Patent Application 17648321 - RADIAL-RADIAL-AXIAL SWIRLER ASSEMBLY - Rejection
Appearance
Patent Application 17648321 - RADIAL-RADIAL-AXIAL SWIRLER ASSEMBLY
Title: RADIAL-RADIAL-AXIAL SWIRLER ASSEMBLY
Application Information
- Invention Title: RADIAL-RADIAL-AXIAL SWIRLER ASSEMBLY
- Application Number: 17648321
- Submission Date: 2025-05-19T00:00:00.000Z
- Effective Filing Date: 2022-01-19T00:00:00.000Z
- Filing Date: 2022-01-19T00:00:00.000Z
- National Class: 060
- National Sub-Class: 737000
- Examiner Employee Number: 96929
- Art Unit: 3741
- Tech Center: 3700
Rejection Summary
- 102 Rejections: 0
- 103 Rejections: 1
Cited Patents
The following patents were cited in the rejection:
- US 4365470đ
- US 6546732đ
Office Action Text
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 . Continued Examination Under 37 CFR 1.114 A request for continued examination under 37 CFR 1.114, including the fee set forth in 37 CFR 1.17(e), was filed in this application after final rejection. Since this application is eligible for continued examination under 37 CFR 1.114, and the fee set forth in 37 CFR 1.17(e) has been timely paid, the finality of the previous Office action has been withdrawn pursuant to 37 CFR 1.114. Applicant's submission filed on 02/19/2025 has been entered on 03/19/2025. Drawings The drawings were received on 02/19/2025. These drawings are accepted and entered on 03/19/2025. Claim Objections Claims 1, 8, and 15 are objected to because of the following informalities: the recitation âthe plurality of vanes being twisted to generate a desired exit velocity profile of the ferrule axial airflowâ is believed to be in error for - - the plurality of vanes of the ferrule swirler being twisted to generate a desired exit velocity profile of the ferrule axial airflow - - Appropriate correction is required. Claim Rejections - 35 USC § 103 In the event the determination of the status of the application as subject to AIA 35 U.S.C. 102 and 103 (or as subject to pre-AIA 35 U.S.C. 102 and 103) is incorrect, any correction of the statutory basis (i.e., changing from AIA to pre-AIA ) for the rejection will not be considered a new ground of rejection if the prior art relied upon, and the rationale supporting the rejection, would be the same under either status. The following is a quotation of 35 U.S.C. 103 which forms the basis for all obviousness rejections set forth in this Office action: A patent for a claimed invention may not be obtained, notwithstanding that the claimed invention is not identically disclosed as set forth in section 102, if the differences between the claimed invention and the prior art are such that the claimed invention as a whole would have been obvious before the effective filing date of the claimed invention to a person having ordinary skill in the art to which the claimed invention pertains. Patentability shall not be negated by the manner in which the invention was made. The factual inquiries for establishing a background for determining obviousness under 35 U.S.C. 103 are summarized as follows: 1. Determining the scope and contents of the prior art. 2. Ascertaining the differences between the prior art and the claims at issue. 3. Resolving the level of ordinary skill in the pertinent art. 4. Considering objective evidence present in the application indicating obviousness or nonobviousness. Claims 1-3, 8-10, and 15-17 are rejected under 35 U.S.C. 103 as being unpatentable over Sandelis 20110271682 in view of Young 6546732 and COMMARET 20080000234 as evidenced by Matthews 4365470. Regarding claim 1, Sandelis teaches the invention as claimed: a swirler assembly (34) for use in a combustor (comprising a combustion chamber 10), the swirler assembly (34) comprising: a first air swirler (54) having a first swirler vane assembly (the plurality of vanes per [0026], also see Fig. 2), wherein the first swirler vane assembly ([0026] and Fig. 2) is configured to generate a first radial rotating airflow (swirling air stream 50, see Fig. 2), the first radial rotating airflow rotating in a first direction (the swirling direction of swirling air stream 50); a second air swirler (56) adjacent the first air swirler (swirler 56 adjacent swirler 54 via mounting rim 76, see Fig. 2) and having a second swirler vane assembly (the plurality of vanes per [0026], also see Fig. 2), wherein the second swirler vane assembly ([0026] and Fig. 2) is configured to generate a second radial rotating airflow (swirling air stream 52, Fig. 2), the second radial rotating airflow rotating in a second direction (the swirling direction of swirling air stream 52); and a ferrule (ring 60 and nozzle 36, Fig. 2) coupled to the first air swirler and the second air swirler (via busing 64, see Fig. 2), the ferrule (ring 60 and nozzle 36, Fig. 2) comprising a fuel nozzle (36, [0023] and Fig. 2) and a ferrule swirler (ring 60 having a plurality of inclined orifices 168s that imparts the rotation of the air stream 148 passing through as shown in Fig. 6, i.e., the ring 60 is a ferrule swirler) having a plurality of inclined air orifices (168s, see Figs. 2, 4, and 6 and [0042]), wherein the plurality of inclined air orifices (168s) of the ferrule swirler (60) are configured to generate a ferrule axial airflow (148) having a swirl (see Figs. 2, 4, and 6 and [0042]) to interact and mix with the first radial rotating