Custom Ceramic Choked Flow Venturis
Reaction Systems, Inc. has developed a new line of?robust high temperature ceramic choked flow venturis for use in oxidizing and reducing atmospheres at temperatures up to 2700?F (1480?C). These venturis are constructed from a low thermal expansion and highly thermal shock tolerant material that can withstand rapid changes in gas temperature while providing accurate metering of high pressure, high temperature gas flows.
Ceramic sonic metering nozzles are also resistant to oxidation, allowing them to be used in situations where a venturi constructed from stainless steel would suffer throat erosion and increases in throat roughness. Throat inserts of other refractory materials can also be accommodated. Due to the low thermal conductance of the ceramic insert, the outer metal body can be constructed of materials that are compatible with the rest of your system. Standard body materials include 17-4PH and 316L stainless steels, nickel-based superalloys, and low carbon steel. A wide variety of external body threads and fittings are also available including Swagelok, VCR, aircraft AN, and SAE straight threads with O-ring seals, and can be customized to fit your requirements.
Other Reaction Systems Projects
An Advanced Endothermic Fuel System for Hypersonic Propulsion
The development of weapons that can travel at hypersonic speeds is becoming a high priority to the US Air Force. A key technology needed for the continued development of these propulsion systems is the ability to cool the combustor by flowing fuel through channels machined in the walls.
Catalytic N2O Decomposition for Piloted Scramjet Ignition
Aircraft and missiles capable of rapid global strike and reconnaissance must fly at hypersonic speeds to achieve their performance goals. Future air-breathing hypersonic aircraft and missiles are expected to be powered by supersonic combustion ramjet (scramjet) engines.
Chemical Kinetic Pathway Effects in Turbulent Reacting Flows
The Army is very interested in accurate simulations of combustion in devices such as rockets and gas turbines, Otto and Diesel cycle IC engines, scramjet engines, rotating detonation engines, etc.
A Novel Thermal Method for Rapid Coke Measurement in Liquid Fueled Rocket Engines
The surfaces of rocket engines are exposed to high pressure combustion products at temperatures up to 6000?F. Regenerative cooling can cause coke to form on the heat exchanger surfaces.
Membrane for CO2 and H2O Control in Space Suits
The development of new, robust, lightweight life support systems is currently a crucial need for NASA in order to continue making advances in space exploration, particularly in the development of Lunar outposts.
A Supported Liquid Membrane System for Steady State CO2 Control in a Spacecraft Cabin
Reducing the allowable concentration of carbon dioxide (CO2) in spacecraft is a critical need for NASA.
Roadrunner Kinetics Custom Reduced Mechanisms for CFD
Scramjet engines, which likely will provide the next generation propulsion capability, operate at extremely high temperatures and air velocities, conditions that are very difficult to reach in a laboratory.