GB1054739A - - Google Patents

Abstract

1,054,739. Gas turbine engines. L. HUBER. Sept. 14, 1965 [Oct. 14, 1964], No.39210/65. Heading F1G. [Also in Division H1] A thermoelectric generator comprises a plurality of thermocouple elements 11 the hot junctions 15 of which are disposed in a surface which surrounds but does not engage an oscillating column combustion chamber 1, 4. Combustion gases are fed by the end 5 of the coil 4 to a radial turbine 6 and pass through a first silencer 8 and pipe 9 to a second silencer 41, Fig. 4 (not shown), which exhausts through a coiled tube 45 leading to an ejector 47. The reduced pressure produced by the ejector may be employed to evacuate the interior of the ceramic jacket 10, in which the thermocouple elements 11 are mounted, or to evacuate the labyrinth packing 30 of the turbine, pipes 26, 29 being provided for this purpose. Alternatively, as shown, the pipes 26, 29 may be connected to the reduced pressure region inside a cap 28 housing the air intake valve 2 of the combustion chamber. Outside air enters this region through bores 28b, 28c, and the air inlet can be throttled by rotating the cap 28 so that the magnitude of the reduced pressure can be controlled. If large leaks develop in the combustion chamber the exhaust gases entering the cap 28 via the pipes 26, 27 will disturb the air-to-fuel ratio in the chamber and combustion will be extinguished. The turbine 6 drives an impeller 22 which blows air through the space between the ceramic jacket 10 and an outer pipe 25 where it flows over cooling vanes 17 attached to the cold junctions of the thermocouples. The air subsequently flows over the second silencer 41 and the coiled tube 45 and may thereafter be used for space heating.