Office Action 2: Notice of Allowance (2025-08-27)

CLAIMS:
AMENDMENTS TO THE CLAIMS

This listing of claims will replace all prior listing of claims in the application:

1\. (Currently Amended) A thrust reverser, comprising:
an outer articulating panel comprising an outer thrust reverser door pivotally coupled to the outer articulating panel, the outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel to create a first opening in the outer articulating panel; and
an inner articulating panel comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel;
wherein the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses through the second opening and the first opening in a direction having a forward component to generate reverse thrust to an aircraft.
2\. (Original) The thrust reverser of claim 1, wherein the inner articulating panel further comprises a forward inner skin and an aft inner skin.
3\. (Original) The thrust reverser of claim 2, wherein a nozzle throat is at least partially defined at an interface between the forward inner skin and the aft inner skin.
4\. (Original) The thrust reverser of claim 3, wherein the forward inner skin is configured to pivot to vary a nozzle throat area.
5\. (Original) The thrust reverser of claim 3, further comprising a sliding joint offset from the interface between the forward inner skin and the aft inner skin, wherein the forward inner skin and the aft inner skin are coupled together at the sliding joint.
6\. (Original) The thrust reverser of claim 1, wherein a nozzle exit is at least partially defined at an aft end of the inner articulating panel.

7\. (Original) The thrust reverser of claim 6, wherein the outer articulating panel is configured to pivot to vary a nozzle exit area.
8\. (Currently Amended) The thrust reverser of claim \[\[1\]\]2, further comprising a first thrust reverser actuator configured to pivot the outer thrust reverser door with respect to the outer articulating panel between the outer door deployed position and the outer door stowed position.
9\. (Original) The thrust reverser of claim 8, further comprising a second thrust reverser actuator configured to pivot the inner thrust reverser door with respect to the inner articulating panel between the deployed inner door position and the stowed inner door position.

10\. (Currently Amended) The thrust reverser of claim \[\[1\]\]9, further comprising a first nozzle actuator configured to pivot the outer articulating panel.

11\. (Original) The thrust reverser of claim 10, further comprising a second nozzle actuator configured to pivot the forward inner skin.

12\. (Original) The thrust reverser of claim 11, further comprising:a first linear joint disposed between the first nozzle actuator and the outer articulating panel;
and a second linear joint disposed between the second nozzle actuator and the forward inner skin.

13\. (Original) The thrust reverser of claim 12, further comprising:a third linear joint disposed between the first thrust reverser actuator and the outer thrust reverser door; and
a fourth linear joint disposed between the second thrust reverser actuator and the inner thrust reverser door.

14\. (Original) The thrust reverser of claim 1, wherein the outer articulating panel further comprises an outer skin.

15\. (Original) The thrust reverser of claim 14, further comprising a flap located at a forward edge of the outer skin, wherein the flap is slidingly coupled to the outer skin to maintain a continuous aerodynamic surface while the outer articulating panel pivots.

16\. (New) The thrust reverser of claim 2, wherein the forward inner skin is pivotably coupled to a forward bulkhead.

17\. (New) The thrust reverser of claim 10, wherein the first nozzle actuator is pivotably coupled to an interior of the outer articulating panel.

18\. (New) The thrust reverser of claim 11, wherein the second nozzle actuator is pivotably coupled to an interior of the forward inner skin.

OFFICE ACTION:
Notice of Pre-AIA  or AIA  Status
The present application, filed on or after March 16, 2013, is being examined under the first inventor to file provisions of the AIA .
EXAMINER’S AMENDMENT
An examiner’s amendment to the record appears below. Should the changes and/or additions be unacceptable to applicant, an amendment may be filed as provided by 37 CFR 1.312. To ensure consideration of such an amendment, it MUST be submitted no later than the payment of the issue fee.
Authorization for this examiner’s amendment was given in an interview with Trent Hoffman on 8/18/25.
IN THE CLAIMS:
1. (Currently Amended) A thrust reverser, comprising:
an outer articulating panel comprising an outer thrust reverser door pivotally coupled to the outer articulating panel, the outer thrust reverser door is movable between an outer door stowed position and an outer door deployed position with respect to the outer articulating panel to create a first opening in the outer articulating panel; and
an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis and comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel;
wherein the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses through the second opening and the first opening in a direction having a forward component to generate reverse thrust to an aircraft.
Allowable Subject Matter
Claim 1-18 are allowed.
The following is an examiner’s statement of reasons for allowance: the prior art fails to teach, in combination with the other claim limitations, an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis and comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel. US 4836451 teaches inner and outer articulating panels and inner and outer thrust reverser doors, but fails to teach the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel to create a second opening in the inner articulating panel. US 4382551 teaches articulating panels and thrust reverser doors that are movable to create openings in the articulating panels, but fails to teach an inner articulating panel positioned radially inward of the outer articulating panel relative to an engine central longitudinal axis.
Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee.  Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Conclusion

