US3747855A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Propulsion nozzles
Assignee: General Electric Co
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Filing: 1972-03-01
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Granted: 1973-07-24
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Expires: 1992-03-01
Abstract
Abstract A propulsion nozzle is disclosed in combination with a gas turbine engine. The nozzle is of the variable geometry, convergent-divergent type adapted for both subsonic and supersonic operation. The nozzle is also of the two stage ejector type, selectively utilizing tertiary, or ambient, air during subsonic operation. A variable ejector is provided between the convergent and divergent portions of the nozzle. The variable ejector provides a positive expanson surface during supersonic operation and facilitates introduction of secondary and tertiary air during subsonic operation for improved efficiency. The variable ejector may be displaced in a downstream direction and its flaps swung inwardly to block the hot gas stream discharge of the gas turbine engine, for reverse thrut.
Inventors
- 👤 J Vdoviak
- 👤 D Dusa
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 07:12
CPC Classifications
F; F02; F02K; F02K1/00; F02K1/54; F02K1/56; F02K1/62; F02K1/06; F02K1/12; F02K1/1269; F02K1/36
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
231 words
A propulsion nozzle for receiving a motive fluid stream and discharging same to produce a propulsive force, said nozzle comprising, in series flow relationship: a variable geometry, primary nozzle; a variable ejector having a plurality of flaps mounted at their upstream ends and aerodynamically aligned to form a continuous surface when the propulsion nozzle is positioned in its supersonic operation and subsonic operation configurations; a variable geometry, secondary nozzle; said propulsion nozzle further comprising means for introducing secondary air at the upstream end of the variable ejector; means for selectively introducing tertiary air into the upstream end of the secondary nozzle; means for positioning said propulsion nozzle in a supersonic operation configuration wherein the secondary nozzle is divergent and the variable ejector is closely spaced from the primary and secondary nozzles and divergently aligned, generally with the secondary nozzle to thus comprise a positive expansion surface for the motive fluid stream as it is discharged from the primary nozzle; and means for positioning said propulsion nozzle in a subsonic operation configuration wherein the secondary nozzle is generally parallel with the propulsion nozzle axis, tertiary air is introduced into the secondary nozzle, and the variable ejector is reduced in outlet area and guides secondary and tertiary air into generally parallel flow relationship with the motive fluid stream discharge from the primary nozzle, thereby aerodynamically neutralizing the variable ejector and the secondary nozzle.
Claim 2
Dependent Claim
231 words
A propulsion nozzle for receiving a motive fluid stream and discharging same to produce a propulsive force, said nozzle comprising, in series flow relationship: a variable geometry, primary nozzle; a variable ejector having a plurality of flaps mounted at their upstream ends and aerodynamically aligned to form a continuous surface when the propulsion nozzle is positioned in its supersonic operation and subsonic operation configurations; a variable geometry, secondary nozzle; said propulsion nozzle further comprising means for introducing secondary air at the upstream end of the variable ejector; means for selectively introducing tertiary air into the upstream end of the secondary nozzle; means for positioning said propulsion nozzle in a supersonic operation configuration wherein the secondary nozzle is divergent and the variable ejector is closely spaced from the primary and secondary nozzles and divergently aligned, generally with the secondary nozzle to thus comprise a positive expansion surface for the motive fluid stream as it is discharged from the primary nozzle; and means for positioning said propulsion nozzle in a subsonic operation configuration wherein the secondary nozzle is generally parallel with the propulsion nozzle axis, tertiary air is introduced into the secondary nozzle, and the variable ejector is reduced in outlet area and guides secondary and tertiary air into generally parallel flow relationship with the motive fluid stream discharge from the primary nozzle, thereby aerodynamically neutralizing the variable ejector and the secondary nozzle.
Claim 3
Dependent Claim
60 words
A propulsion nozzle as in claim 1 wherein the variable ejector is displaceable to a position spaced downstream from the primary nozzle and in blocking relation to the motive fluid stream discharge therefrom; and at least a portion of the tertiary air introducing means are open for the discharge therefrom of the blocked motive fluid stream, thereby producing reverse thrust.
Claim 4
Dependent Claim
124 words
A propulsion nozzle as in claim 1 further comprising a surrounding pod structure supporting the secondary nozzle and further wherein the means for selectively introducing tertiary air comprise a plurality of passageways spaced around said pod structure, each passageway extending from the exterior of the pod structure, rearwardly and inwardly, to the secondary nozzle, and blow in doors pivotal from sealing positions, flush with the exterior of the pod structure, to inwardly angled positions in which said passageways are open for the introduction of tertiary air, and the plurality of flaps pivotally mounted at thier upstream ends are generally aligned with the inner ends of the blow in doors when the latter are swung inwardly for the introduction of tertiary air during subsonic operation.
Claim 5
Dependent Claim
54 words
A propulsion nozzle as in claim 3 wherein the variable ejector comprises an actuation ring on which the flaps thereof are pivotally mounted and means are provided for pivoting said flaps relative to said actuation ring and said ejector flaps are slightly convergent when the propulsion nozzle is positioned in its subsonic operation configuration.
Claim 6
Dependent Claim
83 words
A propulsion nozzle as in claim 4 wherein the means for pivoting the variable ejector flaps comprise links pivotally connected, at their inner ends, to said ejector falps and pivotally connected, at their outer ends, to said pod structure in spaced relation therearound, thereby supporting said variable ejector, and actuator means for pivoting said links relative to the pod structure to thus pivot said ejector flaps relative to said actuation ring, as well as to displace said actuation ring in an axial direction.
Claim 7
Dependent Claim
133 words
A propulsion nozzle as in claim 5 wherein the variable ejector comprises sealing flaps pivotally mounted on said actuation ring in alternating relation with the link-connected flaps and aerodynamically aligned therewith to form a continuous surface when the propulsion nozzle is positioned in its supersonic operation and subsonic operation configurations, and the variable ejector actuator means has sufficient stroke to displace the variable ejector into spaced, downstream relationship from the primary nozzle and also swing the link-connected flaps thereof away from said sealing flaps and into blocking relationship relative to the motive fluid stream discharge from the primary nozzle, and further wherein at least a portion of the blow in doors are swung inwardly to permit discharge of the blocked, motive fluid stream through the pod structure passageways, to thereby produce reverse thrust.
Claim 8
Dependent Claim
83 words
A propulsion nozzle as in claim 6 wherein the secondary nozzle comprises, at its inlet end, a fixed portion of said pod structure, the actuation ring sealingly engages said fixed portion when displaced for reverse thrust, and the secondary air introducing means comprises passageways which are blocked off by the blow in doors when the latter are swung to extreme inward positions and the blow in doors are so swung to such extreme positions when the variable ejector is positioned for reverse thrust.
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) | 1976-07-23 | 1977-01-22 | 1977-07-24 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-07-23 | 1981-01-22 | 1981-07-24 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-07-23 | 1985-01-22 | 1985-07-24 | $7700.00 | Window Closed / Lapsed |