Abstract: A gas-cycle system operable using a Bell-Coleman cycle, the gas-cycle system comprising an expander (23) and a compressor (27) incorporated in a flow path (13). The expander (23) and compressor (27) are integrated in a rotary machine (41), and each comprises a rotor assembly (70) configured to define one or more zones (80) each of which changes continuously in volume during a rotation cycle of the rotor assembly. The expander (23) and compressor (27) are drivingly interconnected whereby rotational drive applied to one is transmitted directly to the other. Each rotor assembly (70) comprises an inner rotor (73) and an outer rotor (75) adapted to rotate about parallel axes at different rotational speeds. The inner rotors (73) are each drivingly connected to a common shaft for rotation therewith. The two outer rotors (75) are coupled together such that rotational drive applied to one is transmitted directly to the other.

Abstract: A method and structure for thermal management for a vehicle is provided. The method includes extracting a flow of compressed fluid from a compressor section of a propulsion system in which the flow of compressed fluid includes a pressure parameter, and generating an output torque via expanding at least a portion of the flow of compressed fluid across a turbine operably connected to a driveshaft. The turbine is positioned downstream of the compressor section and upstream of a cooling system.

Abstract: An air conditioning pack management system for controlling distribution of a predetermined amount of conditioned air from a system comprising two or more air conditioning packs, the pack management system comprising a management unit arranged to proportion the predetermined amount of conditioned air to be provided by one or more of the two or more packs based on the respective operating efficiencies of the packs or other pre-selected metrics.

Abstract: In some examples, a cooling system includes a brake assembly defining a plurality of cooling channels. The brake assembly is configured to be positioned within a wheel cavity of a wheel. The cooling system includes a distributor configured to receive a flow of cooling fluid and supply the cooling fluid to the plurality of cooling channels. One or more cooling channels are configured to receive the cooling fluid and discharge the cooling fluid into the wheel cavity of the wheel. The cooling system may include a fan configured to provide the cooling fluid to the distributor.

Abstract: The invention discloses a new type of integrated cycle to compete with the standard gas-steam combined cycle in terms of full load/part load efficiency besides ramp rate, startup time and other off design performance. The topping cycle is intercooled recuperative gas turbine (ICR GT) with multiple intercoolers. The bottoming compound cycles consists of supercritical refrigerant Rankine cycle (RRC) and vapor compression refrigeration cycle (VCRC). The refrigerant can be chosen from various organic and inorganic working fluids. The topping and bottoming cycles are highly coupled and form a new integrated cycle rising to the challenge of incoming renewable energy era when thermal power plants undergo frequent load change and long-term part load operation. This invention also markedly outperforms single intercooler ICR GT bottomed by single pressure subcritical RRC system in terms of efficiency, ramp rate etc., and could be an incredibly competitive solution for stationary power generation and marine propulsion.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein and a divider arranged within the ram air shell to separate the ram air shell into a first region and a second region. The at least one heat exchanger is arranged within both the first region and the second region. A first medium is configured to flow through the first region and a second, distinct medium is configured to flow through the second region. The environmental control system additionally includes a dehumidification system arranged in fluid communication with the ram air circuit and a compression device arranged in fluid communication with the ram air circuit and the dehumidification system.

Abstract: Disclosed is a stowable airflow diverter for removable attachment to a floor vent of a turbine aircraft. The air diverter comprises vertical ducting extending from a base. A flexible gasket and magnets are attached to the base for engagement with the floor vent. A nozzle attached to the vertical ducting redirects the airflow emanating from the floor vent from horizontal to vertical in order to direct air conditioned air into the cock pit of the aircraft. In an alternate embodiment, the nozzle is rotatable with respect to the vertical axis of the duct. In another alternate embodiment, the nozzle and vertical duct comprise telescoping segments such that the device can be collapsed into the floor vent.

