The present invention discloses a novel modular system and methods of operating an increased air supply to a gas turbine engine such that the upon supplying a source of external air to the system, a bias is added to the exhaust temperature such that a firing temperature with air injection is substantially equivalent to the firing temperature without air injection.

Provided herein is a system and method for tuning the operation of a turbine and optimizing the mechanical life of a heat recovery steam generator. Provided therewith is a turbine controller, sensor means for sensing operational parameters, control means for adjusting operational control elements. The controller is adapted to tune the operation of the gas turbine in accordance preprogrammed steps in response to operational priorities selected by a user. The operational priorities preferably comprise optimal heat recovery steam generator life.

A system for operating a gas turbine includes a controller configured to execute logic stored in a memory that causes the controller to determine two or more of a frequency, a coherence, a phase, and an amplitude, of a combustion instability; to compare two of more of the frequency, the coherence, the phase, and the amplitude of the combustion instability to a respective predetermined limit; and to adjust at least one parameter of the gas turbine if two or more of the frequency, the coherence, the phase, and the amplitude of the combustion instability are actionable relative to their respective predetermined limits. A related method of operating the gas turbine is also disclosed.

Systems and methods for regulating a bulk flame temperature in a dry low emission (DLE) engine are provided. According to one embodiment of the disclosure, a method may include measuring an exhaust gas temperature (EGT) and determining a target EGT. The target EGT is determined based at least in part on a compressor bleed air flow percentage and a combustor burning mode. The method may include calculating a bias based at least in part on the EGT and the target EGT and applying the bias to a bulk flame temperature schedule. The method may include regulating one or more staging valves and compressor bleeds of the DLE engine based at least in part on the bulk flame temperature schedule. The bulk flame temperature schedule is mapped to parameters of the staging valves and compressor bleeds to reduce nitric oxide, nitrogen dioxide, and carbon monoxide emissions.

A system for operating a gas turbine includes a controller configured to execute logic stored in a memory that causes the controller to determine a frequency, a coherence and, optionally, a phase and/or an amplitude, of a combustion instability; to compare the frequency and the coherence, and, optionally, the phase and/or the amplitude, of the combustion instability to a respective predetermined limit; and to adjust at least one parameter of the gas turbine if the frequency, the coherence, and, optionally, the phase and/or the amplitude of the combustion instability is actionable relative to the respective predetermined limit. A related method of operating the gas turbine is also disclosed.

Systems and methods to control gas turbine firing temperatures during air injection. A method of achieving a desired firing temperature of a gas turbine engine during air injection comprises injecting compressed air into the gas turbine engine using an external source. The external source includes a compressor and a recuperator. The method comprises using a controller of the gas turbine engine to: (a) determine an air injection exhaust bias gain using an inlet temperature of the gas turbine engine; (b) calculate, based on the determined air injection exhaust bias gain and a flow rate of the injected compressed air, an air injection exhaust curve bias; and (c) change a fuel flow of the gas turbine engine by adding the air injection exhaust curve bias to an existing exhaust curve of the gas turbine engine to thereby achieve the desired firing temperature during air injection.

A system is provided for an aircraft. This aircraft system includes an aircraft powerplant, a powerplant sensor system, an environment sensor system and a monitoring system. The aircraft powerplant includes a heat engine. The powerplant sensor system is configured to provide engine data indicative of one or more operating parameters of the heat engine. The environment sensor system is configured to provide environment data indicative of one or more environmental parameters of an environment in which the heat engine is operating. The monitoring system is configured to determine formation of a contrail and quantify an impact of the contrail when formed based on the engine data and the environment data.

Systems and methods to control gas turbine firing temperatures during air injection. A method of achieving a desired firing temperature of a gas turbine engine during air injection comprises injecting compressed air into the gas turbine engine using an external source. The external source includes a compressor and a recuperator. The method comprises using a controller of the gas turbine engine to: (a) determine an air injection exhaust bias gain using an inlet temperature of the gas turbine engine; (b) calculate, based on the determined air injection exhaust bias gain and a flow rate of the injected compressed air, an air injection exhaust curve bias; and (c) change a fuel flow of the gas turbine engine by adding the air injection exhaust curve bias to an existing exhaust curve of the gas turbine engine to thereby achieve the desired firing temperature during air injection.