Fan case for use in a turbofan engine, and method of assembling a turbofan engine

1. A turbofan engine comprising:

a nacelle housing; and

a fan case coupled to said nacelle housing, said fan case comprising:

an aft portion that is substantially cylindrical and axi-symmetric about a centerline of the turbofan engine;

a forward portion extending from said aft portion, wherein a cross-sectional shape of said forward portion progressively decreases in radial size as said forward portion extends from said aft portion, said forward portion further defining concave portion extending from said aft portion and a convex portion extending from said concave portion;

a radial inner wall, a radial outer wall and an interior cavity defined between the radial inner wall and the radial outer wall;

a leading edge of the forward portion extending between the radial inner wall and radial outer wall;

a sheet of acoustic lining extending continuously from said aft portion at a location radially outward of a plurality of fan blades of the turbofan engine to the convex portion of said forward portion; and

an attachment flange at the forward portion, the attachment flange positioned aft of the leading edge of the forward portion,

wherein the sheet of acoustic lining is selectively removable from the interior cavity to thereby reduce the radial height of the fan case,

wherein the forward portion comprises a first arcuate portion and a second arcuate portion,

wherein at least a portion of the first arcuate portion extends a greater distance from the aft portion than the second arcuate portion such that a droop angle is formed with respect to the centerline at the intake, and

wherein the attachment flange extends obliquely relative to the centerline such that a direction orthogonal to a front surface of the attachment flange is aligned with the droop angle.

2. The turbofan engine in accordance with claim 1 further comprising a forward bulkhead positioned within said nacelle housing, wherein said forward portion of said fan case extends from said aft portion towards said forward bulkhead.

3. The turbofan engine in accordance with claim 2 , wherein a leading edge of said forward portion is coupled to said forward bulkhead.

4. The turbofan engine in accordance with claim 1 , wherein said nacelle housing comprises a second attachment flange for coupling to the attachment at the forward portion.

5. The turbofan engine in accordance with claim 1 , further comprising a fan assembly positioned within said nacelle housing, wherein said forward portion of said fan case is positioned upstream from said fan assembly.

6. The turbofan engine in accordance with claim 1 , wherein an entirety of said first arcuate portion extends a greater distance from said aft portion than an entirety of said second arcuate portion.

7. The turbofan engine in accordance with claim 6 , wherein said droop angle is less than about 10 degrees relative to the centerline of said fan case.

8. The turbofan engine in accordance with claim 6 , wherein said nacelle housing comprises a second attachment flange for coupling to the attachment flange at the forward portion.

9. The turbofan engine in accordance with claim 1 , wherein, when viewed from interior of said fan case, said forward portion comprises a sweeping profile that progressively transitions from a concave shape at the concave portion to a convex shape at the convex portion as said forward portion extends from said aft portion.

10. A method of assembling a turbofan engine, said method comprising:

providing a fan case that includes

an aft portion that is substantially cylindrical and axi-symmetric about a centerline of the turbofan engine,

a forward portion extending from the aft portion, a radial inner wall,

a radially outer wall and an interior cavity defined between the radial inner wall and the radial outer wall,

a leading edge of the forward portion extending between the radial inner wall and radial outer wall,

said forward portion further defining concave portion extending from said aft portion and a convex portion extending from said concave portion; and

positioning a sheet of acoustic lining within the fan case extending continuously from said aft portion at a location radially outward of a plurality of fan blades of the turbofan engine and to the convex portion of forward portion;

wherein a cross-sectional shape of the forward portion progressively decreases in radial size as the forward portion extends from the aft portion and further wherein the sheet of acoustic lining is selectively removable from the interior cavity to thereby reduce the radial height of the fan case; and

coupling the forward portion of the fan case to a nacelle housing utilizing an attachment flange at the forward portion, the attachment flange positioned aft of the leading edge of the forward portion,

wherein the forward portion comprises a first arcuate portion and a second arcuate portion,

wherein at least a portion of the first arcuate portion extends a greater distance from the aft portion than the second arcuate portion such that a droop angle is formed with respect to the centerline at the intake, and

wherein the attachment flange extends obliquely relative to the centerline such that a direction orthogonal to a front surface of the attachment flange is aligned with the droop angle.

11. The method in accordance with claim 10 , wherein coupling the forward portion comprises coupling a second attachment flange of the nacelle housing to the attachment flange at the forward portion.

12. The method in accordance with claim 11 , wherein an entirety of said first arcuate portion extends a greater distance from said aft portion than an entirety of said second arcuate portion.

13. The method in accordance with claim 10 , wherein coupling the forward portion comprises extending the forward portion of the fan case towards a forward bulkhead positioned within the nacelle housing.

14. The method in accordance with claim 13 , wherein extending the forward portion comprises coupling a leading edge of the forward portion to the forward bulkhead positioned within the nacelle housing.