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 .
Priority
Applicant’s claim for the benefit of a prior-filed application under 35 U.S.C. 119(e) or under 35 U.S.C. 120, 121, 365(c), or 386(c) is acknowledged. Applicant has not complied with one or more conditions for receiving the benefit of an earlier filing date under 35 U.S.C. 120 as follows:
The later-filed application must be an application for a patent for an invention which is also disclosed in the prior application (the parent or original nonprovisional application or provisional application). The disclosure of the invention in the parent application and in the later-filed application must be sufficient to comply with the requirements of 35 U.S.C. 112(a) or the first paragraph of pre-AIA 35 U.S.C. 112, except for the best mode requirement. See Transco Products, Inc. v. Performance Contracting, Inc., 38 F.3d 551, 32 USPQ2d 1077 (Fed. Cir. 1994).
The disclosure of the prior-filed application, Applications Nos. 17/978,629; 18/481,515; 18/500,517; 18/650,586; 18/976,748 fail to provide adequate support or enablement in the manner provided by 35 U.S.C. 112(a) or pre-AIA 35 U.S.C. 112, first paragraph for one or more claims of this application.
Applications Nos. 17/978,629; 18/481,515; 18/500,517 fail to disclose a corrected specific power (CSP) as described in claims 1 and 18. Therefore, claims 1-20 are not entitled to the benefit of the prior applications.
Applications Nos. 18/650,586; 18/976,748 fail to disclose an anti-ice flow passage described in claims 2, 4-5 and 19; a tip portion that defines a radial gap described in claims 6-9 and 20. Therefore, claims 2, 4-9 and 19-20 are not entitled to the benefit of the prior applications.
Claim Objections
Claims 2, 4, 6 and 19-20 are objected to because of the following informalities:
Claims 2 and 19 recite “wherein defining an internal cavity and an anti-ice flow passage located at a tip region of the inlet guide vane between the internal cavity and an outer surface of the inlet guide vane” and should recite “wherein an internal cavity and an anti-ice flow passage located at a tip region of the inlet guide vane are defined between the internal cavity and an outer surface of the inlet guide vane”
Claim 4 recites “the anti-ice flow passage” and “the tip region” and should recite “an anti-ice flow passage” and “a tip region”.
Claims 6 and 20 each recite “an inlet guide vane” in line 2 and should recite “the inlet guide vane”.
Appropriate correction is required.
Double Patenting
The nonstatutory double patenting rejection is based on a judicially created doctrine grounded in public policy (a policy reflected in the statute) so as to prevent the unjustified or improper timewise extension of the “right to exclude” granted by a patent and to prevent possible harassment by multiple assignees. A nonstatutory double patenting rejection is appropriate where the conflicting claims are not identical, but at least one examined application claim is not patentably distinct from the reference claim(s) because the examined application claim is either anticipated by, or would have been obvious over, the reference claim(s). See, e.g., In re Berg, 140 F.3d 1428, 46 USPQ2d 1226 (Fed. Cir. 1998); In re Goodman, 11 F.3d 1046, 29 USPQ2d 2010 (Fed. Cir. 1993); In re Longi, 759 F.2d 887, 225 USPQ 645 (Fed. Cir. 1985); In re Van Ornum, 686 F.2d 937, 214 USPQ 761 (CCPA 1982); In re Vogel, 422 F.2d 438, 164 USPQ 619 (CCPA 1970); In re Thorington, 418 F.2d 528, 163 USPQ 644 (CCPA 1969).
A timely filed terminal disclaimer in compliance with 37 CFR 1.321(c) or 1.321(d) may be used to overcome an actual or provisional rejection based on nonstatutory double patenting provided the reference application or patent either is shown to be commonly owned with the examined application, or claims an invention made as a result of activities undertaken within the scope of a joint research agreement. See MPEP § 717.02 for applications subject to examination under the first inventor to file provisions of the AIA as explained in MPEP § 2159. See MPEP § 2146 et seq. for applications not subject to examination under the first inventor to file provisions of the AIA . A terminal disclaimer must be signed in compliance with 37 CFR 1.321(b).
The filing of a terminal disclaimer by itself is not a complete reply to a nonstatutory double patenting (NSDP) rejection. A complete reply requires that the terminal disclaimer be accompanied by a reply requesting reconsideration of the prior Office action. Even where the NSDP rejection is provisional the reply must be complete. See MPEP § 804, subsection I.B.1. For a reply to a non-final Office action, see 37 CFR 1.111(a). For a reply to final Office action, see 37 CFR 1.113(c). A request for reconsideration while not provided for in 37 CFR 1.113(c) may be filed after final for consideration. See MPEP §§ 706.07(e) and 714.13.
