Taylor, Derby
Christopher Jonathan Taylor, Derby GB
Patent application number | Description | Published |
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20150369050 | ROTOR BLADE MANUFACTURE - A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; applying tape at one or both sides of the slot such that when the blades are loaded in the slot the tape reduces a range of tilt angles which can be adopted by the blades; loading the blades in the slot; and performing a processing operation on the loaded blades. | 12-24-2015 |
20150369051 | ROTOR BLADE MANUFACTURE - A method is provided of processing one or more blades of a row of blades which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc having a slot for mounting one or more blades; loading the blades in the slot and loading the wax blocks in or adjacent the slot, the wax blocks being configured and positioned such that, on loading, the blades shear material from the wax blocks, the sheared wax blocks reducing a range of tilt angles which can be adopted by the blades; and performing a processing operation on the loaded blades. | 12-24-2015 |
Jonathan Paul Taylor, Derby GB
Patent application number | Description | Published |
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20150135535 | GAS TURBINE SPLITTING - A gas turbine engine fan stand ( | 05-21-2015 |
20150136935 | GAS TURBINE ENGINE STAND - A gas turbine engine stand ( | 05-21-2015 |
Mark D. Taylor, Derby GB
Patent application number | Description | Published |
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20090286189 | COMBUSTOR - A pressure rise combustor is provided with fuel provided at intermittent periods. The fuel is pulsed at timings such that the phase lag between the addition of the fuel and a resultant pressure rise is minimised. The fuel is pulsed such that the unsteady addition of heat reinforces the amplitude of an unsteady pressure fluctuation. | 11-19-2009 |
20100043443 | METHOD AND APPARATUS FOR SUPPRESSING AEROENGINE CONTRAILS - An aircraft comprising a gas turbine engine that exhausts a plume of gases in use, the aircraft comprises an ultrasound generator having an ultrasonic actuator and a waveguide to direct ultrasonic waves at the exhaust plume to avoid the formation of contrails. | 02-25-2010 |
20100132330 | METHOD AND APPARATUS FOR SUPPRESSING AEROENGINE CONTRAILS - A method of operating an aircraft, and the aircraft itself, comprising a gas turbine engine that exhausts a plume of gases in use, the aircraft is characterised by comprising an electromagnetic radiation generator and a waveguide to direct electromagnetic radiation at the exhaust plume to avoid the formation of contrails. | 06-03-2010 |
20100150705 | Gas turbine engine - A gas turbine engine ( | 06-17-2010 |
20120023898 | GAS TURBINE ENGINE - A gas turbine engine includes, in flow series, a generator section and a free power turbine. The generator section includes one or more generator turbine stages. One or more respective generator drive shafts extend axially forwardly from the generator turbine stages to one or more corresponding compressor stages. The free power turbine includes a first turbine stage and a contra-rotating second turbine stage. The gas turbine engine further includes a first drive shaft extending axially from the free power turbine to transmit rotational drive from the first turbine stage to a first propeller. The gas turbine engine further includes a second drive shaft extending from the free power turbine coaxially with the first drive shaft to transmit contra-rotational drive from the second turbine stage to a contra-rotating second propeller. | 02-02-2012 |
Mark David Taylor, Derby GB
Patent application number | Description | Published |
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20150308353 | CONTROL OF A GAS TURBINE ENGINE - An engine that has, in axial flow series, booster compressor, core compressor, combustion equipment, core turbine, and low-pressure turbine. Core turbine drives core compressor via an interconnecting high-pressure shaft. Low-pressure turbine drives booster compressor via an interconnecting low-pressure shaft. Low-pressure turbine also drives external load having a defined speed characteristic that dictates speed of the low-pressure turbine and booster compressor. Booster compressor has one or more rows of variable stator vanes. The method includes: scheduling variation in the angle of variable stator vanes as a function of speed of the booster compressor wherein the vanes open as booster compressor speed increases; measuring or setting one or more operational parameters which are determinative of temperature at entry to core turbine; and biasing scheduling of angle variation of variable stator vanes as a function of operational parameter(s) to reduce variation in temperature at entry to core turbine. | 10-29-2015 |
Robert A. J. Taylor, Derby GB
Patent application number | Description | Published |
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20100263755 | FUEL DISTRIBUTOR VALVE - A fuel distributor valve ( | 10-21-2010 |
20120144835 | COMBUSTION CHAMBER - A combustion chamber has an outer wall supporting a number of wall elements or tiles. The tiles are located on the wall by bosses so that a cooling space is provided between the wall and the tiles. Air holes are provided through the wall and the tiles and a flow passage is provided adjacent the air holes. A flow passage is defined by changing the profiles of the air holes in the outer wall and/or the location features to provide a localised gap through which cooling air is directed to cool regions subject to overheating and extend service life. | 06-14-2012 |