Abstract: In some examples, propulsion, electrical generation, and cooling system. The system comprises a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a first fluid, wherein a portion of the compressed first fluid is directed out of the bleed air outlet to define bleed air from the compressor. The system also includes a turbo-generator including a combustor, wherein the combustor is configured to receive the bleed air from the compressor and combust a fuel with the bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor. The system also includes an air cycle cooling system configured to remove heat via an air cycle cooling process, wherein the air cycle cooling process is charged via the bleed air from the compressor. A compressor of the air cycle cooling system may be driven by a turbine of the turbo-generator or a turbine of the gas turbine engine.

Abstract: In examples, a propulsion and electrical generation system including a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a fluid, wherein a portion of the compressed fluid is directed out of the bleed air outlet to define bleed air from the compressor; and a turbo-generator including a combustor, wherein the combustor includes a fuel inlet and a bleed air inlet, wherein the bleed air inlet is in fluid communication with the bleed air outlet from the compressor, wherein the combustor is configured to receive the bleed air via the bleed air inlet from the bleed air outlet of the gas turbine engine and receive fuel via the fuel inlet, wherein the combustor is configured to combust the received fuel with the received bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor.

Abstract: A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Abstract: In some examples, propulsion, electrical generation, and cooling system. The system comprises a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a first fluid, wherein a portion of the compressed first fluid is directed out of the bleed air outlet to define bleed air from the compressor. The system also includes a turbo-generator including a combustor, wherein the combustor is configured to receive the bleed air from the compressor and combust a fuel with the bleed air, wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor. The system also includes an air cycle cooling system configured to remove heat via an air cycle cooling process, wherein the air cycle cooling process is charged via the bleed air from the compressor. A compressor of the air cycle cooling system may be driven by a turbine of the turbo-generator or a turbine of the gas turbine engine.

Abstract: In some examples, a propulsion and electrical generation system including a gas turbine engine including a compressor and a bleed air outlet from the compressor, wherein the compressor is configured to compress a fluid, wherein a portion of the compressed fluid is directed out of the bleed air outlet to define bleed air from the compressor; and a turbo-generator including a combustor, wherein the combustor includes a fuel inlet and a bleed air inlet, wherein the bleed air inlet is in fluid communication with the bleed air outlet from the compressor, wherein the combustor is configured to receive the bleed air via the bleed air inlet from the bleed air outlet of the gas turbine engine and receive fuel via the fuel inlet, wherein the combustor is configured to combust the received fuel with the received bleed air, and wherein the turbo-generator is configured to generate electrical energy via the combustion of the fuel by the combustor.

Abstract: A thermal management system for a pulse load on an aircraft. The thermal management system utilizing the reserve fuel from the aircraft to create thermal capacitance such that the instantaneous capacity of the cooling system to remove heat from the aircraft may be sized less than the rate of heat generated by the pulsed load (e.g. laser, radar, rail gun etc.) The reserve fuel is maintained at a temperature in a reservoir and cooled via a cooling system. Fuel from the reservoir is selectively mixed with fuel exiting the pulsed load heat exchanger to provide fuel to the inlet of the heat exchanger at a predetermined temperature, the temperature based at least upon the heat generated by the laser, flow rate of fuel and efficiency of the heat exchanger.

Abstract: Systems and methods for thermal management are provided. Thermal management components may include an electrical source and a cooling source. The electrical source may supply electricity to an electrical apparatus. In addition, the thermal management components store thermal energy. A controller may cause the electrical apparatus to be cooled by the cooling source and delay or suspend cooling the electrical source with the cooling source while a state of charge of the electrical source is greater than a predefined value for the electrical source. The state of charge of the electrical source may include a measurement of cooling capacity available by the electrical source.

Abstract: A turbine engine includes a fan connected to a fan shaft, a combustion chamber, and an electric motor/generator in communication with the fan shaft. A controller is configured to direct power into the electric motor/generator during engine accelerations from steady state such that air flow to the combustion chamber is increased. The controller is further configured to direct power out of the electric motor/generator during engine decelerations from steady state such that air flow to the combustion chamber is decreased.

Abstract: A power control system for providing power sharing is provided. An energy storage device is configured to supply a first portion of power of an electrical power as a total load power and an engine-driven electrical machine is configured to supply a second portion of power of the total load power. A power converter is electrically coupled to the energy storage device and the engine-driven electrical machine such that the power converter is configured to supply the total load power to an electrical load device. A controller is coupled to the power converter and the controller receives characteristic data from at least one of the energy storage device, the engine-driven electrical machine, and the electrical load device. Based on the received characteristic data, the controller determines a power sharing proportion of a power sharing amount of each of the first portion of power and the second portion of power of the total load power to be supplied via the power converter to the electrical load device.

Abstract: Methods and systems are provided to control engine speed droop. One such system may include an electric generator; an engine configured to power the electric generator via an output shaft; a control circuit configured to cause a speed of the output shaft to match a speed setpoint based on a feedback loop; and a processor configured to anticipate a change in a mechanical load on the engine and cause the speed setpoint of the output shaft to increase or decrease from a first value to a second value in response to anticipation of the change in the mechanical load on the engine.

Abstract: Methods and systems are provided to control engine speed droop. One such system may include an electric generator; an engine configured to power the electric generator via an output shaft; a control circuit configured to cause a speed of the output shaft to match a speed setpoint based on a feedback loop; and a processor configured to anticipate a change in a mechanical load on the engine and cause the speed setpoint of the output shaft to increase or decrease from a first value to a second value in response to anticipation of the change in the mechanical load on the engine.

Abstract: Systems and methods for thermal management are provided. Thermal management components may include an electrical source and a cooling source. The electrical source may supply electricity to an electrical apparatus. In addition, the thermal management components store thermal energy. A controller may cause the electrical apparatus to be cooled by the cooling source and delay or suspend cooling the electrical source with the cooling source while a state of charge of the electrical source is greater than a predefined value for the electrical source. The state of charge of the electrical source may include a measurement of cooling capacity available by the electrical source.

Abstract: A power control system for providing power sharing is provided. An energy storage device is configured to supply a first portion of power of an electrical power as a total load power and an engine-driven electrical machine is configured to supply a second portion of power of the total load power. A power converter is electrically coupled to the energy storage device and the engine-driven electrical machine such that the power converter is configured to supply the total load power to an electrical load device. A controller is coupled to the power converter and the controller receives characteristic data from at least one of the energy storage device, the engine-driven electrical machine, and the electrical load device. Based on the received characteristic data, the controller determines a power sharing proportion of a power sharing amount of each of the first portion of power and the second portion of power of the total load power to be supplied via the power converter to the electrical load device.

Abstract: A turbine engine includes a fan connected to a fan shaft, a combustion chamber, and an electric motor/generator in communication with the fan shaft. A controller is configured to direct power into the electric motor/generator during engine accelerations from steady state such that air flow to the combustion chamber is increased. The controller is further configured to direct power out of the electric motor/generator during engine decelerations from steady state such that air flow to the combustion chamber is decreased.