ALSTOM TECHNOLOGIES LTD.
|ALSTOM TECHNOLOGIES LTD. Patent applications|
|Patent application number||Title||Published|
|20140033728||GAS TURBINE ASSEMBLY AND CORRESPONDING OPERATING METHOD - The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.||02-06-2014|
|20130239573||METHOD FOR OPERATING A COMBINED CYCLE POWER PLANT AND PLANT TO CARRY OUT SUCH A METHOD - Disclosed is a method for operating a gas turbine (||09-19-2013|
|20130205827||METHOD AND INSTALLATION FOR LIQUEFYING FLUE GAS FROM COMBUSTION INSTALLATIONS - A plant for CO||08-15-2013|
|20110116917||Compressor Stator Vane - A compressor component having a non-linear thickness distribution along the span length is disclosed. By altering the thickness distribution to a non-linear arrangement so as to locally increase airfoil thickness proximate a mid-span location, the natural frequency of the airfoil is increased so as to not coincide with a critical engine order of the compressor. Further, the present invention provides a novel airfoil profile in accordance with the coordinates of Table 1. The present invention also includes a carrier segment or disk fabricated from a material so as to eliminate corrosion with the compressor component.||05-19-2011|
|20110061393||Gas Turbine Transition Duct Profile - A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1. The coordinates are taken at a sweep angle Θ wherein Θ is an angle measured from the inlet end and X, Y, and Z are coordinates define the panel assembly profile at each angle Θ. An alternate embodiment of the invention defines an envelope for the uncoated internal profile of the panel assembly.||03-17-2011|
|20110038710||Application of Dense Vertically Cracked and Porous Thermal Barrier Coating to a Gas Turbine Component - A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is disclosed. A gas path surface of the platform, airfoil and airfoil fillet region are first coated with a bond coating. A dense vertically cracked (DVC) thermal barrier coating is then applied to at least the gas path surface of the platform and can be applied to the fillet region. A porous thermal barrier coating is then applied to at least the airfoil. The porous thermal barrier coating can also be applied over the DVC thermal barrier coating if desired.||02-17-2011|
|20100300108||STABILIZING A GAS TURBINE ENGINE VIA INCREMENTAL TUNING - An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine.||12-02-2010|
Patent applications by ALSTOM TECHNOLOGIES LTD.