The USPTO Internet website contains terminal disclaimer forms which may be used. Please visit www.uspto.gov/patent/patents-forms. The actual filing date of the application in which the form is filed determines what form (e.g., PTO/SB/25, PTO/SB/26, PTO/AIA /25, or PTO/AIA /26) should be used. A web-based eTerminal Disclaimer may be filled out completely online using web-screens. An eTerminal Disclaimer that meets all requirements is auto-processed and approved immediately upon submission. For more information about eTerminal Disclaimers, refer to www.uspto.gov/patents/apply/applying-online/eterminal-disclaimer.
Claims 1-5 and 18-19 are rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 20 and 27 of US Patent 12,535,037 (‘037) in view of Olczak (US 2024/0369073), hereinafter Olczak ‘073.
Regarding claim 1, claim 1 of ‘037 teaches a gas turbine engine comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine;
wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:
T
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U
T
A
D
T
E
x
i
t
2
*
E
G
T
A
H
P
C
E
x
i
t
*
10
-
11
;
wherein CSP is greater than
0.0001194
×
E
G
T
2
-
0.103
×
E
G
T
+
22.14
and less than
0.0003294
×
E
G
T
2
-
0.306
×
E
G
T
+
77.9
1
; and
wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
Claim 1 of ‘037 is silent on wherein the gas turbine engine further comprises an inlet guide vane.
Olczak ‘073 teaches wherein the gas turbine engine (Figure 1, 100) further comprises an inlet guide vane (Figure 1, 186).
Therefore it would have been obvious to one having ordinary skill in the art before the effective filing date of the claimed invention to modify ‘037 invention to include wherein the gas turbine engine further comprises an inlet guide vane in order to prevent ice build-up and thus engine damage as suggested and taught by Olczak ‘073 in paragraph 3.
Regarding claim 2, claim 1 of ‘037 in view of Olczak ‘073 teach the invention as claimed and described above. Olczak ‘073 further teaches wherein defining an internal cavity (Figure 8, 244) and an anti-ice flow passage (228) located at a tip region (222) of the inlet guide vane between the internal cavity and an outer surface (220) of the inlet guide vane.
Regarding claim 3, claim 1 of ‘037 in view of Olczak ‘073 teach the invention as claimed and described above. Olczak ‘073 further teaches wherein the inlet guide vane is positioned within an inlet duct (Figure 1, 180) of the turbomachine (120), downstream of an inlet (182) of the inlet duct and upstream of the compressor section (126 and 128).
Regarding claim 4, claim 1 of ‘037 in view of Olczak ‘073 teach the invention as claimed and described above. Olczak ‘073 further teaches wherein the anti-ice flow passage (Figure 8, 228) includes a flow port (Figure 8, 230) structured to eject (paragraph 73) a flow of an anti-ice air (214), the anti-ice flow passage oriented in a direction having a radial component such that the anti-ice air is flowed in a substantially radial direction (Figure 8 and paragraph 73 describe this) through the internal cavity over an entirety of the tip region (Annotated figure 8) exposed in an inlet duct of the turbomachine (Figure 10, 260).
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620
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Regarding claim 5, claim 1 of ‘037 in view of Olczak ‘073 teach the invention as claimed and described above. Olczak ‘073 further teaches wherein the internal cavity (244) extends from a root region (Annotated figure 8) of the inlet guide vane to the tip region (Annotated figure 8), and wherein the anti-ice air is conveyed from the root region to the tip region by the internal cavity (anti-ice air 214 flows into the internal cavity and recirculated throughout, i.e. from the root region to the tip region).
Regarding claim 18, claim 20 of ‘037 teaches a gas turbine engine comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine and defining an overall pressure ratio greater than 14:1 and less than or equal to 22:1; and
wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) greater than 600 degrees Celsius and less than 1000 degrees Celsius, an output power of at least 550 horsepower and up to 2,000 horsepower when operated at a rated speed, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein CSP is greater than 3.3 and less than 101 and is determined as follows:
T
O
U
T
A
D
T
E
x
i
t
2
*
E
G
T
A
H
P
C
E
x
i
t
*
10
-
11
.
