Ramgen Power Systems, Inc.

Other

Dresser-Rand Company

Next Gen Compression LLC

Ramgen Power Systrms, Inc.

Advanced Wind Turbines, Inc.

Creative Motion Control, Inc

Lawlor, Shawn

Cornelius, Charles C.

Lawlor, Shawn P.

Shawn P Lawlor

Charles C Cornelius

Mark Alfred Novaresi

William Byron Roberts, Ii

Robert C Steele

Donald Kendrick

Robert E Breidenthal

Kenneth H Hicks, Ii

A method of continuously compressing gas in a supersonic compressor. A gas compressor system is provided. The gas compressor may include a two rotor low pressure stage and a two rotor high pressure stage. The two rotor low pressure stage and the two rotor high pressure stage each have a first rotor with subsonic blades and a second rotor with supersonic compression passageways. The supersonic passageways each include a helically adjustable centerbody and boundary layer bleed passageways. The compressor continuously compresses inlet gas to provide a first compressed gas stream. That stream is cooled, then fed to the low pressure inlet of the high pressure stage, and compressed to provide a second compressed gas stream. For part load operation, the rotating speeds are higher than the nominal design rotating speed for full mass flow operation.

Method for efficient part load compressor operation

A counter-rotating supersonic compressor. A first subsonic rotor includes a plurality of unshrouded impulse rotor blades operating at sub-sonic conditions. A second, supersonic rotor includes a fixed second rotor portion and an adjustable second rotor portion. The fixed second rotor portion includes a plurality of supersonic passageways having converging-diverging sidewalls, and internal boundary layer bleed passageways. The adjustable second rotor portion includes a plurality of centerbodies which are disposed in the supersonic passageways. Helical movement (circumferential and axial) movement of the adjustable second rotor portion with respect to the fixed second rotor portion enables upstream and downstream movement of the centerbodies in the supersonic passageways. This movement facilitates ease of supersonic startup, and automatic adjustment for changes in operation conditions, such as pressure, temperature, or mass flow rate of a working fluid such as carbon dioxide.

Variable geometry supersonic compressor

A hand tool with a mechanical linear drive mechanism coupled to a work implement. The drive mechanism includes a roller screw with a torque tube connected to a roller screw's nut body. The roller screw includes a fixed outer race, a rotating set of rollers axially aligned inside the outer race, a cylindrical nut body located inside the set of rollers, a plurality of inner rollers axially aligned and inside the nut body, a threaded shaft axially aligned and inside the inner rollers, and a torque tube axially aligned inside the inner rollers. The torque tube is connected to a multiple speed gearbox which includes a primary motor coupled to a carrier gear with three planet gears. Disposed around the planet gears is an outer ring gear. Coupled to the outer ring gear is a secondary motor which when activated causes the ring gear to rotate in the opposite direction of the planet gears.

Tool with linear drive mechanism, dual speed gearbox and elastomeric control system

A hand tool with a mechanical linear drive mechanism coupled to a linear activated working implement. The drive mechanism includes a geared planetary roller screw that includes a torque tube connected to a roller screw's nut body. The planetary roller screw includes a fixed outer race, a rotating set of grooved rollers axially aligned inside the outer race, a cylindrical nut body located inside the set of grooved roller, a plurality of inner rollers axially aligned and inside the nut body, a threaded shaft axially aligned and inside the inner rollers, and a torque tube axially aligned inside the inner rollers. The torque tube is connected at one end to a gear box which is coupled to an electric motor. When the electric motor is activated, the torque tube is rotated which causes a threaded shaft in the tool to move axially. A working implement is coupled to the distal end of the threaded shaft.

Tool with linear drive mechanism

A supersonic compressor including a rotor to 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 vortex generating structures for controlling boundary layer, and 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.

Supersonic compressor

A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.

Gas turbine engine

A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.

Gas turbine engine with supersonic compressor

A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas collector, to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is effectively eliminated.

Method and apparatus for starting supersonic compressors

A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated.

A gas turbine engine. The engine is based on the use of a gas turbine driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. The supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdynamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by use of a lean pre-mix system, a pre-swirl compressor, and a bypass stream to bleed a portion of the gas after passing through the pre-swirl compressor to the combustion gas outlet. Use of a stationary low NOx combustor provides excellent emissions results.

Gas turbine power plant with supersonic shock compression ramps

A gas compressor based on the use of a driven rotor having an axially oriented compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which forms a supersonic shockwave axially, between adjacent strakes. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the gas compression ramp on a strake, the shock capture lip on the adjacent strake, and captures the resultant pressure within the stationary external housing while providing a diffuser downstream of the compression ramp.

A gas compressor based on the use of a driven rotor having a compression ramp traveling at a local supersonic inlet velocity (based on the combination of inlet gas velocity and tangential speed of the ramp) which compresses inlet gas against a stationary sidewall. In using this method to compress inlet gas, the supersonic compressor efficiently achieves high compression ratios while utilizing a compact, stabilized gasdynamic flow path. Operated at supersonic speeds, the inlet stabilizes an oblique/normal shock system in the gasdyanamic flow path formed between the rim of the rotor, the strakes, and a stationary external housing. Part load efficiency is enhanced by the use of a pre-swirl compressor, and using a bypass stream to bleed a portion of the intermediate pressure gas after passing through the pre-swirl compressor back to the inlet of the pre-swirl compressor. Inlet guide vanes to the compression ramp enhance overall efficiency.

Supersonic gas compressor

A higher efficiency roller screw system that includes a nut body designed to engage a threaded shaft. The nut body includes a center bore with closed, partial helical grooves formed therein. Disposed inside the center bore is a shaft with open helical threads formed thereon. A plurality of rollers with non-helical grooves formed thereon are also disposed inside the nut body's center bore and longitudinally aligned with the shaft. The grooves on each roller are designed to engage the grooves on the nut body and the threads on the shaft. The nut body includes a cross-over region where the trajectory of the internal grooves extend radially outward and axially. When the rollers' grooves contact the grooves in the cross-over region, the rollers are forced outward to maintain contact with the grooves on the nut body and are deflected axially. When they move outward, they disengage from the helical threads on the shaft. As the nut body continues to rotate, the grooves on the rollers maintain contact with the grooves on the nut body and re-engage the helical threads on the shaft.

Roller screw system

A trapped vortex combustor for gas turbine engines. An annular combustor housing is provided having a plurality of inlet centerbodies disposed along a helical axis. The inlet centerbodies include a leading edge structure, opposing sidewalls, a pressurizable cavity, and a rear wall. Inlet centerbodies cooperate with adjacent structure and an aft bluff body to define a trapped vortex cavity combustion chamber for mixing an inlet fluid and burning fuel to form hot combustion gases. Mixing is enhanced by utilizing struts adjacent to the rear wall to create eddies in the fluid flow, and by injecting fuel and/or air in opposition to swirl created by the bulk fluid flow. Hot combustion gases are utilized in a turbine for extraction of kinetic energy, or in heat exchange equipment for recovery of thermal energy. High combustion efficiencies and less than 10 ppm emissions of oxides of nitrogen and of carbon monoxide are achieved.

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Bellevue, WA, United States of America

Shawn P Lawlor