Abstract: Sustor2 provides deep cooling of a gas flow, practically total condensation of a vapor, and fast and effective removal of the condensed liquid with a significantly reduced pressure losses compared with the prior art. Sustor2 performs the said operations by developing a strong swirling flow starting from its entrance, followed by spiral flow convergence in the inlet disc-like part, and then in a converging-diverging nozzle, by centrifugal removal of droplets, and removal of the liquid film through slits, then by spiral flow divergence and leaving the vortex chamber through tangential outlet. A gas enters from a pipeline (see the arrow in the A-A cross-section shown in FIG. 7) connected to Sustor2 by a flange and the inlet transition pipe ITP in FIG. 7, spirally converged in the disc-like part, marked by A-A in FIG. 6, enters the converging-diverging nozzle (FIG. 6). The flow is high-speed and swirling even at the near-entrance region of the vortex chamber.

Abstract: Sustor2 provides deep cooling of a gas flow, practically total condensation of a vapor, and fast and effective removal of the condensed liquid with a significantly reduced pressure losses compared with the prior art. Sustor2 performs the said operations by developing a strong swirling flow starting from its entrance, followed by spiral flow convergence in the inlet disc-like part, and then in a converging-diverging nozzle, by centrifugal removal of droplets, and removal of the liquid film through slits, then by spiral flow divergence and leaving the vortex chamber through tangential outlet. A gas enters from a pipeline (see the arrow in the A-A cross-section shown in FIG. 7) connected to Sustor2 by a flange and the inlet transition pipe ITP in FIG. 7, spirally converged in the disc-like part, marked by A-A in FIG. 6, enters the converging-diverging nozzle (FIG. 6). The flow is high-speed and swirling even at the near-entrance region of the vortex chamber.

Abstract: A recuperator for use in transferring heat from gas turbine exhaust gases to compressed air inlet gases before combustion. The recuperator utilizes a plurality of planar or curved layers filled with metal wire mesh and bounded by thin metal sheets to form a heat exchanger having high effectiveness, low weight, and low pressure drop. The use of wire is a unique feature of the recuperator that makes it significantly low-cost compared with the prior art. Accordingly, the recuperator presented herein may be incorporated into a micro- or mini-turbine system for electric power generation or for developing thrust in airborne vehicles, aircraft, and helicopters.

Abstract: A combustion apparatus is described having a generally elongated combustion container with a longitudinal axis, a proximal end, an exhaust end spaced axially forward from the proximal end, a proximal end wall, an exhaust end wall, and an all-around sidewall extending between the end walls and about the longitudinal axis. The end walls and sidewall substantially define a combustion chamber. The apparatus also includes a combustion chamber exhaust positioned on the exhaust end, a fuel-air delivery system positioned to direct fuel into the combustion chamber, and an air inlet located generally tangentially on the sidewall to direct air flow generally tangentially into the chamber and induce swirl about the longitudinal axis.

Abstract: A rotary drill bit (10) is provided for drilling a hole in a subsurface formation. The bit body (12) includes a plurality of axially extending ribs (16a, b, c and d) and a flow channel between adjacent ribs. A plurality of cutting elements are fixedly mounting on a respective one of the plurality of ribs. A plurality of flow nozzles (20a, b, c and d) direct fluid to a respective one of the plurality of cutting elements to clean and cool the cutting elements.

Abstract: A combustor apparatus and method for the combustion of viscous fuels are provided. The combustor apparatus can include a precombustion chamber particularly adapted to heat and at least partially combust a heavy primary fuel, and a main combustion chamber adapted to combust the primary fuel uniformly through the main combustion chamber (in flameless mode). The precombustion chamber can include at least one air injection inlet port positioned to induce a first stage vortex in the main body portion of the housing of the precombustion chamber. Further, the precombustion chamber can be interfaced with a main combustion chamber to induce a second stage vortex within the main combustion chamber. The main combustion chamber can have an extended axial length in order to accommodate heavier fuels that require additional time to sufficiently combust (oxidize) within the combustion chamber.

Abstract: A rotary drill bit (10) is provided for drilling a hole in a subsurface formation. The bit body (12) includes a plurality of axially extending ribs (16a, b, c and d) and a flow channel between adjacent ribs. A plurality of cutting elements (19) are fixedly mounting on a respective one of the plurality of ribs. A plurality of flow nozzles (20a, b, c and d) direct fluid to a respective one of the plurality of cutting elements to clean and cool the cutting elements.

