Patent US3457003A successfully refreshed from Google Patents.
Patent US3565208A successfully refreshed from Google Patents.
US3565208A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Retractable silencing shield for jet engine nozzle
Assignee: Rohr Inc
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Filing: 1970-02-02
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Granted: 1971-02-23
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Expires: 1990-02-02
Abstract
Abstract Support means carried by an aircraft jet engine housing has pivots at its aft end and is slidable axially of the housing between forward stowed position and aft deployed position, said pivots being located adjacent exit of engine nozzle in latter position. Elongate shield is mounted on the pivots to swing vertically about an axis transverse to longitudinal axis of housing, and is preferably trough-shaped to surround jetstream discharged from the nozzle and reflect noise upward. Aft end of shield is supported or forced up in flight by aerodynamic reacting vanes mounted on inner side of said aft end. When support means is stowed, shield is carried forward to stow in streamlined relation to housing.
Inventors
- 👤 Victor Millman
- 👤 Remo Tontini
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 07:52
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/44
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
152 words
Sound suppressing apparatus for use with an aircraft, comprising: a housing surrounding a jet engine having a rearwardly discharging thrust nozzle; support means carried by said housing and movable axially thereof; an elongate noise reflecting and suppressing shield pivotally connected adjacent its forward end to said support means for swinging about a generally horizontal axis transverse to the longitudinal axis of said nozzle, said shield extending downstream from said housing with its forward end disposed in the vicinity of the lowermost portion of the exit of said nozzle when said support means is positioned at the aft portion of said housing; and at least one vane mounted inside said shield, whereby when said shield is in said downstream position the exhaust gas stream discharged from said engine exerts aerodynamic lifting force upon said vane to thereby swing said shield to a selected angular position relative to the longitudinal axis of said nozzle.
Claim 2
Dependent Claim
152 words
Sound suppressing apparatus for use with an aircraft, comprising: a housing surrounding a jet engine having a rearwardly discharging thrust nozzle; support means carried by said housing and movable axially thereof; an elongate noise reflecting and suppressing shield pivotally connected adjacent its forward end to said support means for swinging about a generally horizontal axis transverse to the longitudinal axis of said nozzle, said shield extending downstream from said housing with its forward end disposed in the vicinity of the lowermost portion of the exit of said nozzle when said support means is positioned at the aft portion of said housing; and at least one vane mounted inside said shield, whereby when said shield is in said downstream position the exhaust gas stream discharged from said engine exerts aerodynamic lifting force upon said vane to thereby swing said shield to a selected angular position relative to the longitudinal axis of said nozzle.
Claim 3
Dependent Claim
36 words
Apparatus as defined in claim 1 wherein said vane is presettable to cause said shield to move to a desired angular position relative to the longitudinal axis of said nozzle when said aircraft is in flight.
Claim 4
Dependent Claim
74 words
Apparatus as defined in claim 1 including: sensing means carried by said shield to sense the operating relation between said shield and said exhaust gas stream; and control means responsive to indications given by said sensing means to vary the attitude of said vane relative to said shield and thereby cause said shield to swing about said transverse axis until its optimum angular position relative to the longitudinal axis of said nozzle is attained.
Claim 5
Dependent Claim
24 words
Apparatus ad defined in claim 1 wherein said shield is substantially hemicylindrical in form and a vane is mounted adjacent each longitudinal edge thereof.
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) | 1974-02-22 | 1974-08-24 | 1975-02-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-02-22 | 1978-08-24 | 1979-02-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-02-22 | 1982-08-24 | 1983-02-23 | $7700.00 | Window Closed / Lapsed |