Jet engine nozzle exit configurations and associated systems and methods

• US 7,966,824 B2
• Filed: 08/09/2006
• Issued: 06/28/2011
• Est. Priority Date: 08/09/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Mengle, Vinod G.
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): SUNG, GERALD LUTHER
• Application Number:
  US11/502,130
• Publication Number:
  US 20100257865A1
• Time in Patent Office: 1,784 Days
• Field of Search: 607/70, 607/71, 60/395, 239/265.19, 239/265.37, 239/265.43, 239/265.39, 181/213
• US Class Current: 60/770
• CPC Class Codes: B64D 33/04 of exhaust outlets or jet pipes exhaust outlets for combustion engines in general F01N; jet pipes or nozzles for jet-propulsion plants per se F02K; plants characterised by the form or arrangement of the jet pipe or nozzle F02K ; attitude, flight direction, or altitude control by jet reaction B64C
• CPC Class Codes: F02K 1/48 Corrugated nozzles
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49 Method of mechanical manufacture

Abstract

Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter.

Claims

1. An aircraft system, comprising:

a jet engine exhaust nozzle having an internal flow surface positioned outwardly from a core flow path, the nozzle having an exit aperture, the exit aperture having a perimeter, the perimeter including multiple projections that are (a) non-moveable relative to the core flow path or (b) movable relative to the perimeter, the projections extending in an aft direction and circumferentially spaced about the perimeter with a length of the multiple projections in a first group decreasing successively over at least three projections from one projection to the next along a first portion of the perimeter, and a length of projections in a second group decreasing successively over at least three projections from one projection to the next along a second portion of the perimeter, the second portion being mirrored relative to the first portion about an axially extending plane.

2. The aircraft system of claim 1, further comprising:

a fuselage;

a wing carried by the fuselage; and

an engine carried by at least one of the wing and the fuselage, the engine being coupled to the exhaust nozzle.

3. The aircraft system of claim 2 wherein successive projections have a length that decreases in a direction away from the wing along the perimeter.

4. The system of claim 3 wherein the nozzle is positioned below the wing and wherein projections toward an upper portion of the perimeter are longer than projections toward a lower portion of the perimeter.

5. The system of claim 3 wherein the nozzle is positioned above the wing and wherein projections toward a lower portion of the perimeter are longer than projections toward an upper portion of the perimeter.

6. The system of claim 2 wherein the nozzle is laterally offset from the fuselage, wherein projections toward an inboard portion of the perimeter are longer than projections toward an outboard portion of the perimeter.

7. The system of claim 1 wherein the length of the projections decreases successively from one projection to the next around half the perimeter.

8. The system of claim 1 wherein an angular deflection of the projections relative to a direction of gas flow through the nozzle decreases successively over at least three projections form one projection to the next.

9. The system of claim 1 wherein a density of projections decreases along the portion of the perimeter.

10. The system of claim 1 wherein the projections are movable relative to the exit aperture.

11. The system of claim 10 wherein the projections are actively controlled to have different positions at different flight regimes.

12. The system of claim 1 wherein the projections have a generally triangular shape.

13. The system of claim 1 wherein the length of the projections changes in a monotonic manner from a 12:

00 position at the perimeter clockwise to a 6;

00 position, and from the 12;

00 position counterclockwise to the 6;

00 position.

14. The system of claim 1 wherein the perimeter is generally round, and wherein the length of the projections changes in a monotonic manner from a 3:

00 position at the perimeter clockwise to a 9;

00 position, and from the 3;

00 position counterclockwise to the 9;

00 position.

15. The system of claim 1 wherein individual projections include a root and a tip, and wherein a plane passing through the roots of the projections is generally perpendicular to a direction of gas flow through the nozzle.

16. The system of claim 1 wherein individual projections include a root and a tip, and wherein a plane passing through the roots of the projections is canted relative to a direction of gas flow through the nozzle.

17. The system of claim 1 wherein the nozzle is a turbofan nozzle, the internal flow surface is a first internal flow surface positioned to receive a fan flow, the exit aperture is a first exit aperture, the perimeter is a first perimeter, the projections are first projections, and the length decreases in a first manner along a portion of the first perimeter, and wherein the system further comprises:

a second internal flow surface positioned to receive an engine core flow, the second flow surface terminating at a second exit aperture, the second exit aperture having a second perimeter, the second perimeter including multiple second projections extending in an aft direction, with an aft portion of individual neighboring second projections spaced apart from each other by a gap, and with a geometric feature of the multiple second projections varying in a second manner different than the first manner along a portion of the second perimeter.