Abstract: A heat exchanger includes a header and an annular core fluidly connected to the header. The annular core includes an inner diameter, an outer diameter, first flow channels arranged in a first set of layers, and second flow channels arranged in a second set of layers and interleaved with the first flow channels. Each of the first flow channels includes a first inlet, a first outlet, and a first axial region extending between the first inlet and the first outlet. Each of the second flow channels includes a second inlet, a second outlet, and a second axial region extending between the second inlet and the second outlet.

Abstract: An airplane is provided. The airplane includes an environmental control system coupled to an engine and an inlet. The engine provides a bleed. The inlet provides a fresh medium. The environmental control system includes a compressing device comprising a compressor and a turbine. The environmental control system also includes a moisture removal circuit that separately removes moisture from each of the first and second mediums prior to combining the first medium and the second medium to form mixed air.

Abstract: An environmental control system (ECS) of an aircraft includes an inlet for a first medium, an outlet for the first medium, an air cycle machine including a compressor, a turbine, and a shaft operably coupling the compressor and the turbine, and a plurality of heat exchangers arranged in fluid communication with the air cycle machine. A first heat exchanger of the plurality of heat exchangers is arranged directly downstream from the turbine and heat is transferred to the first medium within the first heat exchanger. A water extractor is arranged directly downstream from the first heat exchanger and a flow path connects the air cycle machine, the plurality of heat exchangers, and the water extractor with the inlet and the outlet.

Abstract: A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine, wherein the first medium is provided to the compressor and the turbine sequentially and extracting work from a second medium provided to a power turbine operably coupled to the compressor to drive the compressor. In a first mode of operation, the first medium to be provided to a downstream load is output from the turbine, in a second mode of operation, at least a portion of the first medium to be provided to a downstream load bypasses the turbine, and in a third mode of operation, at least a portion of the first medium output from the compressor is provided to the power turbine.

Abstract: A method of determining and controlling a weight flow in an environmental control system includes sensing, using a turbine inlet temperature sensor, a turbine inlet temperature. A turbine inlet pressure is sensed using a turbine inlet pressure sensor. A turbine outlet pressure is sensed using a turbine outlet pressure sensor. A rotational shaft speed of a shaft is sensed using a rotational shaft speed sensor. The sensed turbine inlet temperature, the sensed turbine inlet pressure, the sensed turbine outlet pressure, and the sensed rotational shaft speed are received by a controller. A flow coefficient is determined by the controller using the turbine inlet pressure, the turbine outlet pressure, the shaft speed, and a Turbine Flow Coefficient Map. A weight flow through the turbine is determined by the controller using the flow coefficient, the turbine inlet temperature, a nozzle area, and the turbine inlet pressure.

Abstract: A method of regulating a temperature associated with a heat exchanger assembly of a turbine engine, the method includes, in a single cycle: measuring the temperature of an air stream at the outlet from a heat exchanger; receiving a setpoint temperature for the air stream at the outlet from the heat exchanger; estimating a theoretical temperature for the air stream at the outlet from the heat exchanger as a function of an estimate of the shutter position of a controlled valve bleeding off a cooling air stream for the heat exchanger; determining a correction current from the difference between the measured temperature and the theoretical temperature; and determining a control current for the shutter from the difference between the measured temperature and the setpoint temperature and the correction current determined during the preceding cycle, the shutter position being determined from the control and correction currents determined during the preceding cycle.

Abstract: An environmental control system of a vehicle includes a ram air circuit including a ram air shell having a ram air heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, a first compression device arranged in fluid communication with the dehumidification system, the first compression device including a first compressor, and a second compression device arranged in fluid communication with the ram air circuit. The second compression device includes a second compressor. A first medium is provided to the first compressor and to the second compressor in series.

Abstract: A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine. The first medium is provided to the compressor and the turbine sequentially. A second medium is provided to the environmental control system. In a first mode of operation, the first medium and the second medium mix within the turbine and in a second mode of operation the second medium bypasses the turbine such that the first medium and the second medium mix downstream from the turbine.

