Abstract: A method of starting a gas turbine engine is generally provided. The engine includes a rotor assembly including a compressor rotor and a turbine rotor each coupled to a shaft. The rotor assembly is coupled to a bearing assembly within a casing enabling rotation of the rotor assembly. The method includes determining, based on a lubricant parameter, a period of time within which a rotational speed of the rotor assembly is maintained within a bowed rotor mitigation speed range; rotating the rotor assembly for the period of time within the bowed rotor mitigation speed range; and accelerating the rotor assembly to the combustion speed to ignite a fuel-oxidizer mixture for combustion.

Abstract: An apparatus for transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ci

Abstract: An apparatus for transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

Abstract: A system for airfoil vibration control is generally provided. The system includes an airfoil including a ferromagnetic material, and a static structure including an electromagnet adjacent to the ferromagnetic material of the airfoil. A method for controlling vibration at an airfoil of a turbo machine is further provided. The method includes placing a ferromagnetic material at the airfoil, placing an electromagnet at a static structure adjacent to the ferromagnetic material at the airfoil, and applying an electromagnetic force to the ferromagnetic material at the airfoil via the electromagnet at the static structure.

Abstract: An apparatus and method of transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.

Abstract: A method of starting a gas turbine engine is generally provided. The engine includes a rotor assembly including a compressor rotor and a turbine rotor each coupled to a shaft. The rotor assembly is coupled to a bearing assembly within a casing enabling rotation of the rotor assembly. The method includes determining, based on a lubricant parameter, a period of time within which a rotational speed of the rotor assembly is maintained within a bowed rotor mitigation speed range; rotating the rotor assembly for the period of time within the bowed rotor mitigation speed range; and accelerating the rotor assembly to the combustion speed to ignite a fuel-oxidizer mixture for combustion.

Abstract: Embodiments are generally provided of a gas turbine engine including a rotor assembly comprising a shaft extended along a longitudinal direction, in which a compressor rotor and a turbine rotor are each coupled to the shaft; a casing surrounding the rotor assembly, in which the casing defines a first opening radially outward of the compressor rotor, the turbine rotor, or both, and a second opening radially outward of the compressor rotor, the turbine rotor, or both; a first manifold assembly coupled to the casing at the first opening; a second manifold assembly coupled to the casing at the second opening, in which the first manifold, the casing, and the second manifold together define a thermal circuit in thermal communication with the rotor assembly; and a fluid flow device in fluid communication with the first manifold assembly, in which the fluid flow device provides a flow of fluid to the first manifold assembly and through the thermal circuit, and further wherein the flow of fluid egresses the thermal ci

Abstract: An apparatus and method of transporting a turbine engine with a transportation fixture including a turbine engine jig having mounts for securing the turbine engine, a rotor with a drive shaft rotationally supported by a bearing, the method includes supplying a lubricant to the bearing and rotating the drive shaft while the turbine engine is in transport.