A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer.

A compressor module (200) wherein the compressor module (200) defines a working fluid flow duct (60) between a compressor module inlet (210) and a compressor module outlet (214). The compressor module comprises: a first heat exchanger (37) and a compressor rotor stage (24) each provided in the working fluid flow duct (60). The first heat exchanger (37) is provided in flow series between the compressor module inlet (210) and the compressor rotor stage (24). The compressor stage (24) is provided in flow series between the first heat exchanger (37) and the compressor module outlet (214). The first heat exchanger (37) is defined by a wall (226) having an external surface (282) which is located in the working fluid flow duct (60). There is provided a heat sink unit (236) which defines a portion (240) of the working fluid flow duct (60) in flow series between the compressor rotor stage (24) and compressor module outlet (214). The first heat exchanger (37) is in heat transfer communication with the heat sink unit (236). The first heat exchanger (37) is configured such that it is operable to transfer heat to the heat sink unit (236) from the working fluid (250) passing the first heat exchanger (37).

An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

An engine driven environmental control system (ECS) air circuit includes a gas turbine engine having a compressor section. The compressor section includes a plurality of compressor bleeds. A selection valve selectively connects each of said bleeds to an input of an intercooler. A second valve is configured to selectively connect an output of said intercooler to at least one auxiliary compressor. The output of each of the at least one auxiliary compressors is connected to an ECS air input.

The present invention relates to a bypass air/fluid heat exchanger (2) for a turbofan engine. According to the invention, this exchanger (2) comprises: —an annular outer shroud (3) with two walls, an inner wall (32) and an outer wall (31), —an annular inner shroud (4) concentric with the outer shroud (3), —a series of OGV guide vanes (5) which connect said outer shroud to said inner shroud, —and a circulation circuit (6) for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit (6) is formed in the body of the outer shroud (3) and in the body of at least one of the OGV guide vanes (5), this circulation circuit (6) opening at the two respective ends thereof into an inlet opening (34) and into an outlet opening (35), formed through said outer wall (31) of the outer shroud, and the two shrouds (3, 4), the OGV guide vanes (5) and the circulation circuit (6) of said fluid are integral.

The present invention relates to a bypass air/fluid heat exchanger (2) for a turbofan engine. According to the invention, this exchanger (2) comprises: —an annular outer shroud (3) with two walls, an inner wall (32) and an outer wall (31), —an annular inner shroud (4) concentric with the outer shroud (3), —a series of OGV guide vanes (5) which connect said outer shroud to said inner shroud, —and a circulation circuit (6) for circulating said fluid, the two shrouds delimiting a bypass air flow path, the fluid circulation circuit (6) is formed in the body of the outer shroud (3) and in the body of at least one of the OGV guide vanes (5), this circulation circuit (6) opening at the two respective ends thereof into an inlet opening (34) and into an outlet opening (35), formed through said outer wall (31) of the outer shroud, and the two shrouds (3, 4), the OGV guide vanes (5) and the circulation circuit (6) of said fluid are integral.

Air conditioning system of an aircraft, comprising a thermal management system supplied with air, referred to as pressurized air (12), by at least one compressor (14) of the aircraft, and supplied with non-pressurized flow air (206; 208) from at least one engine of the aircraft, and characterized in that the thermal management system comprises: at least one pressurized-air/oil heat exchanger (20) designed to provide heat exchanges between a stream of pressurized air (12) and a first oil circuit (26), allowing heat to be transferred from the pressurized air (12) to the oil of the first oil circuit (26); at least one oil/flow-air heat exchanger (22a, 22b, 22c, 22d) designed to provide heat exchanges between a second oil circuit (28) and the flow air (206; 208), allowing the heat from said second oil circuit (26) to be transferred to the flow air (206; 208); and at least one circuit (30) connecting the first oil circuit (26) and said second oil circuit (28).

Air conditioning system of an aircraft, comprising a thermal management system supplied with air, referred to as pressurized air (12), by at least one compressor (14) of the aircraft, and supplied with non-pressurized flow air (206; 208) from at least one engine of the aircraft, and characterized in that the thermal management system comprises: at least one pressurized-air/oil heat exchanger (20) designed to provide heat exchanges between a stream of pressurized air (12) and a first oil circuit (26), allowing heat to be transferred from the pressurized air (12) to the oil of the first oil circuit (26); at least one oil/flow-air heat exchanger (22a, 22b, 22c, 22d) designed to provide heat exchanges between a second oil circuit (28) and the flow air (206; 208), allowing the heat from said second oil circuit (26) to be transferred to the flow air (206; 208); and at least one circuit (30) connecting the first oil circuit (26) and said second oil circuit (28).

A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.

A gas turbine engine has a compressor section and a turbine section. A secondary cooling air includes a first fluid connection to tap cooling air and pass the cooling air through a plurality of tubes, and a second fluid connection for returning air from the tubes back to at least one of the compressor and turbine for cooling. A sensor senses a condition of the cooling air downstream of the tubes and a control compares the sensed condition of the cooling air to an expected condition, and to identify a potential concern in the cooling air system should the sensed condition differ from the expected condition by more than a predetermined amount.