Abstract: Provided are systems and methods for a hydrogen-fueled supersonic turbojet engine system comprising: an inlet; combustor; fuel storage; high-pressure turbine and low-pressure turbine wherein the initial pressure of the high-pressure turbine is greater than the initial-pressure of the low-pressure turbine; a compressor operably attached to the low-pressure turbine; and a plurality of stream lines configured to circulate cryogenic liquid molecular hydrogen fuel through a plurality of heat exchangers positioned in the airframe and a precooler in the engine, wherein the plurality of fuel stream lines connects the fuel storage to the low-pressure and high-pressure turbines and the combustor.

Abstract: Provided is a wind tunnel system capable of supporting high velocity applications and methods for constructing the same. Some aspects include a sub-surface storage space for storing large volumes of air for one or more of extended testing times, large test sections, and supersonic airspeeds. Some aspects include test sections sized for use with full scale sections of aircraft or major aircraft parts. Some embodiments store air at a constant volume and some sore at a constant pressure. Some embodiments include the use of cavities that appear as a result of industrial or geologic processes, including salt domes and abscesses remaining after carbon extraction.

Abstract: Provided are methods and systems for a modular multi-stage aerospace system having a first-stage vehicle that lifts and accelerates and is capable of achieving velocities of Mach 2.5, the first-stage vehicle powered by at least one turbine engine, and capable of autonomous and remote control; and a second-stage atmospheric flight vehicle capable of velocities of Mach 5.0, the second-stage atmospheric flight vehicle powered by at least one hydrogen-fueled turboramjet engine, and capable of carrying an internal payload; wherein the first-stage vehicle is adapted to support the second-stage atmospheric flight vehicle, as the first-stage vehicle reaches velocities sufficient to launch the second-stage atmospheric flight vehicle, and the second-stage atmospheric flight vehicle is capable of travel 12,000 miles.

Abstract: Apparatuses and methods related to an engine for converting heat into mechanical output using a working fluid in a closed circulating system are disclosed. In some embodiments, the engine includes a pump to pressurize the working fluid, a regenerative heat exchanger to transfer heat from a first portion of the working fluid to a second portion, a heating device to heat the working fluid, and a scroll expander to expand the working fluid and generate the mechanical output. Other embodiments may be described and claimed.

Abstract: Apparatuses and methods related to an engine for converting heat into mechanical output using a working fluid in a closed circulating system are disclosed. In some embodiments, the engine includes a pump to pressurize the working fluid, a regenerative heat exchanger to transfer heat from a first portion of the working fluid to a second portion, a heating device to heat the working fluid, and a scroll expander to expand the working fluid and generate the mechanical output.

Abstract: Apparatuses and methods related to an engine for converting heat into mechanical output using a working fluid in a closed circulating system are disclosed. In some embodiments, the engine includes a pump to pressurize the working fluid, a regenerative heat exchanger to transfer heat from a first portion of the working fluid to a second portion, a heating device to heat the working fluid, and first and second scroll expanders to expand the working fluid and generate the mechanical output. Other embodiments may be described and claimed.

Abstract: The present invention relates to the field of combustion engines and more specifically to a rotary positive displacement combustor engine. The device employs a scroll compressor and a scroll expander with an orbital shaft displaced between the compressor and expander supplying a means and link for compressing fluids within the scroll compressor and disposing the fluid within the scroll expander within which an ignition source is placed at strategic points within a pair of first isolated zones of the orbiting scroll expander generating a highly efficient process for capturing mechanical and thermal energy from combustion.

Abstract: An engine comprising a closed circulating system containing a working fluid, the system comprising; means to raise the pressure of said working fluid from a low cycle pressure to a high cycle pressure by use of at least one variable displacement pump; means to add heat to said fluid substantially at said high cycle pressure to raise it to its high cycle temperature substantially above its critical temperature; means to expand said fluid by use of at least one scroll expander to do useful work; means to cool said fluid substantially at said low cycle pressure to a low cycle temperature by a regenerator and a condenser; and means to power said at least one variable displacement pump from said at least one scroll expander. With the working fluid in the closed circulating system able to have temperatures and entropies associated with a Rankine, Brayton, or supercritical cycle.

Abstract: The present invention relates to the field of combustion engines and more specifically to a rotary positive displacement combustor engine. The device employs a scroll compressor and a scroll expander with an orbital shaft displaced between the compressor and expander supplying a means and link for compressing fluids within the scroll compressor and disposing the fluid within the scroll expander within which an ignition source is placed at strategic points within a pair of first isolated zones of the orbiting scroll expander generating a highly efficient process for capturing mechanical and thermal energy from combustion.