Inlet assembly for a turbofan engine
A nacelle for a turbofan engine includes a fan case, an inner barrel and a nose lip generally concentrically disposed about an axis. The inner barrel projects forward from and is engaged to the fan case at a first split line. The nose lip is engaged to the inner barrel at a second split line, and extends substantially radially outward directly from the second split line, then substantially axially rearward to the fan cowl as one unitary piece.
1. A nacelle for a turbofan engine comprising:
a fan case concentrically disposed about an axis;
an inner barrel projecting forward from and engaged to the fan case at a first split line; and
a nose lip engaged to the inner barrel at a second split line, and wherein the nose lip extends substantially radially outward directly from the second split line then substantially axially rearward as one unitary piece.
2. The nacelle set forth in claim 1 , wherein the second split line is disposed proximate to a stagnation point.
3. The nacelle set forth in claim 1 further comprising:
a first bulkhead disposed between and engaged to the inner barrel and the nose lip.
4. The nacelle set forth in claim 3 , wherein the first bulkhead is axially spaced rearward of the second split line and axially spaced forward of the first split line.
5. The nacelle set forth in claim 4 further comprising:
a fan cowl spaced radially outward from the fan case; and
a second bulkhead extending substantially radially between and proximate to the first split line and a third split line located where the nose lip meets the fan cowl.
6. The nacelle set forth in claim 5 , wherein the second split line is disposed proximate to a stagnation point of the turbofan engine when operating at a pre-determined flight condition.
7. The nacelle set forth in claim 6 , wherein the pre-determined flight condition is cruising speed.
8. The nacelle set forth in claim 2 , wherein the fan case, the inner barrel and the nose lip define a generally annular cavity.
9. The nacelle set forth in claim 8 further comprising:
a first bulkhead disposed in the cavity, extending between and engaged to the nose lip and the inner barrel, and spaced axially rearward from the second split line.
10. The nacelle set forth in claim 9 further comprising:
a fan cowl spaced radially outward from the fan case; and
a second bulkhead disposed in the cavity, and extending between the first split line and a third split line located where the nose lip meets the fan cowl.
11. The nacelle set forth in claim 10 further comprising:
an inner flange connection disposed at the first split line for attaching the second bulkhead, the inner barrel, and the nose lip together; and
an outer flange connection disposed at the third split line for connecting the nose lip to the second bulkhead, and wherein the second bulkhead extends between the inner and outer flange connections.
12. The nacelle set forth in claim 11 , wherein the outer flange connection is disposed axially forward of the inner flange connection.
13. The nacelle set forth in claim 12 , wherein the outer flange connection includes a landing for contact with the fan cowl.
14. The nacelle set forth in claim 3 , wherein the inner barrel is a one-piece inner barrel.
15. The nacelle set forth in claim 14 , wherein the inner barrel includes an acoustic feature extending axially forward of the first bulkhead.
16. The nacelle set forth in claim 15 , wherein the acoustic feature extends axially between and is proximate to the first and second split lines.
17. The nacelle set forth in claim 5 , wherein the third split line is disposed axially forward of the first split line.
18. The nacelle set forth in claim 9 , wherein the third split line is disposed axially forward of the first split line.
19. An inlet assembly for a turbofan engine comprising:
an inner barrel centered about an axis and including a forward end portion and a rearward end portion;
a nose lip extending circumferentially about the axis and including a forward end portion engaged to and extending at least in-part radially outward from the forward end portion of the inner barrel at a split line, and a rearward end portion projecting at least in-part axially rearward and spaced radially outward from the rearward end portion of the inner barrel; and
wherein the split line is proximate to a stagnation point of the turbofan engine when operating at a pre-determined flight condition.
20. The inlet assembly set forth in claim 19 further comprising:
a first bulkhead engaged to and spanning radially between the inner barrel and the nose lip, and wherein the split line is axially spaced forward of the first bulkhead; and
a second bulkhead engaged to and spanning radially between the aft end portion of the inner barrel and the aft end portion of the nose lip, and wherein the second bulkhead is axially spaced rearward from the first bulkhead.