US3667680A — Jet engine exhaust nozzle system

Claim 1

Independent Claim 103 words

A variable area nozzle for jet engine exhaust gases comprising, a primary nozzle having a spherical nozzle shell and being of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its shell wall in a closed loop load path of hoop tension, two spherical segments having a conical inner surface and a spherical outer surface complementary to the inner surface of said shell, said segments being pivotally mounted within said shell and rotatably adjustable to vary the position of the conical inner surface for providing a smooth area reduction to a variable exit area nozzle choke plane.

Claim 2

Dependent Claim 103 words

A variable area nozzle for jet engine exhaust gases comprising, a primary nozzle having a spherical nozzle shell and being of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its shell wall in a closed loop load path of hoop tension, two spherical segments having a conical inner surface and a spherical outer surface complementary to the inner surface of said shell, said segments being pivotally mounted within said shell and rotatably adjustable to vary the position of the conical inner surface for providing a smooth area reduction to a variable exit area nozzle choke plane.

Claim 3

Dependent Claim 41 words

The variable area nozzle set forth in claim 1, further including an afterburner section upstream of the pivotal spherical segments and actuator means for rotatably positioning said spherical segments to increase the nozzle exit area when in the thrust augmentation mode.

Claim 4

Dependent Claim 44 words

The structure set forth in claim 2, wherein said after burner section has its combustion chamber housed within said spherical nozzle shell such that the spherical nozzle shell reacts to the augmented pressure loads directly through hoop tension load paths in the shell wall.

Claim 5

Dependent Claim 129 words

A variable area two-stage ejection nozzle system for jet engine exhaust gases comprising; a primary nozzle having a spherical nozzle shell of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its shell wall in a closed loop loadpath of hoop tension, two pivotal spherical segments having a spherical outer surface complementary to the inner surface of said shell and rotatably adjustable within the shell, said spherical segments having an internal conical shaping for providing a smooth area reduction to a variable exit area nozzle choke plane; a secondary nozzle downstream of said primary nozzle and having blow-in doors and aerodynamically actuated pivotable trailing edge flaps for varying the secondary nozzle exit area in response to pressure variations created by primary nozzle adjustments.

Claim 6

Dependent Claim 129 words

A variable area two-stage ejection nozzle system for jet engine exhaust gases comprising; a primary nozzle having a spherical nozzle shell of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its shell wall in a closed loop loadpath of hoop tension, two pivotal spherical segments having a spherical outer surface complementary to the inner surface of said shell and rotatably adjustable within the shell, said spherical segments having an internal conical shaping for providing a smooth area reduction to a variable exit area nozzle choke plane; a secondary nozzle downstream of said primary nozzle and having blow-in doors and aerodynamically actuated pivotable trailing edge flaps for varying the secondary nozzle exit area in response to pressure variations created by primary nozzle adjustments.

Claim 7

Dependent Claim 41 words

The variable area nozzle set forth in claim 4, further including an afterburner section upstream of the pivotal spherical segments and actuator means for rotatably positioning said spherical segments to increase the nozzle exit area when in the thrust augmentation mode.

Claim 8

Dependent Claim 43 words

The structure set forth in claim 5, wherein said afterburner section haS its combustion chamber housed within said spherical nozzle shell such that the spherical nozzle shell reacts to the augmented pressure loads directly through hoop tension load paths in the shell wall.

Claim 9

Dependent Claim 122 words

A variable area ejection nozzle system for turbojet afterburning engines comprising in combination: a primary nozzle having a spherical nozzle shell of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its shell wall in a closed loop load path of hoop tension; two spherical segments having a conical inner surface and a spherical outer surface sized to conform to the internal surface contour of said shell, said segments being mounted for pivotal rotation within the shell; and actuator means for rotating said spherical segments to an abutment position to provide a continuous axially extending conical inner surface, thereby providing a smooth internal cross-section area reduction for the turbo-jet exhaust gases to the primary nozzle exit.

Claim 10

Dependent Claim 122 words

A variable area ejection nozzle system for turbojet afterburning engines comprising in combination: a primary nozzle having a spherical nozzle shell of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its shell wall in a closed loop load path of hoop tension; two spherical segments having a conical inner surface and a spherical outer surface sized to conform to the internal surface contour of said shell, said segments being mounted for pivotal rotation within the shell; and actuator means for rotating said spherical segments to an abutment position to provide a continuous axially extending conical inner surface, thereby providing a smooth internal cross-section area reduction for the turbo-jet exhaust gases to the primary nozzle exit.

Claim 11

Dependent Claim 51 words

The ejection nozzle system set forth in claim 7, further including a secondary nozzle downstream of said primary nozzle and having circumferentially spaced blow-in doors and trailing edge flaps pivotally mounted and aerodynamically actuated for varying the secondary nozzle exit area in response to pressure variations created by primary nozzle adjustments.

Claim 12

Dependent Claim 54 words

The ejection nozzle system set forth in claim 8, further including an afterburner section upstream of the pivotally mounted spherical segments wherein its combustion chamber is housed within said spherical nozzle shell such that the spherical nozzle shell reacts to the augmented pressure loads directly through hoop tension load paths in the shell wall.

