Vast Power Portfolio, LLC

Other

Morgan Aircraft, LLC

Vast Holdings, LLC

Vast Power Systems, Inc.

David Leroy Hagen

Gary Ginter

Bill Goheen

Janet Rankin

Allan McGuire

L Allan McGuire

Ronald L Klaus

Ian Wylie

Alberto Traverso

Brian Herman Morgan

Aristide Massardo

Paul Andrew Campbell

Allan Mcguire

Bradley Lee Eckwielen

Gary D Ginter

L Allan Mcguire

Allen McGuire

Timothy Naylor

Doug Charles Fetters

Aristride Massardo

Albert Traverso

Clean combustion and equilibration equipment and methods are provided to progressively deliver, combust and equilibrate mixture of fuel, oxidant and aqueous diluent in a plurality of combustion regions and in one or more equilibration regions to further progress oxidation of products of incomplete combustion, in a manner that sustains combustion while controlling temperatures and residence times sufficiently to reduce CO and NOx emissions to below 25 ppmvd, and preferably to below 3 ppmvd at 15% O.

Low emissions combustion apparatus and method

A system to calcine crushed carbonate, discharge alkaline oxide, and deliver an enhancing fluid having CO2, comprising: a pressurized insulated calciner having descendingly, a crushed alkaline carbonate feeder, a calciner fluid outlet manifold, a heated sideflow calciner fluid intake manifold, a preheated sideflow calciner fluid outtake manifold, a fluid inlet manifold to recirculate calciner fluid from the outlet manifold, and an alkaline oxide discharger; a pressurizer to repressurize sideflow calciner fluid, connected to intake and outtake manifolds; pressurizers to recirculate calciner outlet fluid to the inlet manifold, pressurize the calciner and deliver enhancing fluid comprising CO2; delivery and combustion systems to form a combustion fluid; a recuperating or regenerating refractory heat exchanger to heat sideflow calciner fluid with combustion fluid connected to the sideflow pressurizer, and fluid outtake and intake manifolds; and a controller operable to control combustion, heat exchange, calciner fluid formation and delivery, carbonate feed and oxide discharge.

CO2 producing calciner

A method of forming a bendable slotted liner with multiple circumferentially overlapping non-axial keystone slots comprising: transversely profiling a rod to form a profiled rod, having bending members outwardly profiled wider than intermediate and inward widths, interspersed with bases profiled to bondably mate with axially adjacent bases on a neighboring winding; forming the profiled rod into alternating port and starboard bending members and base pairs, by one of, bonding transverse spacers to the rod, transversely corrugating the rod, and forming the rod with one of transverse outdents and indents; winding the profiled rod to the outer diameter; and bonding axially paired bases together; wherein configuring the non-axial slot circumferential length greater than the circumferential base length on adjacent rod windings, forming non-axial keystone slots between bending members providing axial strain relief, with outer slot widths within a prescribed slot range and axial strain relief capacity greater than 0.1%.

Bendable strain relief fluid filter liner, method and apparatus

A method of forming a slotted liner, having a wall comprising a plurality of non-axial bending members axially separated by non-axial slots and circumferentially interspersed with bases, for providing strain relief, the method comprising: forming the bending members and the non-axial slots by one of: cutting non-axial slots, and winding a rod; configuring the circumferential lengths of the plurality of non-axial slots and bases relative to the liner circumference; wherein positioning a first base axially adjacent to a non-axial slot; configuring the non-axial slot circumferential length longer than the circumferential length of the first base; and positioning a second base axially adjacent to a first base; providing connections between the pair of bases or leaving uncut the wall between the base pair; configuring the plurality of non-axial slots and adjacent base pairs.

Method and apparatus for strain relief in thermal liners for fluid transfer

The part load method controls delivery of diluent fluid, fuel fluid, and oxidant fluid in thermodynamic cycles using diluent, to increase the Turbine Inlet Temperature (TIT) and thermal efficiency in part load operation above that obtained by relevant art part load operation of Brayton cycles, fogged Brayton cycles, or cycles operating with some steam delivery, or with maximum steam delivery. The part load method may control the TIT at the design level by controlling one or both of liquid and/or gaseous fluid water over a range from full load to less than 45% load. This extends operation to lower operating loads while providing higher efficiencies and lower operating costs using water, steam and/or CO2 as diluents, than in simple cycle operation.

Partial load combustion cycles

Thermodynamic cycles with diluent that produce mechanical power, electrical power, and/or fluid streams for heating and/or cooling are described. Systems contain a combustion system producing an energetic fluid by combusting fuel with oxidant. Thermal diluent is preferably used in the cycle to improve performance, including one or more of power, efficiency, economics, emissions, dynamic and off-peak load performance, temperature regulation, and/or cooling heated components. Cycles include a heat recovery system and preferably recover and recycle thermal diluent from expanded energetic fluid to improve cycle thermodynamic efficiency and reduce energy conversion costs. Cycles preferably include controls for temperatures, pressures, and flow rates within a combined heat and power (CHP) system, and controls for power, thermal output, efficiency, and/or emissions.

