Abstract: An integrated environmental control system for providing conditioned air supply in an aircraft is provided. The system includes an integrated bootstrap air cycle subsystem and a regenerative air cycle subsystem, which are in heat exchange relationship. The bootstrap and the regenerative air cycle systems are also in heat exchange relationship with a liquid cooling cycle subsystem. In the bootstrap cycle, bleed air is compressed and expanded. After absorbing heat from the liquid cycle, the expanded air from the bootstrap cycle is received and expanded by a first turbine of the regenerative air cycle. Before it is received by a compressor of the regenerative cycle, the air flow, which is expanded and cooled by the first turbine, absorbs heat from the liquid cycle, supplies air to the cabin and absorbs heat from the bootstrap cycle. After the compression, the air flow is received by a second turbine of the regenerative cycle and expanded.

Abstract: A microturbine engine core with gas bearings used to support a rotating group is provided, including methods of optimizing the engine core's performance. It is emphasized that this abstract is provided to comply with the rules requiring an abstract that will allow a searcher or other reader to ascertain quickly the subject matter of the technical disclosure. The abstract is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.

Abstract: A gas adsorbent is made by dissolving a polymer in one or more first solvents to form a polymer solution; mixing an inorganic adsorbent with the polymer solution to form a precursor; molding the precursor; and leaching the first solvents from the precursor with a second solvent.

Abstract: A counter pressure glove system, that can be used in low pressure environments such as outer space, is provided. The system includes a pressure member, pressure inducing glove and a support member. The pressure member is disposed on the dorsal metacarpals and the palmar knuckles of a hand of a wearer. The pressure member applies a predetermined amount of pressure against the dorsal metacarpals and the palmar knuckles. The pressure inducing glove is donned on the hand. The pressure inducing glove applies a second predetermined pressure against the pressure member as well as against the exposed regions of the hand that are not covered by the pressure member. The support member is disposed on the pressure inducing glove and inhibits lateral and vertical displacement of the pressure member.

Abstract: A mechanical counter pressure glove system, that can be used in low-pressure environments such as outer space, is provided. The system includes a low friction base glove defining an internal volume for receiving a hand of a wearer. A pressure inducing glove is donned on the low friction glove so as to apply a mechanical pressure on the hand. The low friction material of the base glove facilitates donning of the pressure inducing glove.

Abstract: An active filter is coupled to a dc line of a converter such as a dc-dc converter. The active filter traps a harmonic frequency component of chopped current on the dc line. A passive EMI filter may also be coupled to the dc line to remove higher harmonic frequency components of the chopped current on the dc line.

Abstract: A two spool environmental control system includes a low pressure spool subsystem comprising a low pressure turbine and a condenser downstream of the low pressure turbine. A high pressure spool subsystem is in air flow communication with the low pressure spool subsystem and includes the condenser, a first water extractor in air communication with the condenser, a high pressure turbine downstream of the condenser, a second water extractor in air flow communication with the condenser, and a reheater downstream of the high pressure turbine.

Abstract: In an aircraft, tap water is filtered, vaporized and injected into a trim line of an environmental control system. Filtering is performed by a reverse osmosis filter. Hot, humidified air leaving the trim line is supplied to a cabin of the aircraft.

Abstract: A method of sealing at least a first seal surface to a second seal surface comprises the steps of placing a flexible ring member between the first and second seal surfaces and juxtaposing the first and second seal surfaces. The flexible ring member is compressed between the first and second seal surfaces. Thereafter, the flexible ring member is expanded into at least one of a first recessed area in the first seal surface and a second recessed area in the second seal surface, with at least one of the first and second recessed areas having a plurality of spaced apart pressure points that contact the ring member. This method of sealing assures that when the O-ring (flexible ring) permanently sets over time, it takes the shape that makes the seal effective for a long time under high temperature, high pressure.

Abstract: A hybrid deicing system for deicing ice or snow covered surfaces comprises a source of pressurized air and a source of pressurized deicing fluid. A nozzle assembly receives the pressurized air and the pressurized deicing fluid at a forward position, a middle position or a rearward position of the nozzle assembly. The nozzle assembly discharges the pressurized deicing fluid and pressurized air as a first independent stream within a second independent stream.

Abstract: An improved foil thrust bearing includes a pair of members arranged for relative rotation with respect to one another. One of the pair of members is adapted to rotatably support the other. A thrust bearing disk is operatively disposed between the pair of relatively rotatable members. The thrust bearing disk has a plurality of diverging surface ramps. The surface ramps can comprise an inner ramp and an outer ramp. The thrust bearing disk can also comprise a plurality of radial slots. A plurality of separately formed, converging surface compliant foils are disposed on the thrust bearing disk and between the ramps. An underspring element is operatively disposed between the thrust bearing disk and one of the rotatable members, with the underspring element having a plurality of alternating upper and lower ridges.

