A fluid compressor system configured to supply a compressed working fluid including at least a first air-end and a second air-end, a first and second intercooler, and a coolant circulation system having at least one throttle valve. The first and second intercoolers are configured to cool the compressed working fluid delivered by the first and second air-ends of the fluid compressor system, respectively. The coolant circulation system includes a coolant supplying header and a coolant collecting header, where the coolant supplying header supplies a coolant to the first intercooler and the second intercooler, and the coolant collecting header collects the coolant from the first intercooler and the second intercooler. The at least one throttle valve regulates a coolant flow discharged by one of the first intercooler or the second intercooler prior to entering the coolant collecting header.

An aircraft turboprop engine has at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the means for supplying air has at least one compressor of which the rotor is coupled to the low-pressure body. The compressor has an air inlet connected to means for bleeding air from an air inlet duct of the turboprop engine.

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.

A system and a method for processing air prior to separating components of the air are disclosed. The system comprises an air cooler, one or more compression stages operated in series, and one or more intercoolers installed between two adjacent compression stages. A blowdown storage tank is configured to collect water blowdown from one or more intercoolers and provide cooling medium to the air cooler. Atmospheric air is first sprayed by the water blowdown in the air cooler to form a cooled air stream. The cooled air stream is subsequently compressed in the one or more compression stages and cooled by the intercoolers between two adjacent compression stages. The water blowdown from one or more of the intercoolers is collected and recycled as the cooling medium to cool the atmospheric air before it enters the first compression stage.

A compressor 1 includes a casing 2 that covers a rotating shaft 4 and an impeller 6 and is provided with a diffuser 66 for guiding the working fluid discharged from the impeller 6 to an outside in a radial direction, a heat exchanger 71 that is cools at least a portion of the working fluid compressed by the impeller 6, a cooling fluid supplying unit 7 that supplies the working fluid cooled by the heat exchanger 71 into the casing 2 as a cooling fluid for cooling a motor 5 disposed in the casing 2, and a cooling fluid circulating unit 8 that discharges the cooling fluid that has passed through the motor 5 to an outside of the casing 2, and supplies the discharged cooling fluid downstream of an outlet 6o of a first impeller 6A and upstream of the diffuser 66.

A compressor cooling apparatus includes: a blade row mounted for rotation about a centerline axis; a stationary diffuser located downstream of, and in flow communication with, the blade row; an inducer disposed between the diffuser and the blade row, the inducer having an inlet in flow communication with the diffuser, and having an outlet oriented to direct flow towards the blade row.

A gas turbine engine includes a plurality of rotating components housed within a main compressor section and a turbine section. A first tap is connected to the main compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A cooling air valve is configured to selectively block flow of cooling air across the heat exchanger. A cooling compressor is connected downstream of the heat exchanger. A shut off valve stops flow between the heat exchanger and the cooling compressor. A second tap is configured to deliver air at a second pressure which is higher than the first pressure. A mixing chamber is connected downstream of the cooling compressor and the second tap. The mixing chamber is configured to deliver air to at least one of the plurality of rotating components. A system stops flow between the cooling compressor and the plurality of rotating components. A controller is configured to modulate flow between the heat exchanger and the plurality of rotating components under certain power conditions of the gas turbine engine. The controller is programmed to control the cooling air valve, the shut off valve and the system such that flow is stopped between the heat exchanger and the cooling compressor only after the cooling compressor has been stopped.

An axial fan wheel, in particular for the radiator of a motor vehicle engine, is described. The axial fan wheel includes a crown ring having a multiplicity of rotor blades, a hub having an inner ring which is connected or connectable to a drive shaft, and having, for the purpose of torque transmission, connection surfaces along an outer periphery of the hub which are connected to the inner ring and to the crown ring. The hub has through-passages between the inner ring and the outer periphery. At least one element, arranged rotationally fixedly on the axial fan wheel inside the crown ring, is designed to maintain a pressure difference in the axial direction when the axial fan wheel rotates.

An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

A compressor module for compressing gas composed of a compressor element with a housing with integrated compressor element cooler; a motor and a gas cooler for cooling the compressed gas originating from the compressor element. The gas cooler includes a primary section through which the gas to be cooled can be guided and a secondary section that is in heat-exchanging contact with the primary section. A first cooling circuit can guide a coolant through the secondary section of the gas cooler or through a section thereof and a second cooling circuit can guide a coolant through the compressor element cooler. The first cooling circuit and the second cooling circuit are joined together in series or in parallel and are guided to a common output.