Thermodynamic cycles with thermal diluent

This wet compression invention with a vaporizable fluid mist demonstrates major performance improvements over the relevant art in achieving a high degree of saturation, providing sensible cooling, strongly reducing the temperature increase due to compression work, reducing excess diluent air flow for downstream combustion, reducing compression noise, and increasing the achievable compressor pressure ratio. These improvements are obtained by one or more of: high mist or overspray from a) progressive axial injection of vaporizable fluid along the streamwise compression flow path, and b) transverse vaporizable fluid delivery from stators, rotors, perforated tubes, and/or duct walls, matching the gaseous fluid flow distribution across the compressor stream; c) reducing the compressor cross-sectional flow area of downstream compressor stages relative to up-stream stages, and d) increasing the rate of downstream vaporizable fluid injection relative to the rate of upstream injection, as a function of each compressor stage pressure ratio.

Wet compression apparatus and method

Combustion gases with relatively high levels of carbon dioxide (CO), steam, and/or hot water, may be used to improve recovery of heavy hydrocarbons from geologic formations and/or from surface mined materials. These gases reduce the viscosity and/or increase hydrocarbon extraction rates through improvements in thermal efficiency and/or higher rates of heat delivery for a given combustor an capital investment. Such high water/COcontent combustion gases can be formed by adding water to combustion gases formed by burning fuel. The pressure to inject the combustion gases and extract heavy hydrocarbons may be provided by diverting high pressure expanded gases from wet combustion in a gas turbine, or by reducing the pressure drop across a turbine and using the expanded hot gases for extraction.

Hot fluid recovery of heavy oil with steam and carbon dioxide

Clean combustion and equilibration equipment and methods are provided to progressively deliver, combust and equilibrate mixtures of fuel, oxidant and aqueous diluent in a plurality of combustion regions and in one or more equilibration regions to further progress oxidation of products of incomplete combustion, in a manner that sustains combustion while controlling temperatures and residence times sufficiently to reduce CO and NOx emissions to below 25 ppmvd, and preferably to below 3 ppmvd at 15% O.

Control surfaces in an aircraft attitude control configuration provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes thrusters mounted to an aircraft, a first control surface kinematically coupled to the aircraft downstream of a first thruster to enable a first vector force to be generated by a portion of thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft of a second thruster. The control surfaces are displaced symmetrically a longitudinal axis of the aircraft. The control surfaces are independently and differentially movable with respect to each other to enable generation of a second vector force by a portion of thrusted air from the second thruster on the second control surface.

Aircraft attitude control configuration

A thermally diluted exothermic reactor system is comprised of numerous orifices distributed within a combustor by distributed perforated contactor tubes or ducts. The perforated contactors deliver and mix diluent fluid and one or more reactant fluids with an oxidant fluid. Numerous micro-jets about the perforated tubes deliver, mix and control the composition of reactant fluid, oxidant fluid and diluent fluid. The reactor controls one or more of composition profiles, composition ratio profiles and temperature profiles in one or more of the axial direction and one or two transverse directions, reduces temperature gradients and improves power, efficiency and emissions.

Trifluid reactor

A remediation system for decontaminating a polluted site that delivers a remediation fluid to the polluted site and receives a contaminated effluent from the polluted site. The system includes a reactor that receives the contaminated effluent and generates an exit fluid stream and a first flow control mechanism coupled to the outlet of the reactor that releases a controlled portion of the exit fluid from the system, and delivers the remaining portion of the exit fluid as the remediation fluid, or delivers the remaining portion to a second flow control mechanism for combination with a controlled quantity of the second reactant to form the remediation fluid.

Thermogenerator to remediate contaminated sites

A thermodynamic system that produces mechanical, electrical power, and/or fluid streams for heating or cooling. The cycle contains a combustion system that produces an energetic fluid by combustion of a fuel with an oxidant. A thermal diluent may be used in the cycle to improve performance, including but not limited to power, efficiency, economics, emissions, dynamic and off-peak load performance, and/or turbine inlet temperature (TIT) regulation and cooling heated components. The cycle preferably includes a heat recovery system and a condenser or other means to recover and recycle heat and the thermal diluent from the energetic fluid to improve the cycle thermodynamic efficiency and reduce energy conversion costs. The cycle may also include controls for temperatures, pressures, and flow rates throughout the cycle, and controls power output, efficiency, and energetic fluid composition.

Thermodynamic cycles using thermal diluent

An aircraft attitude control configuration enables control surfaces to provide attitude control for an aircraft at hover or low air speed conditions. The aircraft attitude control configuration includes a plurality of thrusters mounted to an aircraft for thrusting air, a first control surface kinematically coupled to the aircraft at a position downstream of a first thruster to enable a first vector force to be generated by a portion of the thrusted air from the first thruster on the first control surface, and a second control surface kinematically coupled to the aircraft at a position downstream of a second thruster, the first and the second control surfaces being displaced symmetrically on opposite sides of a longitudinal axis of the aircraft, the second control surface being configured to be independently and differentially movable with respect to the first control surface to enable a second vector force to be generated by a portion of the thrusted air from the second thruster on the second control surface.

Growing community of inventors

Goshen, IN, United States of America

David Leroy Hagen