Gas laser apparatus, method and turbine compressor therefor

Claim 2

A two stage, double sided, regenerative turbine type compressor comprising an impeller rotatable about an axis and having a plurality of blades thereon for forming first and second stages of said compressor on respective sides of said impeller for compressing gas, means defining a passage opposite said blades of the impeller with an inlet and an outlet being provided in said passage for communicating gas to be compressed to and from said passage, means for rotating said impeller and the blades thereon to compress the gas, wherein said compressor has a pressure or head coefficient of at least 0.8 and is capable of operating with a pressure ratio for flowing gas at a speed of at least half the speed of sound in said gas in a fast axial flow laser with inlet pressures to said compressor of less than one-third atmospheric pressure, wherein an intercooler is provided between said first and second stages of said compressor for cooling gas compressed in said first stage before it enters the second stage for further compression, and wherein said means defining a passage opposite said blades includes means for cooling essentially the entire surface of both sides of the compressor and also the radially outer or circumferential surface thereof.

Claim 3

A compressor according to claim 1, wherein the blades of the impeller of said regenerative compressor are generally radial blades extending from at or near the tip of said impeller inward a maximum distance of about 50% of the radius of said impeller, and wherein said passage includes a pair of stationary annular passages for peripheral flow of gas in the direction of rotation of said impeller in respective ones of the first and second stages of the compressor.

Claim 4

A compressor according to claim 2, wherein an inlet and an outlet are provided in each stationary annular passage for communicating gas to be compressed to and from the annular passage, and wherein a dam is provided blocking each annular passage between the inlet and outlet, each dam having close clearance over the impeller.

Claim 5

A compressor according to claim 1, wherein said intercooler includes a heat exchanger and a coolant for heat exchange to cool said gas as it passes through said heat exchanger.

Claim 6

A compressor according to claim 2, wherein said means for rotatably driving said impeller comprises a drive shaft upon which said impeller is mounted for rotation at a first location, bearing means for rotatably supporting said drive shaft at a second location on said drive shaft, and a positive pressure fluid seal means located intermediate said first and second locations for preventing contamination and laser gas being compressed of said impeller and laser gas being compressed.

Claim 7

A regenerative turbine type compressor comprising an impeller rotatable about an axis and having a plurality of blades thereon for compressing gas, means defining a passage opposite said blades of the impeller with an inlet and an outlet being provided in said passage for communicating gas to be compressed to and from said passage, means for rotating said impeller and the blades thereon to compress the gas, wherein said compressor has a pressure or head coefficient of at least 0.8 and is capable of operating with a pressure ratio for flowing gas at a speed of at least half the speed of sound in said gas in a fast axial flow laser with inlet pressures to said compressor of less than one-third atmospheric pressure, wherein the blades of said impeller are generally radial blades extending from at or near the tip of said impeller inward a maximum distance of about 50% of the radius of said impeller, wherein said passage is a stationary annular passage for peripheral flow of gas in the direction of rotation of said impeller, wherein said means for rotably driving said impeller comprises a drive shaft upon which said impeller is mounted for rotation at a first location bearing means for rotatably supporting said drive shaft at a second location on said drive shaft, and a positive pressure fluid seal means located intermediate said first and second locations for preventing contamination from said bearing means from moving along said drive shaft in the direction of said impeller, and wherein said fluid seal means includes a mating ring sealingly attached to said drive shaft at a location between said first and second locations for rotation with said shaft, a pair of spaced stationary members presenting respective sliding faces adjacent respective opposite sides of said mating ring, and means for directing a fluid under a pressure above the pressure of gas in said compressor between said sliding faces and said mating ring and along said shaft during operation of said compressor to prevent contamination from said bearing means from moving along said drive shaft to said impeller.

Claim 8

A regenerative turbine type compressor comprising an impeller rotatable about an axis and having a plurality of blades thereon for compressing gas, means defining a passage opposite said blades of the impeller with an inlet and an outlet being provided in said passage for communicating gas to be compressed to and from said passage, means for rotating said impeller and the blades thereon to compress the gas, wherein said compressor has a pressure or head coefficient of at least 0.8 and is capable of operating with a pressure ratio for flowing gas at a speed of at least half the speed of sound in said gas in a fast axial flow laser with inlet pressures to said compressor of less than one-third atmospheric pressure, wherein the blades of said impeller are generally radial blades extending from at or near the tip of said impeller inward a maximum distance of about 50% of the radius of said impeller, wherein said passage is a stationary annular passage for peripheral flow of gas in the direction of rotation of said impeller, wherein said means for rotably driving said impeller comprises a drive shaft upon which said impeller is mounted for rotation at a first location bearing means for rotatably supporting said drive shaft at a second location on said drive shaft, and a positive pressure fluid seal means located intermediate said first and second locations for preventing contamination from said bearing means from moving along said drive shaft in the direction of said impeller, and wherein said fluid seal means includes a mating ring sealingly attached to said drive shaft at a location between said first and second locations for rotation with said shaft, a pair of spaced stationary members presenting respective sliding faces adjacent respective opposite sides of said mating ring, and means for directing a fluid under a pressure above the pressure of gas in said compressor between said sliding faces and said mating ring and along said shaft during operation of said compressor to prevent contamination from said bearing means from moving along said drive shaft to said impeller.