18. The system of claim 1 wherein the nozzle is elongated along a longitudinal axis, and wherein an uninstalled thrust vector of the nozzle is parallel to the longitudinal axis.

19. The system of claim 1, further comprising a pylon carrying the nozzle, and wherein the length of the projections decreases in a direction away from the pylon.

20. The system of claim 1 wherein a thrust vector of the nozzle is not aligned with an acoustic intensity vector of the nozzle.

21. The system of claim 20 wherein the acoustic intensity vector is for a single frequency.

22. The system of claim 20 wherein the acoustic intensity vector is one of multiple acoustic intensity vectors, each corresponding to a single frequency.

23. The system of claim 1 wherein the nozzle is a turbofan nozzle having a fan flow path in addition to the core flow path, and wherein the internal flow surface bounds at least part of the fan flow path.

24. The system of claim 1 wherein the nozzle is a turbofan nozzle having a fan flow path in addition to the core flow path, and wherein the internal flow surface bounds at least part of the core flow path.

25. The system of claim 1 wherein the nozzle is a turbofan nozzle, the internal flow surface is a first internal flow surface positioned to receive a fan flow, and the exit aperture is a first exit aperture, and wherein the system further comprises a second internal flow surface positioned to receive an engine core flow, the second flow surface terminating at a second exit aperture, the second exit aperture being downstream of the first exit aperture.

26. The system of claim 1 wherein the nozzle is a turbofan nozzle, the internal flow surface is a first internal flow surface positioned to receive a fan flow, the exit aperture is a first exit aperture, the perimeter is a first perimeter, the projections are first projections, and the length of the first projections varies in a first manner along a portion of the first perimeter, and wherein the system further comprises:

a second internal flow surface positioned to receive an engine core flow, the second flow surface terminating at a second exit aperture, the second exit aperture having a second perimeter, the second perimeter including multiple second projections extending in an aft direction, with an aft portion of individual neighboring second projections spaced apart from each other by a gap, and with a geometric feature of the multiple second projections varying in a second manner different than the first manner along a portion of the second perimeter; and

wherein;

the first projections decrease in length around the first perimeter from a 12;

00 position at the first perimeter to a 6;

00 position at the first perimeter; and

wherein

the second projections increase in length around the second perimeter from a 12;

00 position at the second perimeter to a 6;

00 position at the second perimeter; and

wherein

the first internal flow surface includes a portion of a fan flow duct having a varying flow area with a convergent section, a divergent section downstream of the convergent section and a throat between the convergent and divergent sections, with gaps between neighboring first projections originating downstream of the fan duct throat.

55. The aircraft system of claim 1 wherein the projections are generally sheet-like elements.

27. An aircraft system, comprising:

a jet engine exhaust nozzle having an internal flow surface positioned outwardly form a core flow path, the nozzle having an exit aperture, the exit aperture having a perimeter, the perimeter including multiple projections that are (a) non-moveable relative to the core flow path or (b) movable relative to the perimeter, the projections extending in an aft direction and circumferentially spaced about the perimeter with a length of the multiple projections decreasing successively from one projection to the next around half the perimeter.

54. The nozzle of claim 27 wherein the first projections decrease in length around the perimeter from a 12:

00 position to a 6;

00.

28. An aircraft system, comprising:

a turbofan engine exhaust nozzle that includes;

a fan flow duct having a first internal flow surface positioned to receive a fan flow;

a core flow duct having a second internal flow surface positioned to receive an engine core flow; and

wherein at least one of the fan flow duct and the core flow duct has a varying flow area with a convergent section, a divergent section downstream of the convergent section, a throat between the convergent and divergent sections, and an exit aperture having a perimeter that includes multiple projections that are (a) non-moveable relative to the core flow duct or (b) moveable relative to the perimeter, the projections extending in an aft direction, with circumferentially adjacent projections spaced apart from each other by a gap, and wherein the gaps are positioned downstream of the throat, and wherein a length of the projections in a first group decreases successively over at least three projections from one projection to the next along a first portion of the perimeter, and a length of projections in a second group decreasing successively over at least three projections from one projection to the next along a second portion of the perimeter, the second portion being mirrored relative to the first portion about an axially extending plane.

