WILLIAM BYRON ROBERTS, II
Pilots in Wellington, NV
License number
Nevada A1605193
Issued Date
Jun 2016
Expiration Date
Jun 2017
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
PO Box 2, Wellington, NV 89444
Professional information
Supersonic Compressor
US Patent:
2013016, Jun 27, 2013
Filed:
Jul 6, 2012
Appl. No.:
13/542676
Inventors:
WILLIAM BYRON ROBERTS II - WELLINGTON NV, US
SHAWN P. LAWLOR - BELLEVUE WA, US
SHAWN P. LAWLOR - BELLEVUE WA, US
Assignee:
RAMGEN POWER SYSTEMS, LLC - BELLEVUE WA
International Classification:
F04D 21/00
US Classification:
415181
Abstract:
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 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, compared to the number of blades in the accompanying rotor.
Supersonic Compressor
US Patent:
2013014, Jun 6, 2013
Filed:
Jul 6, 2012
Appl. No.:
13/542678
Inventors:
WILLIAM BYRON ROBERTS II - WELLINGTON NV, US
SHAWN P. LAWLOR - BELLEVUE WA, US
ROBERT E. BREIDENTHAL - SEATTLE WA, US
SHAWN P. LAWLOR - BELLEVUE WA, US
ROBERT E. BREIDENTHAL - SEATTLE WA, US
Assignee:
RAMGEN POWER SYSTEMS, LLC - BELLEVUE WA
International Classification:
F04D 21/00
US Classification:
415181
Abstract:
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.
Gas Turbine Engine With Supersonic Compressor
US Patent:
2013016, Jun 27, 2013
Filed:
Jul 6, 2012
Appl. No.:
13/542669
Inventors:
WILLIAM BYRON ROBERTS II - WELLINGTON NV, US
SHAWN P. LAWLOR - BELLEVUE WA, US
SHAWN P. LAWLOR - BELLEVUE WA, US
Assignee:
RAMGEN POWER SYSTEMS, LLC - BELLEVUE WA
International Classification:
F02C 7/00
US Classification:
60726
Abstract:
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.