Claim 13

Dependent Claim 181 words

A variable area nozzle and thrust reverser for jet engine exhaust gases comprising: a structurally rigid spherical nozzle shell having a continuous and integral inner surface for directly reacting to internal pressure loads through its shell wall in a closed loop load path of hoop tension; two spherical segments having a spherical inner surface and a spherical outer surface sized to conform to the internal surface contour of said shell, said segments being pivotally mounted to said shell and rotatably adjustable within said shell; clam shell blocker doors having a conical inner surface and a spherical outer surface sized to conform to the internal surface contour of said segments, said doors being concentrically incorporated within said pivotal spherical segments and pivotally mounted therewith for rotatable adjustment with respect thereto for blocking the flow through the variable area nozzle to provide for reverse thrust control and for rotatable adjustment in unison therewith for varying the position of the conical inner surface to provide an internal cross-section area reduction for the jet engine exhaust gases when not in the thrust reversal operating position.

Claim 14

Dependent Claim 181 words

A variable area nozzle and thrust reverser for jet engine exhaust gases comprising: a structurally rigid spherical nozzle shell having a continuous and integral inner surface for directly reacting to internal pressure loads through its shell wall in a closed loop load path of hoop tension; two spherical segments having a spherical inner surface and a spherical outer surface sized to conform to the internal surface contour of said shell, said segments being pivotally mounted to said shell and rotatably adjustable within said shell; clam shell blocker doors having a conical inner surface and a spherical outer surface sized to conform to the internal surface contour of said segments, said doors being concentrically incorporated within said pivotal spherical segments and pivotally mounted therewith for rotatable adjustment with respect thereto for blocking the flow through the variable area nozzle to provide for reverse thrust control and for rotatable adjustment in unison therewith for varying the position of the conical inner surface to provide an internal cross-section area reduction for the jet engine exhaust gases when not in the thrust reversal operating position.

Claim 15

Dependent Claim 47 words

The variable area nozzle and thrust reverser set forth in claim 10, further including a flow reverser opening in said spherical nozzle shell to provide reverse gas directional control, and reverser cascades positioned in said opening for receiving gas flow and directing it forwardly for thrust reversal.

Claim 16

Dependent Claim 46 words

The variable area nozzle and thrust reverser set forth in claim 10, further including an interlock mechanism between the clam shell blocker doors and the said spherical segments to provide for their moving together except when the blocker doors are actuated to the reverse thrust position.

Claim 17

Dependent Claim 45 words

The variable area nozzle and thrust reverser set forth in claim 11, further including a reverser cover for uncovering said opening in said spherical nozzle shell when said clam shell blocker doors are rotated to block the forward thrust flow through said variable area nozzle.

Claim 18

Dependent Claim 195 words

A variable area nozzle and thrust reverser for jet engine exhaust gases comprising: a structurally rigid spherical nozzle shell having a continuous and integral inner surface for directly reacting to internAl pressure loads through its shell wall in a closed loop load path of hoop tension; two spherical segments having a spherical inner surface and a spherical outer surface sized to conform to the internal surface contour of said shell, said segments being pivotally mounted to said shell and rotatably adjustable within said shell; clam shell blocker doors having a conical inner surface and a spherical outer surface sized to conform to the internal surface contour of said segments, said doors being concentrically incorporated within said pivotal spherical segments and pivotally mounted therewith for rotatable adjustment with respect thereto; actuator means for pivoting the spherical segments between a first and second position for a range of exit area variation in the non-thrust reversing mode and between a second and third position wherein the clam shell blocker doors are rotated with respect to said pivotal spherical segments to block the axial flow of exhaust gases through the variable area nozzle to provide for reverse thrust control.

Claim 19

Dependent Claim 195 words

A variable area nozzle and thrust reverser for jet engine exhaust gases comprising: a structurally rigid spherical nozzle shell having a continuous and integral inner surface for directly reacting to internAl pressure loads through its shell wall in a closed loop load path of hoop tension; two spherical segments having a spherical inner surface and a spherical outer surface sized to conform to the internal surface contour of said shell, said segments being pivotally mounted to said shell and rotatably adjustable within said shell; clam shell blocker doors having a conical inner surface and a spherical outer surface sized to conform to the internal surface contour of said segments, said doors being concentrically incorporated within said pivotal spherical segments and pivotally mounted therewith for rotatable adjustment with respect thereto; actuator means for pivoting the spherical segments between a first and second position for a range of exit area variation in the non-thrust reversing mode and between a second and third position wherein the clam shell blocker doors are rotated with respect to said pivotal spherical segments to block the axial flow of exhaust gases through the variable area nozzle to provide for reverse thrust control.

Claim 20

Dependent Claim 71 words

The variable area nozzle and thrust reverser set forth in claim 14, further including a flow reverser opening in said spherical nozzle shell to provide for reverse gas flow from the spherical nozzle shell when the clam shell blocker doors are rotated with respect to the pivotal spherical segments from the second to the third position by said actuator means to block the forward thrust flow through the variable area nozzle.

