Variable shape inlet section for a nacelle assembly of a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsAshok K. Jain, Zaffir A. Chaudhry
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Abstract
A method of improving the aerodynamic performance of an inlet section of a nacelle assembly of a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, (a) sensing an operability condition, (b) adjusting a leading edge of the inlet section in response to the step (a), and (c) adjusting a thickness of the inlet section in response to the step (a).
Claims15
A method of improving the aerodynamic performance of an inlet section of a nacelle assembly of a gas turbine engine, comprising the steps of:
- (a) sensing an operability condition;
- (b) adjusting a leading edge of the inlet section in response to said step (a);
- and
- (c) adjusting a thickness of the inlet section in response to said step (a).
A method of influencing an adaptive structure of a plurality of discrete sections of a gas turbine engine, comprising the steps of:
- positioning the plurality of discrete sections circumferentially about an engine longitudinal centerline axis, each of the plurality of discrete sections having a leading edge and a body panel portion aft of the leading edge that includes the adaptive structure;
- and
- adjusting a thickness of at least one body panel portion in each of a radially outer direction and a radially inner direction relative to the engine longitudinal centerline axis to alter the adaptive structure.
Dependencies are inferred from the claim text.