US3598319A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Propulsion nozzles
Assignee: General Electric Co
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Filing: 1969-07-14
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Granted: 1971-08-10
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Expires: 1989-07-14
Abstract
Abstract The disclosure shows a propulsion nozzle having angularly spaced afterbodies projecting downstream of the convergent portion of the nozzle. Secondary flaps are pivotally mounted between the afterbodies, forming, in combination therewith, a divergent nozzle portion for maximum supersonic exhaust gas velocities. The flaps are pivoted inwardly to aerodynamically reduce the nozzle exit area for reduced exhaust gas velocities, particularly for subsonic flight. The flaps may be pivoted further inwardly against a central plug to block rearward gas flow and produce reverse thrust. The pivotal mountings of the flaps form a structural hoop, and the actuators for the flaps are mounted within the afterbodies. Alternate forms of flaps and hoop means are shown as well as features of cooling air conservation.
Inventors
- 👤 Werner E Howald
- 👤 Elmore Verne Sprunger
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 08:00
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/06; F02K1/12; F02K1/123; F02K1/38; F02K1/383; F02K1/54; F02K1/56; F02K1/62; Y; Y02; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 25
Claim 1
Independent Claim
158 words
A propulsion nozzle comprising, a convergent portion into which a high energy gas stream is introduced, a plurality of afterbodies projecting downstream from said convergent portion, said afterbodies being angularly spaced from each other about the axis of said convergent nozzle portion, said afterbodies having inner Surfaces which are divergently tapered from a nozzle throat at the downstream end of said convergent portion, secondary flap means disposed in the spaces between said afterbodies and extending from said throat to the downstream ends of adjacent inner surfaces of the afterbodies, said secondary flaps forming, in combination with said afterbodies, a divergent nozzle portion for expansion of said gas stream to a supersonic velocity, said secondary flaps being displaceable to positions in which their upstream ends introduce air, at said throat, along their inner surfaces and their downstream ends move inwardly, the combination of which reduces the nozzle discharge area for propulsion with subsonic and reduced supersonic gas stream velocities.
Claim 2
Dependent Claim
158 words
A propulsion nozzle comprising, a convergent portion into which a high energy gas stream is introduced, a plurality of afterbodies projecting downstream from said convergent portion, said afterbodies being angularly spaced from each other about the axis of said convergent nozzle portion, said afterbodies having inner Surfaces which are divergently tapered from a nozzle throat at the downstream end of said convergent portion, secondary flap means disposed in the spaces between said afterbodies and extending from said throat to the downstream ends of adjacent inner surfaces of the afterbodies, said secondary flaps forming, in combination with said afterbodies, a divergent nozzle portion for expansion of said gas stream to a supersonic velocity, said secondary flaps being displaceable to positions in which their upstream ends introduce air, at said throat, along their inner surfaces and their downstream ends move inwardly, the combination of which reduces the nozzle discharge area for propulsion with subsonic and reduced supersonic gas stream velocities.
Claim 3
Dependent Claim
71 words
A propulsion nozzle as in claim 1 wherein, the outer surfaces of the afterbodies are generally parallel to the nozzle axis and extend upstream of the convergent nozzle portion and ramp means respectively between said afterbodies incline inwardly from the upstream portions of the outer surfaces of the afterbodies to facilitate the introduction of air along the inner surfaces of said secondary flap means when said flap means are so displaced.
Claim 4
Dependent Claim
76 words
A propulsion nozzle as in claim 2 wherein, said secondary flap means are in the form of single, relatively thin airfoils disposed respectively between each adjacent pair of afterbodies, and said secondary flaps are pivoted intermediate their respective ends, relative to said afterbodies to provide for said flap means displaceability and the ramp means extend to the upstream ends of said secondary flaps when said secondary flaps are aligned with the inner surfaces of said afterbodies.
Claim 5
Dependent Claim
71 words
A propulsion nozzle as in claim 2 wherein, the secondary flap means comprise single flaps disposed respectively between each adjacent pair of afterbodies, said flaps have outer surfaces generally aligned with the outer surfaces of said afterbodies and the outer surfaces of the secondary flaps extend to the upstream ends of said ramp means when the inner surfaces of the secondary flaps are aligned with the inner surfaces of the afterbodies.
Claim 6
Dependent Claim
63 words
A propulsion nozzle as in claim 2 wherein, the convergent nozzle portion comprises a plurality of primary flaps pivotable to vary the discharge area of the convergent nozzle portion, said primary flaps being respectively radially aligned with said afterbodies and said secondary flap means, and the primary flaps, aligned with said secondary flap means, forming the downstream end portions of said ramp means.
Claim 7
Dependent Claim
54 words
A propulsion nozzle as in claim 2 wherein, the convergent nozzle portion comprises a plurality of primary flaps pivotal to vary the discharge area of the convergent nozzle portion, said primary flaps underlying and spaced inwardly from said ramp means, and means for introducing secondary air between said ramp means and said primary flaps.
Claim 8
Dependent Claim
42 words
A propulsion nozzle as in claim 2, in further combination with a pod which provides a housing for an engine generating the high energy gas stream, and wherein, the outer surfaces of said afterbodies are formed as aerodynamic continuations of said pod.
Claim 9
Dependent Claim
39 words
A propulsion nozzle as in claim 1, further comprising, a plug forming an annular discharge nozzle area in combination with said convergent portion and said afterbodies and secondary flap means, said plug being convergently tapered in a downstream direction.
Claim 10
Dependent Claim
53 words
A propulsion nozzle as in claim 8 wherein, said secondary flap means comprise single flaps disposed respectively between each adjacent pair of afterbodies, which secondary flaps are displaceable to positions in which their downstream ends engage said plug to divert the gas stream laterally and forwardly from the nozzle to provide reverse thrust.
