Abstract: An engine assembly (10) for a propeller-driven aircraft is disclosed, the assembly including an engine (11), a drive shaft (13) driven by the engine (11), and a radiator (20) comprising an aperture (24) for receiving the drive shaft (13), the aperture (24) being located such that the radiator (20) substantially circumferentially surrounds the drive shaft (13). The aperture (24) may take various forms, such as a hole within the interior of the radiator (20) or a blind slit formed within the radiator (20).

Abstract: An engine assembly (10) for a propeller-driven aircraft is disclosed, the assembly including an engine (11), a drive shaft (13) driven by the engine (11), and a radiator (20) comprising an aperture (24) for receiving the drive shaft (13), the aperture (24) being located such that the radiator (20) substantially circumferentially surrounds the drive shaft (13). The aperture (24) may take various forms, such as a hole within the interior of the radiator (20) or a blind slit formed within the radiator (20).

Abstract: A rotary engine rotor (10) comprising three rotor flanks (12) arranged in a generally equilateral triangle shape, each rotor flank (12) having a leading edge (16) and a trailing edge (17), an elongate lip (21) being provided on the leading edge (16) of at least one of the rotor flanks (12), the elongate lip (21) extending the full axial length of the rotor flank (12). In another aspect, at least one rotor flank (12) comprises a cavity having a leading edge and a trailing edge, and at least a portion of the base of the cavity proximal to a trailing edge thereof is curved outwardly.

Abstract: A rotary engine rotor (10) comprises a body (12) comprising an outer surface (18), an inner surface (22), an insert (14) and a fixing member (16). The outer surface (18) comprises three rotor sides (20) arranged in an equilateral triangle shape. The inner surface (22) comprises a location portion (24) at the midpoint of each rotor side (20), the location portions (24) together defining a location aperture (26). One location portion (24) is provided with a first fixing socket (28) extending radially from the inner surface (22) of the body (12), towards the outer surface (18) of the body (12). Cooling channels (30) are provided axially through the body (12) in the region of each apex (31). The insert (14) is provided in the location aperture (26) and comprises a bearing part (38) with a second fixing socket (40) extending radially through the insert (14) and in alignment with the first fixing socket (28).

Abstract: A rotary engine rotor (10) comprises a body (12) comprising an outer surface (18), an inner surface (22), an insert (14) and a fixing 31 member (16). The outer surface (18) comprises three rotor sides (20) arranged in an equilateral triangle shape. The inner surface (22) comprises a location portion (24) at the midpoint of each rotor side (20), the location portions (24) together defining a location aperture (26). One location portion (24) is provided with a first fixing socket (28) extending radially from the inner surface (22) of the body (12), towards the outer surface (18) of the body (12). Cooling channels (30) are provided axially through the body (12) in the region of each apex (31). The insert (14) is provided in the location aperture (26) and comprises a bearing part (38) with a second fixing socket (40) extending radially through the insert (14) and in alignment with the first fixing socket (28).