Abstract: Turbomachines and methods for coupling first and second turbomachine components are provided. The components include castellated flange arrangements that provide an improved retention method for retaining the components that is far superior in than bolts and nuts, especially for massive unbalance loading.

Abstract: The present invention provides a turbofan engine including leading edge erosion protection for composite stator vanes contained therein. The composite stator vanes are defined by a leading edge, a trailing edge, a concave surface and a convex surface. The vanes are generally formed of a graphite fiber and an aramid fiber braided preform that is laminated with an epoxy matrix resin or other high temperature matrix resin. A wire mesh screen is embedded during a molding process into an outermost surface of the leading edge of the epoxy matrix resin. A tapering erosion protection layer comprised of an erosion protective material is applied to the wire mesh screen at the leading edge of the composite stator vane an aids in protecting the leading edge of the stator vane from debris and contaminants, including operational fluids, dust, and sand that may be carried in an air stream passing therethrough the turbofan engine, as well as an erosive operational environment.

Abstract: The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending from an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

Abstract: The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending from an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

Abstract: The present invention provides a tailcone and power assembly mountable to the body of an aircraft using a height adjustable dolly. The tailcone assembly comprises a longitudinal support member, a gas turbine engine mounted to the support member; a firewall; two curved rotatable casings hingeably connected to the support member; an inlet duct extending from an aperture in one of the rotatable casings to the engine inlet; an integral exhaust casing, and interface means for making necessary engine accessory connections to the aircraft. The tailcone is installed on the aircraft by mounting the tailcone in the adjustable dolly, rolling the dolly up to the aircraft, adjusting the dolly until the auxiliary power assembly is properly aligned for attachment to the aircraft, connecting the engine accessories to the aircraft, and bolting the assembly to the aircraft.

Abstract: A blade containment system for fan blades of a gas turbine engine includes a fan casing surrounding the fan blades and serving as a first blade containment structure and a second blade containment structure positioned axially forward of the fan casing within an engine nacelle. The second containment structure preferably includes an inner liner of noise absorbing material, such as honeycomb paneling. Preferably, the second containment structure comprises a ring of titanium material having axially oriented stiffeners for controlling bending upon impact by a broken blade or blade fragment. The stiffeners are desirably integrally formed in the ring and the ring is illustratively produced by super plastic forming. The ring may be formed as a plurality of arcuate segments having edges adapted for joining with adjacent segments to form a complete ring. A flange may be attached to an aft edge of the ring and used to connect the ring to the fan casing.