airflow (50) and to interact with and to mix with the second radial rotating airflow (52) resulting in a mixture of the ferrule axial airflow with the first radial rotating airflow and with the second radial rotating airflow (such mixture is formed downstream of the venturi 58, see Fig. 2 and [0030-0031]), the plurality of inclined air orifices (168s) of the ferrule swirler (60) being inclined to generate an exit velocity profile of the ferrule axial air flow (the swirled air stream 148 having a tangential velocity profile determined by an inclined angle of orifices 168s, see Fig. 6 and [0042]), the fuel nozzle (36) being configured to generate a fuel jet to mix with the ferrule axial airflow, the first radial rotating airflow and the second radial rotating airflow ([0023 and 0030-0031] and Fig. 2), wherein the first air swirler (54) and the second air swirler (56) are separated by a wall (76 and 58, Fig. 2) so that each of the first radial rotating airflow (swirling air stream 50) and the second radial rotating airflow (swirling air stream 52) are separated by the wall (76 and 58) to interact and mix with the ferrule axial air flow (148, best seen in Figs. 2 and 6), wherein the ferrule axial airflow (148) forms an angle (the inclined angle per [0042]) relative to a longitudinal axis of the swirler assembly (A, Fig. 1), and wherein the ferrule (ring 60 part) is movable radially ([0004 and 0038]) in a direction generally perpendicular to the longitudinal axis of the swirler assembly (axis A, see Figs. 1-2 and [0037]), wherein the ferrule swirler (ring 60 comprising the plurality of inclined air orifices 168s, see Figs. 2, 4, and 6 and [0042]) is configured to optimize an interaction of the ferrule axial airflow (148, see Fig. 6) with the first radial rotating airflow (50) and the second radial rotating airflow (52; per [0042 and 0031] and Figs. 2 and 6, swirling airflow 148 and swirling air flow 50 are selected to have a same or different rotational direction(s) to mix with the fuel injected from 36 to form and pre-mixture and said pre-mixture is further mix with the swirling air flow 52 to form a cone of spay, i.e., the selection of rotation directions is an optimization), wherein the plurality of inclined air orifices (168s) of the ferrule swirler (60) are configured so that the ferrule axial airflow (148) rotates in a same direction of the first radial rotating airflow (50; [0042] and Figs. 4 and 6), wherein the ferrule axial airflow (148) interacting with the first radial rotating airflow (50) and the second radial rotating airflow (52) enables control of swirler flow aerodynamics ([0042 and 0031]). Sandelis does not teach said second direction is opposite to said first direction. However, Young teaches a swirler assembly (130) comprising a first swirler vane assembly (134) configured to turn a first radial rotating airflow (first direction, col. 5, ll. 62-64) and a second swirler vane assembly (132) configured to turn a second radial rotating airflow (second direction, col. 5, ll. 62-64), wherein the first swirler vane assembly (134) and the second swirler vane assembly (132) is separated by a wall (90), and the second radial rotating airflow (second direction, col. 5, ll. 62-64) is opposite to the first direction (the second direction is opposite to the first direction, col. 5, ll. 62-64). It would have been obvious to one of ordinary skill in the art before the effective filling date of the claimed invention to provide Sandelis with Youngâs opposite rotating airflow directions in order to use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle (Young, col. 6, ll. 1-9), and such configuration decreases a rate of oxidation formation on the flare cone and temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (Young, col. 1, ll. 25-32). Sandelis in view of Young does not teach said ferrule swirler having a plurality of vanes, the plurality of vanes of said ferrule swirler being formed by three sides and a radially inner most side that is closed by an outer surface of said fuel nozzle, the plurality of vanes being twisted to generate a desired exit velocity profile of said ferrule axial airflow, wherein said angle of said ferrule axial airflow is between zero degree and sixty degrees. However, COMMARET teaches a swirler assembly (20 in Figs. 3-6) comprising: a radial air swirler (60) and a ferrule (bushing 30 and injector 40, see Figs. 3-6) coupled to the radial air swirler (60), the ferrule comprising a fuel nozzle (40, [0042]) and a ferrule swirler (bushing 30 is a swirler because the grooves 35 forms on the internal surface of bushing 30 are tangential inclined with angle beta 1, which impart rotation of the purge air passing through, see Figs. 3-6 and [0046-0047]) having a plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) or a plurality of inclined air orifices (34, see Fig. 3-4 and [0046]), wherein the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) of the ferrule swirler (bushing 30) are configured to generate a ferrule axial airflow having a swirl ([0046-0047]), the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) of the ferrule swirler (bushing 30) being formed by three sides (three sides of each grooves 35 formed on the internal surface of bushing 30) and a radially inner most side that is closed by an outer surface (the surface of nozzle 40 contact