A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

Disclosed herein is a sealing gas supply apparatus. In the sealing gas supply apparatus for supplying sealing gas to a turbomachine of a power generation system, a source comprises at least one low-temperature source for supplying a working fluid to the sealing gas supply apparatus and at least one high-temperature source for supplying a working fluid having a higher temperature than the low-temperature source to the sealing gas supply apparatus, and the working fluids are mixed in the sealing gas supply apparatus to be suitable for a sealing condition as a temperature condition required in a sealing system so as to be supplied to the sealing system of the turbomachine. In accordance with the present disclosure, since separate electric power is not consumed during normal operation by improving a turbine sealing gas source, it is possible to enhance power generation performance by a reduction in power consumption.

A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

A deicing system for an aircraft may supply heat to an aircraft component in pulses. A first series of pulses may melt ice built up on the aircraft component. A second series of pulses may prevent ice from forming on the aircraft component. The length of each of the pulses in the first series of pulses may be longer than the length of each of the pulses in the second series of pulses. The pulses may be supplied by a pneumatic deicing system or an electrical deicing system.

A fuel leak detection system for hydrogen fuel system including a monitored component. The fuel leak detection system including a sensor and controller communicatively coupled to the sensor. The sensor is positioned to monitor at least a portion of the monitored component. The sensor is configured (i) to sense a parameter corresponding to a hydrogen fuel leak of the monitored component and (ii) to generate an output. The controller is configured (i) to receive the output of the sensor, (ii) to determine, based on the output of the sensor, if a leak has occurred in the monitored component, and (iii) to generate an output indicating a fuel system leak when the controller determines that the leak has occurred in the monitored component. The monitored component may be a component of one of a fuel tank, a power generator, and a fuel delivery assembly.

An apparatus and method for controlling a cooling fan of a battery of a vehicle are provided. The apparatus includes a motor controller that drives a cooling fan motor of the battery based on information regarding control conditions of the cooling fan motor, and requests a backup process of a control of the cooling fan motor when an error in CAN communication by a CAN communicator or an error of the vehicle occurs. A backup processor then compensates for an output signal of the cooling fan based on at least one of an air conditioner pressure transducer (APT) output value, a vehicle speed, and a cooled water temperature and transmits the compensated output signal of the cooling fan to the motor controller.

A blocking device for preventing an inappropriate shut-off of an engine of an aircraft. The blocking device enables by default the actuation of the shut-off unit and receives information representative of an activated or inactivated state of a fuel shut-off lever, of a reduced or non-reduced speed state of a throttle lever, and a correct or incorrect operating state of the engine. The blocking device blocks the actuation of the shut-off unit when the throttle lever is in an inactivated state, when the engine is in a correct operating state, and when, in addition, the throttle lever is in a non-reduced speed state or the throttle lever is in a reduced speed state and, in addition, the opposite propulsion engine is in a failed state or in an incorrect operating state.