Why Do Gas Turbines and Compressors Have Specific Design Features?

AI Thread Summary
Gas turbines and compressors are designed with specific features to optimize performance and efficiency. The flow channels in turbomachines are typically non-parallel to manage pressure gradients and improve flow stability. In axial turbines, static pressure decreases from inlet to outlet due to energy conversion, while compressor blades are thinner and less curved to facilitate efficient airflow, contrasting with thicker, highly curved turbine blades that enhance energy extraction. Diffusing flow is more challenging than accelerating it due to the complexities of pressure recovery and flow separation. Understanding these design principles is crucial for effective turbomachinery design.
CHeema
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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 a lot of questions but i am in real need of these...

Regards

Cheema
 
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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.
 
what is the difference between tensile and yield strength
 

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