Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical power demand.

Method of operating an engine and electricity generator powered by torque from the engine is provided. The engine has a working-line which is a locus of engine operating points as the engine is throttled. The method includes increasing electrical-load on the generator. Repeatedly performing steps of: (i) detecting the engine working-line position; (ii) determining if the detected working-line position is sufficient for the engine to provide additional torque to power the generator while maintaining engine operation within range of acceptable engine operating conditions relative to the detected working-line position; (iii) when determination at step (ii) is that the engine operating condition is insufficient, modifying engine operational parameters to adjust the working-line position for the engine to provide additional torque while maintaining engine operation within the range of acceptable engine operating conditions; and (iv) increasing electrical-output from the generator by an amount so the engine provides additional torque. Repeating steps until the generator electrical-output matches electrical-load.

A method of operating a train system for driving a mechanical driven equipment is disclosed. The train system comprises a hybrid gearbox connected between a power source and a load to be driven. The hybrid gearbox includes a lay shaft gear, which transmission ratio between the power source and the load and a motor-generator unit can be adjusted, to adjust the transmission speed ratio arranged, to balance the power generated by the power source and to improve the efficiency of the train system in a number of operating conditions.

Systems and methods for detecting and accommodating for loss of a torque signal of a gas turbine engine are described herein. An engine deterioration offset may be determined while the torque signal of the engine is available. Then, in the event that the torque signal is lost, a predicted operating offset may be determined. A synthesized torque signal may be generated when the torque signal is lost at least in part from the engine deterioration offset and the predicted operating offset.

Electrical power systems, including generating capacity of a gas turbine, where additional electrical power is generated utilizing a separately fueled system during periods of peak electrical power demand.

A gas turbine engine system includes a gas turbine engine and a control system including sensors for monitoring operating properties of the engine, a signaling device that outputs a discrete switching signal indicative of an engine load change, such as connecting or disconnecting an electrical load in an electrical power system powered by the gas turbine engine, and an electronic control unit. The control unit calculates an engine load estimate based upon the switching signal, the operating properties, and statistical information in a recursive statistical estimator.

An engine that has, in axial flow series, booster compressor, core compressor, combustion equipment, core turbine, and low-pressure turbine. Core turbine drives core compressor via an interconnecting high-pressure shaft. Low-pressure turbine drives booster compressor via an interconnecting low-pressure shaft. Low-pressure turbine also drives external load having a defined speed characteristic that dictates speed of the low-pressure turbine and booster compressor. Booster compressor has one or more rows of variable stator vanes. The method includes: scheduling variation in the angle of variable stator vanes as a function of speed of the booster compressor wherein the vanes open as booster compressor speed increases; measuring or setting one or more operational parameters which are determinative of temperature at entry to core turbine; and biasing scheduling of angle variation of variable stator vanes as a function of operational parameter(s) to reduce variation in temperature at entry to core turbine.

A gas turbine power generation system has a dual-shaft gas turbine, an electric generator mechanically connected to a low pressure turbine of the dual-shaft gas turbine and electrically connected to an electric power system, a rotary electric machine mechanically connected to a high pressure turbine through a compressor of the dual-shaft gas turbine and electrically connected to the electric power system, and an electric power output from the electric generator side to the electric power system is adjusted by operation of the rotary electric machine as a motor or as a generator.

An engine bleed air system providing air to an aircraft system includes a port for extracting high pressure bleed air from an engine and a turbo-generator having a turbine and a generator. The generator is driven by rotation of the turbine. A bleed passage fluidly couples the port and an inlet of the turbo-generator. An outlet passage fluidly coupling an outlet of the turbo-generator and the aircraft system.

An engine bleed air system for providing air to an aircraft system includes a port for extracting bleed air from a compressor section of an engine. The system additionally includes a turbo-generator having a turbine and a generator. The generator is driven by rotation of the turbine. A boost compressor is fluidly coupled to the port. Bleed air from the port is selectively provided to one of the turbo-generator and the boost compressor based on a demand of the aircraft system.