Abstract: A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Abstract: One embodiment of the present disclosure is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Abstract: A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Abstract: One embodiment of the present disclosure is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A unique airborne electrical power and thermal management system and a unique aircraft having a unique airborne electrical power and thermal management system are provided. The electrical power and thermal management system includes a turbine, which may power loads, for example but not limited to, a generator and a refrigerant compressor. The turbine may be in fluid communication with a gas turbine engine bleed air source to extract power from bleed air for powering the loads. A combustor may be fluidly disposed between the bleed air source and the turbine. The turbine may be part of a gas turbine engine distinct from a propulsion gas turbine engine. In one aspect, at least a portion of the electrical power and thermal management system may be disposed within an aircraft external pod. The pod may be configured to appear similar to a conventional external fuel tank pod employed by the aircraft.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique external pod for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and external pods for aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A system is disclosed one form of which is an aircraft that includes a pod capable of housing a work providing device. The pod can also include a thermal conditioning system and a power generation device that can be powered from the work providing device. The pod can provide thermal conditioning services and power services to a payload aboard the aircraft. In one non-limiting form the payload is a directed energy member that can be cooled using the thermal conditioning system and powered using the power generation device.

Abstract: One embodiment of the present invention is a unique airborne electrical power and thermal management system. Another embodiment is a unique aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and electrical power and thermal management systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: One embodiment of the present invention is a unique aircraft. Another embodiment is a unique external pod for an aircraft. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for aircraft and external pods for aircraft. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

Abstract: A combustion liner for a gas turbine combustion apparatus or the like has a head wall and a side wall extending downstream to an outlet for combustion products. A reaction zone is contained within the upstream end of the side wall and a dilution zone downstream. A barrier ring extends inwardly from the side wall to provide a constricted path between the zones. Combustion air is admitted from a cluster of nozzles in the head wall and a ring of nozzles extending forwardly from the side wall. Each nozzle in the head wall is axially aligned with one of the nozzles in the side wall so that air jets entering into the combustion zone through each such pair of nozzles impinge to create a high degree of turbulence. Fuel is jetted against a spatter plate in each nozzle in the head wall so that the fuel is atomized and entrained by the air flowing through the head wall air nozzle.