Abstract: Embodiments of the present invention employ a closed loop controls philosophy, which actively controls the starting means of a powerplant machine, throughout the start-up process. Here, the present invention may provide a method for adjusting a nominal operating schedule of the starting means, which may have the form of a Load Commutated Inverter (LCI). Embodiments of the method may adjust the nominal operating schedule based, in part, on an operating parameter, which is associated with the gas turbine 100. The operating parameter may include, but is not limited to: a rotor speed, a desired start-up time, or the like. Here, the control system may receive data on the operating parameter associated with the gas turbine.

Abstract: The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine.

Abstract: An embodiment of the present invention provides a method of starting a powerplant machine, such as, but not limiting of, a turbomachine set to operate in a Fast Start mode. The turbomachine may include, but is not limited to, a steam turbine, a heavy-duty gas turbine, an aero-derivative gas turbine, and the like. An embodiment of the method of the present invention provides a new philosophy for controlling a starting system associated with the turbomachine. An embodiment of the present invention may be applied to a powerplant having multiple turbomachines and a starting system having multiple starting means, which may include at least one LCI system. Here, an embodiment of the present invention may eliminate the manual process of preparing and integrating a desired turbomachine with a desired starting means.

Abstract: Embodiments of the present invention employ a closed loop controls philosophy, which actively controls the starting means of a powerplant machine, throughout the start-up process. Here, the present invention may provide a method for adjusting a nominal operating schedule of the starting means, which may have the form of a Load Commutated Inverter (LCI). Embodiments of the method may adjust the nominal operating schedule based, in part, on an operating parameter, which is associated with the gas turbine 100. The operating parameter may include, but is not limited to: a rotor speed, a desired start-up time, or the like. Here, the control system may receive data on the operating parameter associated with the gas turbine.

Abstract: The present invention takes the form of a method that may reduce the effect of a transient of a fuel system. Essentially, an embodiment of the present invention incorporates a pressure control cell (PCC) with the fuel system. The PCC may be considered an additional volume that removes some of the fuel remaining in the fuel system during a transient event. During a transient event, when a rapid reduction of fuel is required for a fuel circuit, fuel may be allowed to exit a manifold of the fuel system and enter the PCC. This fuel may now be stored within the PCC and may no longer be available to the combustion can. A benefit of the present invention may be a reduced possibility of an undesired increase in rotor speed, and a lean blowout event.

Abstract: The present invention takes the form of a system that may reduce the effect of a transient of a fuel system. Essentially, an embodiment of the present invention incorporates a pressure control cell (PCC) with the fuel system. The PCC may be considered an additional volume that removes some of the fuel remaining in the fuel system during a transient event. During a transient event, when a rapid reduction of fuel is required for a fuel circuit, fuel may be allowed to exit a manifold of the fuel system and enter the PCC. This fuel may now be stored within the PCC and may no longer be available to the combustion can. A benefit of the present invention may be a reduced possibility of an undesired increase in rotor speed, and a lean blowout event.

Abstract: The present application provides a compressor clearance control system for a gas turbine engine. The gas turbine engine includes a turbine producing exhaust gases and a compressor with a casing and a number of rotor blades. The compressor clearance control system may include a casing heat exchanger positioned about the casing of the compressor and an extraction port for exhaust gases from the turbine. The extraction port is in communication with the casing heat exchanger so as to heat the casing of the compressor with the exhaust gases from the turbine.

Abstract: A method is provided for augmenting power output in a gas turbine electrical power-generating plant including a multistage compressor, a combustor and a multistage turbine component, during events when grid frequency drops below a predetermined target frequency. The method is carried out by a) providing a supply of liquified air arranged to permit selective addition of liquified air to an ambient air inlet to the compressor; and b) flowing controlled amounts of the liquified air into the ambient air inlet during such events.

Abstract: A combined cycle (CC) power plant comprises a gas turbine; a steam turbine; a condenser; a heat recovery steam generator (HRSG), the HRSG comprising an attemperator and a high pressure superheater and attemperator, the high pressure superheater and attemperator disposed at a discharge terminal of the high pressure superheater and attemperator and at a discharge terminal of the HRSG reheater; a generator, and a fuel supply. The steam turbine is connected by multiple conduits to the heat recovery steam generator (HRSG) and the steam turbine exhaust is connected to the condenser wherein support multiple ancillary and reserves to load follow, execute regulation, and meet intermediate power generation service needs in an expedited start process.

Abstract: A flexible joint is provided for facilitating bending of tubular segments. The flexible joint includes an outer cylindrical housing and at least one inner tubular member disposed within the outer cylindrical housing. The outer cylindrical housing has a first end which has an inwardly projecting bevel-shaped portion. The inner tubular member has a first end which has an outwardly projecting bevel-shaped portion. An elastomeric pad is bonded between an inner surface of the outer cylindrical housing and an outer surface of the inner tubular member at their respective first ends. The elastomeric pad has a bevel-shaped section which is adjacent to the inwardly projecting bevel-shaped portion of the first end of the outer cylindrical housing and the outwardly projecting bevel-shaped portion of the first end of the inner tubular member.