied to the GUI before axialguitrial2_OpeningFunction getscalled. An% unrecognized property name or invalid value makes propertyapplication% stop. All inputs are passed to axialguitrial2_OpeningFcn viavarargin.%


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% --- Executes on button press in pushbutton1.function pushbutton1_Callback(hObject, eventdata, handles)% hObject handle to pushbutton1 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles structure with handles and user data (see GUIDATA)cp=1.148si = 2*handles.var8*cp*1000/(handles.var3*handles.var3)% flow coffiecient(phi) is assumed

set(handles.edit9, 'String',si)phi=.8%bthree is the angle we find in degressbthree= atand (1/phi)set(handles.edit10, 'String', bthree)% degree of reaction is found outr= phi* tand(bthree)-si/4set(handles.edit11, 'String', r)% btwo is the blade angle at rotor oulet in degreesbtwo= atand((si/2-2*r)/(2*phi))set(handles.edit12, 'String', btwo)% finding the direction of the absolute velocity at inlet and outlet in% degrees

atwo= atand(tand(btwo)+1/phi)set(handles.edit13, 'String', atwo)%athree is the absolute velocity angle at rotor outletathree= atand(tand(bthree)-1/phi)set(handles.edit14, 'String', athree)%$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$$%the method below is for the contruction of the velocity triangles using%the above angles and speeds% we are scaling the mean blade speed on the x axis on scale from 0 to 5%for that we are using two variables x1=0 y1=0 to mark origin and x2=5y2=0%to mark the maxium point till we are extendingx1=0;y1=0;x2=5;y2=0

%absolute velocity vector is assumed to pass through origin thanequation%of this vector will be x=tan(90-atwo). in the same way equation ofrepersenting vector%relative velocity and passing through will be y=tan(90-btwo)(x-5). now%intersection of these two line gives third vortex of triangle at inletof%rotor and same procedure is repated at outlet of triangle.x3=-5*(tand(90-btwo))/(tand(90-atwo)-tand(90-btwo))y3=x3*tand(90-atwo)x4=-5*(tand(90+bthree))/(tand(90+athree)-tand(bthree+90))y4=x4*tand(90+athree)% we are definiing the scale with respect to the mean blade speed for

the% velocity trianglescale=handles.var3/5% we are calculating the lenth of the side which represents v1 and v2ie.% absolute velocity at inlet and outlet.v1=sqrt(x3^2+y3^2)*scalev2=sqrt(x4^2+y4^2)*scale%power is calucated by euler's formulap=handles.var1*handles.var3*v1*cosd(90-atwo)set(handles.edit15, 'String', p)x5=linspace(0,x3,100);% for each corresponding value of x5 a value y5 is found

y5=x5*tand(90-atwo);% we are splitting the x3 again for the second line which starts from 5till x3 into 100


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% diffrent intervals and storing it in x6x6=linspace(5,x3,100);% corresponding y values for this x6 values are stored in y6y6=tand(90-btwo)*(x6-5);% for second triangle%we are spliting the x4 which is the first point into 100 intervals for% ie. it forms array starting from 0 to x4 containing 100 elementsx7= linspace(0,x4,100);

% for each corresponding value of x7 a value y7 is foundy7=x7*tand(90+athree);% we are splitting the x4 again for the second line which starts from 5till x4 into 100% diffrent intervals and storing it in x8x8=linspace(5,x4,100);%corresponding y values for this x8 values are stored in y8y8=tand(90+bthree)*(x8-5);% now the plotting of the all the arrays obtained above begins to makethe% velocity triangles desired by usplot(x5,y5,'r')xlabel('mean blade speed(u)(m/s)')

ylabel('axial velocity(m/s)')text(1.5,3.7,'Velocity Triangle at Inlet and Outlet ofRotor','Edgecolor','c','LineWidth',2)hold onplot(x7,y7,'k')plot(x6,y6,'g')plot(x8,y8,'b')legend('absolute velocity at inlet','absolute velocity atoutlet','relative velocity at inlet','relative velocity at outlet',-1)hold off

function edit1_Callback(hObject, eventdata, handles)% hObject handle to edit1 (see GCBO)

% eventdata reserved - to be defined in a future version of MATLAB% handles structure with handles and user data (see GUIDATA)

% Hints: get(hObject,'String') returns contents of edit1 as text% str2double(get(hObject,'String')) returns contents of edit1 asa doublecontent = str2double(get(hObject,'String'))handles.var1 = contentguidata(hObject,handles)

% --- Executes during object creation, after setting all properties.function edit1_CreateFcn(hObject, eventdata, handles)

% hObject handle to edit1 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles empty - handles not created until after all CreateFcnscalled

% Hint: edit controls usually have a white background on Windows.% See ISPC and COMPUTER.if ispc

set(hObject,'BackgroundColor','white');else

set(hObject,'BackgroundColor',get(0,'defaultUicontrolBackgroundColor'));end


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function edit2_Callback(hObject, eventdata, handles)% hObject handle to edit2 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles structure with handles and user data (see GUIDATA)

% Hints: get(hObject,'String') returns contents of edit2 as text% str2double(get(hObject,'String')) returns contents of edit2 asa double

content = str2double(get(hObject,'String'))handles.var2 = contentguidata(hObject,handles)

% --- Executes during object creation, after setting all properties.function edit2_CreateFcn(hObject, eventdata, handles)% hObject handle to edit2 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles empty - handles not created until after all CreateFcnscalled

% Hint: edit controls usually have a white background on Windows.

