A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.

A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.

A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.

An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

A turbine diagnostic machine learning system builds one or more turbine engine performance models using one or more parameter or parameter characteristics. A model of turbine engine performance includes ranked parameters or parameter characteristics, the ranking of which is calculated by a model builder based upon a function of AIC, AUC and p-value, resulting in a corresponding importance rank. These raw parameters and raw parameter characteristics are then sorted according to their importance rank, and selected by a selection component to form one or more completed models. The one or more models are operatively coupled to one or more other models to facilitate further machine learning capabilities by the system.

A gearbox for a gas turbine engine with a rotatably mounted structural component that is formed with an at least approximately rotationally symmetrical duct into which, starting from its radially inner area, oil from an oil supply which is fixedly attached at the housing can be introduced. Starting from the oil supply, an introduction direction of the oil into the duct encloses an angle of 90° or an angle of between 60° and 90° with the axial extension direction of the duct. Additionally, in the circumferential direction of the duct, the introduction direction of the oil encloses an angle with the radial extension direction that is larger than or equal to 0° and smaller than 90°.

A gearbox for a gas turbine engine with a rotatably mounted structural component that is formed with an at least approximately rotationally symmetrical duct into which, starting from its radially inner area, oil from an oil supply which is fixedly attached at the housing can be introduced. Starting from the oil supply, an introduction direction of the oil into the duct encloses an angle of 90° or an angle of between 60° and 90° with the axial extension direction of the duct. Additionally, in the circumferential direction of the duct, the introduction direction of the oil encloses an angle with the radial extension direction that is larger than or equal to 0° and smaller than 90°.

An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.