Thank you for an AMAZING video. I’m an aircraft maintenance School as we speak. Today is day one of turbines, and I felt a little bit overwhelmed, even though I understand the concept and its simplest form.. Seeing this video after reading the first couple pages in this chapter, I was able to go back and fully understand what I just read on a deeper level because of the effort and time you took to create this video for a visual learner like me. thank you sometimes I feel like I have a learning disability because it takes this level of animation for me to understand the concepts fully.
Why there is a restriction on pressure ratio at a given stage of compression? Why can't it be compressed up to 5 or 6? Is it due to material capability?
It is from the point of view of separation in the stator blades. AS already told they act like a diffuser, which is an adverse pressure gradient component. If we allow the velocity to drop more than a critical value by having higher divergence passage, the flow separates and no further pressure rise can take place.
Thank you for an AMAZING video. I’m an aircraft maintenance School as we speak. Today is day one of turbines, and I felt a little bit overwhelmed, even though I understand the concept and its simplest form.. Seeing this video after reading the first couple pages in this chapter, I was able to go back and fully understand what I just read on a deeper level because of the effort and time you took to create this video for a visual learner like me. thank you sometimes I feel like I have a learning disability because it takes this level of animation for me to understand the concepts fully.
Thank you for creating videos like this! It's really a great help ♥️
Great video. I'm taking my powerplant exam and starting an A&P job in just under 2 months. Really appreciate this explanation and the visuals
thank you ,nice turn of expression
thank you, very clear :)
what is the first stage of compressor? Stator or rotor? I searched and saw it many different pictures which is different from each other.
Rotor
Why there is a restriction on pressure ratio at a given stage of compression? Why can't it be compressed up to 5 or 6? Is it due to material capability?
i believe so, i think it's due to shear
It is from the point of view of separation in the stator blades. AS already told they act like a diffuser, which is an adverse pressure gradient component. If we allow the velocity to drop more than a critical value by having higher divergence passage, the flow separates and no further pressure rise can take place.