Abstract: A gas turbine engine assembly and a method for assembling a gas turbine engine assembly are disclosed herein. The gas turbine engine assembly includes an engine core and a gearbox. The gearbox includes a lubrication system having a first sump and a second sump. The lubrication system is configurable to provide oil from either of the first and second sumps in various configurations of the gas turbine engine assembly.

Abstract: Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

Abstract: Methods and systems to electrically assist an internal combustion engine of an aircraft may be provided. A first bladed rotor may be rotated by a first internal combustion engine. Electricity may be generated from a first motor generator by rotating a first shaft of the first motor generator with the first internal combustion engine. In response to a predetermined event, such as an engine failure, mechanical power may be generated from the first motor generator instead of electricity. The mechanical power may be transferred to the first bladed rotor. The mechanical power may be generated by applying electricity to the first motor generator. The electricity applied is received from a second motor generator, where the electricity received from the second motor generator is generated by rotating a second shaft of the second motor generator with a second internal combustion engine that powers a second bladed rotor.

Abstract: A gas turbine engine assembly and a method for assembling a gas turbine engine assembly are disclosed herein. The gas turbine engine assembly includes an engine core and a gearbox. The gearbox includes a lubrication system having a first sump and a second sump. The lubrication system is configurable to provide oil from either of the first and second sumps in various configurations of the gas turbine engine assembly.

Abstract: One embodiment of the present disclosure is a unique gas turbine engine having a bearing system and method of operating the engine. Another embodiment is a unique rotor machine. Desired clearances are maintained in the engine and rotor and by the method. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for rotor machines, such as but not limited to, gas turbine engines.