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: A gas turbine engine starter-generator includes a housing assembly, a motor-generator, and a lubricant pump. The housing assembly includes a lubricant inlet port for receiving a flow of lubricant. The motor-generator is disposed within the housing assembly and is adapted to be coupled to an auxiliary power unit. The motor-generator is configured to selectively operate in either a motor mode or a generator mode. The lubricant pump is disposed within the housing assembly and includes one or more pump inlets and one or more pump outlets.

Abstract: Systems and methods for monitoring engine oil temperatures to detect higher than normal oil temperatures are provided. The system comprises a plurality of sensors for obtaining input signals from the operating engine for a predetermined set of engine conditions. At least one of the plurality of sensors includes an oil temperature sensor for measuring an engine oil temperature. The system also includes an engine control unit (ECU) where a plurality of predetermined limit values corresponding to at least one predetermined set of engine operating conditions is stored. The engine control unit is configured to select a predetermined limit value corresponding to a measured set of engine operating conditions, to calculate a maintenance limit value using the selected predetermined limit value, and to compare the measured oil temperature with the maintenance limit value. An output unit outputs a predetermined output depending on the result of the comparison.

Abstract: An engine system for starting a gas turbine engine is provided. The system includes a starter generator coupled to the gas turbine engine and configured to provide torque to the gas turbine engine and a controller coupled to the starter generator and configured to provide a command signal to the starter generator. The starter generator provides the torque to the gas turbine engine based on the command signal, and the controller is configured to command the starter generator at a dwell speed until ignition.

Abstract: Systems and methods for monitoring engine oil temperatures to detect higher than normal oil temperatures are provided. The system comprises a plurality of sensors for obtaining input signals from the operating engine for a predetermined set of engine conditions. At least one of the plurality of sensors includes an oil temperature sensor for measuring an engine oil temperature. The system also includes an engine control unit (ECU) where a plurality of predetermined limit values corresponding to at least one predetermined set of engine operating conditions is stored. The engine control unit is configured to select a predetermined limit value corresponding to a measured set of engine operating conditions, to calculate a maintenance limit value using the selected predetermined limit value, and to compare the measured oil temperature with the maintenance limit value. An output unit outputs a predetermined output depending on the result of the comparison.

Abstract: An engine system for starting a gas turbine engine is provided. The system includes a starter generator coupled to the gas turbine engine and configured to provide torque to the gas turbine engine and a controller coupled to the starter generator and configured to provide a command signal to the starter generator. The starter generator provides the torque to the gas turbine engine based on the command signal, and the controller is configured to command the starter generator at a dwell speed until ignition.

Abstract: A gas turbine engine starter-generator includes a housing assembly, a motor-generator, and a lubricant pump. The housing assembly includes a lubricant inlet port for receiving a flow of lubricant. The motor-generator is disposed within the housing assembly and is adapted to be coupled to an auxiliary power unit. The motor-generator is configured to selectively operate in either a motor mode or a generator mode. The lubricant pump is disposed within the housing assembly and includes one or more pump inlets and one or more pump outlets.

Abstract: Methods and apparatus are provided for controlling an auxiliary power unit (APU) inlet door. A plurality of APU operational parameters and a plurality of aircraft operational parameters are sensed. The APU operational parameters and the aircraft operational parameters are processed to determine a minimum APU inlet door position that will maintain APU turbine inlet temperature at a predetermined value. The APU inlet door is then moved to the determined minimum APU inlet door position.

Abstract: An auxiliary power unit (APU) is provided and configured to be mounted in an APU compartment that defines an inlet opening. The APU includes a power section having components lubricated with oil; an intake duct coupled to the inlet opening and the power section and configured to direct a first portion of air flow through the inlet opening into the power section; an oil cooler coupled to the power section and configured to cool the oil of the power unit; a cooling duct coupled to the oil cooler and the intake opening; an inlet door mounted at the inlet opening and configured to open and close the inlet opening, the inlet door further configured to be positioned in at least a first open position and a second open position; and a thermal management system configured to adjust the inlet door between the first open position and the second open position based on one or more operating temperatures within the APU.

Abstract: Methods integrated tailcone muffler (ITM) is provided for minimizing noise generated while discharging pressurized air from one or more aircraft gas turbine engines. The ITM comprises a tail cone defining a conical backing cavity, the conical backing cavity having a large forward end and a narrow aft end and a porous exhaust liner with a first end and a second end, the first end coupled to an oil cooler eductor discharge plenum of a first gas turbine engine of the one or more gas turbine engines and a second end discharging to atmosphere via the narrow aft end of the conical backing cavity.

Abstract: A combustor for an engine assembly includes a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling.

Abstract: A combustor for an engine assembly includes a cylindrical wall forming a combustion chamber in which an air and fuel mixture is combusted; and a plurality of effusion cooling holes formed in the cylindrical wall, the plurality of effusion cooling holes oriented such that cooling air flowing therethrough cools the cylindrical wall with effusion cooling, convection cooling, and impingement cooling.