Method for manufacturing and assembly of a thrust reverser cascade

Patent metadata

Field	Value
Publication number	US-10823112-B2
Application number	US-201715605120-A
Country	US
Kind code	B2
Filing date	May 25, 2017
Priority date	May 25, 2017
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.

First claim

What is claimed:

1. A method for manufacturing a cascade for a thrust reverser for a jet engine, comprising:
forming a first strip assembly, wherein the first strip assembly comprises:
a first strong back member comprising a length; and
a plurality of first vane members which extend from a first side of the first strong back member in a first direction nonparallel relative to the length of the first strong back member, wherein:
the plurality of first vane members are spaced apart from one another along the length of the first strong back member;
two consecutive first vane members of the plurality of first vane members and the first strong back member form a three sided open configuration; and
at least one of the plurality of first vane members comprises a curvilinear surface wherein the curvilinear surface forms a recess facing a forward direction; and

a plurality of second vane members which extend from a second side of the first strong back member, opposing the first side of the first strong back member, in a second direction nonparallel relative to the length of the first strong back member, wherein:
the plurality of second vane members are spaced apart from one another along the length of the first strong back member; and
two consecutive second vane members of the plurality of second vane members and the first strong back member form a three sided open configuration.

2. The method of claim 1 , wherein a top portion of the curvilinear surface extends in a surface direction nonparallel relative to a central axis of the jet engine such that, with the first strip assembly positioned on a nacelle of the jet engine, the surface direction forms an angle relative to the central axis of the jet engine in a range, from and including thirty degrees and up to and to include ninety degrees.

3. The method of claim 1 , wherein forming the first strip assembly further includes forming a front portion of the first strong back member which extends from the first side of the first strong back member.

4. The method of claim 3 , further including forming a second strip assembly including forming a second front portion which extends from a second side of a second strong back member.

5. The method of claim 4 , further including positioning the first strip assembly in a first position and the second strip assembly in a second position adjoining the front portion of the first strong back member with the second front portion of the second strong back member.

6. The method of claim 1 , further including securing opposing end portions of the first strip assembly to a nacelle.

7. The method of claim 1 , further including forming a distal end of the plurality of first vane members to extend along a first plane.

8. The method of claim 1 , further including forming a distal end of the plurality of first vane members to extend along in an angularly shaped configuration.

9. The method of claim 1 , further including forming a distal end of the plurality of first vane members to be one of a protrusion or a notch configuration.

10. A method for manufacturing a cascade for a thrust reverser for a jet engine, comprising:
forming a strip assembly, wherein the strip assembly comprises:
a strong back member comprising a length;
a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of the strong back member, wherein:
the plurality of first vane members are spaced apart from one another along the length of the strong back member; and
two consecutive first vane members of the plurality of first vane members and the strong back member form a three sided open configuration; and

a plurality of second vane members which extend from a second side of the strong back member, opposing the first side of the strong back member, in a second direction nonparallel relative to the length of the strong back member, wherein:
the plurality of second vane members are spaced apart from one another along the length of the strong back member; and
two consecutive second vane members of the plurality of second vane members and the strong back member form a three sided open configuration.

11. The method of claim 10 , wherein one first vane member of the plurality of first vane members and one second vane member of the plurality of second vane members extend in alignment with one another.

12. The method of claim 11 , wherein each first vane member of the plurality of the first vane members is positioned to extend from the strong back member in alignment with one second vane member of the plurality of the second vane members.

13. The method of claim 10 , wherein a length of one first vane member of the plurality of first vane members and a length of one second vane member of the plurality of second vane members are positioned in angular relationship to one another.

14. The method of claim 10 , wherein at least one second vane member of the plurality of the second vane members comprises a curvilinear surface wherein the curvilinear surface forms a recess which faces a front portion of the strip assembly.

15. The method of claim 14 , wherein a top portion of the curvilinear surface extends in a surface direction nonparallel relative to a central axis of the jet engine such that, with the strip assembly positioned on a nacelle of the jet engine, the-surface direction forms an angle relative to a central axis of the jet engine in a range, from and including thirty degrees and up to and to include ninety degrees.

16. A method for manufacturing a cascade for a thrust reverser for a jet engine, comprising:
forming a strip assembly, wherein the strip assembly comprises:
a strong back member comprising a length; and
a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of the strong back member, wherein:
the plurality of first vane members are spaced apart from one another along the length of the strong back member; and
two consecutive first vane members of the plurality of first vane members and the strong back member form a three sided open configuration;

a plurality of second vane members which extend from a second side of the strong back member, opposing the first side of the strong back member, in a second direction nonparallel relative to the length of the strong back member, wherein:
the plurality of second vane members are spaced apart from one another along the length of the strong back member; and
two consecutive second vane members of the plurality of second vane members and the strong back member form a three-sided open configuration, wherein:
the first side extends along the length of the strong back member and extends transverse to the length of the strong back member;
the first side of the strong back member has a top portion, such that with the strip assembly positioned on a nacelle of the jet engine, the top portion of the first side extends in a third direction relative to a radial direction;
the radial direction extends from a central axis of the jet engine and aligns with a bottom portion of the strong back member positioned closer to the central axis of the jet engine than the top portion of the first side of the strong back member;
the third direction extends relative to the radial direction within an angular range, from and including extending parallel with the radial direction and up to and to include being angularly displaced sixty degrees from the radial direction;
the second side opposing the first side extends along the length o

Assignees

• Boeing Co

Inventors

• Harpal Naimishkumar
• Chuck Chen
• Vandemark Zachariah
• Olaniyan Tunde A
• Han Minkoo

Classifications

• F02K1/64 Primary

  Reversing fan flow · 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

• F05D2240/40

  Use of a multiplicity of similar components · CPC title

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title