Abstract: An aircraft gas turbine engine includes a heat exchanger module, and a core engine including an intermediate-pressure compressor, a high-pressure compressor, a high pressure turbine, and a low-pressure turbine. The high-pressure compressor is connected to the high-pressure turbine by a first shaft, and the intermediate-pressure compressor is connected to the low-pressure turbine by a second shaft. The heat exchanger module includes a central hub and heat transfer elements extending radially from the central hub and spaced in a circumferential array, for transferring heat energy from a fluid within the heat transfer elements to an inlet airflow passing over the heat transfer elements prior to entry of the airflow into an inlet to the core engine. The gas turbine engine further includes a first electric machine connected to the first shaft and positioned downstream of the heat exchanger module, and a second electric machines connected to the second shaft.

Abstract: A method for generating and displaying in real time performance parameters of a turbine including: monitoring the performance of the turbine and collecting real time data regarding turbine performance; determining a corrected turbine output value and corrected heat rate value from the collected real time data; electronically storing the corrected turbine output value and heat rate value and a corresponding time, and displaying a current corrected turbine output value, heat rate and a corresponding time.

Abstract: A method for generating and displaying in real time performance parameters of a turbine including: monitoring the performance of the turbine and collecting real time data regarding turbine performance; determining a corrected turbine output value and corrected heat rate value from the collected real time data; electronically storing the corrected turbine output value and heat rate value and a corresponding time, and displaying a current corrected turbine output value, heat rate and a corresponding time.

Abstract: A redundant fan system includes an in-series configuration of adjustable speed fans. A speed controller coupled to the fan system includes a first fan operated at a constant operating speed and a second fan operated at an adjusted operating speed to maintain a speed differential between the first and second fan speeds. A sensing device is connected to the first and second fans and to the speed controller for maintaining the speed differential constant.