29. The system of claim 28 wherein the fan flow duct has the convergent section, the divergent section and the throat.

30. The system of claim 28 wherein the fan flow duct has a varying flow area with a convergent section, a divergent section downstream of the convergent section, a throat between the convergent and divergent sections, and wherein the core flow duct has an exit aperture with a perimeter that includes multiple projections extending in an aft direction, with an aft portion of individual neighboring projections spaced apart from each other by a gap.

31. The system of claim 30 wherein the projections of the fan flow duct vary in a first manner around the perimeter of the exit aperture of the fan flow duct, and wherein the projections of the core flow duct vary in a second manner around the perimeter of the exit aperture of the core flow duct, the second manner being different than the first manner.

32. The system of claim 30 wherein the projections of the fan flow duct are first projections at a first perimeter, and wherein the projections of the core flow duct are second projections at a second perimeter, and wherein

the first projections decrease in length around the first perimeter from a 12:

00 position at the first perimeter to a 6;

00 position at the first perimeter; and

the second projections increase in length around the second perimeter from a 12;

00 position at the second perimeter to a 6;

00 position at the second perimeter.

33. The system of claim 28 wherein the projections have a length that varies in a monotonic manner around a portion of the perimeter.

34. An aircraft, comprising:

a fuselage;

a wing depending from the fuselage;

a jet engine nozzle carried by at least one of the fuselage and the wing, the nozzle having an internal flow surface positioned outwardly from a core flow path, the nozzle having an exit aperture, the exit aperture having a perimeter with an outboard section facing away from the fuselage and an inboard section facing toward the fuselage between the outboard section and the fuselage, the perimeter including multiple projections that are (a) non-moveable relative to the core flow path or (b) movable relative to the perimeter, the projections extending in an aft direction, with an aft portion of individual neighboring projections spaced apart from each other by a gap, and with inboard projections at the inboard section having a length different than a length of outboard projections at the outboard section, the length of the projections in a first group decreasing successively over at least three projections from one projection to the next along a first portion of the perimeter, and a length of projections in a second group decreasing successively over at least three projections from one projection to the next along a second portion of the perimeter, the second portion being mirrored relative to the first portion about an axially extending plane.

35. The aircraft of claim 34 wherein the inboard projections have a different angular deflection relative to a direction of gas flow through the nozzle than do the outboard projections.

36. The aircraft of claim 34 wherein the inboard projections have a different shape than do the outboard projections.

37. The aircraft of claim 34 wherein the inboard projections have a different number density per unit length along the perimeter than do the outboard projections.

38. The aircraft of claim 34 wherein the nozzle is a turbofan nozzle, the internal flow surface is a first internal flow surface positioned to receive a fan flow, the exit aperture is a first exit aperture, the perimeter is a first perimeter, the projections are first projections, and the length of the first projections varies in a first manner along a portion of the first perimeter, and wherein the system further comprises:

a second internal flow surface positioned to receive an engine core flow, the second flow surface terminating at a second exit aperture, the second exit aperture having a second perimeter, the second perimeter including multiple second projections extending in an aft direction, with an aft portion of individual neighboring second projections spaced apart from each other by a gap, and with a geometric feature of the multiple second projections varying in a second manner different than the first manner along a portion of the second perimeter; and

wherein;

the first projections decrease in length around the first perimeter from a 12;

00 position at the first perimeter to a 6;

00 position at the first perimeter; and

wherein

the second projections increase in length around the second perimeter from a 12;

00 position at the second perimeter to a 6;

00 position at the second perimeter; and

wherein

the first internal flow surface includes a portion of a fan flow duct having a varying flow area with a convergent section, a divergent section downstream of the convergent section and a throat between the convergent and divergent sections, with gaps between neighboring first projections terminating downstream of the fan duct throat.