Claim 9

A compressor according to claim 6, wherein said regenerative compressor is a single stage compressor.

Claim 10

A compressor according to claim 6, wherein said regenerative compressor comprises at least two stages.

Claim 11

A compressor according to claim 8, wherein first and second stages of said compressor are located on respective sides of said impeller.

Claim 12

A compressor according to claim 8, wherein an intercooler is provided between said first and second stages of said compressor for cooling gas compressed in said first stage before it enters that second stage for further compression.

Claim 13

A regenerative turbine type compressor comprising an impeller rotatable about an axis and having a plurality of blades thereon for compressing gas, means defining a passage opposite said blades of the impeller with an inlet and outlet being provided in said passage for communicating gas to be compressed to and from said passage, means for rotating said impeller and the blades thereon to compress the gas, and wherein said compressor has a pressure or head coefficient of at least 0.8 and is capable of operating with a pressure ratio for flowing gas at a speed of at least half the speed of sound in said gas in a fast axial flow laser with inlet pressures to said compressor of less than one-third atmospheric pressure, wherein the blades of the impeller of said regenerative compressor are generally radial blades extending from at or near the tip of said impeller inward a maximum distance of about 50% of the radius of said impeller, wherein said passage is a stationary annular passage for peripheral flow of gas in the direction of rotation of said impeller, wherein said means for rotatably driving said impeller comprises a drive shaft upon which said impeller is mounted for rotation at a first location, bearing means for rotatably supporting said drive shaft at a second location on said drive shaft, and a positive pressure fluid seal means located intermediate said first and second locations for preventing contamination from said bearing means from moving along said drive shaft in the direction of said impeller, and wherein said fluid seal means is located adjacent an impeller housing of said impeller and the positive pressure fluid of said seal is a gas which is non contaminating with respect to said laser gas and which is permitted to migrate into said passage as a make-up gas for said gas to be compressed and to thereby prevent the ambient atmosphere from leading into the gas.

Claim 14

A regenerative turbine type compressor comprising an impeller rotatable about an axis and having a plurality of blades thereon for compressing gas, means defining a passage opposite said blades of the impeller with an inlet and outlet being provided in said passage for communicating gas to be compressed to and from said passage, means for rotating said impeller and the blades thereon to compress the gas, and wherein said compressor has a pressure or head coefficient of at least 0.8 and is capable of operating with a pressure ratio for flowing gas at a speed of at least half the speed of sound in said gas in a fast axial flow laser with inlet pressures to said compressor of less than one-third atmospheric pressure, wherein the blades of the impeller of said regenerative compressor are generally radial blades extending from at or near the tip of said impeller inward a maximum distance of about 50% of the radius of said impeller, wherein said passage is a stationary annular passage for peripheral flow of gas in the direction of rotation of said impeller, wherein said means for rotatably driving said impeller comprises a drive shaft upon which said impeller is mounted for rotation at a first location, bearing means for rotatably supporting said drive shaft at a second location on said drive shaft, and a positive pressure fluid seal means located intermediate said first and second locations for preventing contamination from said bearing means from moving along said drive shaft in the direction of said impeller, and wherein said fluid seal means is located adjacent an impeller housing of said impeller and the positive pressure fluid of said seal is a gas which is non contaminating with respect to said laser gas and which is permitted to migrate into said passage as a make-up gas for said gas to be compressed and to thereby prevent the ambient atmosphere from leading into the gas.

Claim 15

A compressor according to claim 1, wherein said means for driving said shaft rotates said shaft at a speed of about 10,000 rpm.

Claim 16

A compressor according to claim 1, wherein said compressor comprises an impeller rotatable about an axis and means for rotating the impeller at a speed such that the circumferential speed of the impeller is a substantial portion of the sonic speed vs for said gas where vs=nRT where n is the isentropic exponent of the gas, R is the individual gas constant, and T is the absolute temperature.

Claim 17

A compressor according to claim 1, wherein the pressure ratio pr of the compressor depends on the mixture of gas used therewith and the mixing ratio of the components of the gas mixture, the pressure ratio pr being expressed by pr=(2/(n+1) exp (n/n-1) where n is the isentropic exponent of the gas mixture.

Claim 18

A compressor according to claim 1, wherein said gas is a mixture of helium, nitrogen and carbon dioxide.

Claim 19

A compressor according to claim 6, wherein means are provided for cooling essentially the entire surface of both sides of the compressor and also the radially outer or circumferential surface thereof.