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A nozzle of converging-diverging shape for creating mist flow at supersonic velocity comprising: a throat having a characteristic diameter D*; an inlet having a characteristic diameter D1, positioned a distance L1 upstream of the nozzle throat; and an outlet having a characteristic diameter D2, posi

A nozzle of converging-diverging shape for creating mist flow at supersonic velocity comprising: a throat having a characteristic diameter D*; an inlet having a characteristic diameter D1, positioned a distance L1 upstream of the nozzle throat; and an outlet having a characteristic diameter D2, positioned a distance L2 downstream of the nozzle throat, wherein the ratio of L2/(D2-D*) is larger than 4, but smaller than 250; an inertia separator based thereon, and a method for supersonic separation of one or more components of a predominantly gaseous stream.

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1. A nozzle of converging-diverging shape comprising: a throat having a characteristic diameter D*; an inlet having a characteristic diameter D1, positioned a distance L1 upstream of the nozzle throat; and an outlet having a characteristic diameter D2, positioned a distance L2 downstream of the

1. A nozzle of converging-diverging shape comprising: a throat having a characteristic diameter D*; an inlet having a characteristic diameter D1, positioned a distance L1 upstream of the nozzle throat; and an outlet having a characteristic diameter D2, positioned a distance L2 downstream of the nozzle throat, wherein the ratio of L2/(D2-D*) is larger than 4, but smaller than 250. 2. A nozzle as claimed in claim 1, wherein the ratio of L2/(D2-D*) is larger than 100, but smaller than 200. 3. A nozzle as claimed in claim 2, wherein the ratio of said length of said nozzle L2 to the diameter of said nozzle D* is less than 300. 4. An inertia separator for supersonic separation of a component of a predominantly gaseous stream, comprising a nozzle, the nozzle comprising: a throat having a characteristic diameter D*; an inlet having a characteristic diameter D1, positioned a distance L1 upstream of the nozzle throat; and an outlet having a characteristic diameter D2, positioned a distance L2 downstream of the nozzle throat, wherein the ratio of L2/(D2-D*) is larger than 50, but smaller than 220; and a separation section downstream thereof having at least one outlet for the component that is separated and at least one outlet for the remaining gaseous stream. 5. An inertia separator as claimed in claim 4, having a vortex inducer upstream to the separation section and downstream of the nozzle. 6. An inertia separator as claimed in claim 5, wherein the vortex inducer comprises one or more delta-shaped elements protruding radially inwardly from the inner wall of the inertia separator, the leading edge and plane of which makes an angle of incidence not larger than 10° with the axial coordinate of the inertia separator. 7. An inertia separator as claimed in claim 4, having a shock wave generator downstream of the nozzle. 8. An inertia separator as claimed in claim 7, wherein the shock wave generator is a diffuser (nozzle of diverging/converging shape) located upstream or downstream of the separation section. 9. A method for the supersonic separation of a component of a predominantly gaseous stream, using an inertia separator comprising a nozzle, the nozzle comprising: a throat having a characteristic diameter D*; an inlet having a characteristic diameter D1, positioned a distance L1 upstream of the nozzle throat; and an outlet having a characteristic diameter D2, positioned a distance L2 downstream of the nozzle throat, wherein the ratio of L2/(D2-D*) is larger than 50, but smaller than 220; and a separation section downstream thereof having at least one outlet for the component that is separated and at least one outlet for the remaining gaseous stream. 10. A method as claimed in claim 9, wherein the predominantly gaseous stream comprises a mixture of methane and higher hydrocarbons and/or water vapour. 11. A method as claimed in claim 9, wherein the predominantly gaseous stream comprises a flue gas and said component to be removed is selected from the group of CO2,N2,NOxand H2S. 12. A method as claimed in claim 9, wherein said component is separated as droplets having a particle size of from 0.1 micrometers to 2.5 micrometers. 13. A method as claimed in claim 9, wherein the change in temperature over the length L2 of said nozzle is from -100,000° K/s to -1,000° K/s. 14. A method as claimed in claim 9, where said component is separated as droplets having a particle size of from 0.5 micrometers to 1.0 micrometers.