Length adjustable strut link with low aerodynamic drag

• US 4,571,936 A
• Filed: 07/10/1985
• Issued: 02/25/1986
• Est. Priority Date: 07/10/1985
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Nash, Dudley O., Crowley, James A.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): NOT, DEFINED
• Application Number:
  US06/753,462
• Time in Patent Office: 230 Days
• Field of Search: 60/39.31, 60/39.32, 60/226.1, 60/262, 60/263, 248/554, 248/555, 248/556, 248/557, 244/54, 244/55
• US Class Current: 60/797
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A low aerodynamic drag structural link suitable for use within the housing of a turbofan jet engine; the link includes length adjustment capability, pivotal end mounting provision, maintained airstream orientation capability, low mass and jam nut length and orientation locking. Several variations in link construction including a single ball and socket arrangement, varying link cross-section along its longitudinal length and the use of fairing nose and tail inserts are disclosed.

Claims

1. In combination:

an aircraft jet engine;

an engine housing concentrically surrounding said engine and separated therefrom by an annular air flow space;

fan means within said housing and connected with said jet engine for generating high velocity axial air flow in said annular air flow space along the length of said engine and housing;

a structural link body member disposed across said annular airflow space between said jet engine and engine housing, said link body member having an air foil cross-section lengthwise disposed in said axial airflow in said annular airflow space;

and including means for limiting pivotal movement of said link body member about its longitudinal axis; and

differentially threaded termination means for connecting respective ends of said link body member with said jet engine and said engine housing;

whereby lengthwise disposition of said air foil cross-section in said axial airflow and high resolution adjustment of the annular space between said jet engine and said housing are simultaneously achievable.

2. The apparatus of claim 1 including a plurality of said structural link body members each including differentially threaded termination means.

3. The apparatus of claim 2 wherein said differentially threaded termination means includes first and second terminal members, one at each end of said structural link body member and wherein said first terminal member is connected with said structural link body member by threads of a first pitch and said second terminal member is connected with said structural link body member by threads of a second, different, pitch.

4. The apparatus of claim 3 wherein said terminal members include ball and socket pivotal connector means for receiving link to engine and link to housing attachment members disposed along axes substantially orthogonal of said link body member.

5. The apparatus of claim 4 wherein said means for limiting pivotal movement includes protuberance means located on the link body member attached portions of said ball and socket pivotal means of each said terminal members and engageable with engine connected and housing connected planar surfaces, respectively.

6. The apparatus of claim 5 wherein said link body member air foil cross-section is symmetrical about each axis of a pair of link cross-section axes.

7. The apparatus of claim 6 wherein said link cross-sectional axes are disposed respectively along said axial airflow direction and radially orthogonal thereto with respect to said jet engine.

8. The apparatus of claim 7 further including jam nut means received on said threads of each of said terminal members and engageable with said link body portion for retaining said terminal members and link body portion in predetermined fixed relationship.

9. The apparatus of claim 8 further including jam nut means retaining means for retaining said link body portion and said jam nut means in fixed relationship.

10. Low drag structural link apparatus for mounting in a high velocity airflow stream region of an aircraft while retaining first and second elements of said aircraft in predetermined juxtaposition comprising:

a link body member disposed logitudinally between said aircraft independent elements and across said airflow stream region, said link body member having a streamlined cross-section extending along first and second link cross-sectional axes with the longer first cross-sectional axis extending substantially parallel to said airflow stream;

a first link terminal member threadably received in said link body member at a first end thereof and capable of connecting said body member with said first aircraft element;

a second link terminal member threadably received in said link body member at the second end thereof and capable of connecting said body member with said second aircraft element;

spherical pivot means located at a predetermined one of said first and second link terminal members for enabling pivoting and off-link-orthogonal engagement of said predetermined terminal member with one of said aircraft elements; and

means for retaining said first link body member cross-sectional axis parallel with said airflow stream, notwithstanding pivot capability residing in said spherical pivot means.

11. The apparatus of claim 10 further including a second of said spherical pivot means located at the remaining one of said link terminal members for enabling pivoting and off-link-orthogonal engagement of said remaining terminal members with the remaining of said aircraft elements.

12. The apparatus of claim 11 wherein said means for retaining said link body member cross-sectional axis parallel with said airflow stream includes protuberance elements integral with one of said link terminal members and engageable with one of said aircraft elements.

13. The apparatus of claim 12 wherein said first and second link terminal members include rotationally similar, differentially pitched threads.