Abstract: Chemical reactor (10) and method for cracking are disclosed. A process fluid is accelerated with axial impulse impellers (40A, 40B) to a velocity greater than Mach 1 and, in turn, generating a shock wave (90) in the process fluid by decelerating it in a static diffuser (70) having diverging diffuser passages (72). Temperature increase of the process fluid downstream of the shockwave cracks or splits molecules, such as hydrocarbons entrained in the process fluid, in a single pass, through a unidirectional flow path (F), within a single stage, without recirculating the process fluid for another pass through the same stage. In some embodiments, a system involving at least two turbomachine chemical reactors (110) may provide multiple successive stages of one or more axial impulse impellers (40A, 40B), paired with a diverging passage, static diffuser (70).

Abstract: A turbomachine type chemical reactor for processing a process fluid is presented. The turbomachine type chemical reactor includes at least one impeller section and a stationary diffuser section arranged downstream. The impeller section accelerates the process fluid to a supersonic flow. A shock wave is generated in the stationary diffuser section that instantaneously increases static temperature of the process fluid downstream the shock wave for processing the process fluid. which allows thermally cracking a chemical compound, such as hydrocarbon, in the process fluid. Static pressure of the process fluid is simultaneously increased across the shock wave. The turbomachine type chemical reactor significantly reduces residence time of the process fluid in the chemical reactor and improves efficiency of the chemical reactor.

Abstract: A turbomachine type chemical reactor for processing a process fluid is presented. The turbomachine type chemical reactor includes at least one impeller section and a stationary diffuser section arranged downstream. The impeller section accelerates the process fluid to a supersonic flow. A shock wave is generated in the stationary diffuser section that instantaneously increases static temperature of the process fluid downstream the shock wave for processing the process fluid. which allows thermally cracking a chemical compound, such as hydrocarbon, in the process fluid. Static pressure of the process fluid is simultaneously increased across the shock wave. The turbomachine type chemical reactor significantly reduces residence time of the process fluid in the chemical reactor and improves efficiency of the chemical reactor.

Abstract: A turbomachine type chemical reactor for processing a process fluid is presented. The turbomachine type chemical reactor includes at least one impeller section and a stationary diffuser section arranged downstream. The impeller section accelerates the process fluid to a supersonic flow. A shock wave is generated in the stationary diffuser section that instantaneously increases static temperature of the process fluid downstream the shock wave for processing the process fluid. Static pressure of the process fluid is simultaneously increased across the shock wave. The turbomachine type chemical reactor significantly reduces residence time of the process fluid in the chemical reactor and improves efficiency of the chemical reactor.

Abstract: Chemical reactor (10) and method for cracking are disclosed. A process fluid is accelerated with axial impulse impellers (40A, 40B) to a velocity greater than Mach 1 and, in turn, generating a shock wave (90) in the process fluid by decelerating it in a static diffuser (70) having diverging diffuser passages (72). Temperature increase of the process fluid downstream of the shockwave cracks or splits molecules, such as hydrocarbons entrained in the process fluid, in a single pass, through a unidirectional flow path (F), within a single stage, without recirculating the process fluid for another pass through the same stage. In some embodiments, a system involving at least two turbomachine chemical reactors (110) may provide multiple successive stages of one or more axial impulse impellers (40A, 40B), paired with a diverging passage, static diffuser (70).

Abstract: A turbomachine type chemical reactor for processing a process fluid is presented. The turbomachine type chemical reactor includes at least one impeller section and a stationary diffuser section arranged downstream. The impeller section accelerates the process fluid to a supersonic flow. A shock wave is generated in the stationary diffuser section that instantaneously increases static temperature of the process fluid downstream the shock wave for processing the process fluid. Static pressure of the process fluid is simultaneously increased across the shock wave. The turbomachine type chemical reactor significantly reduces residence time of the process fluid in the chemical reactor and improves efficiency of the chemical reactor.

Abstract: Chemical reactors (10) and methods crack hydrocarbons in process fluids by accelerating the process fluid to a velocity greater than Mach 1 with an axial impulse impeller (40) and generating a shock wave (90) in the process fluid by decelerating it in a static diffuser (70) having diverging diffuser passages (72). Temperature increase of the process fluid downstream of the shockwave cracks the entrained hydrocarbons in a single pass, through a unidirectional flow path (F), within a single stage, without recirculating the process fluid for another pass through the same stage. In some embodiments, the turbomachine chemical reactor (110) has multiple successive stages of one or more axial impulse impellers (40A, 40B), paired with a diverging passage, static diffuser (70). Successive stages crack additional hydrocarbons by successively raising temperature of the flowing process fluid.