APPLICANT REBUTTAL: REMARKSClaims 1-18 will be pending after entry of the present paper. Claims 1, 8, and 10 are amended. Claims 16-18 are new. Support for the amendments and the new claims may be found in the originally filed  specification, drawings, and  claims. Applicant respectfully requests reconsideration of this application in view of the amendments and remarks submitted herein.Allowable Subject Matter Applicant thanks the Examiner for the indication that claim 13 would be allowable if rewritten in independent form.Telephonic Interview Applicant thanks the Examiner for the courtesies extended in the telephonic interview of July 10, 2025, wherein Applicant's representative and the Office discussed the proposed claim amendments. During the Interview, the Examiner agreed that the enclosed amendments overcome the current rejections. As agreed upon during the Examiner Interview, reference A (Herrick, US Patent No. 4,836,451) fails to disclose or contemplate each and every feature of amended claim 1.Applicant herein presents claim amendments and arguments consistent with the discussion in that interview. No formal agreement as to allowability was reached.Rejections under 35 U.S.C. § 112 Claims 11-13 are rejected under 35 U.S.C. 112(b) as being indefinite for failing to particularly point out and distinctly claim the subject matter which the inventor or a joint inventor regards as the invention.Claim 11 is rejected under 35 U.S.C. §112(b) as lacking antecedent basis for "the forward inner skin" and claim 13 as lacking antecedent basis for "the first thrust reverser actuator" and "the second thrust reverser actuator." Applicant herein amends claims 8 and 10 to obviate these rejections and respectfully requests reconsideration and withdrawal of these rejections.Rejections under 35 U.S.C. § 102 Claim(s) 1, 6-7, and 14 are rejected under 35 U.S.C. 102(a)(1) as being anticipated by US Patent No. 4,836,451 ("Herrick"). Applicant respectfully disagrees with these rejections, but Applicant presents claim amendments in order to clarify the patentable aspects of the claims and to expedite prosecution.Independent Claim 1 The Examiner asserts that Herrick discloses "the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gases to generate reverse thrust to an aircraft" as recited by claim 1. However, as agreed upon during the Examiner Interview, Herrick fails to disclose an outer thrust reverser door movable to "create a first opening in the outer articulating panel," an inner thrust reverser door movable to "create a second opening in the inner articulating panel" and "the inner thrust reverser door and the outer thrust reverser door are configured to redirect exhaust gasses through the second opening and the first opening in a direction having a forward component to generate reverse thrust to an aircraft," as required by amended claim 1.Herrick merely discloses "Exterior reverser doors" that "exhaust the diverted gases." (Herrick, col 5 1. 7-9). Applicant respectfully submits that the rejections under Herrick be withdrawn in light of the above reasons.The Office Action also asserts that both the claims and figures of Herrick teach a thrust reverser comprising "an inner articulating panel comprising an inner thrust reverser door pivotally coupled to the inner articulating panel, the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel" as recited by claim 1. FIG. 4 of Herrick is reproduced below for convenience.?   60  64'   1 1  1
