ROBERT EDWARD BREIDENTHAL, JR
Pilots at 56 St, Seattle, WA

5340306, Aug 23, 1994

Dec 4, 1992

7/985316

Jakob Keller - Redmond WA
Robert E. Breidenthal - Seattle WA

Asea Brown Boveri Ltd. - Baden

F23C 500

431351

A device for mixing two gaseous components, particularly in the context of a burner in which it is desired to mix the two gaseous components prior to combustion. The device includes a tangential inlet flow duct which opens into an inlet flow gap. A first gaseous component flows in through this inlet flow gap, and a second gaseous component flows through inlet flow nozzles provided in the region of the inlet flow gap. The arrangement achieves particularly intimate mixing, such that an improved burner is provided. Ramps are disposed in the region of the inlet flow duct, with the ramps including an end having a separation edge in the inlet flow gap. The inlet flow nozzles are arranged in the region around the separation edge such that mixing is promoted by longitudinal vortices occurring in the region.

2014006, Mar 6, 2014

Jul 24, 2013

13/950249

ROBERT E. BREIDENTHAL - SEATTLE WA, US
IGOR A. KRICHTAFOVITCH - KIRKLAND WA, US
CHRISTOPHER A. WIKLOF - EVERETT WA, US

ClearSign Combustion Corporation - Seattle WA

F23D 14/68, F23D 14/62

431 6, 431354

An electrically stabilized burner is configured to support a combustion reaction such as a combustion reaction substantially at a selected fuel dilution and with a mixing rate selected to maximize the reaction rate without quenching the combustion reaction.

4468241, Aug 28, 1984

Sep 29, 1982

6/427166

Robert E. Breidenthal - Seattle WA

C03B 3706

65 5

The high velocity gradients associated with the shear layer or boundary layer of a supersonic gas stream, especially the potential core thereof, are applied to form fibers of a melted material projected across such gradients. Optimization of the effects of such gradients is sought by sustaining the magnitude of the gradients as long as possible by minimizing shear layer growth rate and/or stabilizing the rate of vortex formation, and by synchronizing the rate of projection of melt with the rate of vortex production. Provisions such as vortex triggering or density loading are made for reducing the shear layer growth rate. Provisions are also made for intermittently feeding melt at a rate synchronized with the rate of vortex formation. Provisions for regulating the temperature in the shear layer are made such as appropriately controlling stagnation gas temperature, causing an exothermal reaction within the gas stream, or causing combustion of the gas stream within an oxygen containing fiberization chamber.

2002015, Oct 24, 2002

Apr 19, 2001

09/838744

Michael Hartman - Kirkland WA, US
Eric Moe - Seattle WA, US
Robert Breidenthal - Seattle WA, US
Jesse Rehr - Seattle WA, US

E21B043/16

166/302000, 166/369000, 166/066400, 166/062000

The production rate, useful life and operating efficiency of electric submergible pumping systems (ESP) is improved by operating the system so that the motor is cooled by two passes of production. The two passes of production fluid are achieved by employing a shroud with the inlet at the opposite end of the production fluid intake or by installing the motor below the perforations that allow production fluids to enter a well. The motor is designed with an internal conduit through which the production fluids are pumped. Production fluids remove waste heat from the motor by passing in fluid contact with the exterior of the motor and again by passing through the internal conduit of the motor. The improved cooling permits the motor to be operated at a lower temperature improving life and efficiency, and/or to be operated at higher power at a similar temperature. Additionally, oversized and excess equipment is not required, further improving performance and economics for the user. In another aspect, the invention is a method of pumping fluids using a motor having vortex generators on its exterior surfaces or on the interior surfaces of a surrounding shroud, and a method for determining optimum well operating conditions.

