Concentric nozzles for enhanced mixing of fluids

Patent metadata

Field	Value
Publication number	US-9494050-B2
Application number	US-201314033409-A
Country	US
Kind code	B2
Filing date	Sep 20, 2013
Priority date	Sep 20, 2013
Publication date	Nov 15, 2016
Grant date	Nov 15, 2016

Abstract

An article for mixing ambient fluid with a motive fluid comprises a conduit, and thermally conductive concentric inner and outer nozzles extending from the conduit. The conduit is configured to supply the motive fluid to the outer nozzle and the ambient fluid to the inner nozzle. The inner nozzle extends further downstream from the conduit than the outer nozzle.

First claim

The invention claimed is:

1. An article for mixing ambient fluid with a motive fluid, the article comprising:
a conduit; and
thermally conductive concentric inner and outer nozzles extending from the conduit;
the conduit configured to supply the motive fluid to the outer nozzle and the ambient fluid to the inner nozzle;
wherein the inner nozzle extends further downstream from the conduit than the outer nozzle by a distance that is sufficient for flow from the outer nozzle to expand to ambient pressure prior to reaching an exit station of the inner nozzle.

2. The article of claim 1 , wherein the inner nozzle extends downstream of the outer nozzle by a downstream distance equal to about one-quarter diameter of the inner nozzle to one full diameter of the inner nozzle.

3. The article of claim 1 , wherein the nozzles extend from a first side of the conduit; and wherein an inlet to the inner nozzle is located at an opposite side of the conduit in axial alignment with the inner nozzle.

4. The article of claim 1 , wherein the conduit is configured to turn the motive fluid about 90 degrees before entering the outer nozzle.

5. The article of claim 1 , further comprising a second pair of thermally conductive concentric inner and outer nozzles extending from the conduit, wherein the inner nozzle of the second pair extends further downstream from the conduit than the outer nozzle of the second pair.

6. The article of claim 5 , wherein the conduit defines a first passage for supplying the motive fluid to the outer nozzle of each pair.

7. The article of claim 5 , wherein the nozzles extend from a first side of the conduit; and wherein inlets to the inner nozzles are located at an opposite side of the conduit and axially aligned with their corresponding inner nozzles.

8. An engine nacelle lipskin comprising:
a channel forming a lipskin cavity; and
an article including a conduit and thermally conductive concentric inner and outer nozzles extending from the conduit with the inner nozzle extending further downstream from the conduit than the outer nozzle by a distance that is sufficient for flow from the outer nozzle to expand to ambient pressure prior to reaching an exit station of the inner nozzle, the conduit secured to the channel such that the nozzles are located within the cavity and oriented in a direction of anti-icing flow, the conduit configured to supply motive fluid to the outer nozzle and ambient fluid within the cavity to the inner nozzle.

9. The engine nacelle lipskin of claim 8 , further comprising a second pair of thermally conductive concentric inner and outer nozzles extending from the conduit, wherein the inner nozzle of the second pair extends further downstream from the conduit than the outer nozzle of the second pair.

10. The engine nacelle lipskin of claim 8 , wherein the nozzles extend from a first side of the conduit; and wherein an inlet to the inner nozzle is located at an opposite side of the conduit in axial alignment with the inner nozzle.

11. The engine nacelle lipskin of claim 8 , wherein the second inlet of the article is coupled to a source of high temperature, high pressure air.

12. The engine nacelle lipskin of claim 8 , wherein the channel includes skin made of nominal grade aluminum.

13. A method comprising:
mounting thermally conductive concentric inner and outer nozzles within a lipskin cavity of an engine nacelle such that ambient air flowing within the cavity is supplied to an inlet of the inner nozzle; and
coupling a bleed air source to an inlet of the outer nozzle to eject a jet stream of high pressure, high temperature air into the lipskin cavity, wherein the jet stream expands to ambient pressure before being mixed with the ambient air.

14. A method comprising heating an engine nacelle lipskin, including:
ejecting a jet stream of high pressure, high temperature air into a cavity of the lipskin via a nozzle, wherein ambient air surrounding the nozzle mixes with the jet stream; and
supplying a stream of ambient air through a central portion of the jet stream, wherein the jet stream expands to ambient pressure before being mixed with the ambient air stream.

15. The method of claim 14 , wherein the nozzle is an outer nozzle, and wherein the ambient air stream is supplied by an inner nozzle that is concentric with the outer nozzle.

16. The method of claim 15 , further comprising also using a second concentric nozzle pair to eject a second jet stream of high temperature, high pressure air into the lipskin cavity.

17. The method of claim 14 , further comprising supplying bleed air to an inlet of the nozzle.

18. The method of claim 14 , wherein the bleed air has a higher temperature than maximum allowable temperature of aluminum skin of the lipskin.

Assignees

• Boeing Co

Inventors

• Schnoebelen Joseph K
• Acheson Kurt E

Classifications

• B64D2033/0233

  comprising de-icing means · CPC title

• B64D15/04

  Hot gas application · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title

• B64D33/02

  of combustion air intakes · CPC title