Abstract: Systems and methods for generating electrical power combine pressurized fluidized bed combustors (PFBC) and molten carbonate fuel cells (MCFC) to provide a low cost solution for electricity generation with CO2 capture. A solid fuel is introduced fuel into a pressurized fluidized bed combustor to produce steam, a first quantity of electrical power, and a flue gas including CO2. Air, natural gas, at least a portion of the steam and at least a portion of the flue gas including CO2 are introduced to a molten carbonate fuel cell to produce a second quantity of electrical power and an output stream comprising primarily CO2. The pressurized fluidized bed combustor can desirably be air-fired and the solid fuel introduced there into can desirably be in a finely pulverized form.

Abstract: A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements.

Abstract: A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements.

Abstract: The present invention is directed toward a two-stage hypersonic vehicle, comprising a first-stage vehicle and a second stage vehicle. The first-stage vehicle includes a combined-cycle engine and a swirl generator for propelling the first-stage vehicle and the second-stage vehicle to a threshold velocity, which in one embodiment is about Mach 6. In one embodiment, the first-stage combined-cycle engine integrates a swirl generator into a gas turbine engine, providing a highly compact afterburner and a ramjet engine within the gas turbine engine. One benefit of the integrated swirl generator is the ability to significantly reduce overall first-stage gas turbine and afterburner-ramjet size and weight, while retaining high performance. The second-stage vehicle is detachably secured to the first-stage vehicle and includes a hypersonic engine.

Abstract: A dual mode scramjet engine has an isolator that serves to minimize combustor influence on inlet operation, a combustor for operation in both ramjet and scramjet mode, and a centerbody positioned within the isolator. The centerbody has an end at an entrance to the combustor.