Abstract: An oil supply system for supplying oil to a lubricating cavity of a gas turbine engine, the oil supply system has: a de-oiler having a de-oiler air-oil inlet, a de-oiler oil outlet hydraulically connected to the lubricating cavity, and a de-oiler air outlet in fluid flow communication with an environment outside of the oil supply system; and a closed-loop oil circuit including a main pump having a main pump inlet and a main pump outlet, the main pump outlet hydraulically connected to the lubricating cavity, a de-aerator having a de-aerator inlet hydraulically connected to a scavenge outlet of the lubricating cavity, a de-aerator air-oil outlet in fluid flow communication with the de-oiler inlet, and a de-aerator oil outlet hydraulically connected to the main pump inlet.

Abstract: Systems and methods for regulating oil flow to an engine are described herein. An oil pressure target for the engine is determined based on one or more engine operating parameters. Oil flow to the engine is controlled based on the oil pressure target. Closed-loop feedback of oil pressure of the engine is obtained from at least one sensor during the controlling of the oil flow to the engine. A pressure difference between the oil pressure target and the closed-loop feedback of the oil pressure of the engine is determined. The oil flow to the engine is adjusted based on the pressure difference.

Abstract: An aircraft engine having a shaft, an engine casing, at least one bearing located between the shaft and the engine casing, the engine casing defining a bearing cavity containing the at least one bearing, an air distribution system configured to inject compressed air to the bearing cavity to in use provide a sealing air flow entering the bearing cavity, and a labyrinth seal having a seal rotor and a seal stator, fins extending from one of the seal rotor and the seal stator toward the other of the seal rotor and the seal stator, at least one of the fins extending in an angled upstream direction relative to a direction of the sealing air flow.

Abstract: An oil supply system for supplying oil to a lubricating cavity of a gas turbine engine, the oil supply system has: a de-oiler having a de-oiler air-oil inlet, a de-oiler oil outlet hydraulically connected to the lubricating cavity, and a de-oiler air outlet in fluid flow communication with an environment outside of the oil supply system; and a closed-loop oil circuit including a main pump having a main pump inlet and a main pump outlet, the main pump outlet hydraulically connected to the lubricating cavity, a de-aerator having a de-aerator inlet hydraulically connected to a scavenge outlet of the lubricating cavity, a de-aerator air-oil outlet in fluid flow communication with the de-oiler inlet, and a de-aerator oil outlet hydraulically connected to the main pump inlet.

Abstract: Systems and methods for regulating oil flow to an engine are described herein. An oil pressure target for the engine is determined based on one or more engine operating parameters. Oil flow to the engine is controlled based on the oil pressure target. Closed-loop feedback of oil pressure of the engine is obtained from at least one sensor during the controlling of the oil flow to the engine. A pressure difference between the oil pressure target and the closed-loop feedback of the oil pressure of the engine is determined. The oil flow to the engine is adjusted based on the pressure difference.

Abstract: An aircraft engine having a shaft, an engine casing, at least one bearing located between the shaft and the engine casing, the engine casing defining a bearing cavity containing the at least one bearing, an air distribution system configured to inject compressed air to the bearing cavity to in use provide a sealing air flow entering the bearing cavity, and a labyrinth seal having a seal rotor and a seal stator, fins extending from one of the seal rotor and the seal stator toward the other of the seal rotor and the seal stator, at least one of the fins extending in an angled upstream direction relative to a direction of the sealing air flow.

Abstract: An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed.

Abstract: An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed.

Abstract: A compound engine assembly including a common air conduit having an inlet in fluid communication with ambient air, a compressor, at least one internal combustion engine having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the at least one internal combustion engine, the turbine section configured to compound power with the at least one internal combustion engine, and at least one heat exchanger in fluid communication with the common air conduit, each of the at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the common air conduit circulating therethrough. The compressor has an inlet in fluid communication with the common air conduit upstream of the at least one heat exchanger. The internal combustion engine may be a reciprocating engine.

Abstract: An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed.

Abstract: The method for testing the integrity of a seal of a cavity in an engine includes providing a sealed test tank external to the cavity, the test tank having an internal volume that is particularly selected, as described herein. A pressure differential is generated between the test tank and the cavity, by creating an initial test pressure within the test tank that is different than an ambient pressure inside the cavity. Gas flow between the test tank and the cavity is then permitted, and a change in pressure within the test tank is measured, as is a test time required for the pressure inside the test tank to reach a reference pressure. The measured test time is compared with a predetermined reference time, and the integrity of the seal may be confirmed when the test time is greater than or equal to the reference time.

Abstract: A gas turbine engine including a secondary air system with interconnected fluid passages defining at least one flow path between a common source of pressurized air and a common outlet. Some of the fluid passages deliver the pressurized air to components of the gas turbine engine. The fluid passages include a common fluid passage through which all circulation of the pressurized air to the common outlet passes. The common fluid passage has a section including a venturi configured for controlling a flow of the pressurized air from the source to the outlet. In one embodiment, the venturi is provided in a common inlet or common outlet passage. A method of pressurizing a secondary air system is also discussed.