Abstract: A closed-loop Brayton cycle system utilizes supercritical carbon dioxide as the working fluid for the system to achieve higher efficiencies than can be achieved with traditional open-loop gas turbine engines. A bleed channel is used to direct a flow of cooling fluid to cool the turbine blades during operation of the system, preventing damage to the turbine blades during operation of the system. The bleed channel includes a bleed inlet fluidly coupled between a first recuperator and a second recuperator and a bleed outlet fluidly coupled to the turbine blades. The bleed channel is configured to direct the flow of cooling fluid to the turbine blades at a desired temperature and pressure.

Abstract: An air cycle machine includes a compressor in fluid communication with a load cooling heat exchanger, a first valve and a first turbine connecting the compressor to the load cooling heat exchanger, and a second valve and a second turbine. The second valve and the second turbine connect the compressor to the load cooling heat exchanger and connected in parallel with the first valve and the first turbine between the compressor and the load cooling heat exchanger. Air cycle machine systems and methods of controlling air flow through air cycle machines are also described.

Abstract: A system for cooling aircraft components includes a compressor configured to receive air bled from a gas turbine engine and compress the received air. Additionally, the system includes a heat exchanger configured to receive the compressed air from the compressor and cool the compressed air; a turbine configured to receive the cooled air from the heat exchanger, with the cooled air expanding as the cooled air flows through the turbine. Furthermore, the system includes a defroster configured to receive the expanded air from the turbine, with the defroster further configured to capture frozen particulate matter from the expanded air. As such, at least a portion of the cooled air from the heat exchanger is routed to the defroster to melt the captured frozen particulate matter.

Abstract: An air cycle machine includes a housing, a duct, a bypass valve, and a plug. The duct extends from and connects two different portions of the housing and includes a first port and a second port. The first port is attached to the first inlet of the housing. The second duct is attached to the second inlet of the housing. The bypass valve is inserted into one of the first port and second port of the duct. The plug is inserted into the other of the first port and second port that the bypass valve is not inserted into. Both the first port and the second port are capable of receiving and forming a sealing interface with both of the bypass valve and the plug.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

Abstract: An aircraft environmental control system comprising a bleed air or compressed ambient air input and a RAM air input, heat exchanger means for receiving bleed air from the bleed air input and RAM air from the RAM air input and using RAM air to cool the bleed air, and means for providing the cooled bleed air to an interior of the aircraft; the system further comprising means for feeding back exhaust air emitted from the interior of the aircraft to combine with the RAM air to further cool the bleed air or compressed ambient air.

Abstract: Cryogenic refrigeration device comprising a working circuit intended to cool a working fluid circulating in the said circuit, the working circuit comprising, arranged in series in a loop: a compression portion, a cooling portion, a portion with valve(s), an expansion portion and a reheating portion, in order to subject the working fluid to a recuperative working cycle comprising compression, then cooling, then expansion and then reheating to prepare for a new cycle, wherein the compression portion comprises at least one compressor having a linear piston driven by a linear motor, the expansion proportion comprises at least one expander with a linear piston, the portion with valve(s) comprises at least one regulating valve linearly actuated by a linear motor and controlled in order to supply or extract the working fluid from the at least one expansion piston.

Abstract: An environmental control system includes an airflow source, and an air cycle machine in flow communication with the airflow source, and through which an airflow from the airflow source is directed. The air cycle machine includes a compressor and a turbine. A liquid load heat exchanger is located in flow communication with the turbine such that airflow downstream of the turbine exchanges thermal energy with a liquid flow at the liquid load heat exchanger to cool the liquid flow. A liquid load reheater is located upstream of the turbine and upstream of the liquid load heat exchanger. The liquid load reheater is configured such that a thermal energy exchange between the airflow prior to the airflow entering the turbine and the liquid flow prior to the liquid flow entering the liquid load heat exchanger occurs at the liquid load reheater.

