Variable contraction ratio nacelle assembly for a gas turbine engine

1. A nacelle assembly, comprising:

an inlet lip section having a highlight diameter and a throat diameter, wherein one of said highlight diameter and said throat diameter of said inlet lip section is fixed and the other of said highlight diameter and said throat diameter is selectively adjustable in each of a first direction and a second direction relative to said inlet lip section to influence a contraction ratio associated with said inlet lip section; and

said contraction ratio is selectively adjustable between a range of about 1 to about 1.4.

2. The assembly as recited in claim 1 , comprising an internal linkage housed within said inlet lip section and selectively adjustable to influence said contraction ratio of said inlet lip section.

3. The assembly as recited in claim 1 , wherein said first direction is upstream and said second direction is radially outward relative to said inlet lip section.

4. The assembly as recited in claim 1 , wherein said first direction is downstream and said second direction is radially inward relative to said inlet lip section.

5. A method for adjusting a contraction ratio associated with an inlet lip section of a gas turbine engine, comprising the steps of:

(a) detecting an operability condition;

(b) fixing one of a highlight diameter and a throat diameter of the inlet lip section relative to the inlet lip section;

(c) adjusting the other of the highlight diameter and the throat diameter in each of an axial direction and a radial direction relative to the inlet lip section in response to the operability condition detected in said step (a); and

wherein the contraction ratio is adjustable between a range of about 1.0 to about 1.4.

6. The method as recited in claim 5 , wherein the axial direction is an upstream direction and the radial direction is a radial outward direction, said step (c) comprising:

altering one of the highlight diameter and the throat diameter in each of the radial outward direction and the upstream direction.

7. The method as recited in claim 5 , wherein the axial direction is a downstream direction and the radial direction is a radial inward direction, said step (c) comprising:

altering one of the highlight diameter and the throat diameter in each of the downstream direction and the radial inward direction.

8. The method as recited in claim 5 , wherein a distinct contraction ratio is associated with each operability condition detected at said step (a), the method comprising the step of:

(d) programming each distinct contraction ratio into an engine controller.

9. The assembly as recited in claim 1 , wherein one of said throat diameter and said highlight diameter is simultaneously adjustable in each of an axial direction and a radial direction.

10. A structural assembly for a gas turbine engine, comprising:

a nacelle assembly;

an inlet lip section positioned adjacent a forward segment of said nacelle assembly and having a highlight diameter and a throat diameter, wherein one of said highlight diameter and said throat diameter is fixed relative to said nacelle assembly and the other of said highlight diameter and said throat diameter includes an adjustable shape, and said adjustable shape is selectively manipulated simultaneously in each of an axial direction and a radial direction to influence a contraction ratio of said inlet lip section between a range of about 1 and about 1.4; and

a controller that identifies an operability condition, wherein the controller selectively alters said adjustable shape in response to said operability condition.