with the bushing 30) of the fuel nozzle (40; as evidenced by Matthews, see Figs. 2-3), the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) being twisted (with the angle beta 1, Fig. 5-6 and [0046]) to generate a desired exit velocity profile of the ferrule axial airflow (the swirling purge air passing through grooves 35 having a desired vortexes to improve vaporization, [0046]), wherein the ferrule axial airflow (the swirling purge air passing through the grooves 35) forms an angle (the angle beta 1, [0046] and Figs. 4-6) relative to a longitudinal axis (Y, Figs 4-6) of the swirler assembly (20) between zero degree and sixty degrees (the angle beta 1 is between 0-60 degree, [0046]). It would have been obvious to one of ordinary skill in the art before the effective filling date of the claimed invention to provide Sandelis in view of Young with COMMARETâs i) replacing the plurality of inclined air orifices with the plurality of vanes because, âa simple substitution of one known element, in this case, using a plurality of inclined air orifices, for another, in this case, using a plurality of vanes as taught by COMMARET, to obtain predictable results, in this case, swirling an airflow, was an obvious extension of prior art teachingsâ, MPEP 2141(III)(B); ii) forming an angle of the ferrule axial airflow between zero to sixty degrees in order to improve vaporization of the fuel, to optimize the effective air flow cross section, and to increase the vortexes downstream of the injector (COMMARET, [0046]). Additionally, with respect to the functional limitations, âgenerate a desired exit velocity profile of the ferrule axial airflowâ, âoptimize an interaction of the ferrule axial airflow with the first radial rotating airflow and the second radial rotating airflowâ, and âenables control of swirler flow aerodynamicsâ, it is noted that apparatus claims, i.e., a ferrule swirler of a swirler assembly, covers what a device is, not what a device does. A claim containing a recitation with respect to the manner in which a claimed apparatus is intended to be employed, i.e., the functional limitations listed above, does not differentiate the claimed apparatus from a prior art apparatus, if the prior art apparatus teaches all the structural limitations of the claim, i.e., as taught by Sandelis in view of Young and COMMARET as discussed above, MPEP 2114 (Il). Regarding claim 2, Sandelis in view of Young and COMMARET teaches the invention as claimed and as discussed above. The combination as discussed above teaches the first swirler vane assembly is configured to tum the first radial rotating airflow, the second swirler vane assembly is configured to tum the second radial rotating airflow opposite to the first radial rotating airflow. Sandelis in view of Young and COMMARET as discussed above does not teach said first radial rotating airflow is an anti-clockwise direction, and said second radial rotating airflow is a clockwise direction. However, it has been held to be obvious to try, choosing from a finite number of identified, predictable solutions, in this case two solutions, i.e., 1) the first radial rotating airflow is in an anti-clockwise direction and the second radial rotating airflow is in a clockwise direction; and 2) the first radial rotating airflow is in a clockwise direction and the second radial rotating airflow is in an anti-clockwise direction, with a reasonable expectation of success, in this case, use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle and decrease a rate of oxidation formation on the flare cone in order to decrease the temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (as taught by Young), the obviousness to try being an obvious extension of prior art teachings. See MPEP 2143 I(E). Regarding claim 3, Sandelis in view of Young and COMMARET teaches the invention as claimed and as discussed above. The combination as discussed above teaches the first swirler vane assembly is configured to tum the first radial rotating airflow, the second swirler vane assembly is configured to tum the second radial rotating airflow opposite to the first radial rotating airflow. Sandelis in view of Young and COMMARET as discussed above does not teach said first radial rotating airflow is a clockwise direction, and said second radial rotating airflow is an anti-clockwise direction. However, it has been held to be obvious to try, choosing from a finite number of identified, predictable solutions, in this case two solutions, i.e., 1) the first radial rotating airflow is in an anti-clockwise direction and the second radial rotating airflow is in a clockwise direction; and 2) the first radial rotating airflow is in a clockwise direction and the second radial rotating airflow is in an anti-clockwise direction, with a reasonable expectation of success, in this case, use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle and decrease a rate of oxidation formation on the flare cone in order to decrease the temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (as taught by Young), the obviousness to try being an obvious extension of prior art teachings. See MPEP 2143 I(E). Regarding claim 8, Sandelis teaches the invention as claimed: A fuel-air mixer assembly (34) for use in a combustor (containing a combustion chamber 10), the fuel-air mixer assembly (34) comprising: (A) a