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Gas Turbines and Compressors

  1. Oct 22, 2007 #1
    Dear All!!

    I am in need of the follwing few questions regarding Gas Turbines and Compressors. It will be very nice and helpful if you people reply....an earliest reply will be appriciated

    why the flow channel in turbomachines usually does not have parallel hub and casing walls

    how the static pressure changes qualitatively between in- and outlet in an axial action and reaction turbine.

    Sketch a qualitative pressure distribution over an airfoil.

    why compressor blades feature little curvature and are comparatively thin whereas turbine blades are highly curved and tend to be thicker.

    why it is more difficult to diffuse (i.e. decelerate) than to accelerate flow.

    how the cross section area changes for a parallel wall annular flow channel upon change in flow angle.

    Explain why the flow channel in turbomachines usually does not have parallel hub and casing walls and how you as designer would determine its shape.

    I know these are alot of questions but i am in real need of these...

    Regards

    Cheema
     
  2. jcsd
  3. Oct 22, 2007 #2
    At least make an attempt at answering the questions....

    You should be able to find something in your textbook, and if not, Google is your best friend.
     
  4. Oct 30, 2007 #3
    what is the differance between tensile and yield strength
     
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