Vortex arrestor and visualization system

Claim 3

The method of claim 1 including the step of injecting a visualization agent into the gas for showing the condition of the vortex.

Claim 4

The method of claim 1 wherein the gas is heated under substantially constant static pressure conditions.

Claim 5

The method of claim 3 wherein the gas is accelerated by passage through a venturi nozzle.

Claim 6

The method of claim 4 including the step of injecting a visualization agent into the gas for showing the condition of the vortex.

Claim 7

Apparatus for controlling a vortex produced at the trailing edge of an airfoil, comprising a convergent-divergent nozzle device extending rearwardly from said airfoil, a source of gas under pressure, duct means for conducting said gas to the nozzle device, and thermal control means connected to the duct means for maintaining a predetermined static pressure internally of the nozzle device to increase flow velocity to supersonic value within the nozzle device thereby discharging the gas to arrest development of the vortex.

Claim 8

Apparatus for controlling a vortex produced at the trailing edge of an airfoil, comprising a convergent-divergent nozzle device extending rearwardly from said airfoil, a source of gas under pressure, duct means for conducting said gas to the nozzle device, and thermal control means connected to the duct means for maintaining a predetermined static pressure internally of the nozzle device to increase flow velocity to supersonic value within the nozzle device thereby discharging the gas to arrest development of the vortex.

Claim 9

The combination of claim 6 including means for injecting a visual agent into the gas upstream of the nozzle device.

Claim 10

The combination of claim 6 wherein said source of gas under pressure constitutes an engine driven compressor and means for bleeding air under pressure from the compressor.

Claim 11

The combination of claim 6 wherein said nozzle device includes discharge passage means for inducing vortical flow of the discharging gas in counter-rotating relation to the vortex being arrested.

Claim 12

The combination of claim 6 including means mounted externally on the nozzle device for insuring orderly vortex flow rearwardly from the trailing edge of the airfoil.

Claim 13

The combination of claim 6 wherein said source of gas includes a propelling engine of an aircraft within which intake air is compressed and means for bleeding compressed air from said engine during flight below cruising speeds.

Claim 14

The combination of claim 11 wherein said source of gas further includes scoop means mounted by the aircraft for producing ram pressurized air during flight and means for selectively supplying the pressurized air to the duct means.

Claim 15

In combination with the wing of an aircraft from which a vortex develops along a trailing path from the wing tip during flight, means for arresting development of said vortex comprising nozzle means mounted on said wing adjacent the tip and extending rearwardly therefrom for discharge of air along said trailing path, a source of air under pressure connected to said nozzle means, and control means connected to said source for maintaining a static pressure of the air internally of the nozzle means substantially above the external ambient pressure, said control means including a heating device for increasing the temperature of the air upstream of the nozzle means.

Claim 16

In combination with the wing of an aircraft from which a vortex develops along a trailing path from the wing tip during flight, means for arresting development of said vortex comprising nozzle means mounted on said wing adjacent the tip and extending rearwardly therefrom for discharge of air along said trailing path, a source of air under pressure connected to said nozzle means, and control means connected to said source for maintaining a static pressure of the air internally of the nozzle means substantially above the external ambient pressure, said control means including a heating device for increasing the temperature of the air upstream of the nozzle means.

Claim 17

The combination of claim 13 including means for injecting a visual agent into the air downstream of the heating device.

Claim 18

The combination of claim 13 wherein said nozzle means includes a flow accelerating section having an inlet end, a throat passage and an outlet end of reduced flow area relative to the inlet end, said flow accelerating section being dimensioned to increase the flow velocity of the air from said source to substantially sonic value at the throat passage under said internal static pressure.

Claim 19

The combination of claim 15 wherein the nozzle means further includes an expanding exhaust section discharging the air from the outlet end of the flow accelerating section, said exhaust section including passage means for inducing vortical flow of the discharging air in counter rotating relation to the vortex being arrested.