Patent application number | Description | Published |
20100050646 | Systems and Methods Involving Improved Fuel Atomization in Air-Blast Fuel Nozzles of Gas Turbine Engines - Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface. | 03-04-2010 |
20100101208 | Systems and Methods Involving Reduced Thermo-Acoustic Coupling of Gas Turbine Engine Augmentors - Systems and methods reducing thermo-acoustic coupling of a gas turbine engine augmentors are provided. In this regard, a representative method includes: determining acoustic resonances and heat release phase relationships associated with the augmentor; and determining relative axial positions of a fuel injector and a flame holder of the augmentor that result in reduced thermo-acoustic coupling of the augmentor during operation. | 04-29-2010 |
20100126177 | Augmentor Pilot - A gas turbine engine augmenter has a gas flowpath. A number of vanes extend into the gas flowpath. A number of augmenter fuel conduits have outlets along at least some of the vanes. At least one burner discharge outlet is along at least one of the vanes for discharging a pilot gas. | 05-27-2010 |
20130074514 | SYSTEMS AND METHODS INVOLVING IMPROVED FUEL ATOMIZATION IN AIR BLAST FUEL NOZZLES OF GAS TURBINE ENGINES - Systems and methods involving improved fuel atomization in air-blast fuel nozzles of gas turbine engines are provided. In this regard, a representative method includes: providing fuel to a chamber defined by an inner surface; and continuously atomizing a portion of the fuel via interaction of the fuel with the inner surface. | 03-28-2013 |
20130263572 | ENGINE HOT SECTION VANE WITH TAPERED FLAME HOLDER SURFACE - A gas turbine or rocket engine hot section includes a first duct case, a second duct case, a plurality of vanes arranged about an axial centerline, and an igniter located with a first of the plurality of vanes. The first of the plurality of vanes extends axially between a leading edge and a flame holder surface at a trailing edge. The flame holder surface extends radially between a first vane end connected to the first duct case and a second vane end connected to the second duct case. The flame holder surface includes a first section that tapers towards the first vane end, and a second section that tapers away from the first section and towards the second vane end. | 10-10-2013 |
20140060059 | FUEL DELIVERY SYSTEM WITH A CAVITY COUPLED FUEL INJECTOR - A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area. | 03-06-2014 |
20140118010 | MULTIPLE-EXCITATION MULTIPLE-RECEIVING (MEMR) CAPACITANCE TOMOGRAPHY - A method for operating a sensor, including simultaneously exciting a first set of electrodes and sensing an output of each electrode of a second set of electrodes, storing output data corresponding to the output of each electrode of the second set of electrodes in a memory storage device, shifting at least one electrode from the first set of electrodes to the second set of electrodes and at least one electrode from the second set of electrodes to the first set of electrodes, and repeating the simultaneously exciting and sensing, the storing, and the shifting until an output data has been stored for each possible pair of electrodes in the first and second set of electrodes. | 05-01-2014 |
20140338357 | CAVITY SWIRL FUEL INJECTOR FOR AN AUGMENTOR SECTION OF A GAS TURBINE ENGINE - A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet. | 11-20-2014 |