Abstract: An engine housing includes a rotor housing body, a side housing body a side plate and a seal assembly. The rotor housing body extends about an axis to form a rotor cavity. The rotor housing body extends between and to a first axial end and a second axial end. The side housing body is disposed at the first axial end. The side plate includes an inner side, an outer side, and a perimeter edge extending from the inner side to the outer side. The seal assembly includes a support ring and a spacer. The support ring and the spacer extend about the axis. The support ring is mounted to the perimeter edge by a braze joint. The spacer extends between and to a first axial spacer end and a second axial spacer end. The first axial spacer end is disposed at the support ring and the outer side.

Abstract: An engine assembly includes a propulsor, a first gearbox, an engine, a gas turbine engine, and a variable speed drive. The first gearbox includes a first gear assembly coupled with the propulsor. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The engine output shaft is coupled with the first gear assembly. The gas turbine engine includes a first rotational assembly, a compressor section, a turbine section, and a combustor. The first rotational assembly is configured for rotation about a rotational axis. The first rotational assembly includes a bladed compressor rotor, a bladed first turbine rotor, and a first shaft interconnecting the bladed compressor rotor and the bladed first turbine rotor. The compressor section is connected to the air inlet. The combustor is connected to the exhaust outlet. The VSD couples the first rotational assembly to the first gear assembly.

Abstract: An engine housing for an aircraft rotary engine includes a rotor housing and a side housing assembly. The rotor housing includes a rotor housing body. The rotor housing body extends about an axis to form a rotor cavity of the engine housing. The rotor housing body extends between and to a first axial end and a second axial end. The side housing assembly includes a side housing body, a side plate, and a seal assembly. The side housing body is disposed at the first axial end. The side plate includes an inner side, an outer side, and a perimeter edge extending from the inner side to the outer side. The seal assembly includes a support ring and a spacer. The support ring and the spacer extend about the axis. The support ring is mounted to the perimeter edge by a braze joint. The spacer extends between and to a first axial spacer end and a second axial spacer end. The first axial spacer end is disposed at the support ring and the outer side.

Abstract: A rotary internal combustion engine includes a rotor housing having a peripheral wall circumscribing a rotor cavity and a rotor disposed within the rotor cavity. A side housing is secured to the rotor housing and a plate defines a seal running surface for the rotor. The plate is disposed between a portion of the side housing and the rotor housing and at least one shim is disposed between the plate and the side housing for spacing the plate apart from contact with the side housing.

Abstract: An engine housing includes a rotor housing and a side housing assembly. The rotor housing includes a rotor housing body. The rotor housing body extends about an axis to form a rotor cavity of the engine housing. The rotor housing body extends between and to a first axial end and a second axial end. The side housing assembly includes a side housing body, a side plate, and a seal assembly. The side housing body is disposed at the first axial end. The side plate is disposed axially between the rotor housing body and the side housing body. The side plate includes an inner side, an outer side, and a perimeter edge. The seal assembly includes a support ring and a sealing ring. The support ring is disposed at the perimeter edge and the first axial end. The support ring circumscribes the side plate. The sealing ring extends between and to a first axial sealing ring end and a second axial sealing ring end. The first axial sealing ring end is disposed at the support ring and the outer side.

Abstract: A rotary internal combustion engine includes a rotor housing having a peripheral wall circumscribing a rotor cavity and a rotor disposed within the rotor cavity. A side housing is secured to the rotor housing and a plate defines a seal running surface for the rotor. The plate is disposed between a portion of the side housing and the rotor housing and at least one shim is disposed between the plate and the side housing for spacing the plate apart from contact with the side housing.

Abstract: An assembly includes a rotor housing, a first rotor, a lubrication system, a first vibration sensor, and an engine control system. The rotor housing forms a first rotor cavity. The first rotor is configured for rotation within the first rotor cavity. The first rotor includes the plurality of apex seals. The lubrication system is configured to supply a lubrication flow for lubrication of the plurality of apex seals. The first vibration sensor is on the rotor housing. The first vibration sensor is configured to generate a vibration measurement signal. The engine control system includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: identify that the vibration measurement signal exceeds a first vibration threshold, and increase a flow rate of the lubrication flow based on an identification of the vibration measurement signal exceeding the first vibration threshold.

Abstract: A side housing for a rotary internal combustion engine, has: a side wall; a side plate having a rotor-engaging side facing away from the side wall and a back side opposite the rotor-engaging side and facing the side wall, the side plate defining first threads located on the back side, the first threads extending circumferentially around a central axis of the side plate; and a nut rotatable relative to the side wall about the central axis of the side plate and axially locked to the side wall relative to the central axis, the side plate secured to the side wall via a threaded engagement between the first threads of the side plate and second threads defined by the nut.

