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公开(公告)号：US12129043B1
公开(公告)日：2024-10-29
申请号：US18238755
申请日：2023-08-28
CPC分类号： B64D33/08 , F01M5/005 , F16K1/22 , F16K31/041
摘要： A system is provided for an aircraft. This aircraft system includes a heat exchanger, a lubricant flow circuit and a bypass valve. The lubricant flow circuit includes an inlet passage, an outlet passage, a heat exchanger passage and a bypass passage. The heat exchanger passage extends through the heat exchanger. The bypass passage bypasses the heat exchanger. The heat exchanger passage and the bypass passage are fluidly coupled in parallel between the inlet passage and the outlet passage. The bypass valve is fluidly coupled inline along the lubricant flow circuit. The bypass valve is operable to regulate lubricant flow through the bypass passage. The bypass valve includes a rotary electric motor.
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公开(公告)号：US11459955B2
公开(公告)日：2022-10-04
申请号：US16685151
申请日：2019-11-15
发明人： Thomas Trevor Ricci
摘要： A method of deactivating a liquid distribution system of a gas turbine engine in the event of a fire condition includes introducing a quantity of air into the liquid distribution system at a location upstream of a liquid pump of the liquid distribution system. The quantity of air is greater than a liquid discharge capacity of the liquid pump, thereby starving the liquid pump.
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公开(公告)号：US20240271547A1
公开(公告)日：2024-08-15
申请号：US18436753
申请日：2024-02-08
发明人： Yusuf Syed , Thomas Trevor Ricci , James Jarvo
CPC分类号： F01D25/20 , F01D15/08 , F01D15/12 , F01M1/12 , F01M1/16 , B64C11/325 , F01D15/10 , F05D2220/323
摘要： A hybrid electric propulsion system for an aircraft is provided that includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, a propulsion unit, and a controller. The thermal engine has a main oil pump configured to be driven by the thermal engine. The gearbox is in communication with the thermal and electric motors. The propulsion unit includes a propeller having propeller blades, and a pitch change mechanism. The controller is in communication with the thermal and electric motors, the propulsion unit, and a memory storing instructions. The instructions when executed cause the controller to control the electric motor to operate using electrical power from the electric power storage unit to cause the main oil pump to actuate and produce a flow of engine oil to the pitch change mechanism for a period of time sufficient to feather the propeller blades.
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公开(公告)号：US10705038B2
公开(公告)日：2020-07-07
申请号：US16398492
申请日：2019-04-30
摘要： There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.
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公开(公告)号：US12043402B1
公开(公告)日：2024-07-23
申请号：US18373065
申请日：2023-09-26
摘要： An assembly for an aircraft propulsion system includes an intercooler assembly and a controller. The intercooler assembly includes an intercooler and a flow control assembly. The intercooler includes a primary air inlet, a primary air outlet, a secondary air inlet, and a secondary air outlet. The flow control assembly is disposed at the secondary air outlet. The flow control assembly includes an actuator and at least one flap. The actuator is configured to position the at least one flap in an open position, a closed position, and intermediate positions. The controller is configured to control the actuator to position the at least one flap in the open position, determine a hot-side heat transfer effectiveness of the intercooler and a hot-side mass flow rate for the intercooler, determine a cold-side mass flow rate of the intercooler, identify a position of the actuator, and identify a successful or an unsuccessful actuator range check for the actuator.
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公开(公告)号：US20240271577A1
公开(公告)日：2024-08-15
申请号：US18436826
申请日：2024-02-08
发明人： Yusuf Syed , Thomas Trevor Ricci , James Jarvo
摘要： A method of and system for operating a hybrid electric propulsion system for an aircraft in a start sequence is provided. The hybrid electric propulsion system includes a thermal engine, an electric motor, a gearbox, an electric power storage unit, and a propulsion unit having a propeller having propeller blades. The method includes: driving the propeller from a static state to a target rotational speed within a predetermined range of speeds using the electric motor; transitioning the propeller blades from a feathered mode to an unfeathered mode while the propeller is being driven at the target rotational speed solely by the electric motor; starting the thermal engine; and transitioning the driving of the propeller using the electric motor to driving the propeller using the thermal engine.
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公开(公告)号：US20190257777A1
公开(公告)日：2019-08-22
申请号：US16398492
申请日：2019-04-30
摘要： There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.
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公开(公告)号：US10513985B2
公开(公告)日：2019-12-24
申请号：US15333775
申请日：2016-10-25
发明人： Thomas Trevor Ricci
摘要： The described gas turbine engine includes a fire mitigation system in fluid system thereof, and includes an air-introduction component located in a fluid conveying conduit upstream of a liquid pump of the fluid system. The air-introduction component has a sacrificial element which remains in place during normal operation of the gas turbine engine but has a heat-induced failure point lower than that of a remainder of the fluid conveying conduit such that it fails when exposed to a threshold temperature greater than the heat-induced failure point. Failure of the sacrificial element allows air introduction into the fluid conveying conduit upstream of the liquid pump, thereby starving the liquid pump in the event of a fire condition generating the threshold temperature.
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公开(公告)号：US10317354B2
公开(公告)日：2019-06-11
申请号：US15357282
申请日：2016-11-21
摘要： There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.
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