Abstract: A method for producing a plate-fin heat exchanger core includes the steps of stacking a bottom end sheet, multiple alternately stacked individual hot and cold layers, and a top end sheet, each of the individual hot and cold layers including a fin element forming multiple parallel open-ended fluid channels, a parting sheet separating the various individual layers, and two closure bars positioned on opposite sides of the fin element, parallel to the open-ended channels and extending a length of the open-ended channels, brazing the bottom end sheet, the various layers, and the top end sheet in a brazing furnace; and removing material from each of the exterior faces by precision machining, thereby removing material from each closure bar outer face. The precision machining can include electrical discharge machining, laser cutting, band sawing, drilling, boring, hogging, acid etching, and ion milling, in any combination.

Abstract: A method of making a brazing foil includes flattening the brazing foil to a minimum thickness. Calculating a quantity of material to remove from the brazing foil. Cutting a plurality of perforations into the brazing foil to remove the quantity of material.

Abstract: A method for producing a plate-fin heat exchanger core includes the steps of stacking a bottom end sheet, multiple alternately stacked individual hot and cold layers, and a top end sheet, each of the individual hot and cold layers including a fin element forming multiple parallel open-ended fluid channels, a parting sheet separating the various individual layers, and two closure bars positioned on opposite sides of the fin element, parallel to the open-ended channels and extending a length of the open-ended channels, brazing the bottom end sheet, the various layers, and the top end sheet in a brazing furnace; and removing material from each of the exterior faces by precision machining, thereby removing material from each closure bar outer face. The precision machining can include electrical discharge machining, laser cutting, band sawing, drilling, boring, hogging, acid etching, and ion milling, in any combination.

Abstract: A method for producing a plate-fin heat exchanger core includes the steps of stacking a bottom end sheet, multiple alternately stacked individual hot and cold layers, and a top end sheet, each of the individual hot and cold layers including a fin element forming multiple parallel open-ended fluid channels, a parting sheet separating the various individual layers, and two closure bars positioned on opposite sides of the fin element, parallel to the open-ended channels and extending a length of the open-ended channels, brazing the bottom end sheet, the various layers, and the top end sheet in a brazing furnace; and removing material from each of the exterior faces by precision machining, thereby removing material from each closure bar outer face. The precision machining can include electrical discharge machining, laser cutting, band sawing, drilling, boring, hogging, acid etching, and ion milling, in any combination.

Abstract: Engine inlets are disclosed that include an intake opening for the ingress of incoming air and acoustic filtration means for generating an acoustic wave that separates or clarifies material from the incoming air. The acoustic filtration means can include at least one ultrasonic transducer with a piezoelectric material configured to be driven to create an acoustic wave, such as a multi-dimensional acoustic wave or angled acoustic wave. Physical filtration means, such as an inertial or vortical separator, can be provided. Other engine inlets are also disclosed in which the acoustic filtration means are located within the physical filtration means. Further disclosed are methods for separating material from air employing acoustic separation means and physical filtration means.

Abstract: The present invention relates to an electrically driven aircraft cabin and ventilation and environmental control system. The system includes at least one inlet for capturing ram air, an electrically driven compressor for pressurizing the ram air, and a thermal conditioning subsystem for thermally conditioning the pressurized ram air. The system further includes a subsystem for removing undesirable moisture from the thermally conditioned ram air.

Abstract: The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

Abstract: The present invention relates to an electrically driven aircraft cabin and ventilation and environmental control system. The system includes at least one inlet for capturing ram air, an electrically driven compressor for pressurizing the ram air, and a thermal conditioning subsystem for thermally conditioning the pressurized ram air. The system further includes a subsystem for removing undesirable moisture from the thermally conditioned ram air.

Abstract: The present invention relates to an electrically driven aircraft cabin and ventilation and environmental control system. The system includes at least one inlet for capturing ram air, an electrically driven compressor for pressurizing the ram air, and a thermal conditioning subsystem for thermally conditioning the pressurized ram air. The system further includes a subsystem for removing undesirable moisture from the thermally conditioned ram air.

Abstract: The present invention relates to an electrically driven aircraft cabin and ventilation and environmental control system. The system includes at least one inlet for capturing ram air, an electrically driven compressor for pressurizing the ram air, and a thermal conditioning subsystem for thermally conditioning the pressurized ram air. The system further includes a subsystem for removing undesirable moisture from the thermally conditioned ram air.

Abstract: The present invention relates to an electrical power and cooling system for use in an aircraft having at least one engine. The electrical power and cooling system comprises a single shaft, a power turbine mounted on the shaft for receiving fresh pressurized air from the at least one engine, a cooling turbine mounted on the shaft and receiving the fresh pressurized air from the at least one engine, a generator mounted on the shaft, and a fan mounted on the shaft for creating a flow of cooling air. The system further has a condenser for removing moisture from the air exiting the cooling turbine and a mixing chamber for mixing the cooled dry air with recirculated cabin air. The electrical power and cooling system delivers conditioned air to a cabin and/or a flight deck onboard the aircraft and electrical power to the aircraft's electrical systems.

Abstract: An integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.

Abstract: The present invention relates to an integrated aircraft system which comprises an aircraft frame, a nacelle cowl mounted to the aircraft frame, a primary gas turbine engine mounted within the nacelle cowl, a secondary power system incorporated within the nacelle cowl and being driven by a flow of air created by or through the engine, and an electrical power and cooling unit for supplying electrical power and cabin cooling air. The electrical power and cooling unit is pneumatically driven by engine bleed air.