Abstract: A combustion engine (10) comprises a radial compressor (16) in flow communication via a flow passage (22) with a compressor-combustor array (20) radially outward of the radial compressor (16), both rotatable around a central axis (12). The compressor-combustor (20) comprises an array of rotor blades (26). The walls of the blades (26) define a plurality of chambers (28, 30). Each chamber (28, 30) has a flow inlet (32) to receive fluid from the radial compressor (16), and a flow outlet to exhaust fluid radially outwards from the compressor-combustor (20). The plurality of chambers (28, 30) comprises a first pilot combustion chamber (28a) and a second pilot combustion chamber (28b). The first pilot combustion chamber (28a) is provided with a first fuel injector (40a), and the second pilot combustion chamber (28b) is provided with a second fuel injector (40a).

Abstract: A combustion engine comprising a radial compressor in flow communication via a flow passage with an annular compressor-combustor array radially outward of the radial compressor. Both the radial compressor and compressor-combustor are co-axial with, and rotatable around, a central axis.