Abstract: A rotary internal combustion engine has: a rotor; a housing circumscribing a rotor cavity, the rotor received within the rotor cavity, the housing having a peripheral wall and a side housing assembly secured to the peripheral wall, the side housing assembly having plates located at spaced apart ends of the peripheral wall, the plates defining seal running surfaces in sealing engagement with opposed end faces of the rotor, the plates made of silicon carbide.

Abstract: A housing for a rotary engine has: a peripheral wall defining two end faces and an inner face transverse to the two end faces; two side walls sealingly engaged to the two end faces of the peripheral wall, a core of a side wall of the two side walls having a core face, the core face having a cavity section facing the rotor cavity and an abutment section annularly extending around the cavity section, the abutment section facing an end face of the two end faces, the abutment section having a flared portion flaring away from the end face; and a coating on the core face, the coating made of a material harder than a material of the core of the side wall, the coating covering the cavity section and ending at a coating edge located on the flared portion, the coating edge free of contact with the end face.

Abstract: A mounting arrangement for mounting a rotary engine to an aircraft structure, wherein the engine has a three orthogonal axes comprising: a roll axis; a pitch axis; and a yaw axis. The mounting arrangement comprises: one-degree-of-freedom links with reaction axes passing through the roll axis. A separate roll constraint has a moment reaction about the roll axis to decouple the torque roll mode from the other one-degree-of-freedom links.

Abstract: A rotor assembly for a rotary internal combustion engine is provided. The rotor assembly includes a rotor having a radial groove defined radially in a peripheral surface of the rotor. The groove has a depth and an intermediate shoulder at an intermediate depth. The groove has a first width therealong that is narrower than an intermediate width at the shoulder. An apex seal is received in the groove and protrudes from the peripheral face of the rotor. The apex seal is configured to move radially between a first position and a second position outward of the first position. A biasing member biases the apex seal toward the second position. A platform is disposed in the groove between the apex seal and the biasing member and has a width greater than the first width.

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 mounting arrangement for mounting a rotary engine to an aircraft structure, wherein the engine has a three orthogonal axes comprising: a roll axis; a pitch axis; and a yaw axis. The mounting arrangement comprises: one-degree-of-freedom links with reaction axes passing through the roll axis. A separate roll constraint has a moment reaction about the roll axis to decouple the torque roll mode from the other one-degree-of-freedom links.

Abstract: Systems and methods for detecting at least one non-functional combustion chamber of an engine comprising a plurality of combustion chambers are described herein. In response to detecting a partial output power loss of the engine, one of the plurality of combustion chambers is assessed by monitoring an engine parameter indicative of an output power of the engine, determining whether a change in the engine parameter has occurred, when the change has occurred, determining that the combustion chamber is functional, and when no change has occurred, determining that the combustion chamber is non-functional and discontinuing fuel injection to the non-functional combustion chamber.

Abstract: A rotor assembly for a rotary internal combustion engine is provided. The rotor assembly includes a rotor having a radial groove defined radially in a peripheral surface of the rotor. The groove has a depth and an intermediate shoulder at an intermediate depth. The groove has a first width therealong that is narrower than an intermediate width at the shoulder. An apex seal is received in the groove and protrudes from the peripheral face of the rotor. The apex seal is configured to move radially between a first position and a second position outward of the first position. A biasing member biases the apex seal toward the second position. A platform is disposed in the groove between the apex seal and the biasing member and has a width greater than the first width.

Abstract: A rotary internal combustion engine has: a rotor; a housing circumscribing a rotor cavity, the rotor received within the rotor cavity, the housing having a peripheral wall and a side housing assembly secured to the peripheral wall, the side housing assembly having plates located at spaced apart ends of the peripheral wall, the plates defining seal running surfaces in sealing engagement with opposed end faces of the rotor, the plates made of silicon carbide.

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 has an engine core comprising at least two stacks of rotary internal combustion engines drivingly connected to a common load. The engine further comprises a compressor section having an outlet in fluid communication with an inlet of the engine core, and a turbine section having an inlet in fluid communication with an outlet of the engine core.

Abstract: A rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by a first eccentricity and the rotor has a peripheral outer surface having a peritrochoid inner envelope configuration defined by a second eccentricity larger than the first eccentricity. Also, a rotary engine where the rotor cavity has a peripheral inner surface having a peritrochoid configuration defined by an eccentricity, and a rotor with a peripheral outer surface between adjacent ones of the apex portions being inwardly offset from a peritrochoid inner envelope configuration defined by the eccentricity. The engine may have an expansion ratio with a value of at most 8. The rotary engine may be part of a compound engine system.