Patent application number | Description | Published |
20150276212 | BURNER WITH A PERFORATED FLAME HOLDER AND PRE-HEAT APPARATUS - According to an embodiment, a combustion system is provided, which includes a nozzle configured to emit a diverging fuel flow, a flame holder positioned in the path of the fuel flow and that includes a plurality of apertures extending therethrough, and a preheat mechanism configured to heat the flame to a temperature exceeding a startup temperature threshold. | 10-01-2015 |
20150276213 | METHOD FOR FLAME LOCATION TRANSITION FROM A START-UP LOCATION TO A PERFORATED FLAME HOLDER - According to an embodiment, a combustion system is provided, which includes a nozzle configured to emit a diverging fuel flow, a flame holder positioned in the path of the fuel flow and that includes a plurality of apertures extending therethrough, and a preheat mechanism configured to heat the flame to a temperature exceeding a startup temperature threshold. | 10-01-2015 |
20150276217 | BURNER WITH A FUEL NOZZLE AND A PERFORATED FLAME HOLDER SEPARATED BY AN ENTRAINMENT DISTANCE - A combustion system such as a furnace or boiler includes a perforated reaction holder configured to hold a combustion reaction that produces very low oxides of nitrogen (NOx). | 10-01-2015 |
20150276220 | BURNER WITH A PERFORATED REACTION HOLDER AND HEATING APPARATUS - A combustion system such as a furnace or boiler includes a perforated reaction holder configured to hold a combustion reaction that produces very low oxides of nitrogen (NOx). | 10-01-2015 |
Patent application number | Description | Published |
20100314493 | WINGTIP AND SPONSON INTERACTION ON AN AMPHIBIOUS AIRCRAFT - A system for enhanced lateral stability of an amphibious aircraft includes a buoyancy system laterally displaced from opposite sides of the fuselage of the aircraft and wingtip system having a hydrodynamic planing surface associated with each wingtip. The hydrodynamic planing surface on each wingtip prevents the submersion of an associated buoyancy structure. By supplementing the lateral stability of the buoyancy structures using hydrodynamic planing surfaces, the combined lateral width of the fuselage and buoyancy structures can be reduced without detrimentally impacting operational performance. This reduced lateral width enables the amphibious aircraft to be configured for storage and transportation on a trailer or shipping container. | 12-16-2010 |
20110180657 | TWO-MOTION WING-FOLD MECHANISM WITH INDEPENDENT LOAD PATH - An aircraft wing folding system folds an outboard wing section relative to an inboard wing section between a deployed position and a stored position in two discrete motions where each motion has an independent load path separate of the loading of the wing experienced by in-flight aerodynamic forces. The wing-fold mechanism of the present invention includes a fold assembly comprising a twist component and a fold component operable to fold the outboard wing section from the deployed position to the stored position that remains substantially unloaded with respect to in-flight aerodynamic forces when the wing is in the deployed or flight configuration. | 07-28-2011 |
20120187242 | WINGTIP AND SPONSON INTERACTION ON AN AMPHIBIOUS AIRCRAFT - A system for enhanced lateral stability of an amphibious aircraft includes a buoyancy system laterally displaced from opposite sides of the fuselage of the aircraft and wingtip system having a hydrodynamic planing surface associated with each wingtip. The hydrodynamic planing surface on each wingtip prevents the submersion of an associated buoyancy structure. By supplementing the lateral stability of the buoyancy structures using hydrodynamic planing surfaces, the combined lateral width of the fuselage and buoyancy structures can be reduced without detrimentally impacting operational performance. This reduced lateral width enables the amphibious aircraft to be configured for storage and transportation on a trailer or shipping container. | 07-26-2012 |
20140021302 | Spin Resistant Aircraft Configuration - A configuration and system for rendering an aircraft spin resistant is disclosed. Resistance of the aircraft to spinning is accomplished by constraining a stall cell to a wing region adjacent to the fuselage and distant from the wing tip. Wing features that facilitate this constraint include but are not limited to one or more cuffs, stall strips, vortex generators, wing twists, wing sweeps and horizontal stabilizers. Alone or in combination, aircraft configuration features embodied by the present invention render the aircraft spin resistant by constraining the stall cell, which allows control surfaces of the aircraft to remain operational to control the aircraft. | 01-23-2014 |
20150021434 | SELF-ORIENTING AIRCRAFT LANDING GEAR - An aircraft landing gear self-orients so to align itself within a plane parallel to the plane defined by the aircraft's roll and yaw axis. A nose gear of a tricycle landing gear configuration includes the ability to not only caster 360 degrees but also self-orient itself to be aligned parallel with the plane defined by the aircraft's roll and yaw axis once removed from any interaction with the ground. A simple and efficient mechanical design provides the landing gear with a substantially constant centering torque that neither impedes nor impairs ground movement yet returns the nose gear to a proper alignment for retraction and stowage. | 01-22-2015 |