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Bradbrook
Chris Bradbrook, Palm Bay, FL US
| Patent application number | Description | Published |
|---|---|---|
| 20090059573 | SOLID-STATE LIGHTING DEVICE - A solid-state lighting device for illuminating a predetermined area having a width and length includes a reflector having at least one cavity. At least one edge emitting solid-state light-emitting device is positioned relative to the cavity of the reflector. The cavity includes an inner curved surface terminating at an edge proximate the solid-state light-emitting device. The inner curved surface has a curvature such that a light intensity of the device has a sharp drop-off in intensity at a boundary of the width and a slowly attenuating light at a boundary of the length. | 03-05-2009 |
Stephen J. Bradbrook, Bristol GB
| Patent application number | Description | Published |
|---|---|---|
| 20100329844 | PROPULSIVE FAN SYSTEM - A propulsive fan system comprises a fan unit comprising a first stage array of rotatable blades upstream of a second stage array of rotatable blades. The first stage is coupled to a first drive means. The second stage is coupled to a second drive means. The first drive means is independently operable of the second drive means during operation of the fan system. | 12-30-2010 |
| 20110041511 | Gas turbine engine - A bypass turbofan gas turbine engine is started by means of electric starter motor mounted directly about a downstream end or upstream of the low pressure spool of the engine. This causes air to be driven by a fan through a bypass duct around the engine casing. Closures close to substantially seal an outlet of the bypass duct, and the air is directed into a combustion chamber of the engine and through the turbines, causing the high pressure spool to pick up speed for starting. | 02-24-2011 |
Stephen J. Bradbrook, Clevedon GB
| Patent application number | Description | Published |
|---|---|---|
| 20100219779 | VARIABLE DRIVE GAS TURBINE ENGINE - A system and method for variable drive of a propeller or fan of a gas turbine engine. The gas turbine engine has a combustor and a turbine arranged to be driven by a combustion product from the combustor. The variable drive system comprises a primary shaft arranged for transmission of torque from said turbine to the propeller; an electric generator arranged to be driven by said turbine; and an electric motor arranged to be driven by the output of said generator. A clutch is mounted between the propeller and the primary rotor and is operable to mechanically disconnect the shaft from the propeller so that the propeller can be driven by any or any combination of the turbine and/or electric motor. The invention may be applied to a turboprop or turbofan engine having a gearing between the shaft and propeller or fan and may be particularly suited to unmanned aerial vehicle propulsion. | 09-02-2010 |