Abstract: The present disclosure discloses a compressor, an air conditioning system and a vehicle. The compressor comprises a compression cavity, and further comprises a flash cavity capable of flashing a liquid refrigerant, and a communicating passage that communicates a flash cavity gas outlet of the flash cavity and an enthalpy increasing gas supply port of the compression cavity; the flash cavity is provided with an inlet and a liquid outlet, the inlet of the flash cavity is configured to be communicated with an outlet of a condenser, and the liquid outlet of the flash cavity is configured to be communicated with an inlet of an evaporator. The air conditioning system comprises the compressor, the evaporator, the condenser, a flasher, and various pipelines for connecting the entire system.

Abstract: A two-wheel air cycle machine includes a tie rod defining an axis, a turbine mounted on the tie rod, and a compressor mounted on the tie rod and having a rotor portion and a disk portion with at least one aperture. The air cycle machine further includes a compressor inlet fluidly connecting the compressor and an inlet air source, at least one thrust bearing disposed between the turbine and the compressor, and a compressor end shaft coaxial with the tie rod and abutting the compressor disk portion. The compressor end shaft includes a radially-extending seal disk portion and an axially-extending shaft portion having at least one shaft aperture. The at least one disk aperture and the at least one shaft aperture are fluidly connected by a compressor disk cavity defined by a gap between the tie rod and the compressor disk portion. The at least one disk aperture, the compressor disk cavity, and the at least one shaft aperture at least partially define a compressor inlet flow path.

Abstract: The present invention relates in general to the field of fluid reaction surfaces, and more specifically, to a fluid-foil impeller and method of use. One aspect of the fluid-foil impeller utilizes a plurality of fluid-foil discs that may be of uniform and/or variable thickness and configured to rotate rapidly in series to produce propulsion. Each fluid-foil disc comprises a leading edge, a trailing edge, a chord and a fixed pitch. The fluid-foil impeller may further include a standard or Venturi shroud that is designed to encompass the plurality of fluid-foil discs. The plurality of fluid-foil discs are configured to act in cooperation with the shroud to reduce losses incurred from turbulence and the conversion of mechanical work to fluid movement. Fluid may be acted upon by the plurality of fluid-foil discs and/or shroud, singly or in an array.

Abstract: An environmental control system of an aircraft includes a compressing device having a compressor configured to receive a flow of a first medium and a turbine configured to receive the flow of the first medium from the compressor and a flow of a second medium. The turbine is arranged downstream from the compressor along a flow path of the first medium. A dehumidification system is arranged in fluid communication with the turbine and a bypass valve is operable configured to divert the flow of the first medium around the turbine and at least a portion of the dehumidification system.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a heat exchanger positioned therein and a dehumidification system arranged in fluid communication with the ram air circuit. A plurality of expansion devices is arranged in fluid communication with the ram air circuit and the dehumidification system. At least one of the expansion devices is a simple cycle expansion device.

Abstract: The present disclosure relates to a turbomachine assembly, which includes a shaft, a radial gas expander supported on the shaft between a first bearing and a second bearing, and a compressor supported on the shaft in overhung position adjacent to one or the other of the first and second bearings. The compressor includes a plurality of movable inlet nozzles and the radial gas expander includes a plurality of movable guide vanes.

Abstract: A gas turbine engine includes a main compressor section having a downstream most location, and a cooling air tap at a location upstream of the downstream most location. A main turbine section, each of the main turbine section and the main compressor section are mounted within a housing, and each have rotatable components. A first heat exchanger is connected to the cooling air tap. The first heat exchanger is also connected to receive fuel to be supplied to a combustor in the gas turbine engine, and such that the fuel may cool the cooling air in the first heat exchanger. A boost compressor is connected to receive air downstream of the first heat exchanger and connected to deliver the cooling air to at least one of the rotatable components in at least one of the compressor and turbine sections.

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

Abstract: A blower includes an impeller housing, an impeller rotatably secured to the housing and an electric motor. The motor has a motor housing with a central portion and a radially extending portion extending from the central portion, a venturi chamber adjacent the motor housing and opposed to the impeller housing, a stator secured to the central portion of the motor housing, a rotor rotatably secured to the central portion of the housing, and at least one heat generating electrical component secured to the radially extending portion of the motor housing. The impeller housing has a first air pressure therein and the motor housing has a second air pressure therein different that the first air pressure. The venturi housing and the motor housing define a passageway therebetween whereby the difference in air pressure generates air flow within the motor housing to cool the at least one heat generating electrical component.

