Nozzle for supersonic gas flow and an inertia separator
First Claim
Patent Images
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.
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Abstract
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.
53 Citations
14 Claims
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1. A nozzle of converging-diverging shape comprising:
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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.- View Dependent Claims (2, 3)
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4. An inertia separator for supersonic separation of a component of a predominantly gaseous stream, comprising a nozzle, the nozzle comprising:
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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. - View Dependent Claims (5, 6, 7, 8)
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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:
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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. - View Dependent Claims (10, 11, 12, 13, 14)
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Specification