Methods and systems are provided for a turbocharger. In one example, a method may include bypassing exhaust gases flowing to the turbocharger in response to a catalyst temperature being less than a threshold temperature. The bypassing includes opening a bypass valve and adjusting a position of one or more turbine nozzle vanes.

A monolithic lead separator includes a primary lead tube defining a primary channel, a plurality of secondary lead tubes formed monolithically with the primary lead tube, and an instrumentation lead splitter. A cap is positioned in an aperture in the instrumentation lead splitter in a fluid-tight manner. Each of the secondary channels intersects the primary channel. The instrumentation lead splitter is situated at the intersection of the primary channel and the secondary channels.

A gas turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. At least one of the combustion section or turbine section can have an exhaust gas passage. The turbine engine can also include an exhaust gas temperature sensor with a housing having an elongated probe portion. The elongated probe portion can have an outer wall bounding an interior. A temperature probe can be provided within the housing.

Solar and steam hybrid power generation system including a solar steam generator, an external steam regulator, a turboset, and a power generator. A steam outlet end of the solar steam generator is connected to a steam inlet of the turboset. A steam outlet end of the external steam regulator is connected to the steam inlet of the turboset. A steam outlet of the turboset is connected to the input end of a condenser, and the output end of the condenser is connected to the input end of a deaerator. The output end of the deaerator is connected to the input end of a water feed pump. The output end of the water feed pump is connected to a circulating water input end of the solar steam generator. The output end of the water feed pump is connected to a water-return bypass of the external steam.

Methods and systems for operating an aircraft engine. A health parameter for the aircraft engine is monitored by a health evaluation device, the health parameter received from a first instrument. the health parameter is compared, by the health evaluation device, to a predetermined threshold. When the health parameter reaches the predetermined threshold, the health evaluation device wirelessly transmits a fault signal to a controller associated with the aircraft engine to elicit a health response from the controller, the fault signal containing at least two mutually-exclusive fault codes associated with an operating condition of the aircraft engine monitored by a second instrument.

Methods and systems for operating an aircraft engine. A health parameter for the engine received from a first instrument is monitored by a health evaluation device communicatively coupled to a communication link between an engine controller and a second instrument which generates an operation parameter signal indicative of an engine operating condition. The health parameter is compared, by the health evaluation device, to a predetermined threshold. When the health parameter is below the threshold, the health evaluation device causes the operation parameter signal to be transmitted from the second instrument to the controller. When the health parameter reaches the threshold, the health evaluation device prevents the operation parameter signal from being transmitted from the second instrument to the controller, and transmits to the controller a fault signal to elicit a health response therefrom, the fault signal containing at least two mutually-exclusive fault codes associated with the operating condition.

A gas turbine engine has a housing exposed to a high temperature environment. The housing has a circumferential wall extending around the engine centerline and circumscribing an oil cavity. The wall has a sealing interface at an inner diameter thereof, the sealing interface having a central axis offset from the engine centerline. A boss is formed on the wall on the offset side relative to the engine centerline and a probe is mounted to the boss. The probe projects into the oil cavity. The oil in the oil cavity thermally shields the probe from the high temperature environment.

The present disclosure provides a method of multi-objective and multi-dimensional online joint monitoring for a nuclear turbine. The method includes: obtaining first temperature monitoring data of the nuclear turbine by performing online thermal monitoring on a rotor, a valve cage and a cylinder of the nuclear turbine under quick starting-up; obtaining second temperature monitoring data of tightness of a flange association plane of the cylinder of the nuclear turbine by performing online thermal monitoring on the tightness of the flange association plane; obtaining operation monitoring data of a shafting vibration of a rotor and bearing system of the nuclear turbine by performing online safety monitoring on the shafting vibration of the rotor and bearing system; and optimizing operation and maintenance control of the nuclear turbine according to at least one type of monitoring data among the first temperature monitoring data, the second temperature monitoring data and the operation monitoring data.

A main steam valve includes a cylindrical guide centered about an O-axis, a valve body disposed inside the guide so as to be slidable in the O-axis direction, a valve shaft on which the valve body moves in the O-axis direction between open and closed positions, and a casing having a flow path and a valve seat formed on an inner surface thereof. The flow path guides out a fluid guided into the casing from the inflow direction along the O-axis direction. The valve body abuts against the valve seat when the valve body is in the closed position. A valve chamber, formed in the casing, has a baffle plate provided in a region between an outer circumferential surface of the guide and an inner surface of the casing. The baffle plate interrupts swirling vortex flow with spiral vortex core extending in the circumferential direction of the O-axis of the guide.

A method of monitoring for combustion anomalies in a gas turbomachine includes sensing an exhaust gas temperature at each of a plurality of temperature sensors arranged in an exhaust system of the gas turbomachine, comparing the exhaust gas temperature at each of the plurality of temperature sensors with a mean exhaust gas temperature, determining whether the exhaust gas temperature at one or more of the plurality of temperature sensors deviates from the mean exhaust temperature by a predetermined threshold value, and identifying an instantaneous combustion anomaly at one or more of the temperature sensors sensing a temperature deviating from the mean exhaust temperature by more than the predetermined threshold value.