first air swirler (54) having a first swirler vane assembly (the plurality of vanes per [0026], also see Fig. 2), the first swirler vane assembly ([0026] and Fig. 2) being configured to generate a first radial rotating airflow (swirling air stream 50), the first radial rotating airflow rotating in a first direction (the swirling direction of swirling air stream 50); (B) a second air swirler (56) adjacent the first air swirler (swirler 56 adjacent swirler 54 via mounting rim 76) and having a second swirler vane assembly (the plurality of vanes per [0026], also see Fig. 2), the second swirler vane assembly ( [0026] and Fig. 2) being configured to generate a second radial rotating airflow (swirling air stream 52), the second radial rotating airflow rotating in a second direction (the swirling direction of swirling air stream 52); and (C) a ferrule (ring 60 and nozzle 36, Fig. 2) coupled to the first air swirler and the second air swirler (via busing 64), the ferrule (ring 60 and nozzle 36, Fig. 2) comprising: (a) a fuel nozzle (36, [0023] and Fig. 2) configured to generate a fuel jet ([0023]), and (b) a ferrule swirler (ring 60 having a plurality of inclined orifices 168s that imparts the rotation of the air stream 148 passing through as shown in Fig. 6, i.e., the ring 60 is a ferrule swirler) having a plurality of inclined air orifices (168s, see Figs. 2, 4, and 6 and [0042]), the plurality of inclined air orifices (168s) of the ferrule swirler (60) being configured to generate a ferrule axial airflow (148) having a swirl (see Figs. 2, 4, and 6 and [0042]) to interact and mix with the first radial rotating airflow (50) and to interact with and to mix with the second radial rotating airflow (52) to generate an airflow vortex (in order to form the cone spray per [0032]) resulting in a mixture of the ferrule axial airflow with the first radial rotating airflow and with the second radial rotating airflow (such mixture is formed downstream of the venturi 58, see Fig. 2 and [0030-0031]), the plurality of inclined air orifices (168s) of the ferrule swirler (60) being inclined to generate an exit velocity profile of the ferrule axial air flow (the swirled air stream 148 having a tangential velocity profile determined by an inclined angle of orifices 168s, see Fig. 6 and [0042]), the fuel nozzle (36) being configured to generate a fuel jet to mix with the ferrule axial airflow, the first radial rotating airflow and the second radial rotating airflow ([0023 and 0030-0031] and Fig. 2), wherein the first air swirler (54) and the second air swirler (56) are separated by a wall (76 and 58, Fig. 2) so that each of the first radial rotating airflow (swirling air stream 50) and the second radial rotating airflow (swirling air stream 52) are separated by the wall (76 and 58) to interact and mix with the ferrule axial air flow (148) to generate the airflow vortex (in order to form the con spray per [0031]), wherein the ferrule axial airflow (148) forms an angle (the inclined angle per [0042]) relative to a longitudinal axis of the swirler assembly (A, Fig. 1), and wherein the ferrule (ring 60 part) is movable radially ([0004 and 0038]) in a direction generally perpendicular to the longitudinal axis of the swirler assembly (axis A, see Figs. 1-2 and [0037]), wherein the ferrule swirler (ring 60 comprising the plurality of inclined air orifices 168s, see Figs. 2, 4, and 6 and [0042]) is configured to optimize an interaction of the ferrule axial airflow (148, see Fig. 6) with the first radial rotating airflow (50) and the second radial rotating airflow (52; per [0042 and 0031] and Figs. 2 and 6, swirling airflow 148 and swirling air flow 50 are selected to have a same or different rotational direction(s) to mix with the fuel injected from 36 to form and pre-mixture and said pre-mixture is further mix with the swirling air flow 52 to form a cone of spay, i.e., the selection of rotation directions is an optimization), wherein the fuel jet (generated by 36) is directed to interact with the airflow vortex (used to form the cone spray per [0031]) to generate a controlled fuel-air mixture (the spay having the cone shape, [0022-23 and 0031]), wherein the plurality of inclined air orifices (168s) of the ferrule swirler (60) are configured so that the ferrule axial airflow (148) rotates in a same direction of the first radial rotating airflow (50; [0042] and Figs. 4 and 6), wherein the ferrule axial airflow (148) interacting with the first radial rotating airflow (50) and the second radial rotating airflow (52) enables control of swirler flow aerodynamics ([0042 and 0031]). Sandelis does not teach said second direction is opposite to said first direction. However, Young teaches a swirler assembly (130) comprising a first swirler vane assembly (134) configured to turn a first radial rotating airflow (first direction, col. 5, ll. 62-64) and a second swirler vane assembly (132) configured to turn a second radial rotating airflow (second direction, col. 5, ll. 62-64), wherein the first swirler vane assembly (134) and the second swirler vane assembly (132) is separated by a wall (90), and the second radial rotating airflow (second direction, col. 5, ll. 62-64) is opposite to the first direction (the second direction is opposite to the first direction, col. 5, ll. 62-64). It would have been obvious to one of