5775643, Jul 7, 1998

Oct 18, 1996

8/731755

Daniel McMaster - Bellevue WA
Robert Edward Breidenthal - Seattle WA

The Boeing Company - Seattle WA

H01Q 128, F41G 726, B64C 138, B64C 2106

244130

The invention provides an aero-optical turret assembly that provides high Strehl ratios throughout a wide range of azimuthal look angles. The turret assembly includes a duct extending from aft of the turret to a location aft of an aerodynamic bulge of the turret assembly. During flight, a low pressure zone is formed at the exit end of the duct, aft of the aerodynamic bulge. This low pressure zone causes suction of air from the inlet of the duct, and therefore away from the outer surfaces of the aero-optical turret. By judiciously selecting the shape of the aerodynamic bulge, and the size and location of the inlet end of the duct, substantially all turbulent air can be removed from around the adjacent outer surfaces of the aero-optical turret, thereby removing the source of interference with electromagnetic radiation passing through the window of the turret at azimuthal look angles greater than +60. degree. In accordance with the invention, a high Strehl ratio can be obtained for azimuthal look angles in the range from about +120. degree. to about -120. degree.

5979395, Nov 9, 1999

Apr 30, 1998

9/069995

Brian D. Mallen - Charlottesville VA
Robert E. Breidenthal - Seattle WA

Mallen Research Ltd. Partnership - Charlottesville VA

F02B 5300

123243

A method for reducing the exhaust pollution emissions in a two-stroke sliding vane internal combustion engine. First, fresh air is inducted into a vane cell, and fuel is injected into the cell at an ultra-lean fuel-air equivalence ratio less than about 0. 65. The fuel is injected at a location such that a circumferential distance at mid-cell-height to the stator site at the onset of combustion is at least about 4 times a vane cell height at intake. The ultra-lean fuel-air combination is then compressed and thoroughly premixed prior to combustion to a dimensionless concentration fluctuation fraction below about 0. 25. The ultra-lean, thoroughly premixed fuel-air combination is then combusted. The combusted fuel-air combination is purged after an expansion cycle. The premixing step prior to combustion may use inclined airfoils within the intake duct to produce counter-rotating mixing vortices.

2013014, Jun 6, 2013

Jul 6, 2012

13/542678

WILLIAM BYRON ROBERTS II - WELLINGTON NV, US
SHAWN P. LAWLOR - BELLEVUE WA, US
ROBERT E. BREIDENTHAL - SEATTLE WA, US

RAMGEN POWER SYSTEMS, LLC - BELLEVUE WA

F04D 21/00

415181

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.

5524587, Jun 11, 1996

Mar 3, 1995

8/398443

Brian D. Mallen - Charlottesville VA
Jakob J. Keller - Redmond WA
Robert E. Breidenthal - Seattle WA

Mallen Research Ltd. Partnership - Charlottesville VA

F02B 5300, F04C 1800

123243

A sliding vane engine, where the vanes slide with at least of one of an axial and radial component of vane motion, and where the compression ratio of the engine may be variably controlled. The engine includes a stator and a rotor in relative rotation, and a plurality of vanes in rotor slits defining one or more main chamber cells and one or more vane slit cells. The vanes contain extended pins that move in a pin channel for controlling the sliding motion of the vane. Fuel is mixed by incorporating air turbulence generators at or near the intake region. The intake and exhaust regions of the engine also incorporate a wave pumping mechanism for injecting and scavenging air from the main chamber cells and the vane slits. The compression ratio of the engine may be varied while the engine is in operation, and the engine geometry provides for an extended temporal duration at about peak compression. The engine is insulated by using segmented ceramic inserts on the stator and rotor surfaces.

2013003, Feb 14, 2013

Jul 6, 2012

13/542673

ROBERT E. BREIDENTHAL - SEATTLE WA, US

RAMGEN POWER SYSTEMS, LLC - BELLEVUE WA

F15D 1/12, B64C 5/06, F03D 11/00, B64C 3/00, B62D 35/00, B64C 21/00, B64C 9/00

2442041, 244 91, 244 87, 137561 A, 2961801, 416223 R

A vortex generator, or an array of vortex generators, for attenuating flow separation during flow of fluid over a surface. Vortex generators include a base with a forward end and a leading edge extending outward and rearward from the forward end to an outward end. The leading edge includes a first angular discontinuity at a height Habove the base, and a second angular discontinuity at a height Habove the base. The vortex generator(s) are configured for generating, adjacent a surface, at least two (2) vortices Vand Vin a fluid, and turning the outermost generated vortice toward the surface over which the fluid is passing.