01-09-2012, 01:06 PM
DESIGN AND ANALYSIS OF GAS TURBINE BLADES USING F.E.A
DESIGN AND ANALYSIS.ppt (Size: 582 KB / Downloads: 230)
ABSTRACT
The first stage rotor blade of a two stage gas turbine has been analyzed for structural, thermal,and modal analysis
The first stage rotor blade of the gas turbine is analyzed for the mechanical and radial elongations resulting from the tangential, axial and centrifugal forces
The material of the blade was specified as N155. This material is an iron based super alloy
For Modeling and analyses of the gas turbine blade ,CAD Software packages namely CATIA,ANSYS 9.0,Hypermesh and V5R15 have been used.
The results obtained are discussed and reported.
INTRODUCTION
Turbine stages may be used to turn shafts to power other machinery such as the rotor of a helicopter, the propellers of a ship or electrical generators in power stations.
The major cause of break down in turbo machine is the failure of rotor blade.The failure of the rotor blade may lead to catastrophic consequences both physically and economically.
Proper design of the turbo machine blade plays a vital role in the proper functioning of the turbo machine.
OBJECTIVES OF THE PROJECT
Determination of geometric characteristics from gas dynamic analysis.
Determination of steady loads acting on the blade and stressing due to them.
Determination of natural frequencies and mode shapes.
Determination of unsteady forces due to stage flow interaction.
Determination of dynamic forces and life estimation based on the cumulative damage fatigue theories.
FE MODELING
Aerofoil profile of the rotor blade is generated on the XY plane with the help of key points .Then a number of splines were fitted through the keypoints.
By using these points, blade model is created in CATIA, V5R15 with the help of commands like spline,extrude,add.And the modal is exported into HYPERMESH7.0 and meshed it by using commands like automesh, tetmesh and exported into ANSYS 9.0.
The shaded area are extruded upwards through the blade height along the positive Z direction, Areas 4,5,6 were extruded downwards along the negative direction also the shaded areas are extruded along the X-direction using 3 –D 20 node Brick elements. And a 3-D Model of rotor blade is created.