ordinary skill in the art before the effective filling date of the claimed invention to provide Sandelis with Youngâs opposite rotating airflow directions in order to use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle (Young, col. 6, ll. 1-9), and such configuration decreases a rate of oxidation formation on the flare cone and temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (Young, col. 1, ll. 25-32). Sandelis in view of Young does not teach said ferrule swirler having a plurality of vanes, the plurality of vanes of said ferrule swirler being formed by three sides and a radially inner most side that is closed by an outer surface of said fuel nozzle, the plurality of vanes being twisted to generate a desired exit velocity profile of said ferrule axial airflow, wherein said angle of said ferrule axial airflow is between zero degree and sixty degrees. However, COMMARET teaches A fuel-air mixer (20 in Figs. 3-6) comprising: a radial air swirler (60) and a ferrule (bushing 30 and injector 40, see Figs. 3-6) coupled to the radial air swirler (60), the ferrule comprising a fuel nozzle (40, [0042]) and a ferrule swirler (bushing 30 is a swirler because the grooves 35 forms on the internal surface of bushing 30 are tangential inclined with angle beta 1, which impart rotation of the purge air passing through, see Figs. 3-6 and [0046-0047]) having a plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) or a plurality of inclined air orifices (34, see Fig. 3-4 and [0046]), wherein the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) of the ferrule swirler (bushing 30) are configured to generate a ferrule axial airflow having a swirl ([0046-0047]), the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) of the ferrule swirler (bushing 30) being formed by three sides (three sides of each grooves 35 formed on the internal surface of bushing 30) and a radially inner most side that is closed by an outer surface (the surface of nozzle 40 contact with the bushing 30) of the fuel nozzle (40; as evidenced by Matthews, see Figs. 2-3), the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) being twisted (with the angle beta 1, Fig. 5-6 and [0046]) to generate a desired exit velocity profile of the ferrule axial airflow (the swirling purge air passing through grooves 35 having a desired vortexes to improve vaporization, [0046]), wherein the ferrule axial airflow (the swirling purge air passing through the grooves 35) forms an angle (the angle beta 1, [0046] and Figs. 4-6) relative to a longitudinal axis (Y, Figs 4-6) of the swirler assembly (20) between zero degree and sixty degrees (the angle beta 1 is between 0-60 degree, [0046]). It would have been obvious to one of ordinary skill in the art before the effective filling date of the claimed invention to provide Sandelis in view of Young with COMMARETâs i) replacing the plurality of inclined air orifices with the plurality of vanes because, âa simple substitution of one known element, in this case, using a plurality of inclined air orifices, for another, in this case, using a plurality of vanes as taught by COMMARET, to obtain predictable results, in this case, swirling an airflow, was an obvious extension of prior art teachingsâ, MPEP 2141(III)(B); ii) forming an angle of the ferrule axial airflow between zero to sixty degrees in order to improve vaporization of the fuel, to optimize the effective air flow cross section, and to increase the vortexes downstream of the injector (COMMARET, [0046]). Additionally, with respect to the functional limitations, âgenerate a desired exit velocity profile of the ferrule axial airflowâ, âoptimize an interaction of the ferrule axial airflow with the first radial rotating airflow and the second radial rotating airflowâ, and âenables control of swirler flow aerodynamicsâ, it is noted that apparatus claims, i.e., a ferrule swirler of a swirler assembly, covers what a device is, not what a device does. A claim containing a recitation with respect to the manner in which a claimed apparatus is intended to be employed, i.e., the functional limitations listed above, does not differentiate the claimed apparatus from a prior art apparatus, if the prior art apparatus teaches all the structural limitations of the claim, i.e., as taught by Sandelis in view of Young and COMMARET as discussed above, MPEP 2114 (Il). Regarding claim 9, Sandelis in view of Young and COMMARET teaches the invention as claimed and as discussed above. The combination as discussed above teaches the first swirler vane assembly is configured to tum the first radial rotating airflow, the second swirler vane assembly is configured to tum the second radial rotating airflow opposite to the first radial rotating airflow. Sandelis in view of Young and COMMARET as discussed above does not teach said first radial rotating airflow is an anti-clockwise direction, and said second radial rotating airflow is a clockwise direction. However, it has been held to be obvious to try, choosing from a finite number of identified, predictable solutions, in this case two solutions, i.e., 1) the first radial rotating airflow is in an anti-clockwise direction and the second radial rotating airflow is in a clockwise direction; and 2) the first radial rotating airflow is in a clockwise direction and the second radial rotating airflow is in an anti-clockwise