Engine nozzle system for shock-cell noise reduction

Patent metadata

Field	Value
Publication number	US-2017082063-A1
Application number	US-201615369879-A
Country	US
Kind code	A1
Filing date	Dec 5, 2016
Priority date	Mar 9, 2012
Publication date	Mar 23, 2017
Grant date	—

Abstract

A method and apparatus for reducing noise generated during operation of a propulsion system. In one illustrative embodiment, a nozzle system comprises a first nozzle and a second nozzle at least partially surrounded by the first nozzle. An outer surface of an aft portion of the second nozzle has a shape configured such that a radial cross-section of the outer surface of the aft portion of the second nozzle has a curve that is different from at least one other curve for another radial cross-section of the outer surface of the aft portion of the second nozzle and such that an axial cross-section of the outer surface of the aft portion of the second nozzle has a wavy shape.

First claim

What is claimed is:

1 . A method for shock cell noise reduction comprising:
determining the desired range of operating conditions for an engine having a nozzle system with a fan nozzle and a core nozzle; establishing for a core nozzle radii, H 1 , and a range of distances between exit planes, L, and a range of annular radii H 2 between the fan nozzle and core nozzle, that provide cancellation of shock cells for the range of operating conditions; determining curvature of a plurality of curves in a surface of the core nozzle to provide the range of annular radii, H 2 ; and, shaping a trailing edge of the core nozzle using extensions to define the range of effective exit plane distances, L.

2 . The method for shock cell noise reduction as defined in claim 1 wherein the curves establish a wavy circumferential shape in the core nozzle surface.

3 . The method for shock cell noise reduction as defined in claim 1 further comprising:
shaping a trailing edge of the fan nozzle using extensions to alter the range of exit plane distances, L.

4 . The method for shock cell noise reduction as defined in claim 1 further comprising:
determining curvature of a plurality of curves on an inner surface of the fan nozzle to alter the annular radius H 2 over a range to provide additional matching adjustment of H 2 , H 1 and L to provide shock cell cancellation over the operating range.

5 . A nozzle system for shock cell noise reduction comprising:
a fan nozzle; a core nozzle concentric with the fan nozzle and having
a plurality of curves in a surface of the core nozzle altering the effective annular radius H 2 between the fan nozzle and core nozzle over a first range and
a plurality of circumferential extensions on a trailing edge of the core nozzle varying a distance, L, between an exit plane of the fan nozzle and an exit plane of the core nozzle between tips and roots of each extension over a second range, said first range of H 2 and second range of L determined to establish cancellation of shock cells for a range of operating conditions of an engine.

6 . The nozzle system as defined in claim 5 wherein the curves establish a wavy circumferential shape in the core nozzle surface.

7 . The nozzle system as defined in claim 5 wherein each curve and each extension creates a smooth variation in H 2 and L providing cancellation of shock cells around at least segmented portions of a circumference of the nozzle system at each operating condition in the operating range of the engine in a range established by the total variation in H 2 and L.

8 . The nozzle system as defined in claim 7 further comprising:
a plurality of extensions on a trailing edge of the fan nozzle employed to vary the effective distance, L, between the fan nozzle exit plane and the core nozzle exit plane around the circumference of the nozzle system.

9 . The nozzle system as defined in claim 8 further wherein the plurality of extensions on the trailing edge of the fan nozzle extend over at least a part of the aft portion of the core nozzle to vary the effective annular radius H 2 .

10 . The nozzle system as defined in claim 5 wherein each of the plurality of curves reside on a radial cross-section of an outer surface of an aft portion of the core nozzle and begin at a selected axial plane through the core nozzle and end at the trailing edge of the core nozzle.

11 . The nozzle system as defined in claim 9 wherein each of the plurality of curves for the radial cross-section of the outer surface of the aft portion of the core nozzle has a curvature that continuously changes between a selected axial plane through the core nozzle and a trailing edge of the core nozzle.

12 . The nozzle system as defined in claim 5 further comprising a plug located within the core nozzle, said effective radius, H 1 , of the core nozzle extending between an inner surface of the core nozzle and the plug.

13 . The nozzle system as defined in claim 11 wherein the plug comprises a channel configured to vent gases.

14 . The nozzle system as defined in claim 12 wherein the plug further comprises a plurality of extensions at an aft end of the plug.

15 . The nozzle system as defined in claim 5 wherein the plurality of extensions on the core nozzle are chevrons or serrations.

16 . The nozzle system as defined in claim 8 wherein the plurality of extensions on the fan nozzle are chevrons or serrations.

17 . An engine comprising:
a housing; and
a nozzle system at an aft end of the housing, the nozzle system having
a fan nozzle; a core nozzle concentric with the fan nozzle and having
a plurality of curves in a surface of the core nozzle altering the effective annular radius between the fan nozzle and the core nozzle, H 2 , over a first range and
a plurality of circumferential extensions on a trailing edge of the core nozzle varying a distance, L, between an exit plane of the fan nozzle and an exit plane of the core nozzle between tips and roots of each extension over a second range, said first range of H 2 and second range of L determined to establish cancellation of shock cells for a range of operating conditions of the engine.

18 . The engine as defined in claim 16 wherein each curve and each tip creates a smooth variation in H 2 and L providing cancellation of shock cells around at least segmented portions of a circumference of the nozzle system at each operating condition in the operating range of the engine in a range established by the total variation in H 2 and L.

19 . The engine as defined in claim 17 further comprising:
a plurality of extensions on a trailing edge of the fan nozzle employed to vary the effective distance, L, between the fan nozzle exit plane and the core nozzle exit plane around the circumference of the nozzle system.

20 . The engine as defined in claim 16 wherein each of the plurality of curves reside on a radial cross-section of an outer surface of an aft portion of the core nozzle and begin at a selected axial plane through the core nozzle and end at the trailing edge of the core nozzle.

Assignees

• Boeing Co

Inventors

• Mengle Vinod Govind

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F02K1/46

  Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing (F02K1/28, F02K1/36, F02K1/38 take precedence) · CPC title

• F05D2230/50

  Building or constructing in particular ways · CPC title

• F02K1/386

  mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title

• F02K1/04

  Mounting of an exhaust cone in the jet pipe · CPC title