Abstract: Disclosed is a cooling circuit for cooling a heat load in an aircraft system, having: a compressor; a turbine connected to the compressor by a shaft, the turbine configured to drive the compressor via the shaft when RAM air pressure into a turbine inlet is above a first threshold; and a motor connected to the shaft configured to drive the compressor when RAM air pressure at the turbine inlet is below the first threshold to cause the compressor to draw air into the turbine inlet, through the turbine, a heat exchanger in fluid communication with the heat load, the compressor, and out of a compressor outlet.

Abstract: An aircraft is provided. The aircraft includes a pressurized volume and an air conditioning system. The air conditioning system operates in a first mode or a second mode. The first mode includes when a first medium and a second medium and are mixed and provided to the pressurized volume. The second mode includes when only the first medium is provided to the pressurized volume.

Abstract: Methods and devices for cooling systems (700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling system can include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a VGT cooling system turbine (240) downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) for bypassing the turbine can also be included.

Abstract: Methods and devices for cooling systems (100, 700) are provided that are in fluid communication with bleed air from a jet engine compressor. The cooling systems include: a first precooler (210) receiving bleed air from the jet engine compressor; a heat exchanger (730) downstream from the first precooler (210); a cooling system compressor (220) downstream from the first precooler (210), wherein the heat exchanger (730) and the cooling system compressor (220) are in separate flow paths from the first precooler (210); a cooling system precooler (230) downstream from the cooling system compressor (220); a cooling system turbine (240) with variable guide vanes—VGT—and downstream from the cooling system precooler (230); and a discharge conduit (245) downstream from the cooling system turbine (240) and the heat exchanger (730). A bypass line (290) can also be included that bypasses the cooling system turbine (240).

Abstract: A ram air system for an aircraft having an engine and a fuselage with an outer mold line. The ram air system includes an engine air pathway having an opening in the outer mold line defining an engine inlet. The engine air pathway is configured to supply operating air for combustion in the engine. An auxiliary air pathway includes a first intake disposed inside the outer mold line in the engine inlet and a second intake disposed externally to the engine air pathway. The auxiliary air pathway is configured to draw in cooling air to cool ancillary aircraft components from at least one of the first intake and the second intake based on the airspeed of the aircraft.

Abstract: An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component.

Abstract: 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.

Abstract: A flow conditioning device for conditioning a wet gas stream having a plurality of liquid droplets and a gas flow is presented. The flow conditioning device includes a first segment including a first convergent section configured to break the plurality of liquid droplets from a first size to a second size. Further, the flow conditioning device includes a second segment coupled to the first segment and including a second convergent section configured to break the plurality of liquid droplets from the second size to a third size.

Abstract: A fan and compressor housing for an air cycle machine includes a fan inlet disposed around a center axis of the housing and having a fan inlet mounting flange, a compressor outlet having a compressor outlet mounting flange, and a compressor inlet having a compressor inlet mounting flange. The fan inlet mounting flange has a pinhole disposed thereon configured to receive a pin from a fan inlet diffuser housing and a fan inlet counterbore configured to receive a mating component from the fan inlet diffuser housing. The compressor outlet mounting flange has a compressor outlet counterbore configured to receive a first mating component from a condenser/reheater. The compressor inlet mounting flange has a compressor inlet counterbore configured to receive a second mating component from the condenser/reheater.

Abstract: A gas turbine engine includes a main compressor section. A booster compressor includes an inlet and an outlet. The inlet receives airflow from the main compressor section and the outlet provides airflow to a pneumatic system. A recirculation passage is between the inlet and the outlet. A flow splitter valve controls airflow between the outlet and the inlet through the recirculation passage for controlling airflow to the pneumatic system based on airflow output from the booster compressor. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.

