Patent US4361296A successfully refreshed from Google Patents.
US4361296A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Uniflange coupling assembly
Assignee: Boeing Co
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Filing: 1980-03-10
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Granted: 1982-11-30
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Expires: 2000-03-10
Abstract
Abstract The inlet of a turbofan jet propulsion engine is coupled to the engine fan casing via a unique uniflange coupling assembly. One of the inlet and casing components carries a radial flange while the other of the components carries a pair of radial flanges each spaced on opposite sides of the flange carried by the first component. A pair of toroidally shaped members are positioned respectively between the two pairs of spaced opposing abutment surfaces thus formed by the three flanges. Preferably the members are hollow, have flexible but substantially inelastic walls, and are filled with a fluid. These members allow the two components to angulate relative to each other while allowing loads to be transferred from the first component to the second component only in an axial direction. Other loads are transferred to the engine mounting structure through other linkage.
Inventors
- 👤 Leslie G. Hall
- 👤 David V. Larson
- 👤 Michael A. Smith
- 👤 Stuart K. Wood
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 04:45
CPC Classifications
B; B64; B64D; B64D29/00
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
236 words
An apparatus for securing a first annular aircraft component to a second annular aircraft component, wherein one of said first and second components is a fan inlet duct for a jet propulsion engine and wherein the other of the said first and second components is a fan casing on a jet propulsion engine, the apparatus comprising: a pair of spaced abutment members having annular, mutually opposing abutment surfaces thereon, said mutually opposing abutment surfaces being perpendicular to a longitudinal axis through the center of said annular components, said mutually opposing abutment surfaces being spaced along said longitudinal axis, said pair of abutment members being associated with said first aircraft component, a second component abutment member associated with said second aircraft component, said second component abutment member having oppositely facing abutment surfaces, said oppositely facing abutment surfaces being perpendicular to said longitudinal axis, said second component abutment member being sized and proportioned to reside in spaced relationship between said pair of abutment members so that each abutment surface on said second component abutment member opposes and is spaced from a respective one of the mutually opposing abutment surfaces on said pair of abutment members, thereby forming first and second sets of annularly shaped, mutually opposing surfaces perpendicular to said longitudinal axis; and first and second toroidally shaped, flexible, substantially inelastic members positioned in contact only with said first and said second sets of mutually opposing surfaces respectively.
Claim 2
Independent Claim
236 words
An apparatus for securing a first annular aircraft component to a second annular aircraft component, wherein one of said first and second components is a fan inlet duct for a jet propulsion engine and wherein the other of the said first and second components is a fan casing on a jet propulsion engine, the apparatus comprising: a pair of spaced abutment members having annular, mutually opposing abutment surfaces thereon, said mutually opposing abutment surfaces being perpendicular to a longitudinal axis through the center of said annular components, said mutually opposing abutment surfaces being spaced along said longitudinal axis, said pair of abutment members being associated with said first aircraft component, a second component abutment member associated with said second aircraft component, said second component abutment member having oppositely facing abutment surfaces, said oppositely facing abutment surfaces being perpendicular to said longitudinal axis, said second component abutment member being sized and proportioned to reside in spaced relationship between said pair of abutment members so that each abutment surface on said second component abutment member opposes and is spaced from a respective one of the mutually opposing abutment surfaces on said pair of abutment members, thereby forming first and second sets of annularly shaped, mutually opposing surfaces perpendicular to said longitudinal axis; and first and second toroidally shaped, flexible, substantially inelastic members positioned in contact only with said first and said second sets of mutually opposing surfaces respectively.
Claim 3
Dependent Claim
20 words
The apparatus of claim 1 wherein said first and second toroidally shaped members are hollow and filled with a fluid.
Claim 4
Dependent Claim
12 words
The apparatus of claim 2 wherein said fluid comprises a compressible fluid.
Claim 5
Dependent Claim
12 words
The apparatus of claim 2 wherein said fluid comprises an incompressible fluid.
Claim 6
Independent Claim
216 words
A method for securing a first annular aircraft component to a second annular aircraft component, wherein one of said first and second components is a fan inlet duct for a jet propulsion engine and wherein the other of said first and second components is a fan casing on a jet propulsion engine, comprising the steps of: affixing to said first component, a pair of abutment members having annular, mutually opposing abutment surfaces thereon, said mutually opposing abutment surfaces being spaced along a longitudinal axis through the center of said annular components; affixing to said second component, a second component abutment member having oppositely facing abutment surfaces thereon; positioning said second component abutment member in spaced relationship between said pair of abutment members so that each abutment surface on said second component abutment member opposes and is spaced from a respective, mutually opposing abutment surface on said pair of abutment members, said pair of abutment members and said second component abutment member thereby forming first and second sets of mutually opposing surfaces; and positioning first and second toroidally shaped, flexible, substantially inelastic members in contact only with said first and said second sets of mutually opposing surfaces respectively so that only forces in an axial direction are transmitted between said first and said second annular aircraft components.
Claim 7
Independent Claim
216 words
A method for securing a first annular aircraft component to a second annular aircraft component, wherein one of said first and second components is a fan inlet duct for a jet propulsion engine and wherein the other of said first and second components is a fan casing on a jet propulsion engine, comprising the steps of: affixing to said first component, a pair of abutment members having annular, mutually opposing abutment surfaces thereon, said mutually opposing abutment surfaces being spaced along a longitudinal axis through the center of said annular components; affixing to said second component, a second component abutment member having oppositely facing abutment surfaces thereon; positioning said second component abutment member in spaced relationship between said pair of abutment members so that each abutment surface on said second component abutment member opposes and is spaced from a respective, mutually opposing abutment surface on said pair of abutment members, said pair of abutment members and said second component abutment member thereby forming first and second sets of mutually opposing surfaces; and positioning first and second toroidally shaped, flexible, substantially inelastic members in contact only with said first and said second sets of mutually opposing surfaces respectively so that only forces in an axial direction are transmitted between said first and said second annular aircraft components.
Claim 8
Dependent Claim
20 words
The method of claim 5 wherein said first and second toroidally shaped members are hollow and filled with a fluid.
Claim 9
Dependent Claim
12 words
The method of claim 6 wherein said fluid is a compressible fluid.
Claim 10
Dependent Claim
12 words
The method of claim 6 wherein said fluid is an incompressible fluid.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-11-29 | 1986-05-31 | 1986-11-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-11-29 | 1990-05-31 | 1990-11-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-11-29 | 1994-05-31 | 1994-11-30 | $7700.00 | Window Closed / Lapsed |