Method for controlling a clearance between the tips of the blades of a rotor of an aircraft engine turbine and a turbine ring, comprising the estimation of the clearance to be controlled and the control of a valve delivering an air stream directed towards the turbine ring based on the thus estimated clearance, this method comprising: the detection of a transient acceleration phase based on at least one parameter representative of the engine; the receipt of a data relating to the altitude of the aircraft; the determination of data representative of the temperature of the rotor during the transient acceleration phase and in steady speed and the calculation of a relative temperature deviation.

According to an aspect, a bowed rotor sensor system for a gas turbine engine is provided. The bowed rotor sensor system includes a bowed rotor sensor operable to transmit a sensing field in an observation region and receive a signal indicative of a gap between an air seal and a blade tip within the gas turbine engine. The bowed rotor sensor system also includes a controller operable to monitor a plurality of gap data from the bowed rotor sensor indicative of the gap between the air seal and the blade tip of a plurality of blades passing through the observation region and determine a bowed rotor status of the gas turbine engine based on the gap data.

An engine includes side plates and inner plates, cylinders installed inside the side plates and the inner plates, having a piston compression chamber, and having an inverted triangular shape and an equilateral triangular shape, an integrated crankshaft rotatably installed to pass through central regions of the inner plates and having crank-eccentric shafts eccentrically formed at both ends thereof, eccentric cams installed in the crank-eccentric shafts as eccentric driving holes and positioned in the piston compression chamber, elliptical rotor pistons rotatably installed on outer peripheral surfaces of the eccentric cams as eccentric cam bearings and eccentrically rotated in opposite directions, and eccentric cam eccentric shafts integrally formed at both ends of the eccentric cams and rotatably connected to an eccentric shaft bearing of a rear eccentric shaft and an eccentric bearing of an output shaft.

An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.

An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.

A lubrication system is provided for a turbine engine. This lubrication system includes a lubricant source, a pump, a first turbine engine component, a bypass circuit and a second turbine engine component. The lubricant source includes a source outlet. The pump includes a pump inlet and a pump outlet. The pump inlet is fluidly coupled with the source outlet. The first turbine engine component includes a first volume. The first volume is fluidly coupled with the pump outlet. The bypass circuit includes a bypass inlet and a bypass outlet. The bypass inlet is fluidly coupled with the pump outlet upstream of the first volume. The bypass outlet is fluidly coupled with the pump inlet downstream of the source outlet. The second turbine engine component includes a second volume. The second volume is fluidly coupled with the pump inlet downstream of the bypass outlet.

A lubrication system is provided for a turbine engine. A lubricant source includes a source outlet. Feed circuits are fluidly coupled with the source outlet in parallel. The feed circuits include a first feed circuit and a second feed circuit. The second feed circuit includes a pump with a pump inlet and a pump outlet. A bypass circuit is fluidly coupled with the pump inlet and the pump outlet. A bleed circuit is fluidly coupled with the first feed circuit. A flow regulator is configured to regulate flow through the bypass circuit during a first mode of operation and a second mode of operation. The flow regulator is configured to close the bleed circuit during the second mode of operation. A sensor system is configured to monitor fluid flow directed to the first feed circuit and/or the second feed circuit.

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

A gas turbine engine including a first rotor assembly comprising a first drive shaft extended along a longitudinal direction; a housing coupled to the first rotor assembly to provide rotation of the first rotor assembly around an axial centerline; a first accessory assembly, wherein the first accessory assembly sends and/or extracts energy to and from the first rotor assembly; and a first clutch assembly disposed between the first rotor assembly and the first accessory assembly. The first clutch assembly engages and disengages the first rotor assembly to and from the first accessory assembly.

A gas turbine engine (10) includes a compressor section, a turbine section, and an accessory gearbox (100). A turning unit (200) for the gas turbine engine includes an output assembly (204) configured to be mechanically coupled to the gas turbine engine, and an electric motor (202). The electric motor is operable to rotate, through the output assembly, one or more components of the compressor section or the turbine section at a rotational speed less than about fifty revolutions per minute during a shut-down condition of the gas turbine engine.