39. A method for manufacturing an aircraft, comprising:

selecting a fuselage configuration;

selecting a wing configuration;

selecting configuration of a turbofan nozzle to include;

a fan flow duct having a first internal flow surface positioned to receive a fan flow;

a core flow duct having a second internal flow surface positioned to receive an engine core flow;

selecting an exit aperture of at least one of the ducts to have a perimeter that includes multiple projections that are (a) non-moveable relative to the engine core flow or (b) movable relative to the perimeter, the projections extending in an aft direction, with an aft portion of individual neighboring projections spaced apart from each other by a gap; and

selecting a length of at least some of the projections in a first group to decrease successively over at least three projections from one projection to the next along a first portion of the perimeter, and a length of projections in a second group to decrease successively over at least three projections from one projection to the next along a second portion of the perimeter, the second portion being mirrored relative to the first portion about an axially extending plane.

40. The method of claim 39 wherein the nozzle is carried by the wing and wherein selecting a length includes selecting a length of the projections to be greater for projections closer to the wing than for projections further from the wing.

41. The method of claim 40 wherein selecting a length includes selecting the length of neighboring projections to decrease around the perimeter from a 12:

00 position to a 6;

00 position.

42. The method of claim 39 wherein the nozzle is carried by the fuselage and wherein selecting a length includes selecting a length of the projections to be greater for projections closer to the fuselage than for projections further from the fuselage.

43. The method of claim 42 wherein selecting a length includes selecting the length of neighboring projections to decrease around the perimeter from a 3:

00 position to a 9;

00 position.

44. The method of claim 39 wherein the nozzle is carried by the wing and wherein selecting a length includes:

selecting a length of the projections to be greater for projections closer to the wing than for projections further from the wing; and

selecting a length of the projections to be greater for projections closer to the fuselage than for projections further from the fuselage.

45. The method of claim 39 wherein selecting an exit aperture includes selecting the exit aperture of the fan flow duct to include first projections and selecting the exit aperture of the core flow duct to include second projections, and wherein selecting a length includes selecting a length of the first projections to vary in a first manner and selecting the length of second projections not to vary or to vary in a second manner different than the first.

46. A method for operating an aircraft, comprising:

generating a flow of gas with a jet engine;

delivering the gas through a nozzle having a trailing edge perimeter including multiple projections extending in an aft direction, with an aft portion of individual neighboring projections spaced apart from each other by a gap, and with a length of the projections in a first group decreasing successively over at least three projections from one projection to the next along a first portion of the perimeter, and a length of projections in a second group decreasing successively over at least three projections from one projection to the next along a second portion of the perimeter, the second portion being mirrored relative to the first portion about an axially extending plane; and

generating a first thrust level and producing a first noise level by mixing the gas with an adjacent stream of air external to the nozzle at the gaps to produce more thrust and less noise than is produced with the jet engine coupled to the nozzle without the projections.

47. The method of claim 46 wherein mixing the gases includes mixing the gases at different rates at different points around the trailing edge perimeter.

48. The method of claim 47 wherein mixing the gases includes mixing the gases by a first rate at a projection having a first length, and mixing the gases by a second rate less than the first rate at a second projection having a second length less than the first length.

49. A method for controlling aircraft noise, comprising:

directing gas through a jet engine nozzle; and

controlling a total thrust vector of the gas to be non-parallel to an acoustic intensity vector at one or more one acoustic frequencies by passing the gas adjacent to multiple nozzle projections and mixing the gas with adjacent freestream air at the nozzle projections, wherein the multiple projections extend aft from a perimeter of the nozzle exit, the multiple projections having different lengths, the multiple projections being (a) non-moveable relative to the gas or (b) movable relative to the perimeter, and wherein a length of the projections in a first group decreases successively over at least three projections from one projection to the next along a first portion of the perimeter, and a length of projections in a second group decreased successively over a least three projections from one projection to the next along a second portion of the perimeter, the second portion being mirrored relative to the first portion about an axially extending plane.

50. The method of claim 49 wherein controlling the thrust vector includes controlling the thrust vector for the nozzle when uninstalled to be generally parallel to a longitudinal axis of the nozzle.

51. The method of claim 49 wherein controlling the acoustic vector includes controlling the acoustic intensity vector for the nozzle when installed on an aircraft to be non-parallel to the longitudinal axis of the nozzle.

52. The method of claim 51 wherein controlling the acoustic vector includes controlling the acoustic intensity vector to be directed away from a fuselage of the aircraft.

53. The method of claim 51 wherein controlling the acoustic vector includes controlling the acoustic intensity vector to be directed upwardly, so that the acoustic intensity is lower below the aircraft than above the aircraft.