Exhaust stream mixer

Patent metadata

Field	Value
Publication number	US-9970386-B2
Application number	US-201414298331-A
Country	US
Kind code	B2
Filing date	Jun 6, 2014
Priority date	Jun 7, 2013
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.

First claim

The invention claimed is:

1. A turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section;
a turbine section in fluid communication with the combustor,
an exhaust nozzle in fluid communication with the turbine section;
said exhaust nozzle comprising a plurality of exhaust stream mixers circumferentially disposed about said exhaust nozzle, wherein each of said exhaust stream mixers includes a radially inward base portion and a plurality lobes protruding radially outward from said base portion, wherein a centerline of each lobe in said plurality of lobes intersects with a centerline of each other lobe said plurality of lobes in a middle region of said radially inward base portion, and wherein the centerline of each lobe is an axis of symmetry of the corresponding lobe, wherein each of said exhaust stream mixers is further defined by a corresponding cross section normal to an axis defined by the turbine engine, wherein the cross section of each corresponding exhaust stream mixer has a length extending the entire circumference of the cross section of each corresponding exhaust stream mixer that is at least twice the length of the circumference of a corresponding circle in which the cross section of each corresponding exhaust stream mixer is inscribed.

2. The turbine engine of claim 1 , wherein each of said exhaust stream mixers is defined by a single continuously curved wall.

3. The turbine engine of claim 1 , wherein each of said base portions is defined by a pair of concave walls.

4. The turbine engine of claim 1 , wherein further comprising at least four exhaust stream mixers.

5. The turbine engine of claim 4 , further comprising at least eight exhaust stream mixers.

6. The turbine engine of claim 1 , wherein each of said exhaust stream mixers has a radial height less than one half a total radius of the exhaust nozzle.

7. The turbine engine of claim 6 , wherein each of said exhaust stream mixers has a radial height of less than one quarter the total radius of the exhaust nozzle.

8. The turbine engine of claim 1 , wherein each of said exhaust stream mixers is defined by the corresponding plurality of lobes including at least three radially protruding lobes and a first valley between a first lobe of said radially protruding lobes and a second lobe of said radially protruding lobes, and a second valley between said second lobe of said radially protruding lobes and a third lobe of said radially protruding lobes.

9. The turbine engine of claim 1 , wherein each of said lobes has a smaller cross sectional area than a cross sectional area of said base portion.

10. An exhaust nozzle for a turbine engine comprising:
an axis defined by the exhaust nozzle, wherein a cross section of the exhaust nozzle normal to said axis includes a plurality of daisy style corrugations;
each of said daisy style corrugations further comprises a radially inner base portion, and a plurality of lobes protruding radially outward from said base portion; and
wherein a centerline of each lobe in said plurality of lobes intersects with a centerline of each other lobe said plurality of lobes in a middle region of said radially inward base portion, and wherein the centerline of each lobe is an axis of symmetry of the corresponding lobe, wherein each of said plurality of daisy style corrugations is further defined by a corresponding cross section normal to the axis defined by the exhaust nozzle, wherein the cross section of each of the corresponding daisy style corrugations has a length extending the entire circumference of the cross section of each of the corresponding daisy style corrugations that is at least twice the length of the circumference of a corresponding circle in which the cross section of each of the daisy style corrugations is inscribed.

11. The exhaust nozzle of claim 10 , wherein each of said daisy style corrugations is defined by a plurality of concave sidewalls.

12. The exhaust nozzle of claim 11 , wherein each of said plurality of lobes has a smaller cross sectional area than a cross sectional area of said base portion.

13. The exhaust nozzle of claim 11 , wherein each of said daisy style corrugations is constructed of a single continuous wall.

14. The turbine engine of claim 1 , wherein at least one sidewall of each exhaust stream mixer is bowed away from a sidewall of a circumferentially adjacent exhaust stream mixer.

15. The turbine engine of claim 14 , wherein two sidewalls of each exhaust stream mixer are bowed away from corresponding sidewalls of circumferentially adjacent exhaust stream mixers.

Assignees

• United Technologies Corp

Inventors

• Ribarov Lubomir A
• Elder James S

Classifications

• F02K1/48 Primary

  Corrugated nozzles · CPC title

• F02K1/386

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

• F05D2260/2212

  by creating turbulence · CPC title

• F05D2240/127

  Vortex generators, turbulators, or the like, for mixing · CPC title

• F02K3/062

  with aft fan · CPC title