Abstract: A system, apparatus and method for the combustion of metals and other fuels are provided. The system can include a fuel combustion apparatus including a combustor having a combustion chamber for burning ground particles from a fuel charge, and a fuel supply apparatus for supplying the ground particles. The fuel supply system can include a fuel charge holder assembly to house and store the fuel charge, a grinder assembly including a grinder configured to pulverize the fuel charge to produce a combustible fuel, and a fuel charge linear feed assembly including a piston in contact with the fuel charge to selectively bias the fuel charge into the grinder to control the consumption rate. Exhaust from the combustion chamber can be used in the incineration of radioactive, chemical and mixed hazardous materials, and in the propulsion of a vehicle in both an air or water environment.

Abstract: A system, apparatus and method for the combustion of metals and other fuels are provided. The system can include: a fuel combustion apparatus including a combustor having a combustion chamber for burning ground particles from a fuel charge, and a fuel supply apparatus for supplying the ground particles of fuel from the fuel charge to the combustor. The fuel supply system can include a fuel charge holder assembly to house and store the fuel charge, a grinder assembly including a grinder housed within the charge holder assembly and configured to pulverize the fuel charge to produce a combustible fuel to be consumed in the combustion chamber, and a fuel charge linear feed assembly including a piston in contact with the fuel charge within the charge holder assembly to selectively bias the fuel charge into the grinder to thereby a control consumption rate of the fuel charge.

Abstract: A rotary drill bit (10) is provided for drilling a hole in a subsurface formation. The bit body (12) includes a plurality of axially extending ribs (16a, b, c and d) and a flow channel between adjacent ribs. A plurality of cutting elements are fixedly mounting on a respective one of the plurality of ribs. A plurality of flow nozzles (20a, b, c and d) direct fluid to a respective one of the plurality of cutting elements to clean and cool the cutting elements.

Abstract: A system, apparatus and method for the combustion of metals and other fuels are provided. The system can include: a fuel combustion apparatus including a combustor having a combustion chamber for burning ground particles from a fuel charge, and a fuel supply apparatus for supplying the ground particles of fuel from the fuel charge to the combustor. The fuel supply system can include a fuel charge holder assembly to house and store the fuel charge, a grinder assembly including a grinder housed within the charge holder assembly and configured to pulverize the fuel charge to produce a combustible fuel to be consumed in the combustion chamber, and a fuel charge linear feed assembly including a piston in contact with the fuel charge within the charge holder assembly to selectively bias the fuel charge into the grinder to thereby a control consumption rate of the fuel charge.

Abstract: This invention relates to the injection of compressible gaseous fuel directly into the combustion chamber of a reciprocating piston-type internal combustion engine. In particular, the invention provides apparatus and methods for low-pressure, high-speed direct injection of compressed natural gas into a combustion chamber of an engine. Using the present invention, relatively low intake pressures of about 50 to about 150 PSIG yield high-speed (sonic and supersonic) gas flow through the diverging nozzle portion for injection into the combustion chamber. Preferably, the gas reaches supersonic velocity, approaching Mach 1.5 to 2.5.

Abstract: This invention relates to the injection of compressible gaseous fuel directly into the combustion chamber of a reciprocating piston-type internal combustion engine. In particular, the invention provides apparatus and methods for low-pressure, high-speed direct injection of compressed natural gas into a combustion chamber of an engine. Using the present invention, relatively low intake pressures of about 50 to about 150 PSIG yield high-speed (sonic and supersonic) gas flow through the diverging nozzle portion for injection into the combustion chamber. Preferably, the gas reaches supersonic velocity, approaching Mach 1.5 to 2.5.

Abstract: A nozzle for delivering fuel to an engine is disclosed which is profiled with adjoining converging and diverging sections to accelerate the flow of fuel to a supersonic rate.

Abstract: A nozzle for delivering fuel to an engine is disclosed which is profiled with adjoining converging and diverging sections to accelerate the flow of fuel to a supersonic rate.

Abstract: A nozzle for delivering fuel to an engine is disclosed which is profiled with adjoining converging and diverging sections to accelerate the flow of fuel to a supersonic rate.