| ALSTOM TECHNOLOGIES LTD. Patent applications |
| Patent application number | Title | Published |
|---|
| 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 |