Abstract: Chemical reactors (10) and methods crack hydrocarbons in process fluids by accelerating the process fluid to a velocity greater than Mach 1 with an axial impulse impeller (40) and generating a shock wave (90) in the process fluid by decelerating it in a static diffuser (70) having diverging diffuser passages (72). Temperature increase of the process fluid downstream of the shockwave cracks the entrained hydrocarbons in a single pass, through a unidirectional flow path (F), within a single stage, without recirculating the process fluid for another pass through the same stage. In some embodiments, the turbomachine chemical reactor (110) has multiple successive stages of one or more axial impulse impellers (40A, 40B), paired with a diverging passage, static diffuser (70). Successive stages crack additional hydrocarbons by successively raising temperature of the flowing process fluid.

Abstract: A gas turbine assembly and method for operating the gas turbine assembly are provided. The method for operating the gas turbine assembly may include compressing a process fluid containing inlet air through a compressor to produce compressed inlet air, combining fuel from a main fuel source with the process fluid, and preheating the process fluid containing the inlet air and the fuel in a warmer disposed downstream from the compressor. The method may also include heating an oxidizer by flowing the preheated process fluid from the warmer to the oxidizer, and oxidizing the process fluid containing the compressed inlet air and the fuel in the oxidizer to produce an oxidation product. The method may further include expanding the oxidation product in a turbine to generate rotational energy, and preventing the process fluid from flowing upstream to the compressor with a check valve.

Abstract: An expander may include a longitudinal axis, an inner casing split horizontally along the longitudinal axis, an outer casing split horizontally along the longitudinal axis and spaced radially outward from and encompassing the inner casing. Each axial end of the outer casing may form a respective gland seal housing, and the outer casing and inner casing may define an exhaust chamber therebetween. A plurality of expansion stages including a rotor shaft may be disposed within the inner casing and configured to expand the working fluid received from a working fluid source. A plurality of seals may be disposed within each of the gland seal housings and mounted circumferentially about the rotor shaft. The plurality of seals may include an annular seal, a plurality of dynamically self-adjustable seals disposed outboard of the annular seal, and at least one dry gas seal disposed outboard of the plurality of dynamically self-adjustable seals.

Abstract: A combustor includes a housing and a liner that define an inlet configured to receive an inlet fluid. An inlet splitter is disposed in the inlet which splits the inlet into a first annulus and a second annulus. A fuel supply system selectively injects fuel into the first annulus and the second annulus, and a centerbody that includes a plurality of struts radially extending from a central hub receives the inlet fluid mixed with fuel, thereby creating fluid swirl.

Abstract: A gas turbine assembly and method for operating the gas turbine assembly are provided. The method for operating the gas turbine assembly may include compressing a process fluid containing inlet air through a compressor to produce compressed inlet air, combining fuel from a main fuel source with the process fluid, and preheating the process fluid containing the inlet air and the fuel in a warmer disposed downstream from the compressor. The method may also include heating an oxidizer by flowing the preheated process fluid from the warmer to the oxidizer, and oxidizing the process fluid containing the compressed inlet air and the fuel in the oxidizer to produce an oxidation product. The method may further include expanding the oxidation product in a turbine to generate rotational energy, and preventing the process fluid from flowing upstream to the compressor with a check valve.

Abstract: A supersonic compressor including an inlet configured to receive and flow therethrough a process fluid. The supersonic compressor may further include a rotary shaft and a centrifugal impeller coupled therewith. The centrifugal impeller may be configured to impart energy to the process fluid received and to discharge the process fluid therefrom in at least a partially radial direction at an exit absolute Mach number of about one or greater. The supersonic compressor may further include a static diffuser circumferentially disposed about the centrifugal impeller and configured to receive the process fluid therefrom and convert the energy imparted. The supersonic compressor may further include a collector fluidly coupled to and configured to collect the process fluid exiting the diffuser, such that the supersonic compressor is configured to provide a compression ratio of at least about 8:1.

Abstract: A supersonic compressor including a rotor having reaction blades that deliver a gas at supersonic conditions to a diffuser. The diffuser includes a plurality of aerodynamic ducts that have converging and diverging portions, for deceleration of gas to subsonic conditions and then for expansion of subsonic gas, to change kinetic energy of the gas to static pressure. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when the aerodynamic ducts are designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of in excess of two to one, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct. In an embodiment, the number of leading edges are minimized, and may be less than half, or far less than half, compared to the number of blades in the accompanying rotor.

Abstract: A catalyst includes a carrier of essentially hafnia, up to an equal part zirconia, and optionally additional stabilizers, upon the surface of which is deposited an active metal suitable to promote the reaction of propellants to be used in gas generators and thrusters.