% See ISPC and COMPUTER.if ispc



function edit3_Callback(hObject, eventdata, handles)% hObject handle to edit3 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB

% handles structure with handles and user data (see GUIDATA)


% --- Executes during object creation, after setting all properties.function edit3_CreateFcn(hObject, eventdata, handles)% hObject handle to edit3 (see GCBO)

% eventdata reserved - to be defined in a future version of MATLAB% handles empty - handles not created until after all CreateFcnscalled




function edit4_Callback(hObject, eventdata, handles)


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% hObject handle to edit4 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles structure with handles and user data (see GUIDATA)

% Hints: get(hObject,'String') returns contents of edit4 as text% str2double(get(hObject,'String')) returns contents of edit4 asa doublecontent = str2double(get(hObject,'String'))

handles.var4 = contentguidata(hObject,handles)


% Hint: edit controls usually have a white background on Windows.% See ISPC and COMPUTER.

if ispcset(hObject,'BackgroundColor','white');

else




% --- Executes during object creation, after setting all properties.function edit5_CreateFcn(hObject, eventdata, handles)% hObject handle to edit5 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB

% handles empty - handles not created until after all CreateFcnscalled




function edit6_Callback(hObject, eventdata, handles)% hObject handle to edit6 (see GCBO)


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% eventdata reserved - to be defined in a future version of MATLAB% handles structure with handles and user data (see GUIDATA)

% Hints: get(hObject,'String') returns contents of edit6 as text% str2double(get(hObject,'String')) returns contents of edit6 asa doublecontent = str2double(get(hObject,'String'))handles.var6 = content

guidata(hObject,handles)







% --- Executes during object creation, after setting all properties.function edit7_CreateFcn(hObject, eventdata, handles)% hObject handle to edit7 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles empty - handles not created until after all CreateFcns

called




function edit8_Callback(hObject, eventdata, handles)% hObject handle to edit8 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB


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% handles structure with handles and user data (see GUIDATA)




set(hObject,'BackgroundColor','white');

else



% Hints: get(hObject,'String') returns contents of edit9 as text

% str2double(get(hObject,'String')) returns contents of edit9 asa double




else





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% --- Executes during object creation, after setting all properties.function edit10_CreateFcn(hObject, eventdata, handles)% hObject handle to edit10 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB

% handles empty - handles not created until after all CreateFcnscalled






% --- Executes during object creation, after setting all properties.function edit11_CreateFcn(hObject, eventdata, handles)

% hObject handle to edit11 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles empty - handles not created until after all CreateFcnscalled








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set(hObject,'BackgroundColor','white');

else








else







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% --- Executes during object creation, after setting all properties.function axes2_CreateFcn(hObject, eventdata, handles)% hObject handle to axes2 (see GCBO)% eventdata reserved - to be defined in a future version of MATLAB% handles empty - handles not created until after all CreateFcnscalled

% Hint: place code in OpeningFcn to populate axes2


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CHAPTER 5

CONCLUSION AND FUTURE WORK

5.1 Conclusion

This report is the study of the fluid Super critical Carbon dioxide as

working fluid for the power generation in a closed cycle gas turbines. Euler's

Equation was used To learn the basic concepts of energy conversion . The same

was used for the analytical calculations of the blade profile at the mean blade

diameter. The same calculations were then successfully coded in Mat Lab .The

Code was successfully executed as Graphical User Interface that would be more

user friendly.

The various parameters undertaken by us can be used only to give a blade

profile for two dimensional flow which is effective in the initial stages of the

turbine. The results achieved by the mat lab code were cross verified with the

analytical results and were found to be correct. The velocity triangles were also

found to be correct to the theoretical results.

5.2 Future work

The future work will aim to model the blade profile for three dimensional

flow . This would include the twisting of the blade from hub to tip and inclusion of

the blade thickness and breadth. These all parameters will be included in the GUI

to make it a platform the designing of the blades.


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CHAPTER 6

REFERENCES

[1] http://en.wikipedia.org/wiki/Supercritical_carbon_dioxide

[2] http://en.wikipedia.org/wiki/Supercritical_fluid

[3] Gas Turbine Theory (4thEdition,1996) by H Cohan ,GFC Rogers ,HIH

Saravanamuttoo ,Longman Group Limited, England

[4] Design of an Axial Turbine and Thermodynamic Analysis and Testing of aK03 Turbocharger by Yoshio Samaizu Perez Zuinga ,MassachusettsInstitute of Technology, June 2011, certified and accepted by John H.Leinhard V , MIT.

[5] www.mathworks.in

[6] Software used - Mat lab 7.0.0.19920(R14)

[7] Mat lab Help Manual 7.0.0.19920(R14)
http://en.wikipedia.org/wiki/Supercritical_fluidhttp://en.wikipedia.org/wiki/Supercritical_fluid

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