56' 62  6' FIG. 4 Herrick, FIG. 4 The cited portion of Herrick states "Clamshells 34, 36 are independently pivotable to achieve a varying nozzle throat dimension 42 in order to provide the optimum nozzle outlet area for efficient thrust production. Thrust vectoring in the vertical plane may be achieved by orienting the clamshells 34, 36 asymmetrically with respect to the nozzle center line 40 so as to bias the flow of discharged gas 8 relative thereto." (Herrick, col 3 1. 14-21). At no point does Herrick disclose or contemplate "the inner thrust reverser door is movable between an inner door stowed position and an inner door deployed position with respect to the inner articulating panel." Accordingly, Applicant respectfully requests that the rejection of claim 1 be reconsidered and withdrawn. Claims 2-15 depend from claim 1 and are therefore patentable for the same reasons discussed above, further in view of their own respective features. Accordingly, Applicant respectfully requests that the rejection of claim 2-15 be reconsidered and withdrawn.Rejections under 35 U.S.C. § 103 Claims 2-4 are rejected under 35 U.S.C. § 103 as being unpatentable over Herrick (US 4,836,451) in view of Lidstone (US 5,779,150).Claim 5 is rejected under 35 U.S.C. § 103 as being unpatentable over Herrick (US 4,836,451) in view of Lidstone (US 5,779,150), and further in view of Wolf (US 5,103,639) Claims 8-9 are rejected under 35 U.S.C. § 103 as being unpatentable over Herrick (US 4,836,451) in view of Madden (US 4,690,329).Claims 10-12 are rejected under 35 U.S.C. § 103 as being unpatentable over Herrick (US 4,836,451) in view of Reedy (US 5,120,005).Claim 15 is rejected under 35 U.S.C. § 103 as being unpatentable over Herrick (US 4,836,451) in view of Joyce (US 6,910,328).Dependent claims 2-5, 8-12, and 15 variously depend from independent claim 1 so dependent claims 2-5, 8-12, and 15 are allowable over the cited references for the reasons set forth above, in addition to their own unique features.New Claim 16:New claim 16 is added to recite "the forward inner skin is pivotably coupled to a forward bulkhead." Support for the amendment can be found in at least FIGS. 5A-5E and ¶¶[0041]-[0042].New Claim 17:New claim 17 is added to recite "the first nozzle actuator is pivotably coupled to an interior of the outer articulating panel." Support for the amendment can be found in at least FIGS. 4A-4B and ¶[0046].New Claim 18:New claim 18 is added to recite "the second nozzle actuator is pivotably coupled to an interior of the forward inner skin." Support for the amendment can be found in at least FIGS. 4A- 4B and ¶[0047].CONCLUSIONIn view of the above remarks, Applicant respectfully submits that all pending claims are allowable and requests allowance of the pending claims. The Examiner is invited to telephone the undersigned at the Examiner's convenience, if that would help further prosecution of the subject application. Applicant authorizes and respectfully request that any fees due or overpayments be charged or credited to Deposit Account No. 19-2814. This statement does NOT authorize payment of the issue fee.Respectfully submitted, Dated:   August 1, 2025


