초록 ▼

An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first stream and a second stream. The se

An embodiment of the invention is a technique to suppress noise in a jet engine. A noise suppressor includes an exhaust duct to exhaust a first stream from an air stream taken from an inlet. The exhaust duct has an exit end. The air stream is divided into the first stream and a second stream. The second stream has an axis. A stream director attached to vicinity of the exit end directs the first stream to a direction that is away from or sideward relative to the axis.

대표청구항 ▼

What is claimed is: 1. A turbofan jet engine comprising: a first exhaust duct to exhaust a first stream through a first exit end from an air stream taken from an inlet, the air stream being divided into the first stream and a second stream, one of the first and second streams being a fan bypass str

What is claimed is: 1. A turbofan jet engine comprising: a first exhaust duct to exhaust a first stream through a first exit end from an air stream taken from an inlet, the air stream being divided into the first stream and a second stream, one of the first and second streams being a fan bypass stream; a second exhaust duct to exhaust the second stream through a second exit end, the first and second streams being substantially coaxial at the first and second exit ends; and a noise-reducing stream director attached to a vicinity of at least one of the first and second exit ends to directly deflect the first stream to a direction that is away from and/or sideward relative to the second stream such that the first stream is eccentric relative to the second stream downstream of the first and second exit ends to perform a directional noise reduction. 2. The jet engine of claim 1 wherein the stream director comprises at least one of a vane, a strake, and a fluid injector. 3. The jet engine of claim 2 further comprising: an actuator coupled to the at least one of the vane and the strake to control positioning the at least one of the vane and the strake in one of a retracted position and an extended position, the extended position directing the first stream to the direction that is away from or sideward relative to the second stream. 4. The jet engine of claim 3 wherein the retracted position corresponds to an alignment with respect to the first stream when noise reduction is not desired. 5. The jet engine or claim 3 wherein the extended position corresponds to a deflection with respect to the first stream when noise reduction is desired. 6. The jet engine of claim 3 wherein the retracted position corresponds to the stream director being stowed on one of the first and second exhaust ducts when noise reduction is not desired. 7. The jet engine of claim 3 wherein the extended position corresponds to an outward deployment in an azimuthal motion when noise reduction is desired. 8. The jet engine of claim 2 further comprising: an actuator coupled to the at least one fluid injector to control injecting a fluid at an angle to the first stream, the injected fluid directing the first stream to the direction that is away from or sideward relative to the second stream. 9. The jet engine of claim 8 wherein the fluid is one of a compressed gas and a liquid. 10. The jet engine of claim 1 further comprising: an actuator coupled to the stream director to activate the stream director, the activated stream director directing the first stream. 11. The jet engine of claim 10 wherein one of the first and second exhaust ducts has an inlet area and a first exit area at one of the first and second exit ends such that a first area ratio between the first exit area and the inlet area is greater than unity when the stream director is deactivated. 12. The jet engine of claim 11 wherein one of the first and second exhaust ducts has a second exit area at one of the first and second exit ends such that the second area ratio between the second exit area and the inlet area is less than the first area ratio when the stream director is activated. 13. The jet engine of claim 12 wherein at least one of the first and second area ratios is selected to produce an exit flow that is pressured matched with ambient flow. 14. The jet engine of claim 1 wherein the first exhaust duct is a core duet and the second exhaust duct is a bypass duet exhausting a bypass stream. 15. The jet engine of claim 14 wherein the stream director directs the first stream upward or sideward relative to the bypass stream. 16. The jet engine of claim 13 wherein the stream director causes formation of a substantially unmixed bypass flow from the bypass stream below the first stream. 17. The jet engine of claim 1 wherein the first exhaust duct is a bypass duct and the second exhaust duct is a core duct exhausting a core stream. 18. The jet engine of claim 17 wherein the stream director directs the first stream downward or sideward relative to the core stream. 