Upper bifi frame for a gas turbine engine and methods therefor
An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case is provided. The upper bifi frame includes a forward fairing having a forward fairing midsection extending between the engine casing and the fan case. The forward fairing has a forward fairing first end including a flange configured to couple to the engine casing. The forward fairing has a forward fairing second end extending from the forward fairing midsection and configured to couple to the fan case. At least one aft seal is secured to the forward fairing and forms a seal therewith. A wedge seal is coupled to the forward fairing and the at least one aft seal and is operative to prevent air leakage to a pylon that is secured to the engine casing.
1. An upper bifi frame for preventing air leakage in a gas turbine engine including an engine casing and a fan case, the upper bifi frame comprising:
a forward fairing having a forward fairing midsection extending between the engine casing and the fan case, the forward fairing having a forward fairing first end including a flange to couple to the engine casing, the forward fairing having a forward fairing second end extending from the forward fairing midsection to couple to the fan case;
at least one aft seal secured to the forward fairing and forming a seal; and
a wedge seal coupled to the forward fairing and the at least one aft seal and operative to prevent air leakage to a pylon that is secured to the engine casing.
2. The upper bifi frame of claim 1 , wherein the at least one aft seal comprises:
an aft seal midsection extending along the forward fairing midsection and forming a seal;
an aft seal first end extending along the forward fairing first end and forming a seal; and
an aft seal second end extending along the forward fairing second end and forming a seal.
3. The upper bifi frame of claim 1 , wherein the at least one aft seal comprises a left aft seal and a right aft seal, the left aft seal coupled to a first side of the forward fairing, the right aft seal coupled to a second side of the forward fairing.
4. The upper bifi frame of claim 1 , wherein the at least one aft seal is removable from the forward fairing to allow at least one of raising or dropping the gas turbine engine.
5. The upper bifi frame of claim 3 , wherein the gas turbine engine is at least one of raised or dropped while the forward fairing is joined to the engine casing.
6. The upper bifi frame of claim 1 , wherein the at least one aft seal comprises:
a pin operable to secure the at least one aft seal to the forward fairing; and
a bolt operable to lock the at least one aft seal to the forward fairing.
7. The upper bifi frame of claim 1 , wherein the wedge seal provides a seal between a hinge beam of at least one nacelle door and the at least one aft seal.
8. The upper bifi frame of claim 1 , wherein the gas turbine engine upper bifi frame forms a fairing for the pylon.
9. A gas turbine engine comprising:
an engine casing;
a fan case positioned around the engine casing;
a pylon attached to the engine casing and operative to secure the engine casing to an aircraft; and
an upper bifi frame comprising:
a forward fairing coupled between the engine casing and the fan case;
at least one aft seal secured to the forward fairing; and
a wedge seal coupled to the forward fairing and the at least one aft seal and operative to prevent air leakage to the pylon.
10. The gas turbine engine of claim 9 , wherein the at least one aft seal comprises a left aft seal and a right aft seal, the left aft seal coupled to a first side of the forward fairing, the right aft seal coupled to a second side of the forward fairing.
11. The gas turbine engine of claim 9 , wherein the at least one aft seal is removable from the forward fairing to allow at least one of raising or dropping the gas turbine engine while the forward fairing is still secured to the engine casing.
12. The gas turbine engine of claim 9 further comprising a pin operable to secure the at least one aft seal to the forward fairing.
13. The gas turbine engine of claim 12 further comprising a bolt operable to lock the at least one aft seal to the forward fairing.
14. The gas turbine engine of claim 9 , wherein the at least one aft seal is removable from the forward fairing to allow access to the engine casing when at least one nacelle door is opened.
15. The gas turbine engine of claim 9 , wherein the wedge seal provides a seal between a hinge beam of at least one nacelle door and the at least one aft seal.
16. The gas turbine engine of claim 9 , wherein the upper bifi frame forms a fairing for the pylon.
17. A method of preventing air leakage in a gas turbine engine having an engine casing, a fan case positioned around the engine casing, at least one nacelle door that encloses a portion of the engine casing, and a pylon to secure the engine casing to an aircraft, the method comprising:
coupling a forward fairing of an upper bifi frame between the engine casing and the fan case;
securing at least one aft seal of the upper bifi frame to the forward fairing; and
coupling a wedge seal to the forward fairing and the at least one aft seal.
18. The method of claim 17 further comprising securing the at least one aft seal to the forward fairing with a pin.
19. The method of claim 17 further comprising further comprising:
coupling a left aft seal to a first side of the forward fairing; and
coupling a right aft seal to a second side of the forward fairing.
20. The method of claim 17 , wherein the at least one aft seal is removable from the forward fairing to allow access to the engine casing when the at least one nacelle door is opened.