Abstract: A micro power unit comprises a Rankine cycle circuit powered by combustion of hydrocarbon fuel from tank (2). Combustion takes place on a combustion catalyst (6) in a chamber (5). The fluid circuit includes a boiler (10), turbine (11), a condenser (12) and feed pump (13). The feed pump impeller (13A) is driven by magnetic coupling with the turbine rotor (11A) and further magnetic couplings may be used to drive e.g. a propeller (15) for a micro air vehicle and/or electrical generator (16).

Abstract: A micro power unit comprises a Rankine cycle circuit powered by combustion of hydrocarbon fuel from tank (2). Combustion takes place on a combustion catalyst (6) in a chamber (5). The fluid circuit includes a boiler (10), turbine (11), a condenser (12) and feed pump (13). The feed pump impeller (13A) is driven by magnetic coupling with the turbine rotor (11A) and further magnetic couplings may be used to drive e.g. a propeller (15) for a micro air vehicle and/or electrical generator (16).

Abstract: A flow controller (5) for supplying air to a combustor and a combustor incorporating the same are disclosed. The flow controller comprising a conduit (6, 7, 8) and a control port (9), the conduit including a main section (8) dividing into at least two secondary sections (6, 7) at a junction and the control port being positioned in the conduit adjacent to the junction. In one embodiment, the control port is connected to a reservoir (10) wherein, in use, a change in the flow rate of a main airflow flowing through the main section of conduit causes a control airflow to flow either into or out of the control port whereby the main airflow is selectively diverted into one or other of the secondary sections of conduit. The main airflow may coanda around a surface of the main section. The control port may also be connected to the conduit further upstream of the junction so as to form a control loop (16). The main section of conduit may comprise a convergent-divergent duct.

Abstract: The present invention provides gas turbine reheat combustion apparatus for aircraft propulsion. The apparatus includes means for producing a flame stabilization zone in a stream of combustion supporting gas flowing in a duct, said stabilization zone having a recirculatory flow region therein, an injector for introducing a fluid comprising an inert diluent such as, for example, nitrogen, into the recirculatory flow region, and means for supplying the fluid to the injector.