19. The jet engine of claim 18 wherein the stream director causes formation of a substantially unmixed bypass flow from the first stream below the core stream. 20. The jet engine of claim 1 wherein the stream director is attached to an engine pylon. 21. The jet engine of claim 1 wherein the stream director is located within the first exhaust duct or the second exhaust duct. 22. A turbofan jet engine comprising an engine inlet, a core duct, and a fan bypass duct, wherein the engine inlet receives an air stream and a first portion of the air stream exhausts through the core duct at a core exit end and a second portion of the air stream exhausts through the bypass duct at a bypass exit end, the first and second portions being substantially coaxial at the core and bypass exit ends; and a noise-reducing stream director that directly deflects at least one of the first portion and the second portion to flow in directions that are away from and/or sideward relative to each other such that the first portion is eccentric relative to. the second portion downstream of the core and bypass exit ends to perform a directional noise reduction. 23. The jet engine of claim 22 wherein the stream director comprises at least one of a vane, strake, and fluid injector. 24. The jet engine of claim 22, further comprising an actuator to actuate the stream director. 25. The jet engine of claim 24, wherein the actuator actuates the stream director to a first position for noise suppression, and actuates the stream director to a second position for no noise suppression. 26. The jet engine of claim 25, wherein the stream director causes the first air stream and the second air stream to flow in direction away from and/or sideward relative to each other when it is in the first position. 27. The jet engine of claim 25, wherein the stream director causes formation of a substantially unmixed bypass flow from the first portion below the second portion. 28. The jet engine of claim 25, wherein the stream director causes formation of a substantially unmixed bypass flow from the second portion below the first portion. 29. The jet engine of claim 22 wherein the stream director is located on a core shroud or within the core duct or the bypass duct. 30. A turbofan jet engine comprising an engine inlet, a core duct, and a fan bypass duct, wherein the engine inlet receives an air stream and a first portion of the air stream exhausts through the core duct at a core exit end and a second portion of the air stream exhausts through the bypass duct at a bypass exit end, the first and second portions being substantially coaxial at the core and bypass exit ends; and a noise-reducing stream director attached to an engine pylon to directly deflect the second portion to flow in directions that are away from and/or sideward relative to the first portion such that the first portion is eccentric relative to the second portion downstream of the core and bypass exit ends to perform a directional noise reduction. 31. The jet engine of claim 30 wherein the stream director comprises at least one of a vane, a strake, and a fluid injector. 32. A turbofan jet engine comprising an engine inlet, a core duct having a shroud, and a fan bypass duct, wherein the engine inlet receives an air stream and a first portion of the air stream exhausts through the core duct at a core exit end and a second portion of the air stream exhausts through the bypass duct at a bypass exit end, the first and second portions being substantially coaxial at the core and bypass exit ends; and a noise-reducing stream director located within the bypass duct or the core duct or mounted on the shroud, the stream director causing the first portion and the second portion to flow in directions that are away from and/or sideward relative to each other such that the first portion is eccentric relative to the second portion downstream of the core and bypass exit ends to perform a directional noise reduction. 33. The jet engine of claim 32 wherein the stream director comprises at least one of a vane, a strake, and a fluid injector. 34. A turbofan jet engine comprising an engine inlet, a core duct having a shroud and a fan bypass duct, wherein the engine inlet receives an air stream and a first portion of the air stream exhausts through the core duct at a core exit end and a second portion of the air stream exhausts through the bypass duct at a bypass exit end, the First and second portions being substantially coaxial and parallel at the core and bypass exit ends; and a noise-reducing stream director located within the bypass duct or the core duct or mounted on the shroud, the stream director causing the first portion and the second portion to flow in directions that are away from and/or sideward relative to each other such that the First portion is eccentric relative to the second portion downstream of the core and bypass exit ends to perform a directional noise reduction. 35. The jet engine of claim 34 wherein the stream director comprises at least one of a vane, a strake, and a fluid injector.