Variable shape inlet section for a nacelle assembly of a gas turbine engine

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).

What is claimed is: 
     
         1 . 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).   
     
     
         2 . The method as recited in  claim 1 , wherein the leading edge is adjustable between a thin position and a blunt position and said step (b) includes the step of:
 moving the leading edge between the thin position and the blunt position.   
     
     
         3 . The method as recited in  claim 1 , wherein the thickness of the inlet section is adjustable between a first position and a second position and said step (c) includes the step of:
 adjusting the thickness between the first position and the second position.   
     
     
         4 . The method as recited in  claim 3 , wherein the second position is radially outward from the first position. 
     
     
         5 . The method as recited in  claim 3 , wherein the second position is radially inward from the first position. 
     
     
         6 . The method as recited in  claim 1 , wherein the inlet section includes a plurality of discrete sections circumferentially disposed about an engine longitudinal centerline axis and each having a leading edge and a body panel portion aft of the leading edge that includes an adaptive structure, wherein said step (c) includes adjusting a thickness of each of the body panel portions in each of a radially outer direction and a radially inner direction relative to the engine longitudinal centerline axis to alter the adaptive structure. 
     
     
         7 . The method as recited in  claim 6 , wherein the adaptive structure of a first discrete section of the plurality of discrete sections is altered independently of the adaptive structure of a second discrete section of the plurality of discrete sections. 
     
     
         8 . The method as recited in  claim 1 , wherein said step (a) is performed using a programmable controller. 
     
     
         9 . 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.   
     
     
         10 . The method as recited in  claim 9 , comprising the step of identifying an operability condition prior to the step of adjusting. 
     
     
         11 . The method as recited in  claim 9 , comprising the step of moving the leading edge between a thin position and a blunt position. 
     
     
         12 . The method as recited in  claim 9 , wherein the adaptive structure of a first discrete section of the plurality of discrete sections is altered independently of the adaptive structure of a second discrete section of the plurality of discrete sections. 
     
     
         13 . The method as recited in  claim 12 , wherein the thickness of the first discrete section and the thickness of the second discrete section are adjusted uniformly. 
     
     
         14 . The method as recited in  claim 12 , wherein the thickness of the first discrete section and the thickness of the second discrete section are adjusted by a different thickness amount. 
     
     
         15 . The method as recited in  claim 9 , wherein the plurality of discrete sections include at least a first discrete section and a second discrete section, and said step of adjusting the thickness is performed on one of the first discrete section and the second discrete section but not on the other of the first discrete section and the second discrete section.