A compressor comprising: a casing; an upstream impeller and a downstream impeller for rotation in the casing; a diaphragm comprised of an internal portion and an external portion; an upstream diffuser fluidly coupled to an outlet of the upstream impeller; a return channel fluidly coupled to the upstream diffuser and to an inlet of the downstream impeller, the return channel has a plurality of return-channel blades connecting the internal and external diaphragm portions; and a downstream diffuser fluidly coupled to an outlet of the downstream impeller is disclosed. A first coolant passage is in the internal diaphragm portion and extends around an inner core, the first coolant passage being in heat-exchange relationship with the upstream diffuser and the return channel. A second coolant passage and third coolant passage are separated by a second inner core in the external diaphragm portion and in a heat-exchange relationship with the return channel and the downstream diffuser.

A portable cooling assembly for enhancing the cooling ability of an electric fan includes a tube that is coiled into a spiral and the tube contains a refrigerant. A pair of arms is each coupled to and extends away from the tube. Each of the arms is concavely arcuate to engage opposite sides of the fan for retaining the tube on the fan. In this way the refrigerant in the tube can cool air being blown thereacross by the fan for enhancing comfort for a user in a hot environment.

A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permitting circumferential thermal growth of the fan cooler without suffering from high cycle fatigue.

A solar chemically recuperated gas turbine system includes an exhaust-gas reformer, a solar reformer and a gas turbine unit with a combustion chamber. The reaction outlet of the exhaust-gas reformer is connected to the inlet of the solar reformer, the flue gas side inlet of the exhaust-gas reformer is connected to the exhaust-gas outlet of the gas turbine. The solar reformer outlet is connected to the combustion chamber inlet. Combustion gas drives the gas turbine after fuel burns in the combustion chamber, and the exhaust gas enters the exhaust-gas reformer. Fuel and steam are mixed and enter the reaction side of the exhaust-gas reformer through a fuel inlet. A reforming reaction between the fuel and steam under heating of the exhaust gas generates syngas. A further reforming reaction occurs by absorbing concentrated solar energy after the syngas enters the solar reformer, and the reactant is provided to combustion chamber.

A gas turbine engine has a fan and a compressor section with a first lower pressure location and a second higher pressure location. A heat exchanger and a higher pressure tap from the second higher pressure location pass through the heat exchanger. Air in the higher pressure tap is cooled by air from a lower pressure tap from the first lower pressure location. A valve controls flow to the heat exchanger from the lower pressure tap, the valve being controlled to limit flow from the lower pressure tap under certain conditions.

The present application describes a gas turbine inlet air system for providing a flow of air to a compressor. The gas turbine inlet air system may include an inlet air water cooling system positioned upstream of the compressor for cooling the flow of air with a flow of water and a moisture detection system positioned downstream of the inlet air water cooling system to detect if droplets of the flow of water pass beyond the inlet air water cooling system in the flow of air towards the compressor.

A centrifugal compressor for compressing a fluid in a gas phase or a supercritical phase includes: a rotational shaft; an axial flow path extending along an axial direction of the centrifugal compressor; a radial flow path communicating with the axial flow path and extending along a radial direction of the centrifugal compressor on a downstream side of the axial flow path; an impeller at least partially disposed in the radial flow path and configured to rotate together with the rotational shaft to increase pressure of the fluid flowing in the radial flow path; and a pre-compression unit disposed in the axial flow path at a position distant from a leading edge of the impeller on an upstream side of the leading edge and configured to increase the pressure of the fluid in advance before the fluid is introduced to the leading edge.

A vacuum pump with dynamic control of cooling fan speed and motor flux is provided to reduce transmitted noise and waste heat and provide a quieter, more efficient pump.

A compressor module includes: a compressor; and a high-pressure gas cooler which cools gas discharged from the compressor, wherein the high-pressure gas cooler includes a plurality of gas cooler partial bodies, wherein each gas cooler partial body includes a high-pressure casing which is formed in a cylindrical container shape extending in a horizontal direction and to which the gas is introduced and a high-pressure heat exchange unit which is installed in the high-pressure casing and cools a gas passing in one direction orthogonal to a center axis of the high-pressure casing, and wherein the gas cooler partial bodies are arranged in parallel so that the center axes of the high-pressure casings are parallel to each other, the gas sequentially flows through the gas cooler partial bodies.

A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.