A combustion engine 10 comprises a radial compressor 16 in flow communication with a compressor-combustor 20. Both the radial compressor and compressor-combustor are rotatable around a central axis 12. The compressor-combustor comprises an array of rotor blades (26, figure 3) defining a plurality of chambers (28, 30) each having a flow inlet (32) and a flow outlet (34). The chambers comprises a first pilot combustion chamber (28a) having a first fuel injector (40a), and a second pilot combustion chamber (28b) having a second fuel injector (40b). The first fuel injector is in flow communication with a first fuel reservoir 70a, and the second fuel injector is in flow communication with a second fuel reservoir 70b. The first fuel reservoir and the second fuel reservoir are each in communication with a flow regulator (100, figure 5) which is operable to vary fuel flow delivery rate to the first and second reservoir. The differential regulation of fuel flow between pilot combustion chambers results in different levels of thrust being generated downstream of the combustion chambers. In this way the engine is operable to produce vectored thrust.
展开▼
