Class / Patent application number | Description | Number of patent applications / Date published |
060735000 | Fuel injected into turbine | 9 |
20090013693 | INTEGRATED FUEL NOZZLE WITH FEEDBACK CONTROL FOR A GAS TURBINE ENGINE - A gas turbine engine includes a combustor having a fuel nozzle assembly for delivering fuel to a combustion chamber. A sensor is at least partially housed within the fuel nozzle assembly for sensing a parameter associated with the delivery of fuel to the combustion chamber. In one example, the sensor is an optical sensor coupled to an optical decoder for ascertaining the parameter. A trim valve is in communication with the fuel nozzle assembly. A controller is in communication with the sensor and is programmed to actuate the trim valve to adjust the amount of fuel delivered through the fuel nozzle assembly in response to the parameter. In one example, an end of the optical sensor is arranged near a fuel exit of the fuel nozzle assembly. The controller actuates the trim valve for the fuel nozzle assembly to achieve a desired air/fuel ratio and/or balance the fuel delivery of the fuel nozzle assembly relative to another fuel nozzle assembly within the gas turbine engine's combustor system. | 01-15-2009 |
20120240585 | CONSTANT VOLUME COMBUSTOR - A constant volume combustor device includes detonative combustion. In one form the wave rotor of the constant volume combustor is supported by magnetic bearings. | 09-27-2012 |
20130036739 | GAS TURBINE COMBUSTOR - A gas turbine combustor | 02-14-2013 |
20130291546 | INJECTION DEVICE FOR A TURBINE ENGINE COMBUSTION CHAMBER - A fuel injection device for an annular combustion chamber of a turbine engine, the device including a pilot circuit feeding an injector, a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, and an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices, each fuel-passing orifice formed in the annular ring including a zone of small section that is extended at least downstream or upstream by an orifice portion of increasing section. | 11-07-2013 |
20140020392 | GAS TURBINE - A gas turbine includes downstream side members that face a passage and have guide faces arranged in the passage side as it goes toward the upstream side. In a cross section including an axis center of a rotor shaft extending in a flow direction of a gas main stream, extension sections of the guide faces continuing to the upstream end portion of the guide faces are arranged downstream from the cavity inner wall portion of the upstream side member facing the cavities. | 01-23-2014 |
20150096301 | FUEL INJECTOR FOR A TURBINE ENGINE - The invention relates to a fuel injector ( | 04-09-2015 |
20150128600 | FUEL INJECTION SYSTEM FOR A TURBINE ENGINE - A fuel system for a turbine engine for improving efficiency in a fuel system where a major stage and secondary stage can be combined and held to a relatively constant fuel ratio while maintaining acceptable engine dynamics and NOx emissions is disclosed. The fuel system may be formed from a first premix injector assembly stage positioned upstream from a combustor basket, whereby the first premix injector assembly stage is a secondary injector system. The fuel system may be formed from a first primary injector assembly stage, which is a main injector system, positioned downstream from the first premix injector assembly stage. The first premix injector assembly stage and the first primary injector assembly stage may be coupled together such that the fuel system is capable of emitting fuel into a combustor of the turbine engine via the first premix injector assembly stage and the first primary injector assembly stage simultaneously. | 05-14-2015 |
20160097535 | COMBUSTOR FOR GAS TURBINE ENGINE - A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber. | 04-07-2016 |
20160169112 | FUEL SUPPLY APPARATUS FOR AIRCRAFT ENGINE | 06-16-2016 |