GAS TURBINE ENGINE BLADE WITH INCREASED WALL THICKNESS ZONE IN THE TRAILING EDGE-HUB REGION
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United States of America Patent
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Issued Date -
Jan 12, 2017
app pub date -
Nov 10, 2015
filing date -
Jul 9, 2015
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Abstract
Airfoil outer wall thickness of a gas turbine engine blade is increased in the zone that is proximate the trailing edge and blade hub by forty to sixty percent (40-60%) greater than comparable greatest wall thickness anywhere else along the trailing edge from outboard that zone all the way to the blade tip. The increased thickness zone includes a transition zone that bridges the respective airfoil outer wall thicknesses proximate the hub and tip of the blade. Some embodiments also incorporate pedestals with compound curve fillets in the increased wall thickness zone. The increased thickness zone reduces blade cracking propensity and enhances service life.
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