Abstract: An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is configured to receive at least part of the pulsed flow. The first and second outlet nozzles each define a respective nozzle area communicating between the internal volume and a flow path of the turbine. The first and second outlet nozzles are spaced from one another with the first outlet nozzle located closer to the inlet port than the second outlet nozzle relative to a flow direction through the duct, the nozzle area of the first outlet nozzle being smaller than the nozzle area of the second outlet nozzle. A compound engine assembly and method of introducing a pulsed flow into a flow path of a turbine are also discussed.

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: A compound engine assembly with an engine core including at least one internal combustion engine, a compressor, and a turbine section where the turbine shaft is configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft is rotationally supported by a plurality of bearings all located on a same side of the compressor rotor(s) and all located on a same side of the turbine rotor(s), for example all located between the compressor rotor(s) and the turbine rotor(s), such that the compressor rotor(s) and the turbine rotor(s) are cantilevered. A method of driving a rotatable load of an aircraft is also discussed.

Abstract: A compound cycle engine having an output shaft, at least two rotary units each including an internal combustion engine with the rotor of each rotary unit mounted on the output shaft and in driving engagement therewith, and a turbine including a rotor in driving engagement with the output shaft. The exhaust port of each rotary unit housing is in fluid communication with the flowpath of the turbine upstream of its rotor. The turbine is disposed co-axially between two of the rotary units. The engine may further include a compressor in fluid communication with the inlet port of each housing and a second turbine having an inlet in fluid communication with the flowpath of the first turbine downstream of its rotor. A method of compounding rotary engines is also discussed.

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: In one aspect, described is a rotor of a rotary internal combustion engine, including a phasing gear with an annular meshing section including a plurality of radially inwardly oriented teeth and an annular attachment section connected to the meshing section and coaxial therewith, the attachment section being offset axially inwardly from the teeth and having at least a portion thereof located radially inwardly of the teeth, and a fastener apparatus connecting the phasing gear to the rotor body, the fastener apparatus engaging the rotor body radially inwardly of the teeth.

Abstract: A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a velocity turbine, and a turbocharger is discussed. The velocity turbine includes a rotor in driving engagement with the output shaft between two of the rotary units. The exhaust port of each rotary unit is in fluid communication with the flowpath of the velocity turbine upstream of its rotor. The outlet of the compressor of the turbocharger is in fluid communication with the inlet port of each rotary unit. The inlet of the pressure turbine of the turbocharger is in fluid communication with the flowpath of the velocity turbine downstream of its rotor. A method of compounding at least two rotary engines is also discussed.

Abstract: A valve cage for a fluid flow control device includes a hollow cylindrical body, a noise abatement section, a high capacity flow section, and a transition section. The noise abatement section has a plurality of inlet openings, a plurality of outlet openings, and a plurality of tortuous flow paths extending between the inlet and outlet openings. The high capacity flow section is disposed axially adjacent to the noise abatement section and includes a first axial end, a second axial end, and a plurality of primary flow openings. The transition section is defined at an interface between the noise abatement section and the second axial end of the high capacity flow section and includes a plurality of transition openings. The transition section provides a valve cage with zero dead band between the noise abatement and high capacity flow sections when implemented into a fluid flow control device.

Abstract: A rotary internal combustion engine having an insert opening defined in a hot area of one of the walls of the stator body and in communication with its internal cavity, at least one groove defined within the opening around a perimeter thereof, at least one coolant inlet channel defined therein in communication with each groove, and at least one coolant outlet channel defined therein in communication with each groove. A cooling jacket lines the insert opening, the cooling jacket cooperating with each groove to define a cooling gallery around the insert opening. An insert is sealingly received in the cooling jacket, the insert being made of a material having a greater heat resistance than that of the wall.

Abstract: A rotor of a rotary internal combustion engine, including an annular oil seal assembly snugly received within each oil seal groove, each oil seal assembly including a seal ring retaining first and second axially spaced apart annular sealing elements in substantial radial alignment with one another, the seal ring radially pressing each of the sealing elements in sealing engagement with a respective surface in the groove in opposite directions from one another, and a spring member biasing the seal ring axially away from the end face.

Abstract: A valve cage for a fluid flow control device includes a hollow cylindrical body, a noise abatement section, a high capacity flow section, and a transition section. The noise abatement section has a plurality of inlet openings, a plurality of outlet openings, and a plurality of tortuous flow paths extending between the inlet and outlet openings. The high capacity flow section is disposed axially adjacent to the noise abatement section and includes a first axial end, a second axial end, and a plurality of primary flow openings. The transition section is defined at an interface between the noise abatement section and the second axial end of the high capacity flow section and includes a plurality of transition openings. The transition section provides a valve cage with zero dead band between the noise abatement and high capacity flow sections when implemented into a fluid flow control device.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

Abstract: A rotary internal combustion engine having an insert opening defined in a hot area of one of the walls of the stator body and in communication with its internal cavity, at least one groove defined within the opening around a perimeter thereof, at least one coolant inlet channel defined therein in communication with each groove, and at least one coolant outlet channel defined therein in communication with each groove. A cooling jacket lines the insert opening, the cooling jacket cooperating with each groove to define a cooling gallery around the insert opening. An insert is sealingly received in the cooling jacket, the insert being made of a material having a greater heat resistance than that of the wall.

Abstract: A gas turbine engine case having a working fluid flow, includes inner and outer case portions defining an annular duct for directing the working fluid flow, and a plurality of struts positioned within the annular duct and extending between the inner and outer case portions. The struts are welded to the inner and outer case portions with a first weld along a peripheral line of the respective struts and with second weld, of fillet type, in selected locations for additionally connecting a portion of each strut to the respective inner and outer case portions.

Abstract: A rotor of a rotary internal combustion engine including apex springs each being formed of a continuous band including first and second opposed end sections each contacting the inner surface of the apex seal adjacent to a respective one of the end faces, a respective intermediate section extending radially inwardly from each end section and contacting the outer surface of the groove along a respective contact zone, and a central section extending axially between the intermediate sections and having a portion extending radially outwardly from each of the intermediate sections, the central section extending out of contact with both the outer surface of the groove and the apex seal.

Abstract: In one aspect, described is a rotor of a rotary internal combustion engine, including a phasing gear with an annular meshing section including a plurality of radially inwardly oriented teeth and an annular attachment section connected to the meshing section and coaxial therewith, the attachment section being offset axially inwardly from the teeth and having at least a portion thereof located radially inwardly of the teeth, and a fastener apparatus connecting the phasing gear to the rotor body, the fastener apparatus engaging the rotor body radially inwardly of the teeth.

Abstract: A rotor of a rotary internal combustion engine, including an annular oil seal assembly snugly received within each oil seal groove, each oil seal assembly including a seal ring retaining first and second axially spaced apart annular sealing elements in substantial radial alignment with one another, the seal ring radially pressing each of the sealing elements in sealing engagement with a respective surface in the groove in opposite directions from one another, and a spring member biasing the seal ring axially away from the end face.

Abstract: A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner and outer case portions, airfoils structurally connecting the inner case portion to the outer case portion.

Abstract: A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner and outer case portions, airfoils structurally connecting the inner case portion to the outer case portion.

Abstract: A structural turbine exhaust case of a gas turbine engine, comprises inner and outer case portions; a bearing housing connected to the inner case portion for supporting a main spool of the gas turbine engine; and a plurality of airfoils extending between the inner and outer case portions, airfoils structurally connecting the inner case portion to the outer case portion.