An auxiliary oil distribution system of a geared turbofan engine, with at least one part of the oil transport device driveably connected with at least one rotating part of an epicyclic gearbox of the geared turbofan engine, at least one oil guiding device to collect oil in the gearbox and/or outside the gearbox and to direct the oil to an oil target location.

Various embodiments include a drive system for a vehicle, the system comprising: an internal combustion engine for converting chemical energy stored in a liquid fuel into mechanical energy; a fuel tank for storing fuel for use by the internal combustion engine; and an electric machine having a rotor, a stator, and a cooling system for cooling at least one component of the electric machine using a cooling liquid. The cooling liquid comprises the fuel.

Various embodiments include a drive system for a vehicle, the system comprising: an internal combustion engine for converting chemical energy stored in a liquid fuel into mechanical energy; a fuel tank for storing fuel for use by the internal combustion engine; and an electric machine having a rotor, a stator, and a cooling system for cooling at least one component of the electric machine using a cooling liquid. The cooling liquid comprises the fuel.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a liner at least partially defining a combustion chamber of the gas turbine engine, wherein the liner comprises a looped feature.

A heat exchanger for a gas turbine engine including: a heat exchanger core having an inlet, an outlet, and a fluid passageway; an inlet pipe configured to provide hot airflow to the inlet; and an inlet flow conditioner fluidly connecting the outlet of the inlet pipe to the inlet of the heat exchanger core, the inlet flow conditioner including: a central attachment body; an outer shell located radially outward from the central attachment body, the outer shell including an inlet connected to the outlet of the inlet pipe, and an outlet opposite the inlet and connected to the inlet of the heat exchanger core; and a plurality of guide vanes extending from the central attachment body to the outer shell, the plurality of guide vanes being configured to impart a swirl upon airflow entering the inlet of the inlet flow conditioner and exiting the outlet of the inlet flow conditioner.

Centralizer apparatuses attached around a unison ring include rub buttons at inner ends of stud attached to and spaced apart from the unison ring and include rolling bearings. Each rolling bearing rotatably trapped within bearing chamber in bearing receptacle at inner end of stud.

Tip cap includes bearing aperture trapping rolling bearing within bearing chamber. Rolling bearing extends partially through bearing aperture. Rolling bearing may be spring loaded within chamber by spring between the bearing receptacle and the rolling bearing. Stud may extend through and may be threaded into mounting aperture in unison ring and nut may be threaded onto outer end of stud. Variable stator vanes rotatably mounted to a casing and connected to vane crank arms connected to the unison ring mounted exterior to casing.

In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90?. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.

In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90?. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.

An assembly is provided for an aerial vehicle. This assembly includes a vehicle body, a gas turbine engine and a support structure. The vehicle body includes a body section. The gas turbine engine includes a stationary structure. The gas turbine engine is housed within the vehicle body. The support structure extends between and is connected to the body section and the stationary structure. The support structure supports the gas turbine engine within the vehicle body. The body section, the stationary structure and the support structure are included in a monolithic body.