A power electronics module is provided having one or more power converter semiconductor components. The power electronics module further has a substrate having a first surface to which the one or more components are mounted, and having an opposing second surface from which project a plurality of heat transfer formations for enhancing heat transfer from the substrate. The power electronics module further has a coolant housing which sealingly connects to the substrate to form a void over the heat transfer formations of the second surface. The coolant housing has an inlet for directing a flow of an electrically insulating coolant into the void and an outlet for removing the coolant flow from the void, whereby heat generated during operation of the one or more components is transferred into the coolant flow via the substrate.

A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.

A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.

A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first end and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprising: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the pistons are configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.

A starter air valve comprising: a housing comprising an inlet at a first end, an outlet at a second end opposite the first end, and a center portion between first end and second end, the outlet being fluidly connected to the inlet through a fluid passage; a first piston located within the housing between the first end and center portion, the first piston comprising: a first cupped portion configured to form a first chamber with the housing proximate the first end; and a second piston located within the housing between the second end and center portion, the second piston comprising: a third cupped portion configured to form a third chamber with the housing proximate the second end; wherein the pistons are configured to regulate airflow through the fluid passage by adjusting at least one of a first pressure within the first chamber and a third pressure within the third chamber.

The present application relates to systems and apparatus for providing ground support services to aircrafts. An exemplary system may include a ground support apparatus. The ground support apparatus may include at least one motor controller configured to receive input power and to supply output power. The ground support apparatus may also include a motor configured to receive the output power from the at least one motor controller. The motor may include a rotatable motor shaft. Further, the ground support apparatus may include a gearbox having an input shaft and an output shaft. The input shaft may be coupled to the rotatable motor shaft of the motor. Additionally, the ground support apparatus may include a compressor configured to generate compressed air. The compressor may include an impeller coupled to a compressor shaft and the compressor shaft may be coupled to the output shaft of the gearbox.

The present application relates to systems and apparatus for providing ground support services to aircrafts. An exemplary system may include a ground support apparatus. The ground support apparatus may include at least one motor controller configured to receive input power and to supply output power. The ground support apparatus may also include a motor configured to receive the output power from the at least one motor controller. The motor may include a rotatable motor shaft. Further, the ground support apparatus may include a gearbox having an input shaft and an output shaft. The input shaft may be coupled to the rotatable motor shaft of the motor. Additionally, the ground support apparatus may include a compressor configured to generate compressed air. The compressor may include an impeller coupled to a compressor shaft and the compressor shaft may be coupled to the output shaft of the gearbox.

Output signals from ground power units can be combined to supply more energy for aircraft to use for starting a jet engine. The combining can be possible when the outputs from the ground power units are synchronized. In a synchronization process, a first ground power unit may be started so that its first output signal serves as a reference for the synchronization. Then, an interconnect on a second ground power unit can be toggled to start and stop the generation of a second output signal at different times until the signals are in phase (i.e., synchronized).

Output signals from ground power units can be combined to supply more energy for aircraft to use for starting a jet engine. The combining can be possible when the outputs from the ground power units are synchronized. In a synchronization process, a first ground power unit may be started so that its first output signal serves as a reference for the synchronization. Then, an interconnect on a second ground power unit can be toggled to start and stop the generation of a second output signal at different times until the signals are in phase (i.e., synchronized).

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.