Claim 11
Dependent Claim
32 words
A propulsion nozzle as in claim 9 wherein, the flaps have tapered wings underlying said afterbodies and providing a complete blockage of the gas stream to thereby obtain maximum Reverse thrust energy.
Claim 12
Dependent Claim
107 words
A propulsion nozzle as in claim 10 wherein, the outer surfaces of the afterbodies are generally parallel to the nozzle axis and extend upstream of the convergent nozzle portion and ramp means between each afterbody are inclined inwardly from the upstream portions of the outer surfaces of the afterbodies to facilitate the introduction of air along the inner surfaces of said secondary flaps when said flaps are so displaced for propulsion with subsonic and reduced supersonic gas stream velocities and, further, to facilitate lateral discharge of the high energy gas stream when the secondary flaps are displaced to engage said plug to divert the gas stream laterally.
Claim 13
Dependent Claim
58 words
A propulsion nozzle as in claim 1 wherein, the secondary flap means comprise single flaps disposed respectively between each adjacent pair of afterbodies means are provided for pivotally mounting the secondary flaps, intermediate their lengths, on said afterbodies to provide for displacement thereof and actuator means are housed within said afterbodies for controlling pivotal movement of said flaps.
Claim 14
Dependent Claim
31 words
A propulsion nozzle as in claim 12 wherein, the secondary flap actuator means comprise individual actuators respectively connected to opposite sides of each of said flaps through the pivotal mounting means.
Claim 15
Dependent Claim
62 words
A propulsion nozzle as in claim 12 wherein, the secondary flaps have shaft means extending between the pivotal mounting means of each afterbody and the pivotal mounting means are axially locked between the flaps and the afterbodies to form a transverse, structural hoop minimizing the tendency of the afterbodies to spread outwardly when loaded by the forces of the hot gas stream.
Claim 16
Dependent Claim
81 words
A propulsion nozzle as in claim 14 wherein, the actuator means comprise a pair of actuators mounted within each afterbody and the pivotal mounting means comprise a bellcrank having a face spline connection with each end of the shaft means of each secondary flap, said bellcranks being journaled within said afterbodies and respectively connected to the actuators within the afterbodies, said bellcranks further having flanges preloaded into engagement with structural portions of the afterbodies as part of the referenced structural hoop.
Claim 17
Dependent Claim
28 words
A propulsion nozzle as in claim 15 wherein, a geared interconnection is provided between the bellcranks within each afterbody to assure simultaneous pivotal movement of said secondary flaps.
Claim 18
Dependent Claim
74 words
A propulsion nozzle as in claim 12 wherein, a cooling air plenum chamber is provided in each afterbody and the pivotal mounting means include valve means for directing cooling air to the secondary flaps when the secondary flaps are positioned for expansion of the gas stream at supersonic velocity, said valve means automatically shutting off cooling airflow to the secondary flaps when the secondary flaps are pivoted for propulsion with reduced gas stream velocities.
Claim 19
Dependent Claim
97 words
A propulsion nozzle as in claim 17 further comprising, a plug, forming an annular discharge nozzle in combination with said convergent portion and said afterbodies and said secondary flaps, said plug being convergently tapered in a downstream direction, said secondary flaps being pivotable by the same actuator means to positions in which their downstream ends engage said plug to divert the gas stream laterally and forwardly from the nozzle to provide reverse thrust, and further wherein, the valve means automatically introduce cooling air into the secondary flaps when the secondary flaps are so pivoted for reverse thrust.
Claim 20
Dependent Claim
54 words
A propulsion nozzle as in claim 17 wherein, the pivotal mounting means comprise a bellcrank connected to each side of each secondary flap, said bellcranks being journaled within the respective adjacent afterbodies and connected to said actuator means and said bellcranks and afterbodies have cooperative slots forming valve means for so regulating cooling airflow.
Claim 21
Dependent Claim
68 words
A propulsion nozzle as in claim 12 wherein, the convergent nozzle portion is formed by a plurality of primary flaps with individual flaps being pivotably mounted respectively beneath each afterbody and in alignment with said secondary flaps, sealing means interconnecting said primary flaps, and actuator means mounted within each afterbody and connected to the respective flaps therebeneath to thereby vary the discharge area of the convergent nozzle portion.
Claim 22
Dependent Claim
73 words
A propulsion nozzle as in claim 12 further comprising, a plug forming an annular discharge nozzle in combination with said convergent portion and said afterbodies and said secondary flaps, said plug being convergently tapered in a downstream direction, said secondary flaps being pivotable by the same actuator means to positions in which their downstream ends engage said plug to divert the gas stream laterally and forwardly from the nozzle to provide reverse thrust.
Claim 23
Dependent Claim
46 words
A propulsion nozzle as in claim 1 wherein, the upstream portions of the afterbodies are formed by a cylindrical frame structure and structural hoop means interconnect the afterbodies downstream of said cylindrical frame structure to minimize the cantilever loadings of said afterbodies on said frame structure.
Claim 24
Dependent Claim
26 words
A propulsion nozzle as in claim 22 wherein, the structural hoop means comprise a relatively thin airfoil interconnection between the extreme downstream ends of said afterbodies.
Claim 25
Dependent Claim
28 words
A propulsion nozzle as in claim 22 wherein, said secondary flaps are pivotally mounted on said afterbodies and said pivotal mountings comprise said hoop structure through said afterbodies.
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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) | 1974-08-09 | 1975-02-08 | 1975-08-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-08-09 | 1979-02-08 | 1979-08-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-08-09 | 1983-02-08 | 1983-08-10 | $7700.00 | Window Closed / Lapsed |