A control system uses a modeled steam turbine megawatt (power) change attributed to a gas turbine demand change (i.e., a steam turbine to gas turbine transfer function) within a conventional closed loop feedback control scheme to perform control of a combined cycle power plant. This control system implements a form of internal model control and provides better unit megawatt (power) set-point tracking and disturbance variable rejection for overall more robust control, and thus operates to optimize the gas turbine operation of the combined cycle power plant in a manner that provides cost savings over time.

A control system uses a modeled steam turbine megawatt (power) change attributed to a gas turbine demand change (i.e., a steam turbine to gas turbine transfer function) within a conventional closed loop feedback control scheme to perform control of a combined cycle power plant. This control system implements a form of internal model control and provides better unit megawatt (power) set-point tracking and disturbance variable rejection for overall more robust control, and thus operates to optimize the gas turbine operation of the combined cycle power plant in a manner that provides cost savings over time.

A system for protecting the structural integrity of an engine strut may include a first monitor, a second monitor, and a controller communicatively coupled to the first monitor and the second monitor. The first monitor may be mounted proximate an engine strut coupling a turbine engine to an airframe of an aircraft. The second monitor may be mounted proximate the first monitor. The first monitor and the second monitor may each be configured to fail upon reaching a triggering temperature indicative of a burn-through in an engine case during operation of the turbine engine. The controller may be configured to automatically reduce an operating parameter of the turbine engine upon a failure of both the first monitor and the second monitor.

A system for protecting the structural integrity of an engine strut may include a first monitor, a second monitor, and a controller communicatively coupled to the first monitor and the second monitor. The first monitor may be mounted proximate an engine strut coupling a turbine engine to an airframe of an aircraft. The second monitor may be mounted proximate the first monitor. The first monitor and the second monitor may each be configured to fail upon reaching a triggering temperature indicative of a burn-through in an engine case during operation of the turbine engine. The controller may be configured to automatically reduce an operating parameter of the turbine engine upon a failure of both the first monitor and the second monitor.

According to an aspect, a method includes generating, by a computer processor, thermo-fluid parameter estimates of a thermal management system (TMS) of an engine based on sensed parameters and monitoring for TMS component failures based on the thermo-fluid parameter estimates and the sensed parameters. Thermo-mechanical parameter estimates are generated based on selected thermo-fluid parameters. Life usage estimates and life usage rate estimates are generated based on the selected thermo-fluid parameters and the thermo-mechanical parameter estimates. Life usage rate targets are generated based on external commands and the life usage estimates. Limits and goals are modified based on the life usage rate estimates, failure flags, and the life usage rate targets. A model predictive control is applied to command one or more TMS control components based on thermo-mechanical model parameters, the failure flags, and the limits and goals.

According to an aspect, a method includes generating, by a computer processor, thermo-fluid parameter estimates of a thermal management system (TMS) of an engine based on sensed parameters and monitoring for TMS component failures based on the thermo-fluid parameter estimates and the sensed parameters. Thermo-mechanical parameter estimates are generated based on selected thermo-fluid parameters. Life usage estimates and life usage rate estimates are generated based on the selected thermo-fluid parameters and the thermo-mechanical parameter estimates. Life usage rate targets are generated based on external commands and the life usage estimates. Limits and goals are modified based on the life usage rate estimates, failure flags, and the life usage rate targets. A model predictive control is applied to command one or more TMS control components based on thermo-mechanical model parameters, the failure flags, and the limits and goals.

An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber outside a gas turbine and providing compressed air to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses.

An object of the present invention is to provide a method and a system for implementing the method so as to alleviate the disadvantages of a reciprocating combustion engine and gas turbine in electric energy production. The invention is based on the idea of arranging a combustion chamber outside a gas turbine and providing compressed air to the combustion chamber in order to carry out a combustion process supplemented with high pressure steam pulses.

Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.