GE Vernova Infrastructure Technology LLC

Systems and methods are provided for controlling the mass flow of an exhaust gas to be delivered from an EGR system to a gas turbine system in a power plant. The mass flow control is provided through a mass flow controller including 1) a primary mass flow control that modulates the mass flow of the EGR flow by adjusting operating conditions of an EGR blower, 2) a secondary mass flow control that maintain power optimized operation of the EGR blower by adjusting the position of an EGR outlet damper, and 3) a tertiary flow modulation control that limits the EGR operation within mechanical design boundaries of the EGR duct by throttling the position of an EGR inlet damper. As such, the presently disclosed embodiments may operate independently to provide precise mass flow control within the EGR system, optimize power consumption of the blower, and safeguard the EGR system within its design boundaries.

A gas turbine system includes a gas turbine engine and a gas treatment system for treating an exhaust gas, and a thermal control system to control temperatures of the exhaust gas such that the temperatures may be suitable for the gas treatment system. The thermal control system may include a tempering air control and a sensor grid control, which may cooperatively control a tempering air that may be injected into the exhaust gas. Specifically, the thermal control system may adjust the flow of tempering air by compensating for a failed sensor in a sensor grid system, using a worst case scenario assumption, to protect the gas treatment system from overheating and to allow for continuous operations of the gas turbine system without interruptions due to sensor failures.

The present disclosure is direct to a system for regulating a velocity of gases in a turbomachine. The system includes an exhaust section of the turbomachine. The system also includes a damper having an actuator and a restriction. The damper is positioned within the exhaust section and is operable to adjust the velocity of the gases based on a position of the restriction. The system further includes a controller communicatively coupled to the damper. The controller is configured to control the position of the restriction to regulate the velocity of the gases relative to a predetermined velocity range.

A nozzle segment separation tool for use with a pair of airfoils of adjacent nozzle segments in a turbine is provided. The nozzle segment separation tool includes a pair of separation brackets, a movable separation bracket and a stationary separation bracket, and a hydraulic cylinder positioned between the pair of separation brackets. The movable separation bracket is positioned about a first airfoil of the pair of airfoils and the stationary separation bracket is positioned about a second airfoil of the pair of airfoils. The hydraulic cylinder pushes the movable separation bracket against the first airfoil until the stationary separation bracket pushes the second airfoil to separate from the first airfoil.

The present application provides a deformation correction system for a hot gas path surface of a turbine shroud. The deformation correction system may include a first die having a curved surface and a second die such that the hot gas path surface of the turbine shroud is positioned between the first die and the second die.

A combustor for a gas turbine engine comprises: a head end section defining a head end plenum and containing a fuel nozzle assembly; and a liner extending downstream from the head end section to an aft frame and defining a combustion chamber therein. First injectors, disposed at a first axial location, direct a first fuel/air mixture through the liner. Second injectors, disposed at a different, second axial location, direct a second fuel/air mixture through the liner. Each of the head end section, the first injectors, and the second injectors receives a respective air supply from a compressor discharge plenum that at least partially surrounds the combustor. The respective air supplies are directed to only one of the fuel nozzle assembly, the first injectors, and the second injectors. The first injectors and the second injectors receive more than 50% of the air supply from the compressor discharge plenum.

An airfoil includes a leading edge, a trailing edge, and a pressure side wall and a suction side wall each extending between the leading edge and the trailing edge. The pressure side wall and the suction side wall define a main body region and a trailing edge region. The main body region extends from the leading edge to the trailing edge region and defines an upstream plenum. The trailing edge region extends from the main body region to the trailing edge. The trailing edge region defines pressure side channels and suction side channels in fluid communication with the upstream plenum and arranged in a trussed structure to reduce stress in the trailing edge region. The pressure side channels are disposed adjacent the pressure side wall, and the suction side channels are disposed adjacent the suction side wall.

An integration system for use with a gas turbine engine includes an exhaust gas recirculation (EGR) system in flow communication with a gas turbine section of the gas turbine engine. The EGR system includes an EGR conduit fluidly coupled to an exhaust line of the gas turbine engine and fluidly coupled to an EGR manifold upstream from an inlet of a compressor section of the gas turbine engine. The EGR conduit is oriented to provide a portion of exhaust gases discharged from the gas turbine section to the EGR manifold. Additionally, the EGR system also includes a flow restriction component in flow communication with the exhaust line of the gas turbine engine. The flow restriction component is downstream from the EGR conduit of the EGR system. The flow restriction component facilitates increasing a pressure of the exhaust gases discharged from the gas turbine section.

A system includes an intake heating system having one or more heat exchangers. The one or more heat exchangers are fluidly coupled to a steam turbine system, a gas turbine system, a carbon capture system, and a heat recovery steam generator (HRSG). The one or more heat exchangers are configured to receive steam from the HRSG, the steam turbine system, or a combination thereof. The one or more heat exchangers are also configured to receive an air. The one or more heat exchangers are also configured to place the steam in a heat exchange relationship with the air to produce a heated air and a cooled steam. The one or more heat exchangers are also configured to send the cooled steam to the carbon capture system. The one or more heat exchangers are also configured to send the heated air to one or more injection locations of the gas turbine system.

An impingement module for localized cooling a hot gas path component of a turbomachine includes a plurality of impingement orifices. The impingement module is positioned with the plurality of impingement orifices oriented towards an outer surface of the hot gas path component. Thus, the impingement module is configured to receive a flow of pressurized air and direct the pressurized air through the impingement orifices to impinge on the outer surface of the component.