CITED REFERENCE SUMMARIES: Ref US4382551A: Claims:
A thrust reverser/exhaust nozzle assembly for a gas turbine engine having an axis comprising: gas turbine engine exhaust case structure; first nozzle means including a plurality of axially extending flaps circumferentially disposed about the engine axis and mounted on said case structure, said flaps being movable between a closed position wherein they define a first exhaust gas flow path having a minimum exit area and an open position wherein they define an exhaust gas flow path having a maximum exit area, each of said flaps including a cutout therethrough; and a deflector door attached to each flap and movable between a stowed position wherein said door fits within and closes the said cutout and a deployed position wherein said door extends into the flow path and coacts with deployed doors of adjacent flaps to redirect at least a portion of the flow in an upstream direction through the said cutouts.
gas turbine engine exhaust case structure;
first nozzle means including a plurality of axially extending flaps circumferentially disposed about the engine axis and mounted on said case structure, said flaps being movable between a closed position wherein they define a first exhaust gas flow path having a minimum exit area and an open position wherein they define an exhaust gas flow path having a maximum exit area, each of said flaps including a cutout therethrough; and
a deflector door attached to each flap and movable between a stowed position wherein said door fits within and closes the said cutout and a deployed position wherein said door extends into the flow path and coacts with deployed doors of adjacent flaps to redirect at least a portion of the flow in an upstream direction through the said cutouts.
The nozzle assembly according to claim 1 wherein said flaps are hinged for rotation to said case structure at their upstream ends.
The nozzle assembly according to claims 1 or 2 wherein said flaps are free floating.
The nozzle assembly according to claims 1 or 2 wherein said first gas flow path is a divergent flow path, and each of said flaps includes a forward portion and a rearward portion, said rearward portion defining said divergent flow path, and said assembly includes variable area second nozzle means disposed radially inwardly of and surrounded by said forward portion of said flaps and defining a convergent exhaust gas flow path immediately upstream of said divergent gas flow path.
The nozzle assembly according to claims 1 or 2 wherein each of said doors is mounted for rotation within its respective cutout about a door axis, each of said doors having a forward portion extending upstream from said door axis and a rearward portion extending downstream from said door axis, wherein when said doors are in their fully deployed position their rearward portions extend radially inwardly into the gas flow path and sealingly engage adjacent deployed doors to define a wall which substantially blocks axial flow of exhaust gas and their forward portions extend radially outwardly and redirect gas flow through said cutouts in an upstream direction.
The nozzle assembly according to claim 3 including locking means for locking said flaps in said closed position when said doors are in a deployed position.
The nozzle assembly according to claim 5 including actuation means for rotating said doors about their respective door axes between their deployed and stowed positions.
The nozzle assembly according to claim 7 wherein said first nozzle means has only three or four of said flaps.
The nozzle assembly according to claim 7 wherein each of said flaps include axially extending side surfaces which abut the side surfaces of adjacent flaps when said flaps are in a closed position.
The nozzle assembly according to claim 9 wherein said flaps each have a radially outwardly facing external surface and radially inwardly facing internal surface, said internal surfaces defining the first nozzle means gas flow path, and said doors each have a radially outwardly facing surface and radially inwardly facing surface which, when said doors are in their stowed position are substantially flush with their respective flap external and internal surfaces.
Ref US4836451: Claims:
1. A thrust vectoring exhaust nozzle for directing a gas stream, comprising:a fixed exhaust collar having a semispherical external surface, an internal passage for conducting the gas stream therethrough, and an aftward facing discharge opening; a gimbal assembly including first and second pivots secured adjacent the spherical collar surface and defining therebetween a first gimbal axis passing through a center point defined by the collar spherical surface, and a gimbal ring, surrounding the collar and pivotally supported by the first and second gimbal pivots; third and fourth pivots defining therebetween a second common axis perpendicular to the first gimbal axis; a first clamshell having a spherical interior surface corresponding to the collar spherical exterior surface, the first clamshell secured between the third and fourth pivots and selectably pivotable about the second common axis; a second clamshell having a spherical surface corresponding to the spherical exterior surface of the fixed collar, the second clamshell also secured between the third and fourth pivot points and selectably pivotable about the second common axis; first slidable means for sealing the first clamshell to the exterior of the fixed collar; second slidable means for sealing the second clamshell to the exterior of the fixed collar; and means for selectably rotating the gimbal ring about the first gimbal axis.
2. The nozzle as recited in claim 1, wherein the first and second clamshells each includea facing lip edge for defining an exhaust nozzle throat therebetween, and wherein the first and second clamshells each further include a planer stub flap secured to the respective nozzle lip of the first and second clamshells, each stub flap extending generally radially outward therefrom with respect to the spherical center point and each flap terminating in a first linear hinge oriented perpendicular to the first gimbal axis and parallel with the second common axis, a first upper divergent flap having a leading edge secured to the linear hinge of the stub flap of the first clamshell; a second lower divergent flap having a leading edge secured to the linear hinge of the stub flap of the second clamshell, and means for selectably pivoting the first and second divergent flaps about the corresponding linear hinges of the respective first and second clamshells.