Abstract: A hydraulic power assembly is comprised of a hydraulic pump being attached to and powered by a ram air turbine. A strut is rotatably attached to an aircraft by having one end mounted on a trunion, and the hydraulic power assembly affixed to the other, distal end. Flexible hoses fluidly communicate the pump with a hydraulic interface located inside of the aircraft. The hydraulic interface fluidly communicates with the aircraft's hydraulic system. The hydraulic power assembly and the strut are normally stored within the fuselage of the aircraft and are deployable into an adjacent airstream in an emergency.

Abstract: A water extractor of an environmental control system includes a swirl section and a water collector downstream the swirl section. The water collector includes an upstream sump having an inlet positioned to capture the bulk of water droplets leaving the swirl section. The water collector further includes a downstream sump for capturing water droplets that were not captured by the first sump.

Abstract: A fuel cell bipolar plate including a fuel side having a series of fuel channels defining respective fuel paths and an oxidant side having a series of oxidant channels defining respective oxidant paths. At least some of the fuel channels are offset from adjacent oxidant channels in a direction transverse to the fuel and oxidant paths. A fuel manifold is connected to the fuel channels, while an oxidant manifold is connected to the oxidant channels. One of the two manifolds is located between the biplate and the other manifold, where a connector extends from whichever manifold is outermost to the associated fuel or oxidant channels.

Abstract: A heat exchanger includes a core assembly, a plurality of manifolds for the core assembly, and a webbing wrapped around a portion of the core assembly. The webbing secures at least one of the manifolds to the core assembly.

Abstract: An integrated bleed air and engine starting system for an engine utilizes an innovative flow multiplier air turbine starter to provide bleed air supply to an ECS as well as starting an engine. The technique reduces bleed air consumption by mixing fan stage air and high stage air for ECS fresh air usage. It also can eliminate or reduce the size of the precooler heat exchanger. The system includes an air turbine starter subsystem and an air flow subsystem. The air turbine starter subsystem includes a compressor, a turbine, and a common shaft fixed between the compressor and turbine. Also provided is a gear coupled to a gearbox which links the engine with a shaft, as well as a variable nozzle valve intermediate the turbine and engine. The air flow subsystem comprises a diverter valve downstream of the turbine, an isolation valve intermediate the turbine and an auxiliary power unit, and a check valve downstream of the compressor and turbine. A fan is in air flow communication with the compressor and engine.

Abstract: An axial fan includes a hub within a housing. A cavity is formed between the hub and housing. A plurality of blades is on the hub, with an air separator ring disposed operatively adjacent to the blades. The ring supports a plurality of vanes that are longitudinally aligned with the blades. A diverter is disposed operatively adjacent to the vanes so that the diverter directs a skip-stall air flow about the ring.

Abstract: A floating frame controller determines a current Park vector, selects a reference frame for the current Park vector, and adjusts the reference frame until a quadrature component of a current Park vector in the adjusted reference frame is equal to a predetermined value, whereby a synchronous reference is established. The synchronous frame is used to control a power converter. The floating frame controller can drive a synchronous machine without the use of rotor position sensors.

Abstract: A solid oxide fuel cell stack includes a plurality of solid oxide fuel cells juxtaposed to one another, with at least two of the cells having a substantially flat configuration; and each of the two cells having an anode layer, an electrolyte layer, and a cathode layer. The fuel stack also includes at least one interconnect disposed among the plurality of cells, with the interconnect being capable of providing an electrical connection between the cells, and the interconnect comprising a plurality of first extensions on a first surface of the interconnect and a plurality of second depressions on a second surface of the interconnect. The first extensions and second depressions are integrally formed with one another to provide a plurality of oxidant passageways and fuel passageways.

Abstract: This invention overcomes the disadvantage of the prior systems and produces a high velocity specially formed and constituted pressure aerodynamic stream system for efficiently and effectively removing ice from an aircraft. The specially formed stream system includes a stream within a stream, wherein a deicing fluid such a glycol is entrained within and encased by a surrounding jacket of entraining fluid such as air. This deicing is now known as coaxial stream/stream within a stream deicing. The special nozzle allows the stream to maintain fluid separation over its flight path so that aircraft contact is made by to be known as coaxial stream/stream within a stream deicing. The coaxial stream/stream within a stream deicing is further enhanced by pressurizing the stream to deliver the stream as a high pressure, high velocity stream to improve the aerodynamic sweeping action of the airstream.