Abstract: Provided is a solvent separation method and a solvent separation apparatus that make it possible to efficiently retrieve the thermal energy possessed by an exhaust atmosphere released in a solvent-removal step to suppress reductions in a temperature of the exhaust atmosphere. In the solvent separation method and the solvent separation apparatus, a vaporized solvent is removed from a gas while heat exchange between the gas within a condensation part and the gas within a dust-collection part is conducted by using a heat exchange part that is placed between the condensation part that introduces the gas into a first direction and the dust-collection part that introduce the gas into a second direction opposite to the first direction the gas discharged from a downstream side of the condensation part.

Abstract: A fan and compressor housing for an air cycle machine includes a fan inlet disposed around a center axis of the housing and having a fan inlet mounting flange, a compressor outlet having a compressor outlet mounting flange, and a compressor inlet having a compressor inlet mounting flange. The fan inlet mounting flange has a pinhole disposed thereon configured to receive a pin from a fan inlet diffuser housing and a fan inlet counterbore configured to receive a mating component from the fan inlet diffuser housing. The compressor outlet mounting flange has a compressor outlet counterbore configured to receive a first mating component from a condenser/reheater. The compressor inlet mounting flange has a compressor inlet counterbore configured to receive a second mating component from the condenser/reheater.

Abstract: The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a supercharger (7), and transferring non-propulsive energy from the auxiliary power unit (6) to the aircraft. The invention also concerns a system (5) for generating auxiliary power in an aircraft and an aircraft implementing such a method.

Abstract: An aircraft duct structure includes a first duct through which exhaust air from a front-side equipment compartment flows, and a second duct through which exhaust air from a rear-side equipment compartment flows. The first duct has a terminal end part where the exhaust air inside the second duct flows into the exhaust air inside the first duct at a substantially right angle, and a flow straightening plate located inside the terminal end part. The terminal end part has a jet opening which faces, across a clearance, an air pressure regulating port where an air pressure regulating valve is disposed. The inside of the terminal end part is divided by the flow straightening plate into an upper region and a lower region. The exhaust air inside the first duct and the exhaust air inside the second duct merge together in the upper region.

Abstract: A generator arrangement includes a generator and a pneumatic turbine. The pneumatic turbine is operably connected to the generator. A gas turbine engine compressor section is in fluid communication with the pneumatic turbine through a bleed air conduit to provide pressurized air to the pneumatic turbine for applying mechanical rotation to the generator.

Abstract: A fan housing for an air cycle machine includes a fan exit flow passage and a ring disposed around a center axis of the fan housing and disposed around the fan exit flow passage. The ring includes a first end disposed axially opposite a second end and a guide surface facing radially inward relative the center axis and formed between the first end and the second end. The ring also includes a shelf disposed radially inward from the guide surface. The shelf includes a stop surface extending radially and disposed axially between the second end and the guide surface. The shelf also includes a shelf surface facing radially outward relative the center axis and extending axially between the first end and the stop surface.

Abstract: A heat exchange system includes a core of cross flow passages having a reheater, and a condenser that is downstream of and directly interfaces the reheater. A first water extractor is downstream of the condenser, wherein the first water extractor turns a first fluid from the first pass of the condenser back towards the condenser and produces a second fluid that flows into the second pass of the condenser. A second water extractor is downstream the condenser, wherein the second water extractor turns a third fluid from the second pass of the condenser towards the reheater; and produces a fourth fluid that flows into the reheater.

Abstract: A system and method captures and processes flare gas so that the gas is usable as compressed natural gas (“CNG”). The flare gas is pressurized by a combination of a booster compressor and a CNG compressor. While interstage and between the booster compressor and the CNG compressor, the gas is treated to remove moisture and to separate out higher molecular weight hydrocarbons. The moisture is removed by contacting the interstage gas with a hygroscopic agent within a dehydration unit. The moisture free hydrocarbon fluid is expanded, and/or externally cooled and directed to a knock out drum. Higher molecular weight hydrocarbons are separated from the fluid in the knock out drum. Gas from the knock out drum is compressed in the CNG compressor.