Claim 21

Dependent Claim 45 words

The variable area nozzle and thrust reverser set forth in claim 15, further including a reverser cover for uncovering said opening in said spherical nozzle shell when the clam shell blocker doors are rotated from their second to their third position by the actuator means.

Claim 22

Dependent Claim 100 words

The variable area nozzle and thrust reverser set forth in claim 16, further including locking means for rotatably interlocking the spherical segments incorporating the blocker doors with the reverser cover when the spherical segments including the blocker doors are rotated by the actuator means from their first position to their second position whereby the opening in the nozzle shell is uncovered when the blocker doors are rotated with respect to the spherical segments by the actuator means for blocking the axial flow of exhaust gases as they are moved from their second position to their third thrust reversing mode position.

Claim 23

Dependent Claim 182 words

A variable area nozzle and noise suppressor for jet engine exhaust gases comprising: a primary nozzle having a spherical nozzle wall of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its wall in a closed loop load path of hoop tension, two spherical segments having a conical inner surface and a spherical outer surface complementary to the inner surface of said nozzle wall, said segments being pivotally mounted therein and rotatably adjustable from within the encased nozzle wall to vary the position of the conical inner surface for providing a smooth area reduction to a variable exit area nozzle choke plane; noise suppression elements incorporated into said spherical nozzle wall; actuator means for pivoting the spherical segments between a first and second position for a range of primary nozzle exit area variation in the nonsuppression mode and between a second and third position wherein the noise suppression elements are exposed to the flow of exhaust gases and divert flow radially outward of the nozzle wall through the noise suppression elements and thereby achieve noise suppression.

Claim 24

Dependent Claim 182 words

A variable area nozzle and noise suppressor for jet engine exhaust gases comprising: a primary nozzle having a spherical nozzle wall of a continuous and integral inner surface structure for directly reacting to internal pressure loads through its wall in a closed loop load path of hoop tension, two spherical segments having a conical inner surface and a spherical outer surface complementary to the inner surface of said nozzle wall, said segments being pivotally mounted therein and rotatably adjustable from within the encased nozzle wall to vary the position of the conical inner surface for providing a smooth area reduction to a variable exit area nozzle choke plane; noise suppression elements incorporated into said spherical nozzle wall; actuator means for pivoting the spherical segments between a first and second position for a range of primary nozzle exit area variation in the nonsuppression mode and between a second and third position wherein the noise suppression elements are exposed to the flow of exhaust gases and divert flow radially outward of the nozzle wall through the noise suppression elements and thereby achieve noise suppression.

Claim 25

Dependent Claim 57 words

The variable area nozzle and noise suppressor set forth in claim 18, further including an afterburner section upstream of the pivotally mounted spherical segments wherein its combustion chamber is housed within said spherical nozzle wall such that the spherical nozzle wall reacts to the augmented pressure loads directly through hoop tension load paths in the nozzle wall.

Claim 26

Dependent Claim 62 words

The variable area nozzle and noise suppression system set forth in claim 18, furTher including a secondary nozzle downstream of said primary nozzle and noise suppression spokes retractably mounted within the secondary nozzle wall for extending radially inward from the secondary nozzle wall into the exit flow from the primary nozzle to break up the exhaust flow and thereby achieve noise suppression.

Claim 27

Dependent Claim 110 words

The variable area nozzle and noise suppression system set forth in claim 18, further including a secondary nozzle downstream of said primary nozzle and wherein said noise suppression elements incorporated into the spherical nozzle wall of the primary nozzle further include retractable noise suppression tubes having a segmented vane nozzle, which tubes are pivotally connected and retractably mounted with respect to the secondary nozzle for directing the jet exhaust stream gases from the interior of the spherical nozzle wall of the primary nozzle directly into the free stream flow in order to break up the exhaust gas flow into a plurality of small jet streams and thereby achieve noise suppression.

Claim 28

Dependent Claim 85 words

The variable area nozzle and noise suppression system as set forth in claim 23, wherein said noise suppression tubes having a segmented vane nozzle further include noise suppression spokes retractably mounted within the secondary nozzle wall to project radially inward from the secondary nozzle wall when in the extended position; linkage means connected to said noise suppression tubes and slaved to said noise suppression spokes for providing an over center linkage noise suppression locking mechanism for the tubes and spokes when in the stowed position.

Claim 29

Dependent Claim 52 words

The variable area nozzle and noise suppression system set forth in claim 22, further including blow-in doors extending radially inward from the secondary nozzle wall for admitting tertiary air into the exit flow from the extended spokes to ventilate the base area thereof, thereby reducing base drag of the noise suppression spokes.

Claim 30

Dependent Claim 52 words

The variable area nozzle and noise suppression system set forth in claim 25, further including trailing edge flaps pivotally mounted and aerodynamically actuated for varying the secondary nozzle exit area in response to pressure variations created by primary nozzle adjustments and tertiary air flow into the exit flow from the primary nozzle.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1975-06-06	1975-12-06	1976-06-06	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1979-06-06	1979-12-06	1980-06-06	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1983-06-06	1983-12-06	1984-06-06	$7700.00	Window Closed / Lapsed

Jet engine exhaust nozzle system

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