Inner diameter scallop case flange for a case of a gas turbine engine
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United States of America Patent
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Jan 2, 2018
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N/A
app pub date -
Jun 10, 2015
filing date -
Jun 10, 2015
priority date (Note) -
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Abstract
A case for a gas turbine engine incudes a radial flange with a partial scallop along an inner diameter of the radial flange. A case assembly for a gas turbine engine incudes a first case with a first radial flange with a partial scallop along an inner diameter of the first radial flange, the partial scallop adjacent to a first aperture through the first radial flange and a second case with a second radial flange with a second aperture through the second radial flange, the second radial flange mountable to the first radial flange at an interface such that the second aperture is axially aligned with the first aperture and a seal lip that extends from the second case interfaces with said first case at a longitudinal interface.
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