Abstract: An engine assembly including an engine core including at least one internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide rotating chambers of variable volume in the respective internal cavity, a compressor having an outlet in fluid communication with an inlet of the engine core, a first intake conduit in fluid communication with an inlet of the compressor and with a first source of air, a second intake conduit in fluid communication with the inlet of the compressor and with a second source of air warmer than the first source of air, and a selector valve configurable to selectively open and close at least the fluid communication between the inlet of the compressor and the first intake conduit. A method of supplying air to a compressor is also discussed.

Abstract: A compound engine assembly having an engine core including at least one internal combustion engine in driving engagement with an engine shaft, a compressor having an outlet in fluid communication with an inlet of the engine core and including at least one rotor rotatable about an axis coaxial with the engine shaft, the engine shaft in driving engagement with the compressor rotor, and a turbine section having an inlet in fluid communication with an outlet of the engine core and including at least one rotor engaged on a rotatable turbine shaft, the turbine shaft configured to compound power with the engine shaft. The turbine and engine shafts are parallel to and radially offset from one another, and the turbine shaft and the axis of the compressor rotor are parallel to and radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.

Abstract: A compound engine assembly including a compressor, an engine core including at least one rotary internal combustion engine and having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the engine core and configured to compound power with the engine core, and an air conduit having at least one heat exchanger extending thereacross. An outer wall of the air conduit has a plurality of openings defined therethrough downstream of the heat exchanger(s), each selectively closable by a pivotable flap movable between a retracted position where the opening is obstructed and an extended position away from the opening. Each opening defines a fluid communication between the air conduit and the ambient air when the respective flap is in the extended position. A method of directing flow through a compound engine assembly is also discussed.

Abstract: A compound engine assembly including a common air conduit having an inlet in fluid communication with ambient air, a compressor, at least one internal combustion engine having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the at least one internal combustion engine, the turbine section configured to compound power with the at least one internal combustion engine, and at least one heat exchanger in fluid communication with the common air conduit, each of the at least one heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the common air conduit circulating therethrough. The compressor has an inlet in fluid communication with the common air conduit upstream of the at least one heat exchanger. The internal combustion engine may be a reciprocating engine.

Abstract: An intake assembly for a compressor providing compressed air to an internal combustion engine core, including an air conduit having at least one heat exchanger extending thereacross, an intake plenum for the compressor, a first intake conduit connected to the air conduit upstream of the heat exchanger(s), a second intake conduit connected to the air conduit downstream of the heat exchanger(s), and a selector valve configurable between a first configuration to allow a fluid communication between the intake plenum and the air conduit through the first intake conduit and a second configuration to prevent the fluid communication through the first intake conduit. Fluid communication between the intake plenum and the air conduit through the second intake conduit is allowed at least when the selector valve is in the second configuration. An engine assembly and method of supplying air to a compressor are also discussed.

Abstract: The method for testing the integrity of a seal of a cavity in an engine includes providing a sealed test tank external to the cavity, the test tank having an internal volume that is particularly selected, as described herein. A pressure differential is generated between the test tank and the cavity, by creating an initial test pressure within the test tank that is different than an ambient pressure inside the cavity. Gas flow between the test tank and the cavity is then permitted, and a change in pressure within the test tank is measured, as is a test time required for the pressure inside the test tank to reach a reference pressure. The measured test time is compared with a predetermined reference time, and the integrity of the seal may be confirmed when the test time is greater than or equal to the reference time.

Abstract: A compound engine assembly including an air conduit having an inlet in fluid communication with ambient air around the compound engine assembly, a compressor having an inlet in fluid communication with the air conduit, an engine core including at least one rotary internal combustion engine and having an inlet in fluid communication with an outlet of the compressor, a turbine section having an inlet in fluid communication with an outlet of the engine core and configured to compound power with the engine core; and at least one heat exchanger in fluid communication with the air conduit, each heat exchanger configured to circulate a fluid of the engine assembly in heat exchange relationship with an airflow from the air conduit circulating therethrough. A method of supplying air to a compound engine assembly is also discussed.

Abstract: A fluid delivery assembly for delivering fluid to a component in a gas turbine engine includes a rotating shaft having a central bore and at least one fluid exhaust in communication with the central bore for centrifugally expelling fluid, and a delivery scoop disposed around the rotating shaft and spaced apart from the rotating shaft by an annular gap. The delivery scoop includes an annular body having at least one impingement surface facing the at least one fluid exhaust and configured to scoop the fluid expelled by the at least one fluid exhaust. The impingement surface has at least one outlet for delivering the scooped fluid to the component. A method of delivering pressurised fluid in a fluid system is also presented.