| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060390480 | With fluid pressure feeding of oxidizer, fuel or water | 7 |
| 20120204532 | FUEL SUPPLY SYSTEM WITH MULTIPLE PUMPING MEANS - The invention proposes a system for supplying ( | 08-16-2012 |
| 20130205748 | COMBUSTION APPARATUS - A combustion apparatus includes a first device for mixing a fuel with an oxidant, a combustion chamber in which combustion of the fuel/oxidant mix takes place, a pre-chamber located between the first device and the combustion chamber and a second device for outputting a gas flow into the pre-chamber. The first device is adapted for outputting the oxidant or the fuel or the fuel/oxidant mix to the pre-chamber. The second device is located upstream of the first device and wherein the second device is arranged for mixing fuel with a gas and the gas flow is a fuel/gas mix. | 08-15-2013 |
| 20140013723 | SYSTEM AND METHOD OF SUPPLYING FUEL TO A GAS TURBINE - A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes. | 01-16-2014 |
| 20150047313 | COMBUSTOR OF A GAS TURBINE WITH PRESSURE DROP OPTIMIZED LINER COOLING - A design for an effectively cooling a liner of a gas turbine combustor by means of convective cooling is disclosed. | 02-19-2015 |
| 20150089920 | AIRBLAST FUEL INJECTOR - An airblast fuel injector is provided for a fuel spray nozzle of a gas turbine engine. The injector has an annular air passage for the passage of a swirling air flow therethrough. The swirling air flow is used by the injector to produce an atomised fuel spray. The air passage contains a swirler for producing the swirling air flow, the swirler comprising a circumferential row of vanes which span inner and outer side walls of the air passage. Viewed on a longitudinal section through the injector, the air passage has a bend downstream of the swirler, the bend changing the direction of the air passage. The vanes are configured to introduce a radial component to the air flow exiting the swirler, the radial component guiding the air flow around the bend. | 04-02-2015 |
| 20150337734 | Variable geometries fluid supply circuit and injection system supply circuit - The system for supplying fluid to a turbine machine comprises a low pressure pumping unit designed to increase the pressure in the fluid flowing towards the downstream circuit. The downstream circuit is subdivided at an inlet node into an injection system supply circuit and a variable geometries supply circuit. The variable geometries supply circuit is configured to carry fluid towards variable geometries from the inlet node to an outlet node connecting the variable geometries supply circuit to the upstream circuit. The injection system supply circuit comprises a high pressure volumetric pump and a pressure loss regulator configured to regulate pressure losses in the injection system supply circuit. | 11-26-2015 |
| 20160116168 | ROBUST INSULATED FUEL INJECTOR FOR A GAS TURBINE ENGINE - A fuel injector for a combustor of a gas turbine engine is disclosed. The fuel injector includes a flange, a fitting boss, a stem, a gas fuel passage, a gas fuel fitting, and a gas heat shield. The fitting boss protrudes from the flange. The stem extends from the flange. The gas fuel passage extends through the stem. The gas fuel fitting is joined to the fitting boss. The gas heat shield extends from the gas fuel fitting at least partially through the gas fuel passage. The gas heat shield is sized to form a gas heat shield gap between the gas heat shield and the stem at the gas fuel passage. | 04-28-2016 |
