Lockwire Tab Backcut For Blade Stress Reduction (9E.04)
The present application thus provides a method for reducing stress on a turbine blade wherein each of the turbine blades includes a dovetail with lockwire tab. The method may include the steps of (a) determining a starting line for a backcut relative to a lockwire tab end, (b) determining a cut angl...
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Main Authors | , , , |
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Format | Patent |
Language | English |
Published |
14.12.2017
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Subjects | |
Online Access | Get full text |
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Summary: | The present application thus provides a method for reducing stress on a turbine blade wherein each of the turbine blades includes a dovetail with lockwire tab. The method may include the steps of (a) determining a starting line for a backcut relative to a lockwire tab end, (b) determining a cut angle for the backcut, and (c) removing material from the lockwire tab according to the starting line and the cut angle to form the dovetail backcut. The starting line may be positioned about 0.6 inches (about 15.24 millimeters), plus or minus 0.065 inches (about 1.65 millimeters) from the lockwire tab end along the dovetail axis. |
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Bibliography: | Application Number: US201615180842 |