Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.

Abstract: A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

Abstract: A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

Abstract: A system for controlling the clearance between a turbine blade and the turbine casing that includes an impingement cooling manifold attached to a turbine casing, a temperature sensing device for determining the temperature of the turbine casing, a blower, a control system logic for determining the setting temperature of the casing, and a controller for controlling the blower, wherein the blower forces air onto the impingement cooling manifold to cool the casing towards the setting temperature and control the clearance.

Abstract: A system for controlling the clearance between a turbine blade and the turbine casing that includes an impingement cooling manifold attached to a turbine casing, a temperature sensing device for determining the temperature of the turbine casing, a blower, a control system logic for determining the setting temperature of the casing, and a controller for controlling the blower, wherein the blower forces air onto the impingement cooling manifold to cool the casing towards the setting temperature and control the clearance.

Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.

Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.

Abstract: A system and method to reduce the gas fuel supply pressure requirements of a gas turbine, which results in an increased operability range and a reduction in gas turbine trips. According to the method, the gas turbine is allowed to start and operate at supply pressures determined as a function of ambient conditions and gas turbine compressor pressure ratio. This increases the operability window, and reduces or eliminates the need for gas fuel compressors.