Methods and systems are provided for cooling a compressor in an engine. In one example, a compressor with a liquid coolant passage extending through a section of a housing of the compressor adjacent to a bypass passage, is provide. The bypass passage enable airflow to be directed around a portion of a compressor impeller.

A system includes a controller configured to control a heated flow discharged from an outlet of an eductor to an inlet control system to control a temperature of an intake flow through a compressor inlet of a compressor of a gas turbine system. The controller is configured to control a turbine extraction gas (TEG) flow to a motive inlet of the eductor. The controller is configured to control a suction flow to a suction inlet of the eductor. The TEG flow is extracted through a turbine casing, and the heated flow includes the TEG flow and the suction flow.

A turbo-molecular pump includes a stator provided at a pump base portion, a rotor rotatably driven on the stator, a heating section configured to heat the pump base portion, abase temperature detection section configured to detect a temperature of the pump base portion, and a rotor temperature detection section configured to detect a temperature equivalent as a physical amount equivalent to a temperature of the rotor. A temperature control device of the turbo-molecular pump comprises: a heating control section configured to control heating of the pump base portion by the heating section based on a detection value of the rotor temperature detection section; and an informing section configured to inform a warning when a detection temperature of the base temperature detection section is equal to or lower than a predetermined threshold.

Methods and systems are provided for cooling a compressor in an engine. In one example, a compressor with a liquid coolant passage extending through a section of a housing of the compressor adjacent to a bypass passage, is provide. The bypass passage enable airflow to be directed around a portion of a compressor impeller.

A compressor system including: a first compressor having a compressor suction side and a compressor delivery side; an anti-surge line having an inlet and an outlet; an anti-surge valve arranged along the anti-surge line and controlled for recirculating a gas flow from the compressor delivery side back to the compressor suction side; a gas temperature manipulation arrangement, functionally connected to the inlet of the anti-surge line, configured to reduce or prevent liquid phase in the anti-surge line when the anti-surge valve is open.

A method for pressure and temperature control of fluid in a series of cryogenic compressors. An actual speed for each compressor and an actual inlet pressure and actual inlet temperature at entry are determined. The maximum speed for each compressor and a desired inlet pressure for the first compressor is provided. A speed index for each compressor is determined from the maximum speed and actual speed of each compressor. A proportional value is determined from the deviation of the actual and desired inlet pressure. A priority value is determined from the smaller of the proportional value and the smallest speed index. A desired inlet temperature for the first compressor and a desired speed for each compressor are determined from the priority value. The actual inlet temperature is adjusted to the determined desired inlet temperature and the actual speed for each compressor is adjusted to the determined desired speed.

Systems, apparatus and methods for efficiently operating a chiller plant while minimizing or eliminating the occurrence of centrifugal compressor surge. Taking into account chiller design specifications and current operating conditions, a compressor lift point at which surge is predicted to occur is established. Minima and maxima for various chiller setpoints that avoid or eliminate the occurrence of compressor surge are imposed on setpoints provided by a conventional optimizing chiller controller. The chiller system is operated in accordance with the resultant anti-surge setpoints. Energy savings is realized by modulating coolant tower flow to enable the compressor to operate at near-surge conditions while preventing the onset of actual surge.

The present application provides an inlet bleed heat control system for a compressor of a gas turbine engine. The inlet bleed heat control system provides an inlet bleed heat manifold and an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient air.

A compressor operates within a system having a cooling capacity below 60 tons. The compressor includes a hermetically sealed housing and a drive module and aero module within the housing. The drive module includes a motor, a rotor, and oil free bearings. The aero module has a centrifugal impeller driven by the drive module to compress a working fluid. The compressor is arranged such that the working fluid flows through the drive module before reaching the aero module.

A vacuum pump and a controller are provided with which state information of the vacuum pump is collected in a timely manner. In a controller, control portions control operating states of internal devices (such as a motor, a heater, and a cooling valve) located in a vacuum pump main body. An information collection portion collects the state information of the vacuum pump main body, and a recording processing portion records, in the non-volatile memory, the state information collected by the information collection portion. Also, the information collection portion collects the state information of the vacuum pump main body at a point in time at which a control portion switches the operating state of an internal device.