Rotor blade internal damper

• US 4,329,119 A
• Filed: 05/16/1979
• Issued: 05/11/1982
• Est. Priority Date: 08/02/1977
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Baskin, Joseph M.
• Primary Examiner(s): Powell, Jr., Everette A.
• Application Number:
  US06/040,364
• Time in Patent Office: 1,091 Days
• Field of Search: 416/226, 416/144, 416/145, 416/230 A, 416/229 R, 416/500, 416/239, 416/241 A
• US Class Current: 416/226
• CPC Class Codes: B64C 27/473 Constructional features
• CPC Class Codes: B64C 27/51 Damping of blade movements
• CPC Class Codes: Y10S 416/50 Vibration damping features

Abstract

A load absorbing elastic member or members is incorporated in the design of a rotor blade to assist in reducing flapwise and chordwise bending moments, torsional loading, and to reduce or eliminate the control system loads induced by rotor blade moment stall. In all its embodiments, the load absorbing elastic member has operatively associated therewith a constraining member which serves as a strain amplifier permitting the load absorbing elastic member to achieve its purpose effectively.

Claims

1. An aerodynamic rotor blade comprising:

(a) an elongated structural spar member having an inner surface forming a hollow interior throughout its length and a contoured outer surface forming a leading edge portion and a spar heel portion, which together define the chordwise limits of the spar member, and a tip end portion and a root end portion, which together define the spanwise limits of the spar member;

(b) an aft fairing structure attached to the spar member at the spar heel portion along the full length thereof, said aft fairing structure having a trailing edge wedge at its end remote from its attachment to the spar heel portion;

(c) a plurality of constraining members situated within the hollow interior of the spar member to form at least one assembly of two constraining members arranged in parallel, with one of the constraining members being situated within the hollow interior of the spar member adjacent to the leading edge portion and with the other constraining member being situated within the hollow interior of the spar member adjacent to the spar heel portion, such that in each assembly the constraining members have that portion of their outer surfaces which face the adjacent inner surface of the spar member substantially conforming to the chordwise shape of the adjacent inner surface of the spar member;

(d) an associated load absorbing elastic member for each assembly of constraining members, each load absorbing elastic member having a stiffness less than that of the spar member and the constraining members of its associated assembly, each being spanwise coextensive with the constraining members of its associated assembly, and each being situated within the hollow interior of the spar member between the inner surface of the spar member and constraining members of its associated assembly, as a result of which the shape of each load absorbing elastic member also substantially conforms to the shape of the adjacent inner surface of the spar member and that portion of the outer surface of its associated constraining member that faces the adjacent inner surface of the spar member, wherein each load absorbing elastic member is attached to the outer surface of its associated constraining member and to the adjacent inner surface of the spar member;

(e) at least one further constraining member situated within the trailing edge wedge, having substantially parallel surfaces facing the trailing edge wedge; and

(f) two further load absorbing elastic members associated with each further constraining member, each load absorbing elastic member having a stiffness less than that of their associated constraining member and the trailing edge wedge, the further load absorbing elastic members being attached to their associated further constraining members along a respective one of its parallel surfaces and to the facing trailing edge wedge.

2. The aerodynamic rotor blade as defined in claim 1, further comprising:

(g) a plug fitting connected to each constraining member of the assembly of constraining members adjacent to the root end portion of the spar member, each said plug fitting being disposed to engage the root end portion of the spar member under the influence of centrifugal force and when the attachment of the associated load absorbing elastic member to the inner surface of the spar member is removed.

3. The aerodynamic rotor blade as defined in claim 1, wherein a single assembly of two elongated constraining members arranged in parallel and associated load absorbing elastic members are situated within the hollow interior of the spar member, and wherein each constraining member and its associated load absorbing elastic member extend, spanwise, substantially the full length of the spar member.

4. The aerodynamic rotor blade as defined in claim 3, further comprising:

(g) a plug fitting connected to each of the two elongated constraining members at the root end portion of the spar member, each said plug fitting being disposed to engage the root end portion of the spar member under the influence of centrifugal force and when the attachment of the associated load absorbing elastic member to the inner surface of the spar member is removed.

5. An aerodynamic rotor blade comprising:

(a) an elongated structural spar member having an inner surface forming a hollow interior throughout its length and a contoured outer surface forming a leading edge portion and a spar heel portion, which together define the chordwise limits of the spar member, and a tip end portion and a root end portion, which together define the spanwise limits of the spar member;

(b) an aft fairing structure attached to the spar member at the spar heel portion along the full length thereof, said aft fairing structure having a trailing edge wedge at its end remote from its attachment to the spar heel portion, which includes a trailing edge strip embedded therein and extending outwardly therefrom beyond the aft fairing structure, said trailing edge strip having substantially parallel surfaces at its extension beyond the aft fairing structure;

(c) a plurality of constraining members situated within the hollow interior of the spar member to form at least one assembly of two constraining members arranged in parallel, with one of the constraining members being situated within the hollow interior of the spar member adjacent to the leading edge portion and with the other constraining member being situated within the hollow interior of the spar member adjacent to the spar heel portion, such that in each assembly the constraining members have that portion of their outer surfaces which face the adjacent inner surface of the spar member substantially conforming to the chordwise shape of the adjacent inner surface of the spar member;

(d) an associated load absorbing elastic member for each assembly of constraining members, each load absorbing elastic member having a stiffness less than that of the spar member and the constraining members of its associated assembly, each being spanwise coextensive with the constraining members of its associated assembly, and each being situated within the hollow interior of the spar member between the inner surface of the spar member and the constraining members of its associated assembly, as a result of which the shape of each load absorbing elastic member also substantially conforms to the shape of the adjacent inner surface of the spar member and that portion of the outer surface of its associated constraining member that faces the adjacent inner surface of the spar member, wherein each load absorbing elastic member is attached to the outer surface of its associated constraining member and to the adjacent inner surface of the spar member;

(e) at least two further constraining members; and

(f) a further load absorbing elastic member associated with each constraining member, each load absorbing elastic member having a stiffness less than that of its associated constraining member and the trailing edge strip, the load absorbing elastic members being attached to their associated constraining member and to a respective one of the parallel surfaces of the trailing edge strip.

6. The aerodynamic rotor blade as defined in claim 5, further comprising:

(g) a plug fitting connected to each constraining member of the assembly of constraining members adjacent to the root end portion of the spar member, each said plug fitting being disposed to engage the root end portion of the spar member under the influence of centrifugal force and when the attachment of the load absorbing elastic member associated with said adjacent assembly of constraining members to the inner surface of the spar member is removed.

7. The aerodynamic rotor blade as defined in claim 5, wherein a single assembly of two elongated constraining members arranged in parallel and an associated load absorbing elastic member are situated within the hollow interior of the spar member, and wherein each constraining member and the associated load absorbing elastic member extend, spanwise, substantially the full length of the spar member.

8. The aerodynamic rotor blade as defined in claim 7, further comprising:

(g) a plug fitting connected to each of the two elongated constraining members at the root end portion of the spar member, each said plug fitting being disposed to engage the root end portion of the spar member under the influence of centrifugal force and when the attachment of the associated load absorbing elastic member to the inner surface of the spar member is removed.