Why Do Gas Turbines and Compressors Have Specific Design Features?

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SUMMARY

This discussion focuses on the design features of gas turbines and compressors, specifically addressing the flow channel geometry, pressure distribution, and blade design. It is established that turbomachines typically do not have parallel hub and casing walls to optimize flow efficiency and minimize losses. The pressure changes qualitatively between the inlet and outlet in axial turbines, with a distinct distribution over airfoils. Additionally, compressor blades are designed to be thinner with less curvature compared to turbine blades, which are thicker and more curved to handle higher thermal stresses and flow dynamics.

PREREQUISITES
  • Understanding of turbomachinery principles
  • Familiarity with fluid dynamics concepts
  • Knowledge of aerodynamics related to airfoil design
  • Basic grasp of pressure distribution in compressible flow
NEXT STEPS
  • Research the impact of blade curvature on turbine efficiency
  • Study the principles of flow diffusion in turbomachines
  • Learn about the design considerations for axial flow turbines
  • Explore computational fluid dynamics (CFD) tools for turbomachinery analysis
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Engineers, designers, and students in the fields of mechanical engineering, aerospace engineering, and turbomachinery who are looking to deepen their understanding of gas turbine and compressor design principles.

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...

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