System and method for improved thrust reverser with increased reverse thrust and reduced noise

Patent metadata

Field	Value
Publication number	US-9719466-B2
Application number	US-201414488934-A
Country	US
Kind code	B2
Filing date	Sep 17, 2014
Priority date	Sep 17, 2014
Publication date	Aug 1, 2017
Grant date	Aug 1, 2017

Abstract

A system and method for providing reverse thrust is disclosed. The system can include one or more cascade elements. The one or more cascade elements can each include a plurality of vanes to redirect engine thrust in a forward direction relative to travel. Some, or all, of the vanes can include raised geometric patterns configured to increase the mixing of the airstreams between the reversed engine thrust and the airstream over the vehicle to reduce noise and improve reverse thrust. The angle, curvature, and geometric pattern of the vanes can be optimized for a particular cascade element, engine, location on the engine, row, or can be optimized individually to maximize reverse thrust and minimize noise.

First claim

The invention claimed is:

1. A cascade element for a thrust reverser comprising:
a first plurality of vanes, disposed in a plurality of rows, and comprising a first, raised geometric pattern on a facing surface of each vane, the facing surface comprising the first, raised geometric pattern and a recessed portion with contiguous walls transitioning the facing surface from the first, raised geometric pattern to the recessed portion and defining a plurality of peaks and a plurality of valleys of the first, raised geometric pattern;
wherein the first, raised geometric pattern is configured to increase mixing with a first, internal airflow and a second, external airflow to reduce noise and increase reverse thrust.

2. The cascade element of claim 1 , wherein the vanes in each of the plurality of rows have a different angle of attack.

3. The cascade element of claim 1 , further comprising:
a second plurality of vanes disposed proximate a second end of the cascade element, and comprising a second, raised geometric pattern;
wherein the first plurality of vanes are disposed proximate a first end of the cascade element;
wherein first, raised geometric pattern and the second, raised geometric pattern are configured to increase mixing with a first, internal airflow and a second, external airflow.

4. The cascade element of claim 3 , wherein:
one or more of the first, raised geometric pattern and the second, raised geometric pattern are sinusoidal patterns.

5. The cascade element of claim 3 , wherein:
one or more of the first, raised geometric pattern and the second, raised geometric pattern are sawtooth patterns.

6. The cascade element of claim 3 , wherein
the first plurality of vanes are disposed at a first angle of attack; and
the second plurality of vanes are disposed at a second angle of attack.

7. The cascade element of claim 6 , wherein the first angle of attack is shallower than the second angle of attack.

8. The cascade element of claim 3 , wherein
the first plurality of vanes comprise a first curvature; and
the second plurality of vanes comprise a second curvature.

9. The cascade element of claim 8 , wherein the first curvature is smaller than the second curvature.

10. A thrust reverser comprising:
a first cascade element, disposed proximate a first end of an engine, comprising a first plurality of vanes, each of the first plurality of vanes comprising a first, raised geometric pattern on a facing surface of each vane of the first plurality of vanes, the facing surface comprising the first, raised geometric pattern and a recessed portion with contiguous walls transitioning the facing surface from the first, raised geometric pattern to the recessed portion and defining a plurality of peaks and a plurality of valleys of the first, raised geometric pattern;
a second cascade element, disposed proximate a second end of the engine, comprising a second plurality of vanes, each of the second plurality of vanes comprising a second, raised geometric pattern on a facing surface of each vane of the second plurality of vanes, the facing surface comprising the second, raised geometric pattern and a recessed portion with contiguous walls transitioning the facing surface from the second, raised geometric pattern to the recessed portion and defining a plurality of peaks and a plurality of valleys of the second, raised geometric pattern;
wherein first, raised geometric pattern and the second, raised geometric pattern are configured to increase mixing with a first, internal airflow and a second, external airflow.

11. The thrust reverser of claim 10 , wherein
the first plurality of vanes are disposed at a first angle of attack; and
the second plurality of vanes are disposed at a second angle of attack.

12. The thrust reverser of claim 11 , wherein the first angle of attack is smaller than the second angle of attack.

13. The thrust reverser of claim 12 , wherein the first end of the engine is disposed near an intake of the engine; and
the second end of the engine is disposed near an exhaust of the engine.

14. The thrust reverser of claim 10 , the first cascade element further comprising:
a third plurality of vanes comprising a third, raised geometric pattern on a facing surface of each vane of the third plurality of vanes, the facing surface comprising the third, raised geometric pattern and a recessed portion with contiguous walls transitioning the facing surface from the third, raised geometric pattern to the recessed portion and defining a plurality of peaks and a plurality of valleys of the third, raised geometric pattern.

15. The thrust reverser of claim 10 , the second cascade element further comprising:
a fourth plurality of vanes comprising a fourth, raised geometric pattern on a facing surface of each vane of the fourth plurality of vanes, the facing surface comprising the fourth, raised geometric pattern and a recessed portion with contiguous walls transitioning the facing surface from the fourth, raised geometric pattern to the recessed portion and defining a plurality of peaks and a plurality of valleys of the fourth, raised geometric pattern.

16. A method comprising:
providing a first cascade element of a thrust reverser comprising a first plurality of vanes;
providing a second cascade element of the thrust reverser comprising a second plurality of vanes;
wherein one or more of the first plurality of vanes and the second plurality of vanes comprise a raised geometric pattern on a facing surface of a vane, the facing surface comprising the raised geometric pattern and a recessed portion with contiguous walls transitioning the facing surface from the raised geometric pattern to the recessed portion and defining a plurality of peaks and a plurality of valleys of the raised geometric pattern, the raised geometric pattern configured to increase mixing with a first, internal airflow and a second, external airflow.

17. The method of claim 16 , wherein the raised, geometric pattern comprises a sinusoidal pattern.

18. The method of claim 16 , wherein the raised, geometric pattern comprises a sawtooth pattern.

19. The method of claim 16 , wherein the first plurality of vanes are disposed at a first angle of attack and the second plurality of vanes are disposed at a second angle of attack.

20. The method of claim 16 , further comprising:
installing the first cascade element on an engine in a first location;
installing the second cascade element on the engine in a second location;
wherein the first location is further forward on the engine than the second location.

Assignees

• Boeing Co

Inventors

• Nakhjavani Omid B

Classifications

• F02K1/60

  by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers · CPC title

• F02K1/827 Primary

  Sound absorbing structures or liners · 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

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F05D2250/182

  crenellated, notched · CPC title