Blade/disk dovetail backcut for blade/disk stress reduction (6FA+E, stage2)

Blade/disk dovetail backcut for blade/disk stress reduction (6FA+E, stage2)

Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the...

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Hauptverfasser: Mohr, Patrick J, Fernandez, Emilio, Rajanna, Anil B, Murugesan, Seerangan, Dewangan, Kamlesh
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Sprache:eng
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creator Mohr, Patrick J
Fernandez, Emilio
Rajanna, Anil B
Murugesan, Seerangan
Dewangan, Kamlesh
description Blade load path on a gas turbine disk can be diverted to provide a significant disk fatigue life benefit. A plurality of gas turbine blades are attachable to a gas turbine disk, where each of the gas turbine blades includes a blade dovetail engageable in a correspondingly-shaped dovetail slot in the gas turbine disk. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade. Removing material from the material removal area effects the maximized balance.
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title Blade/disk dovetail backcut for blade/disk stress reduction (6FA+E, stage2)
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