Patent US3684182A successfully refreshed from Google Patents.
US3684182A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Variable nozzle for jet engine
Assignee: Rohr Inc
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Filing: 1970-09-08
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Granted: 1972-08-15
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Expires: 1990-09-08
Abstract
Abstract Invention is embodied in an airplane having at least one jet engine with its longitudinal axis substantially parallel to the longitudinal axis of the airplane and with a tail pipe discharging rearwardly to produce reaction thrust. A variable nozzle is provided for attachment co-extensively to the tail pipe to receive and control the exhaust gas stream. The nozzle comprises a pair of fixedly mounted side plates laterally spaced and having parallel opposed planar faces, between which are mounted a pair of nozzle sections having predetermined profiles in continuation of the profile of the tail pipe. The outer marginal side walls of the sections are in slidable sealed engagement with the opposed faces of the side plates, and are movable toward and away from the engine axis between stowed and deployed positions to vary the cross sectional area of the exhaust gas flow path and to modify the combined profile of the tail pipe and nozzle for varying flight regimes so that optimum flow-pressure requirements may be satisfied. In addition, the sections may be independently actuated for differential movement which alters the effective thrust axis and provides directional control moments to aid in steering the aircraft or for emergency steering control. Direction of movement of sections at installation determines whether pitching or yawing movements are produced. In multiple engine installations both pitch and yaw control may be provided.
Inventors
- 👤 Richard L Maison
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 17:43
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/52; F02K1/002; F02K1/008; F02K1/06; F02K1/09; F02K1/12; F02K1/1207; F02K1/54; F02K1/56; F02K1/60
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
229 words
A thrust controlling mechanism for use in combination with an airplane provided with at least one jet engine having a longitudinal axis substantially parallel to the longitudinal axis of the airplane and having a tail pipe with a fixed profile adapted to discharge rearwardly to produce reaction thrust, said mechanism comprising: a variable nozzle for connection to the tail pipe to receive and control the rearward flow of the exhaust gas stream; the nozzle including a pair of fixedly mounted laterally spaced side plates having parallel planar opposing faces; and a pair of nozzle sections located between the side plates and having inner walls provided with predetermined longitudinal profiles and forming virtual continuations of portions of the tail pipe to control the amount and character of flow of the exhaust gas stream; the nozzle sections having outer marginal side walls in slidable sealing engagement with the opposing faces of the side plates; the nozzle sections being movable to a stowed position toward and a deployed position away from the engine axis to vary the cross sectional area of the flow path and to vary the combined longitudinal profile of the tail pipe and nozzle sections said variable nozzle is deployed through a plurality of intermediate positions from stowed to deployed for varying said cross-sectional flow path from convergent in the stowed position to convergent-divergent in the full deployed position.
Claim 2
Dependent Claim
229 words
A thrust controlling mechanism for use in combination with an airplane provided with at least one jet engine having a longitudinal axis substantially parallel to the longitudinal axis of the airplane and having a tail pipe with a fixed profile adapted to discharge rearwardly to produce reaction thrust, said mechanism comprising: a variable nozzle for connection to the tail pipe to receive and control the rearward flow of the exhaust gas stream; the nozzle including a pair of fixedly mounted laterally spaced side plates having parallel planar opposing faces; and a pair of nozzle sections located between the side plates and having inner walls provided with predetermined longitudinal profiles and forming virtual continuations of portions of the tail pipe to control the amount and character of flow of the exhaust gas stream; the nozzle sections having outer marginal side walls in slidable sealing engagement with the opposing faces of the side plates; the nozzle sections being movable to a stowed position toward and a deployed position away from the engine axis to vary the cross sectional area of the flow path and to vary the combined longitudinal profile of the tail pipe and nozzle sections said variable nozzle is deployed through a plurality of intermediate positions from stowed to deployed for varying said cross-sectional flow path from convergent in the stowed position to convergent-divergent in the full deployed position.
Claim 3
Dependent Claim
29 words
A system as claimed in claim 1; the inner walls of the two nozzle sections combining in stowed position to form the entire inner flow-confronting wall of the nozzle.
Claim 4
Dependent Claim
36 words
A system as claimed in claim 1; portions of the opposing walls of the side plates defining portions of the nozzle inner wall at least when the nozzle sections are displaced outward from their stowed positions.
