Exhaust nozzle for gas turbine engine

Patent metadata

Field	Value
Publication number	US-2017166318-A1
Application number	US-201615369912-A
Country	US
Kind code	A1
Filing date	Dec 6, 2016
Priority date	Dec 10, 2015
Publication date	Jun 15, 2017
Grant date	—

Abstract

A turbofan exhaust nozzle apparatus includes: an inner shell having a centerline axis, the inner shell disposed inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell, the inner shell terminating in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct; wherein an aft portion of the outer shell is non-axisymmetric around a common centerline axis of the nozzle, and the trailing edge of the outer shell is vertically non-coplanar.

First claim

What is claimed is:

1 . A turbofan exhaust nozzle apparatus, comprising:
an inner shell having a centerline axis, the inner shell disposed inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell, the inner shell terminating in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the flow duct; wherein an aft portion of the outer shell is non-axisymmetric around the centerline axis, and the trailing edge of the outer shell is vertically non-coplanar.

2 . The apparatus of claim 1 wherein the inner shell is axisymmetric around the centerline axis.

3 . The apparatus of claim 1 wherein the trailing edge of the outer shell has an oval shape.

4 . The apparatus of claim 1 wherein the outer shell is laterally symmetric on opposite sides of the pylon.

5 . The apparatus of claim 1 wherein a lower portion of the trailing edge of the outer shell located diametrically opposite the pylon is displaced axially downstream relative to the remainder of the trailing edge of the outer shell.

6 . The apparatus of claim 5 wherein the displacement tapers away at positions away from the location of maximum displacement.

7 . The apparatus of claim 1 wherein an upper portion of the trailing edge of the outer shell immediately adjoining the pylon is shifted axially forward relative to the remainder of the trailing edge of the outer shell.

8 . The apparatus of claim 7 wherein the displacement tapers away at positions away from the location of maximum displacement.

9 . The apparatus of claim 1 wherein the inner shell diverges aft inside the duct to a hump and then converges aft to the trailing edge thereof.

10 . The apparatus of claim 7 wherein the axial position of the hump has a varying axial distance from the trailing edge of the outer shell around the circumference of the fan nozzle.

11 . The apparatus of claim 1 wherein a portion of the trailing edge of the outer shell defines an S-shape.

12 . A turbofan exhaust nozzle apparatus comprising:
an inner shell having a centerline axis, the inner shell disposed inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell, the inner shell terminating in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct; wherein the trailing edge of the outer shell varies in both axial position and local radius about the circumference of the outer shell.

13 . The apparatus of claim 12 wherein the inner shell is axisymmetric around the centerline axis.

14 . The apparatus of claim 13 wherein the trailing edge of the outer shell has an oval shape.

15 . The apparatus of claim 12 wherein the outer shell is laterally symmetric on opposite sides of the pylon.

16 . The apparatus of claim 12 wherein a lower portion of the trailing edge of the outer shell located diametrically opposite the pylon is displaced axially downstream relative to the remainder of the trailing edge of the outer shell.

17 . The apparatus of claim 16 wherein the displacement tapers away at positions away from the location of maximum displacement.

18 . The apparatus of claim 17 wherein an upper portion of the trailing edge of the outer shell immediately adjoining the pylon is shifted axially forward relative to the remainder of the trailing edge of the outer shell.

19 . The apparatus of claim 17 wherein the displacement tapers away at positions away from the location of maximum displacement.

20 . The apparatus of claim 12 wherein a portion of the trailing edge of the outer shell defines an S-shape.

Assignees

• Gen Electric

Inventors

• Holt Gavin Joseph
• Iglewski Tomasz
• Holland John Robert

Classifications

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F02K3/06 Primary

  with front fan · CPC title

• F05D2250/14

  elliptical · CPC title

• F02K1/78

  Other construction of jet pipes · CPC title

• B64D27/16

  of jet type · CPC title