An air conditioning pack of a cooling system includes an air cycle machine assembly, a cabin air compressor assembly, and a mixing duct. The air cycle machine assembly includes a compressor configured to receive an air stream that includes bleed air to generate a compressed air stream. The air cycle machine assembly utilizes a first portion of the compressed air stream to power the compressor. The cabin air compressor assembly receives a second portion of the compressed air stream, and utilizes the second portion to generate compressed ram air. The mixing duct receives the compressed ram air and allows the compressed ram air to mix with one or more of the air stream upstream of the compressor or the compressed air stream downstream of the compressor to generate a hybrid air stream that is used for cooling at least a portion of a vehicle.

A waste heat capture system that can be used with at least a gas turbine engine. The system includes: an air scoop connected to a first component, the air scoop configured to direct air from a first duct to an interior compartment of the first component; a second duct along an exterior of the first component; and a thermoelectric material connected to an interior surface of the first component. The interior compartment of the first component is on a first side of the thermoelectric material and the exterior of the first component is on a second side of the thermoelectric material. The first duct is configured to receive air having a first temperature range, and the second duct is configured to receive air having a second temperature range, wherein the second temperature range is an order of magnitude higher than the first temperature range.

An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell stack, a heat exchanger, an elongated shaft, and a motor assembly. The heat exchanger is disposed in fluid communication with the hydrogen fuel source and the fuel cell stack. The elongated shaft supports the air compressor system, the fuel cell stack and the heat exchanger. The motor assembly is disposed in electrical communication with the fuel cell stack.

An integrated hydrogen-electric engine including an air compressor system, a hydrogen fuel source, a fuel cell stack, a heat exchanger, an elongated shaft, and a motor assembly. The heat exchanger is disposed in fluid communication with the hydrogen fuel source and the fuel cell stack. The elongated shaft supports the air compressor system, the fuel cell stack and the heat exchanger. The motor assembly is disposed in electrical communication with the fuel cell stack.

A fracturing system is disclosed. The fracturing may include a turbine engine; a fracturing fluid pump powered by the turbine engine via at least one reduction gearbox; an auxiliary mover for powering a hydraulic system for lubricating the turbine engine or the fracturing fluid pump or for powering a cooling system for cooling the turbine engine or the fracturing fluid pump; a first fire-control subsystem associated with the turbine engine; and a second fire-control subsystem associated with the auxiliary mover. The fracturing system is thus configured to provide fire-control and fire-fighting capabilities to minimize inadvertent consequences to the turbine engine as well as the auxiliary mover.

A fracturing system is disclosed. The fracturing may include a turbine engine; a fracturing fluid pump powered by the turbine engine via at least one reduction gearbox; an auxiliary mover for powering a hydraulic system for lubricating the turbine engine or the fracturing fluid pump or for powering a cooling system for cooling the turbine engine or the fracturing fluid pump; a first fire-control subsystem associated with the turbine engine; and a second fire-control subsystem associated with the auxiliary mover. The fracturing system is thus configured to provide fire-control and fire-fighting capabilities to minimize inadvertent consequences to the turbine engine as well as the auxiliary mover.

A method for manufacturing an annular heat exchanger intended to be mounted on the radially inner or outer face of an annular shell of a casing of a double-flow turbomachine, the method including: obtaining by extrusion a heat exchanger preform by a die shaped so that the preform includes: first pipes for the circulation of a fluid to be cooled, second pipes arranged on either side of the first pipes in a direction perpendicular to the direction of extrusion; making a hole from the outside in the preform, the hole leading into one of the second pipes of the preform; and introducing into the hole of the second given pipe a member for partially closing off its passage cross-section.

A method for manufacturing an annular heat exchanger intended to be mounted on the radially inner or outer face of an annular shell of a casing of a double-flow turbomachine, the method including: obtaining by extrusion a heat exchanger preform by a die shaped so that the preform includes: first pipes for the circulation of a fluid to be cooled, second pipes arranged on either side of the first pipes in a direction perpendicular to the direction of extrusion; making a hole from the outside in the preform, the hole leading into one of the second pipes of the preform; and introducing into the hole of the second given pipe a member for partially closing off its passage cross-section.

An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid cooling flow prior to an entry of the entire fluid cooling flow into the fan module.

An aircraft comprises a machine body. The machine body encloses a turbofan gas turbine engine and a plurality of ancillary systems. The turbofan gas turbine engine comprises, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, a combustor module, a turbine module, and an exhaust module. The machine body comprises a single fluid inlet aperture, with the fluid inlet aperture being configured to allow a fluid cooling flow to enter the machine body and to pass through the heat exchanger module. The heat exchanger module is configured to transfer a waste heat load from the gas turbine engine and the ancillary systems to the fluid cooling flow prior to an entry of the entire fluid cooling flow into the fan module.