Claim 5
Dependent Claim
36 words
A system as claimed in claim 1; each marginal side wall of each nozzle section being provided with a generally longitudinally extending pressurized seal resiliently urged into contact with the adjacent wall of a side plate.
Claim 6
Dependent Claim
24 words
A system as claimed in claim 4; and conduit means to supply compressor bleed air to the interiors of the seals to provide pressurization.
Claim 7
Dependent Claim
43 words
A system as claimed in claim 1; each of the nozzle sections being pivotally mounted adjacent to its forward end to enable the sections to swing toward and away from the engine axis to vary the flow path area and the longitudinal profile.
Claim 8
Dependent Claim
127 words
A system as claimed in claim 6; a first guide track mounted to each marginal side wall of each nozzle section and extending in a predetermined direction in a fore and aft plane; a second guide track mounted to a wall of each side plate for each guide track on the nozzle sections and extending in planes parallel to the planes of the first guide tracks but at predetermined angles thereto and in overlapping relation; a carriage having guide followers movably mounted in each track of a set of two cooperating first and second guide tracks; and actuator means to force the guide follower from end to end of the corresponding tracks of a set to force the nozzle sections toward and away from the engine axis.
Claim 9
Dependent Claim
35 words
A system as claimed in claim 1; each of the nozzle sections being slidably mounted for bodily movement toward and away from the engine axis to vary the flow path area and the longitudinal profile.
Claim 10
Dependent Claim
37 words
A system as claimed in claim 8; including rearwardly diverging guide tracks; the nozzle sections being slidably mounted on said tracks to move from stowed position aft and laterally outward from thE engine axis toward deployed position.
Claim 11
Dependent Claim
37 words
A system as claimed in claim 8; including forwardly diverging guide tracks; the nozzle sections being slidably mounted on said tracks to move from stowed position forward and laterally outward from the engine axis toward deployed position.
Claim 12
Dependent Claim
28 words
A system as claimed in claim 1; the nozzle sections being actuatable independently to produce differential movement and alter the effective thrust axis to provide directional control moments.
Claim 13
Dependent Claim
46 words
A system as claimed in claim 1; the major portions of the longitudinal cross sections of the movable nozzle sections being substantially thicker than the side plates to increase their individual resistance to exhaust gas pressures in compensation for division of the nozzle into separate portions.
Claim 14
Dependent Claim
86 words
A system as claimed in claim 1; and a blocker door forming the aft portion of each nozzle section and pivotally mounted to the main body of the section; the blocker doors being so dimensioned and located that their aft edges meet at a central plane in deployed position when the nozzle sections are in stowed position; the doors being spaced aft of the main bodies of the sections in deployed position to define lateral discharge passages for the exhaust gas stream to produce reverse thrust.
Claim 15
Dependent Claim
48 words
A system as claimed in claim 1; including a pair of engines, one located at each side of the longitudinal axis of the airplane; the nozzle sections of each engine being actuatable independently to produce differential movement and alter the effective thrust axis to provide directional control moments.
Claim 16
Dependent Claim
36 words
A system as claimed in claim 14; the nozzle sections of each engine being movable upward and downward with respect to a generally horizontal plane containing the longitudinal axis of the airplane to provide pitching moments.
Claim 17
Dependent Claim
63 words
A system as claimed in claim 1; the nozzle having a laterally elongate cross section with a movable nozzle section at each lateral margin; each nozzle section being movable laterally in a generally horizontal plane toward and away from the engine axis; and the nozzle sections being actuatable independently to produce differential movement and alter the effective thrust axis to provide yawing moments.
Claim 18
Dependent Claim
119 words
A system as claimed in claim 1; including a first engine having a longitudinal axis parallel to the longitudinal axis of the airplane and located in a vertical plane containing the longitudinal axis of the airplane; and at least a pair of outboard engines having longitudinal axes parallel to and spaced laterally from the longitudinal axis of the airplane; the nozzle sections of each engine being actuatable independently to produce differential movement and alter the effective thrust axis to provide directional control moments; the nozzle sections of the first engine being movable laterally to provide yawing moments, and the nozzle sections of at least some of the outboard engines being movable vertically to provide pitching moments and/or rolling moments.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-08-15 | 1976-02-14 | 1976-08-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-08-15 | 1980-02-14 | 1980-08-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-08-15 | 1984-02-14 | 1984-08-15 | $7700.00 | Window Closed / Lapsed |