| Patent application number | Description | Published |
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| 20100050873 | FILTRATION SYSTEM FOR GAS TURBINES - A system for use with an inlet of a gas turbine through which airflow toward the gas turbine proceeds is provided and includes a first stage to remove primary aerosol droplets from the airflow by coalescing the primary aerosol droplets into secondary aerosol droplets, which are larger than the primary aerosol droplets, and to remove solid particulates from the airflow, a second water tight stage, disposed downstream from the first stage, to prevent the secondary aerosol droplets and aqueous solutions of deliquesced particulates, which are not removed by the first stage and which are re-released into the airflow from the first stage, from proceeding along the airflow and to remove solid particulates not removed by the first stage from the airflow, and a third water removal stage, disposed downstream from the second stage, to remove from the airflow the remaining secondary aerosol droplets leaking from the first and second stages. | 03-04-2010 |
| 20100054919 | FILTRATION SYSTEM FOR GAS TURBINES - A system for use with an inlet of a gas turbine through which an airflow toward the gas turbine proceeds is provided and includes a first self-cleaning stage to remove dust, snow and ice from the airflow, a second water tight stage, disposed downstream from the first stage, to prevent aerosol droplets and aqueous solutions of deliquesced particulates, which include at least portions of the dust not removed by the first stage and which are re-released into the airflow from the first stage, from proceeding along the airflow and to remove solid particulates not removed by the first stage from the airflow, and a third water removal stage, disposed downstream from the second stage, to remove from the airflow aerosol droplets leaking from the second stage. | 03-04-2010 |
| 20110173947 | SYSTEM AND METHOD FOR GAS TURBINE POWER AUGMENTATION - A gas turbine power augmentation system and method are provided. The system includes a chiller, a controller, a heat exchanger, and a gas turbine inlet air flow. The chiller may be operable to chill a coolant flow using energy from a heat source. The controller may be operably connected to the chiller and configured to regulate operation of the chiller in relation to at least one environmental condition. The heat exchanger may be in fluid communication with the chiller and configured to allow the coolant flow to pass through the heat exchanger. The gas turbine inlet air flow may be directed through the heat exchanger before entering a gas turbine inlet, allowing the air flow to interact with the coolant flow, thereby cooling the air flow. | 07-21-2011 |
| Patent application number | Description | Published |
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| 20100183446 | TURBINE BLADE OR VANE WITH IMPROVED COOLING - Disclosed is a turbine blade or vane including a blade or vane body including a leading edge and a trailing edge, a plurality of cooling openings disposed along the trailing edge, a first width of the trailing edge, the first width being disposed across the cooling openings, and a second width of the trailing edge the second width being disposed between the cooling openings, wherein the second width is smaller than the first width. | 07-22-2010 |
| 20100196167 | ROTOR CHAMBER COVER MEMBER HAVING APERTURE FOR DIRT SEPARATION AND RELATED TURBINE - A cover member defining a rotor chamber adjacent to a rotor wheel that supports a rotating blade in a turbine includes a first aperture for introducing a cooling gas stream into the rotor chamber, and a second aperture positioned in a radially outward portion of the cover member for allowing a portion of the cooling gas stream to exit the rotor chamber. The portion of the cooling gas stream exiting the rotor chamber carries dirt particles to purge the rotor chamber. | 08-05-2010 |
| 20110176929 | SYSTEM FOR COOLING TURBINE BLADES - A system, in one embodiment, includes a turbine blade having a radial blade tip. The system further includes a trailing edge trench that is formed in the radial blade tip and which extends towards a trailing edge of the turbine blade. The trailing edge trench further includes a first set of cooling passages, each of which includes a first slot formed along a first sidewall of the trailing edge trench, whereby the slot is coupled to a first respective hole extending through a floor of the trailing edge trench. | 07-21-2011 |
