GB473133A - Improvements in or relating to temperature control apparatus for engines - Google Patents

Abstract

473,133. Cooling turbines. OFFEN, A. April 1, 1936, No. 9682. [Class 110 (iii)] In an engine the control of the temperature of two relatively moving parts between which fine clearances are to be maintained is carried out by controlling the supply of cooling medium to one part by a differential thermostatic control dependent upon the temperatures of the cooling circuit and that of the other part. In a gas turbine of the type described in Specification 469,180, the clearances between the rotor and valve are maintained by adjusting the position of the butterfly valve 129. in the scavenging duct 29. This valve is controlled by the bellows 364, 352 acting through rack 181 and pinion 182. A rise in temperature of the rotor and consequently the scavenging air. causes the liquid in bulb 164 to expand, and bellows 364 expand and move rack 181. An increase in temperature of the valve cooling medium causes the liquid in bulb 152 to expand, and bellows 352 to expand, and rotate bellcrank levers 172, 173 about pivot 174 to move bellows 364 bodily to the right, so counteracting any effect of the expansion of bellows 364. A sudden increase in temperature of the rotor will open butterfly valve 129, but as soon as the turbine valve warms up it will be closed again. The Provisional Specification describes an arrangement in which a separate cooling circuit for each part is provided, one of them having a thermostatically controlled valve governed by the temperature conditions in the other part. Specification 445,550 also is referred to.