direction, with a reasonable expectation of success, in this case, use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle and decrease a rate of oxidation formation on the flare cone in order to decrease the temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (as taught by Young), the obviousness to try being an obvious extension of prior art teachings. See MPEP 2143 I(E). Regarding claim 10, Sandelis in view of Young and COMMARET teaches the invention as claimed and as discussed above. The combination as discussed above teaches the first swirler vane assembly is configured to tum the first radial rotating airflow, the second swirler vane assembly is configured to tum the second radial rotating airflow opposite to the first radial rotating airflow. Sandelis in view of Young and COMMARET as discussed above does not teach said first radial rotating airflow is a clockwise direction, and said second radial rotating airflow is an anti-clockwise direction. However, it has been held to be obvious to try, choosing from a finite number of identified, predictable solutions, in this case two solutions, i.e., 1) the first radial rotating airflow is in an anti-clockwise direction and the second radial rotating airflow is in a clockwise direction; and 2) the first radial rotating airflow is in a clockwise direction and the second radial rotating airflow is in an anti-clockwise direction, with a reasonable expectation of success, in this case, use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle and decrease a rate of oxidation formation on the flare cone in order to decrease the temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (as taught by Young), the obviousness to try being an obvious extension of prior art teachings. See MPEP 2143 I(E). Regarding claim 15, Sandelis teaches the invention as claimed: a turbine engine (turbomachine, abstract) comprising: a combustor (containing a combustion chamber 10) comprising a fuel-air mixer assembly (34) and a fuel ignition assembly (configured to ignite the fuel-air mixture sprayed in the combustion chamber 10, see Fig. 1 and [0032]), the fuel-air mixer assembly (34) comprising: (A) a first air swirler (54) having a first swirler vane assembly (the plurality of vanes per [0026], also see Fig. 2) being configured to generate a first radial rotating airflow (swirling air stream 50), the first radial rotating airflow rotating in a first direction (the swirling direction of swirling air stream 50); (B) a second air swirler (56) adjacent the first air swirler (swirler 56 adjacent swirler 54 via mounting rim 76) and having a second swirler vane assembly (the plurality of vanes per [0026], also see Fig. 2) being configured to generate a second radial rotating airflow (swirling air stream 52), the second radial rotating airflow rotating in a second direction (the swirling direction of swirling air stream 52); and (C) a ferrule (ring 60 and nozzle 36, Fig. 2) coupled to the first air swirler and the second air swirler (via busing 64), the ferrule (ring 60 and nozzle 36, Fig. 2) comprising: (a) a fuel nozzle (36, [0023] and Fig. 2) configured to generate a fuel jet ([0023]), and (b) a ferrule swirler (ring 60 having a plurality of inclined orifices 168s that imparts the rotation of the air stream 148 passing through as shown in Fig. 6, i.e., the ring 60 is a ferrule swirler) having a plurality of inclined air orifices (168s, see Figs. 2, 4, and 6 and [0042]), the plurality of inclined air orifices (168s) of the ferrule swirler (60) being configured to generate a ferrule axial airflow (148) having a swirl (see Figs. 2, 4, and 6 and [0042]) to interact and mix with the first radial rotating airflow (50) and to interact with and to mix with the second radial rotating airflow (52) to generate an airflow vortex (in order to form the cone spray per [0032]) resulting in a mixture of the ferrule axial airflow with the first radial rotating airflow and with the second radial rotating airflow (such mixture is formed downstream of the venturi 58, see Fig. 2 and [0030-0031]), the plurality of inclined air orifices (168s) of the ferrule swirler (60) being inclined to generate an exit velocity profile of the ferrule axial air flow (the swirled air stream 148 having a tangential velocity profile determined by an inclined angle of orifices 168s, see Fig. 6 and [0042]), the fuel nozzle (36) being configured to generate the fuel jet to mix with the ferrule axial airflow, the first radial rotating airflow and the second radial rotating airflow ([0023 and 0030-0031] and Fig. 2), wherein the first air swirler (54) and the second air swirler (56) are separated by a wall (76 and 58, Fig. 2) so that each of the first radial rotating airflow (swirling air stream 50) and the second radial rotating airflow (swirling air stream 52) are separated by the wall (76 and 58) to interact and mix with the ferrule axial air flow (148) to generate the airflow vortex (in order to form the con spray per [0031]), wherein the ferrule axial airflow (148) forms an angle (the inclined angle per [0042]) relative to a longitudinal axis of the swirler assembly (A, Fig. 1), and wherein the ferrule (ring 60 part) is movable radially ([0004 and 0038]) in a direction generally perpendicular to the longitudinal axis of the swirler assembly (axis A, see Figs. 1-2 and [0037]), wherein the