lect - 6...4 prof. bhaskar roy, prof. a m pradeep, department of aerospace, iit bombay lect - 6 3-d...
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Lect - 6
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2Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
3-D Flows in Blade Passagesof
Axial Flow Compressors
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3Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
Local flow field decides blade shape
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4Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
3-D Flows through axial compressor• Axial flow acquires rotational component on entering the blades •Axial compressors blades are normally highly twisted• Airfoils used may significantly vary in camber and stagger settings from hub to tip • Solidity and spacing between the airfoils vary from root to tip• As a result of the above, Cp distributions on the blade surfaces vary from root to tip
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5Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
3-D blade shapes
Top View
Fabricated Blades
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6Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
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7Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
The flow, in passing through the curved, twisted blades, develop asymetricboundary layers on its bounding surface, which promote strong passage vortex development
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8Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
In certain blade shapes the flow, in passing through the blades, develop two passage vortices
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9Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
![Page 10: Lect - 6...4 Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay Lect - 6 3-D Flows through axial compressor • Axial flow acquires rotational component on entering](https://reader033.vdocuments.us/reader033/viewer/2022061000/60af342e4738b26f3e4c51b1/html5/thumbnails/10.jpg)
10Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
Boundary layer development at casing and hub (due to adverse pressure gradient of main flow) further contributes to 3-D flow development
End-wall Boundary layer development
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11Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
• Tip cross flow is opposite in motion to the rotation of the rotor blades• Blade tip scrubs through casing boundary layer
Scrubbing
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12Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
Change of inlet velocity profile through stages
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13Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
• Flow entering the stages downstream of the first stage becomes more and more non-axial
• Boundary layers are developed at the two ends of the blades – casing and hub ends
• The growing end wall boundary layers also act as “blockage” and reduces the main flow rate
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14Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
Flow across blade tip
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15Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
Passage vortex developmentacross blade passage
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16Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
3-D Flow development in rotor blades
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17Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
3-D Flow development in rotor blades
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18Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
3-D Flow development in rotor blades
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19Prof. Bhaskar Roy, Prof. A M Pradeep, Department of Aerospace, IIT Bombay
Lect - 6
Next Class -----
3-D Flow Analysis –Simple Radial Equilibrium theory