GAS LASER APPARATUS, METHOD AND TURBINE COMPRESSOR THEREFOR

摘要

For use in a gas later apparatus a turbine type compressor comprising an impeller rotatable about an axis and having a plurality, of blades thereon for compressing gas, apparatus defining a passage opposite the blades of the impeller with an inlet and an outlet being provided in the passage for communicating gas to be compressed to and from the passage, apparatus for rotating the impeller and the blades thereon to compress the gas, and wherein the compressor is capable of operating with a pressure ratio sufficient to flow gas at a speed of at least half the speed of sound in the gas in a fast axial flow laser with inlet pressures to the compressor of less than one-third atmospheric pressure.