ferrule swirler (ring 60 comprising the plurality of inclined air orifices 168s, see Figs. 2, 4, and 6 and [0042]) is configured to optimize an interaction of the ferrule axial airflow (148, see Fig. 6) with the first radial rotating airflow (50) and the second radial rotating airflow (52; per [0042 and 0031] and Figs. 2 and 6, swirling airflow 148 and swirling air flow 50 are selected to have a same or different rotational direction(s) to mix with the fuel injected from 36 to form and pre-mixture and said pre-mixture is further mix with the swirling air flow 52 to form a cone of spay, i.e., the selection of rotation directions is an optimization), wherein the fuel jet (generated by 36) is directed to interact with the airflow vortex (used to form the cone spray per [0031]) to generate a controlled fuel-air mixture (the spay having the cone shape, [0022-23 and 0031-0032]) for ignition by the fuel ignition assembly (see Fig. 1) wherein the plurality of inclined air orifices (168s) of the ferrule swirler (60) are configured so that the ferrule axial airflow (148) rotates in a same direction of the first radial rotating airflow (50; [0042] and Figs. 4 and 6), and wherein the ferrule axial airflow (148) interacting with the first radial rotating airflow (50) and the second radial rotating airflow (52) enables control of swirler flow aerodynamics ([0042 and 0031]). Sandelis does not teach said second direction is opposite to said first direction. However, Young teaches a swirler assembly (130) comprising a first swirler vane assembly (134) configured to turn a first radial rotating airflow (first direction, col. 5, ll. 62-64) and a second swirler vane assembly (132) configured to turn a second radial rotating airflow (second direction, col. 5, ll. 62-64), wherein the first swirler vane assembly (134) and the second swirler vane assembly (132) is separated by a wall (90), and the second radial rotating airflow (second direction, col. 5, ll. 62-64) is opposite to the first direction (the second direction is opposite to the first direction, col. 5, ll. 62-64). It would have been obvious to one of ordinary skill in the art before the effective filling date of the claimed invention to provide Sandelis with Youngâs opposite rotating airflow directions in order to use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle (Young, col. 6, ll. 1-9), and such configuration decreases a rate of oxidation formation on the flare cone and temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (Young, col. 1, ll. 25-32). Sandelis in view of Young does not teach said ferrule swirler having a plurality of vanes, the plurality of vanes of said ferrule swirler being formed by three sides and a radially inner most side that is closed by an outer surface of said fuel nozzle, the plurality of vanes being twisted to generate a desired exit velocity profile of said ferrule axial airflow, wherein said angle of said ferrule axial airflow is between zero degree and sixty degrees. However, COMMARET teaches A fuel-air mixer (20 in Figs. 3-6) comprising: a radial air swirler (60) and a ferrule (bushing 30 and injector 40, see Figs. 3-6) coupled to the radial air swirler (60), the ferrule comprising a fuel nozzle (40, [0042]) and a ferrule swirler (bushing 30 is a swirler because the grooves 35 forms on the internal surface of bushing 30 are tangential inclined with angle beta 1, which impart rotation of the purge air passing through, see Figs. 3-6 and [0046-0047]) having a plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) or a plurality of inclined air orifices (34, see Fig. 3-4 and [0046]), wherein the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) of the ferrule swirler (bushing 30) are configured to generate a ferrule axial airflow having a swirl ([0046-0047]), the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) of the ferrule swirler (bushing 30) being formed by three sides (three sides of each grooves 35 formed on the internal surface of bushing 30) and a radially inner most side that is closed by an outer surface (the surface of nozzle 40 contact with the bushing 30) of the fuel nozzle (40; as evidenced by Matthews, see Figs. 2-3), the plurality of vanes (the plurality of protruding portions between two adjacent grooves 35, Fig. 5-6 and [0047]; as evidenced by Matthews, see Figs. 2-3) being twisted (with the angle beta 1, Fig. 5-6 and [0046]) to generate a desired exit velocity profile of the ferrule axial airflow (the swirling purge air passing through grooves 35 having a desired vortexes to improve vaporization, [0046]), wherein the ferrule axial airflow (the swirling purge air passing through the grooves 35) forms an angle (the angle beta 1, [0046] and Figs. 4-6) relative to a longitudinal axis (Y, Figs 4-6) of the swirler assembly (20) between zero degree and sixty degrees (the angle beta 1 is between 0-60 degree, [0046]). It would have been obvious to one of ordinary skill in the art before the effective filling date of the claimed invention to provide Sandelis in view of Young with COMMARETâs i) replacing the plurality of inclined air orifices with the plurality of vanes because, âa simple substitution of one known element, in this case, using a plurality of inclined air orifices, for another, in this case, using a plurality of vanes as taught by COMMARET, to obtain predictable