Abstract: A compressed air energy storage system integrated with a source of secondary heat, such as a simple cycle gas turbine, to increase power production and to provide power regulation through the use of stored compressed air heated by said secondary heat to provide power augmentation.

Abstract: A foldable shipping container adjustable between an unfolded condition in which said container is suitable for use as a cargo container, and a folded condition for when said container is not being used to store or ship cargo.

Abstract: This invention relates to electrical power systems, including generating capacity of a gas turbine, and more specifically to augmentation of power output of gas turbine systems, that is useful for providing additional electrical power during periods of peak electrical power demand.

Abstract: A compressed air energy storage system integrated with a source of secondary heat, such as a simple cycle gas turbine, to increase power production and to provide power regulation through the use of stored compressed air heated by said secondary heat to provide power augmentation.

Abstract: A compressed air energy storage system integrated with a source of secondary heat, such as a simple cycle gas turbine, to increase power production and to provide power regulation through the use of stored compressed air heated by said secondary heat to provide power augmentation.

Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.

Abstract: An apparatus and method are disclosed for reducing the operating stresses in a disk of a gas turbine engine while providing a seal plate to minimize leakage of a cooling fluid from the blades positioned in the disk. The seal plate is fastened to a tang of one or more of the blades. The seal plate configuration can be utilized with a newly manufactured disk and blades or with a modification to an existing disk and blades. The disk, blade, and seal plate configuration reduce operating stresses in the disk that are caused by mechanical loading on the disk by one or more rotating blades.

Abstract: Embodiments for an apparatus and associated method for reducing the residence time in a gas turbine combustor are disclosed. The embodiments of the present invention comprise a fuel nozzle that extends to a downstream plane of an end cap for a combustion liner where the axial distance of the premixer is reduced, however the swirl for mixing the fuel and air, is increased. As a result, the mixing of the fuel and air is essentially unchanged, thereby allowing higher air pressures and operating temperatures within the premixer without inducing auto-ignition.

Abstract: An improved secondary fuel distribution system having a readily adjustable premix pilot nozzle for use in a gas turbine combustor is disclosed. The secondary fuel nozzle assembly has a premix fuel nozzle comprising an annular tubular manifold and a premix pilot nozzle. Multiple embodiments of premix pilot nozzles are disclosed that have a fuel flow rate that can be controlled and adjusted as required, including a plate and feed hole combination, a pressfit premix pilot nozzle, and a premix pilot nozzle that is threaded into the secondary fuel nozzle assembly.

Abstract: A premix secondary fuel nozzle for use in transferring a flame from a first combustion chamber to a second combustion chamber is disclosed. The secondary fuel nozzle includes multiple fuel circuits, each of which are fully premixed, and neither of which are injected in a manner to directly initiate or support a pilot flame, thereby lowering emissions. Multiple embodiments are disclosed for alternate configurations of a first fuel injector, including an annular manifold and a plurality of radially extending tubes.

Abstract: A turbine blade is disclosed having a tip shroud that includes internal passages through which cooling air is flowed to minimize creep. The cooling air is provided to the shroud through dedicated cooling passageways which include tube inserts that restrict the transfer of heat from the airfoil portion of the turbine blade to the cooling air within the tube as the cooling air passes through the airfoil portion.

Abstract: A novel pool deck structure channel located beneath a swimming pool deck surface is disclosed that incorporates both a drainage device and a pool safety fence support structure. The unique channel design eliminate the need to have separate support holes drilled in a pool deck surface that can be a safety hazard when not in use, cause functional problems due to dirt and debris, and are not otherwise aesthetically pleasing. The unique channel design includes an elongated trough extending beneath the pool deck surface for supporting a drainage device, a plurality of holes in the trough, and a plurality of inserts within the holes that extend into the trough in order to support pool safety fence support posts.

Abstract: An improved secondary fuel distribution system having a readily adjustable premix pilot nozzle for use in a gas turbine combustor is disclosed. The secondary fuel nozzle assembly has a premix fuel nozzle comprising an annular tubular manifold and a premix pilot nozzle. Multiple embodiments of premix pilot nozzles are disclosed that have a fuel flow rate that can be controlled and adjusted as required, including a plate and feed hole combination, a pressfit premix pilot nozzle, and a premix pilot nozzle that is threaded into the secondary fuel nozzle assembly.

Abstract: A premix secondary fuel nozzle for use in transferring a flame from a first combustion chamber to a second combustion chamber is disclosed. The secondary fuel nozzle includes multiple fuel circuits, each of which are fully premixed, and neither of which are injected in a manner to directly initiate or support a pilot flame, thereby lowering emissions. Multiple embodiments are disclosed for alternate configurations of a first fuel injector, including an annular manifold and a plurality of radially extending tubes.

Abstract: A novel pool deck structure channel located beneath a swimming pool deck surface is disclosed that incorporates both a drainage device and a pool safety fence support structure. The unique channel design eliminate the need to have separate support holes drilled in a pool deck surface that can be a safety hazard when not in use, cause functional problems due to dirt and debris, and are not otherwise aesthetically pleasing. The unique channel design includes an elongated trough extending beneath the pool deck surface for supporting a drainage device, a plurality of holes in the trough, and a plurality of inserts within the holes that extend into the trough in order to support pool safety fence support posts.

Abstract: A turbine blade is disclosed having a tip shroud that includes internal passages through which cooling air is flowed to minimize creep. The cooling air is provided to the shroud through dedicated cooling passageways which include tube inserts that restrict the transfer of heat from the airfoil portion of the turbine blade to the cooling air within the tube as the cooling air passes through the airfoil portion.

Abstract: An improved sealing device for use between a transition duct aft frame and turbine inlet is disclosed. The improved sealing device includes a plurality of corrugated metal seals that are secured to the transition duct aft frame along the arc-like sections of the aft frame. The corrugated seals contact both the transition duct aft frame and turbine inlet to provide a more effective seal and to control the amount of compressor discharge air introduced to cool the turbine vane platforms. In the preferred embodiment, the corrugated seals are coated to reduce wear, fretting, and galling and are used in conjunction with a transition duct thermally free aft frame and pivot bearing mounting system. An alternate embodiment of the seal is also disclosed that utilizes an alternate cooling hole pattern for providing additional cooling air to the turbine vane platform.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.

Abstract: A fuel nozzle system for use in a combustor utilized in a combustion turbine for reducing nitrogen oxides and other pollutants including an annular fuel distribution manifold separately mounted away from a diffusion nozzle, said annular manifold having a plurality of fuel emitting passages or holes disposed along the downstream side of the manifold, said manifold being mounted in a position away from the diffuser nozzle body to allow air to stream around the manifold on all sides allowing for a thorough mixture of fuel and air around the annular manifold for better premixing in the combustion chamber. In an alternate embodiment, the diffusion nozzle is replaced by a pilot flame nozzle that is supplied with both air and fuel through a premix air and fuel chamber to a pilot flame nozzle which is used to sustain combustion in the secondary chamber. The use of a pilot flame nozzle that has a fuel and air mixture is believed to reduced NOx emissions.