A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.

A cooling system for cooling hot components of a radial or axial gas turbine engine, which includes a recuperator heat exchanger, provides engine cooling without loss of thermal efficiency. Air flow leaving a compressor is split between a recuperator flow path and a bleed flow path. Air in the bleed flow path flows through the hot parts of the engine, thereby cooling the engine and heating the air. The air in the bleed flow path is combined with the output flow from a combustor and directed into a turbine inlet. A reduction of air flow in the recuperator flow path increases the thermal effectiveness of the recuperator heat exchanger by increasing a ratio of hot and cold flows inside the heat exchanger. The increase in thermal effectiveness of the heat exchanger compensates for energy losses incurred by diverting a portion of the compressor air flow for cooling.

A method for tuning a gas turbine engine includes performing a sensitivity step process on a tuning parameter. An operating parameter is monitored. The gas turbine is operating in a first operational state and the operating parameter has an initial condition. The tuning parameter is selected for adjustment. The tuning parameter is adjusted by a predefined amount. The adjustment includes applying an incremental bias adjustment to a fuel flow fraction schedule. The gas turbine engine transitions to a second operational state, wherein the operating parameter has an adjusted condition. The adjusted condition and the initial condition of the operating parameter are applied to a cost function. It is then determined that the cost function results in a cost function value indicative of a decreased cost. The incremental bias adjustment and the cost function value is written to a bias look-up table and are associated with the selected tuning parameter.

An electronic controller for an engine and a propeller, a control system and related methods are described herein. The controller comprises a first channel and a second channel independent from and redundant to the first channel. Each channel having a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command comprising instructions for controlling an operation of the engine and at least one propeller control command comprising instructions for controlling an operation of the propeller. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output based on the second engine and propeller parameters, at least one engine protection command comprising instructions for protecting the engine from hazardous conditions and at least one propeller protection command comprising instructions for protecting the propeller from hazardous conditions.

A method for monitoring and controlling a hybrid gas turbine system is disclosed, which is performed by a control logic unit. The method is implemented by executing an optimization among operating variables, so as to obtain control signals to control the operation of the hybrid gas turbine system. The hybrid gas turbine system is also disclosed, which includes at least one gas turbine, to be operated by fuel, and at least one electric motor/generator, capable of operating as a generator or as a motor. The hybrid gas turbine system comprises the control logic unit operatively connected to the fuel controller module and to the electric motor/generator controller.

Systems and methods for configuring operation of an engine are described herein. A computer-readable label associate with the engine is read by a mobile device to obtain label information having at least one trim value for the engine encoded therein. The at least one trim value is extracted from the label information on the mobile device. The at least one trim value is wirelessly transmitted from the mobile device to a data transmission unit of the engine. The data transmission unit is configured for instructing an electronic engine controller to trim the engine with the at least one trim value during operation of the engine.

There are describes methods and systems for operating an engine coupled to a fuel system having a fuel manifold configured to supply fuel to a combustor of the engine. The method comprises receiving a gaseous fuel flow request indicative of a change in demand for gaseous fuel to the engine; applying a fuel loss bias to the gaseous fuel flow request to obtain a biased fuel flow request, the fuel loss bias associated with a change in mass flow rate of the gaseous fuel from the fuel manifold to the combustor in response to the change in demand; and causing the gaseous fuel to flow into the combustor in accordance with the biased fuel flow request.

A turbofan gas turbine engine includes, in axial flow sequence, a heat exchanger module, a fan assembly, a compressor module, and a turbine module. The fan assembly includes a plurality of fan blades defining a fan diameter, and the heat exchanger module is in fluid communication with the fan assembly by an inlet duct. The heat exchanger module includes a plurality of heat transfer elements for transfer of heat from a first fluid contained within the heat transfer elements to an airflow passing over a surface of the heat transfer elements prior to entry of the airflow into an inlet to the fan assembly. At full-power condition, the engine produces a maximum thrust T (N), the heat exchanger module transfers a maximum heat rejection H (W) from the first fluid to the airflow, and a Heat Exchanger Performance parameter P.sub.EX (W/N) defined as P.sub.EX=H/T is 0.4 to 6.0.

A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.

A method and an air treatment system with a fan arrangement having k.sub.max fans. The respective speed n.sub.i of the fans is regulatable. A control and regulation system regulates the speeds n.sub.i, where iϵ[1, 2, 3, 4, 5, . . . , k] of the k of k.sub.max fans. A certain operating point of the air treatment system is set with a specific overall power P.sub.total of the air treatment system as a function of the respective set speeds n.sub.i. The control and regulation system has a mechanism to determine the speed combination(s) of the speeds n.sub.i of the k fans where the total power P.sub.total of the air treatment system is reduced or is minimal compared to other speed combinations of the speeds n.sub.i.