Abstract: A micro air vehicle is propelled by a bipropellant micro engine supplied with hydrogen peroxide and a hydrocarbon fuel. The hydrogen peroxide is decomposed to produce steam and oxygen at high temperature and the hydrocarbon fuel is burnt within a combustion chamber with oxygen produced from such decomposition. Products of such decomposition and combustion are exited through a nozzle to produce thrust. In a preferred embodiment there is also a ducted turbofan located downstream of the nozzle exit.

Abstract: A torch igniter intended particularly for gas turbine engine applications comprises an integral assembly of a flame lighter and a fuel atomizer of the pre-filming air blast type. The fuel atomizer is configured so as to encircle the tip of the flame lighter and this atomizer comprises fuel and air inlets, a fuel/air passage defined between a body portion of the flame lighter and a sleeve this fuel air passage extending from the inlets to an exit mouth around the electrodes at the tip of the flame lighter, and an atomizer lip at the mouth of the fuel/air passage. A secondary passage can be included to aid in atomization of the fuel and in direction of the spray of atomized fuel this secondary passage having an exit annulus encircling the mouth of the fuel/air passage. A further passage can be included which is exposed to heat exchange with exterior air to pre-cool compressor delivery air before supply to the atomizer.

Abstract: A gas turbine combustion including a combustion wall having a plurality of generally cylindrical passages therein which extend around and are generally parallel to, the chamber axis, each of said passages having a series of air inlets disposed along the passage and tangentially directed thereinto, generally towards the center of the chamber, and means for directing cooling air into the series of air inlets in each passage to set up a forced vortex therein. The series of air inlets may be arranged to set up forced vortices of opposite rotation in adjacent passage. A means for directing cooling air into the tube inlets may comprise an annular shroud which extends around the air inlets and directs airflow into the air inlets.