3. The nozzle as recited in claim 1, further including:at least one reverse gas flow passage having means for regulating the flow of gas therethrough, said gas flow passage disposed between the collar internal flow passage and the exterior of the nozzle for discharging the gas stream during selected periods of desired reverse thrust.
4. A thrust vectoring exhaust nozzle comprising:a fixed outlet collar having a generally rearward facing exhaust opening and a semispherical external surface defined about a center point; a gimbal ring, pivotably secured about the fixed collar and rotatable about a gimbal axis passing through the center point, the gimbal axis being oriented transversely with respect to a gas stream flowing through the outlet collar; a first clamshell having a surface corresponding to the exterior collar spherical surface; a second clamshell having a surface corresponding to the exterior collar spherical surface; the first and second clamshells being pivotably secured to the gimbal ring at second and third pivot points and independently pivotable about a common axis defined between the third and fourth pivot points, said common axis passing through the center point and oriented perpendicularly with respect to the gimbal axis and the flowing gas stream.
5. The nozzle as recited in claim 4, wherein:the clamshells each include a nozzle lip defining a nozzle throat thereby, and wherein the clamshells are pivotable into contact at said nozzle lips, the contacted clamshells defining a semispherical blocking structure disposed in the gas stream for substantially closing the flow of exhaust gas aftward from the nozzle, and wherein the nozzle further comprises: at least one reverse flow passage defining an alternate exhaust gas discharge path when the first and second clamshells define said blocking structure.
6. The nozzle as recited in claim 5, wherein:the contacted clamshells define a flow blocking structure smaller than the fixed collar opening, and wherein the exhaust gas flow passes out of the nozzle via upper and lower lateral openings defined between the fixed collar and the corresponding contacted upper and lower clamshells.
7. The nozzle as recited in claim 4, wherein the upper and lower clamshells each further include:a radially extending, planer stub flap secured to the nozzle lip of each clamshell, each stub flap including a linear hinge joint at the radially outward flap edge, and wherein the nozzle further comprises upper and lower divergent flaps, each flap having a leading edge secured to the linear hinge joint of the corresponding first and second clamshell stub flap, and a pair of spaced apart side walls, secured to the gimbal ring and extending aftward adjacent the stub flaps and divergent flaps and oriented generally perpendicular thereto, the stub flaps, divergent flaps, and side walls together defining a variable geometry nozzle outlet passage.
Ref US4382551: Claims:
1. A thrust reverser/exhaust nozzle assembly for a gas turbine engine having an axis comprising:gas turbine engine exhaust case structure; first nozzle means including a plurality of axially extending flaps circumferentially disposed about the engine axis and mounted on said case structure, said flaps being movable between a closed position wherein they define a first exhaust gas flow path having a minimum exit area and an open position wherein they define an exhaust gas flow path having a maximum exit area, each of said flaps including a cutout therethrough; and a deflector door attached to each flap and movable between a stowed position wherein said door fits within and closes the said cutout and a deployed position wherein said door extends into the flow path and coacts with deployed doors of adjacent flaps to redirect at least a portion of the flow in an upstream direction through the said cutouts.
2. The nozzle assembly according to claim 1 wherein said flaps are hinged for rotation to said case structure at their upstream ends.
3. The nozzle assembly according to claims 1 or 2 wherein said flaps are free floating.
4. The nozzle assembly according to claims 1 or 2 wherein said first gas flow path is a divergent flow path, and each of said flaps includes a forward portion and a rearward portion, said rearward portion defining said divergent flow path, and said assembly includes variable area second nozzle means disposed radially inwardly of and surrounded by said forward portion of said flaps and defining a convergent exhaust gas flow path immediately upstream of said divergent gas flow path.
5. The nozzle assembly according to claims 1 or 2 wherein each of said doors is mounted for rotation within its respective cutout about a door axis, each of said doors having a forward portion extending upstream from said door axis and a rearward portion extending downstream from said door axis, wherein when said doors are in their fully deployed position their rearward portions extend radially inwardly into the gas flow path and sealingly engage adjacent deployed doors to define a wall which substantially blocks axial flow of exhaust gas and their forward portions extend radially outwardly and redirect gas flow through said cutouts in an upstream direction.
6. The nozzle assembly according to claim 3 including locking means for locking said flaps in said closed position when said doors are in a deployed position.
7. The nozzle assembly according to claim 5 including actuation means for rotating said doors about their respective door axes between their deployed and stowed positions.
8. The nozzle assembly according to claim 7 wherein said first nozzle means has only three or four of said flaps.
9. The nozzle assembly according to claim 7 wherein each of said flaps include axially extending side surfaces which abut the side surfaces of adjacent flaps when said flaps are in a closed position.
10. The nozzle assembly according to claim 9 wherein said flaps each have a radially outwardly facing external surface and radially inwardly facing internal surface, said internal surfaces defining the first nozzle means gas flow path, and said doors each have a radially outwardly facing surface and radially inwardly facing surface which, when said doors are in their stowed position are substantially flush with their respective flap external and internal surfaces.