Method and system for the removal of large turbine engines
AssigneeGeneral Electric Company
InventorJan C. Schilling
Life of this patent
Estimating the term…
Abstract
A detachable support structure for a large turbine aircraft engine having a nacelle which is attached to an auxiliary support frame. The auxiliary support frame has an upper portion which is attached to an upper portion of the nacelle. The auxiliary support frame has a lower portion which is detachable from the upper portion of the auxiliary frame. The lower portion of the auxiliary frame is connected to a lower portion of the nacelle, the lower portion of the nacelle being detachable from the upper portion of the nacelle. By removing the lower portion of the nacelle and the lower portion of the auxiliary support frame, the thrust producing section of the turbine engine can be removed intact.
Claims10
A detachable support structure for a turbofan engine comprising:
- a fan casing having a distal portion and enclosing a plurality of fan blades;
- a fan outlet guide van assembly connecting the distal end portion of said fan casing to the turbofan;
- a nacelle connected to said fan casing, said nacelle having an upper portion;
- first means for permitting the intact removal of said fan casing, said plurality of fan blades, and said fan outlet guide vane assembly from nacelle;
- an auxiliary support frame having an upper portion connected to said upper portion of said nacelle;
- and
- second means for permitting the intact removal of said fan casing, said plurality of fan blades, and said fan outlet guide van assembly from the auxiliary support frame.
A method for removing intact a thrust section of a turbine aircraft engine assembly from a nacelle, the engine assembly including an engine, a fan casing enclosing a plurality of fan blades and being driven by the engine an outlet guide vane assembly connected to the fan casing and supporting the engine, said nacelle being connected to an upper and lower auxiliary support frame to support the engine assembly, the method comprising the steps of:
- removing a lower half portion of the nacelle from an upper half portion of the nacelle;
- removing the lower half portion of the auxiliary support frame from the upper half portion of the auxiliary support frame after the lower half portion of the nacelle is removed;
- and
- removing intact the engine assembly including the fan casing the plurality of fan blades which are enclosed by the fan casing, the engine and the fan outlet guide van assembly from the nacelle and auxiliary support frame after the lower half portion of the auxiliary support frame is removed.
A gas turbofan engine assembly and support structure comprising:
- a pylon attached to an aircraft;
- a nacelle having an upper half portion detachably connected to a lower half portion;
- means for attaching the upper half portion of the nacelle to the aircraft;
- an engine assembly comprising:
- (a) an engine means having an axial line extending horizontally therethrough;
- (b) a fan disk rotatably connected to the engine and operable to rotate about the axial line;
- (c) a plurality of fan blades attached to the fan disk;
- (d) a fan casing encircling said plurality of fan blades;
- and
- (e) an outlet guide vane assembly connecting said engine to said fan casing;
- an auxiliary support frame encircling said engine means said support frame having an upper support frame portion detachably connected to a lower support frame portion;
- means for attaching said support frame to said nacelle;
- means for removably attaching said engine means to said pylon;
- means for removably attaching said casing to said nacelle;
- and
- said auxiliary support frame including means for removably supporting said engine assembly such that when said lower half of said nacelle is detached from the upper half of said nacelle, when said engine means is detached from said pylon, and when said lower support frame portion is detached from said upper support frame portion, said engine assembly is removable intact from said pylon, said nacelle and said aircraft.
Dependencies are inferred from the claim text.