Aerodynamic feature for aft edge portions of thrust reverser lower bifurcation wall

Patent metadata

Field	Value
Publication number	US-9822733-B2
Application number	US-201414262220-A
Country	US
Kind code	B2
Filing date	Apr 25, 2014
Priority date	Apr 25, 2014
Publication date	Nov 21, 2017
Grant date	Nov 21, 2017

Abstract

A thrust reverser of a propulsion system nacelle is provided. The thrust reverser includes a fixed structure, a translating structure, and an aerodynamic feature. The fixed structure includes an annular wall that partially defines an annular bypass airstream duct. The fixed structure is bifurcated into left and right side sections. The annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section. The translating structure is moveable relative to the fixed structure, between a stowed position and a deployed position. The aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls. The flange aids in preventing aerodynamic drag.

First claim

What is claimed is:

1. A thrust reverser of a propulsion system nacelle, the thrust reverser comprising:
a fixed structure that includes an annular wall that partially defines an annular bypass airstream duct, wherein the fixed structure is bifurcated into left and right side sections, wherein the annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section;
a translating structure that is moveable relative to the fixed structure, between a stowed position and a deployed position; and
an aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls, wherein the flange aids in preventing aerodynamic drag;
wherein the aft end portion of the lower bifurcation wall of the left side section generally extends along a first axis;
wherein the aft end portion of the lower bifurcation wall of the right side section generally extends along a second axis;
wherein the flange includes a first end, a second end, a bent segment, a first intermediate segment that extends between the first end and the bent segment, and a second intermediate segment that extends between the bent segment and the second end; and
wherein the first intermediate segment generally extends along the first axis and the second intermediate segment generally extends along the second axis.

2. The thrust reverser of claim 1 , wherein the flange aids in preventing aerodynamic drag due to flow separation.

3. The thrust reverser of claim 1 , wherein the aerodynamic feature is configured to permit relative movement of respective aft edge portions of the lower bifurcation walls.

4. The thrust reverser of claim 1 , wherein the flange, and the aft end portion that the flange is disposed relative to, generally extend along a common axis.

5. The thrust reverser of claim 1 , wherein the first intermediate segment of the flange is connected to the aft end portion of one of the lower bifurcation walls; and
wherein the bent segment is resilient, and biases the second intermediate segment of the flange towards the aft end portion of the other lower bifurcation wall.

6. A thrust reverser of a propulsion system nacelle, the thrust reverser comprising:
a fixed structure that includes an annular wall that partially defines an annular bypass airstream duct, wherein the fixed structure is bifurcated into left and right side sections, wherein the annular wall extends between upper and lower bifurcation walls of the left side section, and extends between upper and lower bifurcation walls of the right side section;
a translating structure that is moveable relative to the fixed structure, between a stowed position and a deployed position; and
an aerodynamic feature that includes a flange disposed relative to an aft end portion of one of the lower bifurcation walls, wherein the flange aids in preventing aerodynamic drag;
wherein the flange is a first flange and the aerodynamic feature further includes a second flange;
wherein the first and second flanges each include a first end, a second end, and an intermediate segment extending between the first and second ends; and
wherein the first flange is connected to the aft end portion of one of the lower bifurcation walls proximate the first end of the first flange, and the second flange is connected to the aft end portion of the other lower bifurcation wall proximate the first end of the second flange.

7. The thrust reverser of claim 6 , wherein the respective second ends of the first and second flanges are configured to mate with one another.

8. The thrust reverser of claim 7 , wherein the respective intermediate segments of the first and second flanges are resilient, and bias the first and second flanges toward one another such that the respective second ends of the first and second flanges mate.

Assignees

• Rohr Inc

Inventors

• Byrne Stuart J

Classifications

• F02K1/78

  Other construction of jet pipes · CPC title

• F02K1/566 Primary

  by blocking the rearward discharge by means of a translatable member · CPC title

• F02K1/72

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title