Abstract: A combustion turbine having a compressed air cooling circuit that is connected to a nitrogen source. Compressed air is provided to the cooling circuit upon start-up and gradually switched to nitrogen cooling, as the nitrogen becomes available. Transition from compressed air to nitrogen cooling is supplied to the hottest components first in accordance with a pre-selected control scheme. Upon shutdown of the plant, the process is reversed.

Abstract: A two stage expansion and single stage combustor compressed air energy storage cycle that employs a heat exchanger to raise the temperature of the compressed air before it enters a high pressure expander. A combustor heats the exhaust from the high pressure expander and creates a working gas to drive a low pressure expander. The exhaust from the low pressure expander is supplied to the heat exchanger to raise the temperature of the compressed incoming air. A portion of the exhaust of the high pressure expander is cooled and employed in a cooling circuit within the low pressure expander. A starter valve in the compressed air input circuit finely tunes the incoming air during startup. The startup air flow is heated by an auxiliary duct burner until the low pressure turbine exhaust reaches operating temperature and is sufficient to heat the incoming air under normal operating conditions.

Abstract: A gas turbine power plant in which a mixture of steam and compressed air, the mixture being primarily steam, is used to cool the rotating blades and stationary vanes in the turbine section. The air is bled from the compressor. The flow rate of steam that is mixed into the compressed air is adjusted so to maintain the pressure drop experienced by the compressed air as it flows to the turbine within a predetermined range. Consequently, the steam and air mixture has the same volumetric flow rate as if compressed air alone were being used. Thus, any sudden decrease in steam flow rate will automatically result in an offsetting increase in the flow of compressed air due to the decrease in the line pressure in the common line through which the air and steam flow to the turbine. Consequently, no control, isolation or check valves are utilized in the compressed air piping.

Abstract: A method of operating a gas turbine in which variations in power requirements are accomplished by varying the rate of steam injection into the combustor while maintaining the temperature of the fluid flowing to the turbine at a constant value. The steam injection flow rate is varied by varying the pressure in the evaporator of a HRSG that receives exhaust gas from the turbine. Preferably, the flow area of the turbine is increased so as to allow the use of especially high rates of steam injection.

Abstract: A cooling system for stationary vanes in the turbine section of a gas ture. Combustors for the turbine are disposed in a chamber that receives compressed air from a compressor section. This compressed air forms both combustion air and cooling air. The cooling air portion of the compressed air is recirculated through the vanes by bleeding it from the chamber and further pressurizing it, after which it flows through a cooling air flow path in the vanes, thereby resulting in the cooling of the vanes and the heating of the air. The heated air is then returned to the chamber where it mixes with the incoming combustion air, thereby giving up a portion of the heat transferred from the vane to the combustion air. As a result, the temperature of the combustion air is increased, thereby increasing the thermodynamic efficiency of the gas turbine.

Abstract: A novel turbine inlet nozzle assembly is provided for use with a gas turbine engine and includes unique nozzle cooling means. The turbine inlet nozzle of the present invention comprises an inner annular shroud, an outer annular shroud coaxial with and spaced radially outwardly from the inner shroud and a plurality of circumferentially spaced vanes extending between the shrouds. The shrouds and the vanes, moreover, are of integral construction with each other and, preferably, each vane has a hollow interior. An annular impingement plate is fixedly secured about each axial end to the outer periphery of the outer shroud while, similarly, a second impingement plate is secured at each axial end to the inner periphery of the inner shroud. Moreover, the impingement plates include a plurality of holes formed therethrough and through which a portion of the turbine compressor output is bled to cool the inner and outer shrouds.