Patent ID: 8495883
Filing Date: 2013-07-30
Classification: F01D,F02C,F05D

Abstract:
1. A turbine engine assembly for a generator, the assembly comprising: a turbine engine having a compressor section, a combustor section and a turbine section, the combustor section having a primary zone temperature (T_PZ) and the turbine engine having a base load; at least one air bleed line in communication with the combustor section for receiving bleed air comprising combustor shell air from the combustor section; the at least one air bleed line providing cooling air to stationary vanes in a second stage of the turbine section and providing cooling air to stationary vanes in third and fourth stages of the turbine section downstream from the second stage for discharging bleed air into a hot working gas passing through the turbine section; each of the second, third and fourth stages of the turbine section including blades mounted to a common rotor for the compressor section; at least one valve for controlling air flow through the at least one air bleed line; a controller for opening the at least one valve to allow bleed air to flow through the at least one air bleed line when an operating load is less than the base load to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section; and wherein all bleed air for cooling the second, third and fourth stages of the turbine comprises air that has passed from the compressor section to the combustor section to maximize the amount of power that is absorbed at the compressor section prior to passing to the second, third and fourth stages of the turbine section in combination with increasing bleed air flow into the hot working gas to effect in an increased reduction in the temperature of the hot working gas within the turbine section.