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How to change the blade angles of aerofoil in turbine blade
- Thread starter Black0058
- Start date
What part of the turbine and what kind of turbine?
Is whatever sort of turbine typically available with variable pitch blades?
What angle is "edge angle"?
Is this variation as performed during an analysis or is this to happen in a functioning turbine?
Is whatever sort of turbine typically available with variable pitch blades?
What angle is "edge angle"?
Is this variation as performed during an analysis or is this to happen in a functioning turbine?
SWComposites
Aerospace
Go here: and dig thru the paper, software and workshop links.
do you mean you want to change the blade angle while the engine is running, like propeller pitch control on a plane's propeller ?
or are you trying to design a turbine and want to understand the impact of blade pitch angle ?
"Hoffen wir mal, dass alles gut geht !"
General Paulus, Nov 1942, outside Stalingrad after the launch of Operation Uranus.
or are you trying to design a turbine and want to understand the impact of blade pitch angle ?
"Hoffen wir mal, dass alles gut geht !"
General Paulus, Nov 1942, outside Stalingrad after the launch of Operation Uranus.
Typically the compressor and turbine sections have alternating ROTOR[rotating] and STATOR[stationary] blades.
Attempting to adjust the pitch of compressor or turbine blades turning at tens-of-thousands of RPMs would generate terrific forces and frictions... and confine the turning mechanisms within the shaft. This would be a monstrously complex Task for anything except giant slow-turning shafts. not to mention mindboggling balance/dynamics issues.
However IF blade pitch adjustments are required for optimized gas-path flow, then that typically occurs in the STATOR-blade rows. Each STATOR-row is linked-together so it will simultaneously adjust each blade in unison... which may be different for each stator row. This system of STATOR blade adjustment... outside of the compressor/turbine cases... optimizes thru-flow relative to conditions in/out-of conditions each ROTOR-blade stage.
Regards, Wil Taylor
o Trust - But Verify!
o For those who believe, no proof is required; for those who cannot believe, no proof is possible. [variation, Stuart Chase]
o Unfortunately, in science what You 'believe' is irrelevant. ["Orion", HBA forum]
o Only fools and charlatans know everything and understand everything." -Anton Chekhov
Attempting to adjust the pitch of compressor or turbine blades turning at tens-of-thousands of RPMs would generate terrific forces and frictions... and confine the turning mechanisms within the shaft. This would be a monstrously complex Task for anything except giant slow-turning shafts. not to mention mindboggling balance/dynamics issues.
However IF blade pitch adjustments are required for optimized gas-path flow, then that typically occurs in the STATOR-blade rows. Each STATOR-row is linked-together so it will simultaneously adjust each blade in unison... which may be different for each stator row. This system of STATOR blade adjustment... outside of the compressor/turbine cases... optimizes thru-flow relative to conditions in/out-of conditions each ROTOR-blade stage.
Regards, Wil Taylor
o Trust - But Verify!
o For those who believe, no proof is required; for those who cannot believe, no proof is possible. [variation, Stuart Chase]
o Unfortunately, in science what You 'believe' is irrelevant. ["Orion", HBA forum]
o Only fools and charlatans know everything and understand everything." -Anton Chekhov
FREDERICK E MAUPERTUIS
New member
Maybe borrow the concept of low pressure compressor VSV (variable stator vanes and unison ring) eg: P&W JT9D and many others applied to turbines nozzle guide vanes.
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