Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. A density of the lattice varies in at least one of an axial direction and a radial direction. The second projection is configured to interlock with the first projection in a second state.

Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. A density of the lattice varies in at least one of an axial direction and a radial direction. The second projection is configured to interlock with the first projection in a second state.

Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. The second projection is configured to interlock with the first projection in a second state.

Abstract: A containment system for a gas turbine engine includes an outer containment ring having a first projection that extends radially inward and an inner containment ring having at least a second projection that extends radially outward toward the outer containment ring. The second projection is offset and spaced apart from the first projection to define a chamber in a first state. The containment system includes a lattice defined within the chamber that spans the chamber, and the lattice is integrally formed with each of the outer containment ring and the inner containment ring. The second projection is configured to interlock with the first projection in a second state.

Abstract: Apparatuses are provided for a containment ring. The containment ring includes a first portion having a first ring composed of a first material with a first ductility. The containment ring also includes a second portion coupled to the first ring. The second portion is composed of a second material having a second ductility that is less than the first ductility and the first ductility is greater than about forty percent elongation.

Abstract: Apparatuses are provided for a containment ring. The containment ring includes a first portion having a first ring composed of a first material with a first ductility. The containment ring also includes a second portion coupled to the first ring. The second portion is composed of a second material having a second ductility that is less than the first ductility and the first ductility is greater than about forty percent elongation.

Abstract: Assemblies for cooling an aft bearing assembly mounted to a rotor are provided. An assembly includes a static aft bearing structure configured to surround the aft bearing assembly and including a cylindrical section defining a cavity for disposal of the aft bearing assembly, a plurality of hollow struts extending from the static aft bearing structure, each hollow strut including an outer radial end configured to receive a gas from an air source and to provide a pathway for the gas to flow into the cavity, and a center-body cap disposed over an end of the static aft bearing structure, the center-body cap including a rim configured to create a low pressure region at an interface between the static aft bearing structure and the center-body cap, wherein the low pressure region has a pressure that is lower than a pressure within the cavity.

Abstract: An inlet door system including an aft inlet duct mounted door actuator providing RAM air to an auxiliary power unit (APU) contained within an aircraft is provided. The inlet door system includes an inlet duct, the aft inlet duct mounted door actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage. The door actuator is mounted to an exterior surface of the aft portion of the inlet duct. The door is coupled to the actuator. The actuator is configured to selectively rotate the door between at least a first position and a second position.

Abstract: Assemblies for cooling an aft bearing assembly mounted to a rotor are provided. An assembly includes a static aft bearing structure configured to surround the aft bearing assembly and including a cylindrical section defining a cavity for disposal of the aft bearing assembly, a plurality of hollow struts extending from the static aft bearing structure, each hollow strut including an outer radial end configured to receive a gas from an air source and to provide a pathway for the gas to flow into the cavity, and a center-body cap disposed over an end of the static aft bearing structure, the center-body cap including a rim configured to create a low pressure region at an interface between the static aft bearing structure and the center-body cap, wherein the low pressure region has a pressure that is lower than a pressure within the cavity.

Abstract: An inlet door system including an aft inlet duct mounted door actuator providing RAM air to an auxiliary power unit (APU) contained within an aircraft is provided. The inlet door system includes an inlet duct, the aft inlet duct mounted door actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage. The door actuator is mounted to an exterior surface of the aft portion of the inlet duct. The door is coupled to the actuator. The actuator is configured to selectively rotate the door between at least a first position and a second position.

Abstract: The present invention relates to an impeller containment system for containing the burst of an impeller or the burst of impeller fragments from an impeller hub. The containment system utilizes a catcher extending from a shroud plate adjacent the impeller, which engages with a snagger formed as a unitary part of the impeller. The catcher and snagger cooperate to restrain a burst impeller or impeller fragments to their shortest radial distance from their point of burst. The system also includes a shroud which circumferentially surrounds the impeller and a diffuser, which circumferentially surrounds the radial tip portions of the impeller.

Abstract: The present invention is addressed to a multiple layer blade burst control system for use in turbine engines. The system utilizes a first inner containment ring and a second outer containment ring separated by a layer of thin ductile material. The inner containment ring and outer containment ring are each mounted to an engine housing by the use of a plurality of supporting legs. The first inner containment ring and the second outer containment ring each have complementary ribs and grooves on their respective inner and outer surfaces, so that when broken blades or blade fragments strike the inner surface of the inner containment ring, this ring absorbs the transfer of energy and moves towards the second containment ring. The movement of the inner containment ring also deforms the thin ductile material which creates an additional energy transfer. The system may also be utilized without the thin ductile layer, and a set of intermeshing protrusions and recesses.