results, in this case, swirling an airflow, was an obvious extension of prior art teachingsâ, MPEP 2141(III)(B); ii) forming an angle of the ferrule axial airflow between zero to sixty degrees in order to improve vaporization of the fuel, to optimize the effective air flow cross section, and to increase the vortexes downstream of the injector (COMMARET, [0046]). Additionally, with respect to the functional limitations, âgenerate a desired exit velocity profile of the ferrule axial airflowâ, âoptimize an interaction of the ferrule axial airflow with the first radial rotating airflow and the second radial rotating airflowâ, and âenables control of swirler flow aerodynamicsâ, it is noted that apparatus claims, i.e., a ferrule swirler of a swirler assembly, covers what a device is, not what a device does. A claim containing a recitation with respect to the manner in which a claimed apparatus is intended to be employed, i.e., the functional limitations listed above, does not differentiate the claimed apparatus from a prior art apparatus, if the prior art apparatus teaches all the structural limitations of the claim, i.e., as taught by Sandelis in view of Young and COMMARET as discussed above, MPEP 2114 (Il). Regarding claim 16, Sandelis in view of Young and COMMARET teaches the invention as claimed and as discussed above. The combination as discussed above teaches the first swirler vane assembly is configured to tum the first radial rotating airflow, the second swirler vane assembly is configured to tum the second radial rotating airflow opposite to the first radial rotating airflow. Sandelis in view of Young and COMMARET as discussed above does not teach said first radial rotating airflow is an anti-clockwise direction, and said second radial rotating airflow is a clockwise direction. However, it has been held to be obvious to try, choosing from a finite number of identified, predictable solutions, in this case two solutions, i.e., 1) the first radial rotating airflow is in an anti-clockwise direction and the second radial rotating airflow is in a clockwise direction; and 2) the first radial rotating airflow is in a clockwise direction and the second radial rotating airflow is in an anti-clockwise direction, with a reasonable expectation of success, in this case, use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle and decrease a rate of oxidation formation on the flare cone in order to decrease the temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (as taught by Young), the obviousness to try being an obvious extension of prior art teachings. See MPEP 2143 I(E). Regarding claim 17, Sandelis in view of Young and COMMARET teaches the invention as claimed and as discussed above. The combination as discussed above teaches the first swirler vane assembly is configured to tum the first radial rotating airflow, the second swirler vane assembly is configured to tum the second radial rotating airflow opposite to the first radial rotating airflow. Sandelis in view of Young and COMMARET as discussed above does not teach said first radial rotating airflow is a clockwise direction, and said second radial rotating airflow is an anti-clockwise direction. However, it has been held to be obvious to try, choosing from a finite number of identified, predictable solutions, in this case two solutions, i.e., 1) the first radial rotating airflow is in an anti-clockwise direction and the second radial rotating airflow is in a clockwise direction; and 2) the first radial rotating airflow is in a clockwise direction and the second radial rotating airflow is in an anti-clockwise direction, with a reasonable expectation of success, in this case, use the centrifugal effects caused by the opposite rotation directions to radially outwardly spread the fuel/air mixture along the flare cone and deflector with a wide discharge spray angle and decrease a rate of oxidation formation on the flare cone in order to decrease the temperature of the combustion along the flare cone and deflector and prevent melting or failure of the flare cone (as taught by Young), the obviousness to try being an obvious extension of prior art teachings. See MPEP 2143 I(E). Response to Arguments Applicant's argument filed on 02/19/2025 and entered on 03/19/2025 has been fully considered but the argument is moot because it does not apply to a new combination of the previously applied references being used in the current office action, necessitated by amendment. However, to the extent possible, Applicant's argument has been addressed above, at the appropriate locations. Conclusion Any inquiry concerning this communication or earlier communications from the examiner should be directed to JINGCHEN LIU whose telephone number is (571)272-6639. The examiner can normally be reached 9:30-4:30. Examiner interviews are available via telephone, in-person, and video conferencing using a USPTO supplied web-based collaboration tool. To schedule an interview, applicant is encouraged to use the USPTO Automated Interview Request (AIR) at http://www.uspto.gov/interviewpractice. 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If you would like assistance from a USPTO Customer Service Representative, call 800-786-9199 (IN USA OR CANADA) or 571-272-1000. /JINGCHEN LIU/Examiner, Art Unit 3741 /DEVON C KRAMER/Supervisory Patent Examiner, Art Unit 3741