Patent application number | Description | Published |
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 |
20120031596 | HEAT EXCHANGER MEDIA PAD FOR A GAS TURBINE - A media sheet for a heat exchanger is disclosed. The media sheet includes a first layer having a first outer surface and a second layer having a second outer surface. The first and second layers define a plurality of passages extending therebetween. At least one of the first and second outer surfaces comprises a plurality of depressions. The plurality of depressions further define the plurality of passages therebetween. The media sheet is polymer fiber-based and wettable. | 02-09-2012 |
20130011244 | RECONFIGURABLE HEAT TRANSFER SYSTEM FOR GAS TURBINE INLET - A reconfigurable heat transfer system for a turbine inlet for a gas turbine engine is disclosed. The reconfigurable heat transfer system includes reconfigurable heat transfer components may be moved between a first position and a second position, wherein the second position allows a portion of or all of the air in the inlet to bypass the heat transfer components. | 01-10-2013 |
20140321967 | Gas Turbine Power Augmentation System - The present application provides a power augmentation system for use with a gas turbine engine. The power augmentation system may include a compressor discharge manifold, an inlet bleed heat system in communication with the compressor discharge manifold via an inlet bleed heat line, and an auxiliary compressor in communication with the compressor discharge manifold via the inlet bleed heat line. | 10-30-2014 |
Patent application number | Description | Published |
20130087219 | METHOD OF HEATING GAS TURBINE INLET - An air inlet system delivers a flow of air. The system included a temperature controlling section configured to alter temperature of the air flow. The temperature controlling section imparts a temperature variation distribution across different portions of the air flow. The system also includes a transition section, one or more flow diverters, one or more screens and/or a flow splitter to cause mixing of the different, temperature variant portions of the air flow and reduce the temperature variation distribution. | 04-11-2013 |
20130091864 | QUICK DISENGAGING FIELD JOINT FOR EXHAUST SYSTEM COMPONENTS OF GAS TURBINE ENGINES - A quick disengaging field joint connects a first component of an exhaust system of a gas turbine engine to a second component of the exhaust system. The field joint includes a pair of opposed stepped liners connected via exterior-facing connecting flanges. The field joints can be disassembled entirely from outside the exhaust housing without requiring access to the interior of the exhaust housing. | 04-18-2013 |
20130199192 | SYSTEM AND METHOD FOR GAS TURBINE NOX EMISSION IMPROVEMENT - In one embodiment of the present disclosure, a gas turbine system for NOx emission reduction and part load efficiency improvement is described. The system includes a gas turbine having a compressor which receives inlet-air. A direct-contact heat exchanger heats and humidifies the inlet-air before the inlet-air flows to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range. Humidifying the inlet-air can lower NOx emissions from the gas turbine unit. | 08-08-2013 |
20130255208 | QUICK ENGAGEMENT METHOD FOR GAS TURBINE INLET FILTER INSTALLATION AND REPLACEMENT - A filter installation arrangement and an associated method of installing a filter assembly to a partition. A filter assembly includes a filter element that extends along a longitudinal axis. The filter element includes an end cap disposed at an end of the filter element. An adjustment device of the installation arrangement axially displaces the end cap of the filter element in a first direction. An insert portion is inserted adjacent the end cap subsequent to the axial displacement of the end cap. The insert portion is configured to limit axial displacement of the end cap in a second direction that is opposite the first direction. | 10-03-2013 |
20140123674 | Inlet Bleed Heat System with Integrated Air Knife/Silencer Panels - The present application provides an inlet bleed heat system for supplying a flow of bleed air to a flow of incoming air into a compressor of a gas turbine engine. The inlet bleed heat system may include an air knife and a silencer panel. The air knife may include a compressor bleed air port in communication with the flow of bleed air and a discharge gap to discharge the flow of bleed air into the flow of incoming air. The air knife may and the silencer panel may form an integrated air knife/silencer panel. | 05-08-2014 |
20140202235 | CARTRIDGE FILTER ROBUSTNESS TESTING - A method includes providing at least one filter element in a test rig. The at least one filter element separates a clean side from a dirty side within the test rig. The pressure differential between the clean side and the dirty side is measured. The pressure differential between the clean side and the dirty side is increased by filtering particulate matter and fluid from an air flow within the test rig. The at least one filter element is cleaned. The previous three steps are repeated to replicate the conditions the at least one filter element is subjected to during substantially the entire life cycle of the at least one filter element. | 07-24-2014 |
20140230444 | System and Method for Reducing Back Pressure in a Gas Turbine System - In a first embodiment, a system, including an exhaust duct configured to flow an exhaust gas, and an air injection system coupled to the exhaust duct, wherein the air injection system comprises a first air injector configured to inject air into the exhaust duct to assist flow of the exhaust gas through the exhaust duct. | 08-21-2014 |