GB716859A - Improvements in or relating to airplane cabin compressors - Google Patents

Abstract

716,859. Centrifugal compressors. CONAN, Y. July 17, 1951 [July 28, 1950], No. 17325/53. Divided out of 716,793. Class 110(1) [Also in Group XXXV] In an aircraft cabin compressor, the compression ratio is automatically controlled by a device at the compressor discharge which actuates electric contacts in accordance with the compressor output, whereby an electric motor is energized to run in either direction of rotation to adjust a governor at the intake pipe. The output of the compressor 108, Fig. 1, is governed by a flow-sensitive means comprising a venturi 107 of which the throat 109 is connected to an airtight casing 110 and the divergent nozzle 112 is connected to the interior of two or more interconnected aneroid capsules 111, 111<SP>1</SP>. When the compressor output increases or decreases sufficiently from the normal value, a cam 114 actuated by the capsules closes a switch 115 or 116 respectively whereby an electric motor 117 is driven in the appropriate direction to decrease or increase respectively the compressor intake opening 121. For this purpose, shutters 120, 1201 are operated by the motor through pinion 118 and rack 119. A cam 122 on shutter 120 opens a limit switch 123 to stop the motor when the intake opening is a maximum. Preferably instead, a limiting means is embodied in the motor. In a modification, Fig. 2, the intake opening is controlled by shutters 124, each pivoted at 133 and actuated in unison by the engagement of spigots 134 with slide blocks 135 carried by a ring 128. The ring 128 is rotated by a motor 125 through worm gearing 126.