Claim 1 of ‘037 is silent on wherein the gas turbine engine further comprises an inlet guide vane.
Olczak ‘073 teaches wherein the gas turbine engine (Figure 1) further comprises an inlet guide vane (Figure 2, 100).
Therefore it would have been obvious to one having ordinary skill in the art before the effective filing date of the claimed invention to modify ‘073 invention to include wherein the gas turbine engine further comprises an inlet guide vane in order to inhibit or mitigate ice formation as suggested and taught by Olczak ‘073 in paragraph 26.
Regarding claim 19, claim 1 of ‘037 in view of Olczak ‘073 teach the invention as claimed and described above. Olczak ‘073 further teaches wherein defining an internal cavity (Figure 8, 244) and an anti-ice flow passage (228) located at a tip region (222) of the inlet guide vane between the internal cavity and an outer surface (220) of the inlet guide vane.
Claims 1, 6-18 and 20 are rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 20 and 27 of US Patent 12,535,037 (‘037) in view of Olczak (US 2024/0318577), hereinafter Olczak ‘577.
Regarding claim 1, claim 1 of ‘037 teaches a gas turbine engine comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine;
wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:
T
O
U
T
A
D
T
E
x
i
t
2
*
E
G
T
A
H
P
C
E
x
i
t
*
10
-
11
;
wherein CSP is greater than
0.0001194
×
E
G
T
2
-
0.103
×
E
G
T
+
22.14
and less than
0.0003294
×
E
G
T
2
-
0.306
×
E
G
T
+
77.9
1
; and
wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
Claim 1 of ‘037 is silent on wherein the gas turbine engine further comprises an inlet guide vane.
Olczak ‘577 teaches wherein the gas turbine engine (Figure 1) further comprises an inlet guide vane (Figure 2, 100).
Therefore it would have been obvious to one having ordinary skill in the art before the effective filing date of the claimed invention to modify ‘037 invention to include wherein the gas turbine engine further comprises an inlet guide vane in order to inhibit or mitigate ice formation as suggested and taught by Olczak ‘577 in paragraph 26.
Regarding claim 6, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Olczak ‘577 further teaches wherein the gas turbine engine further includes a rotor shaft (Figure 2, 30) and an inlet guide vane (100), wherein the inlet guide vane includes a tip portion (106) that defines a radial gap (112) with the rotor shaft (Figure 2).
Regarding claim 7, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Olczak ‘577 further teaches wherein the rotor shaft is drivingly coupled to the high pressure compressor (Figure 1, the HP compressor is labeled as the 22 to the right side and described as 20 in paragraph 31 and paragraph 31 describes this driving relationship), wherein the rotor shaft comprises a forward end portion (Figure 2, 70), wherein the forward end portion defines an outer surface (72) that defines the radial gap with the tip portion of the inlet guide vane (Figure 2).
Regarding claim 8, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Olczak ‘577 further teaches wherein the forward end portion of the rotor shaft and an inner wall (80) of an inlet frame (50) upstream from the inlet guide vane (Figure 2, with respect to the airflow 46) define an aperture (114) therebetween, wherein the aperture is in fluid communication with a purge-air source (82), wherein the aperture is oriented to direct a flow of purge-air (84) towards the radial gap (Figure 2).
Regarding claim 9, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Olczak ‘577 further teaches further comprising an outer casing (76), and wherein the inlet guide vane is cantilever mounted to the outer casing (paragraph 38).
Regarding claim 10, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 2 of ‘037 teaches wherein CSP is less than 210 and greater than 1.
Regarding claim 11, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 3 of ‘037 teaches wherein the EGT is greater than 750 degree Celsius and less than 1100 degrees Celsius, and wherein CSP is less than 140 and greater than 12.1.
Regarding claim 12, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 4 of ‘037 teaches wherein the TOUT is greater than 530 Newton-meters and less than 4740 Newton-meters.
Regarding claim 13, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 5 of ‘037 teaches further comprising:
an intercooler assembly comprising a heat exchanger, the heat exchanger in thermal communication with the compressor section.
Regarding claim 14, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 11 of ‘037 teaches wherein the compressor section comprises a first compressor, and wherein the first compressor is configured as an axial compressor, a centrifugal compressor, or an axial- centrifugal compressor.
Regarding claim 15, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 13 of ‘037 teaches wherein the turbine section comprises a high pressure turbine having a first stage of high pressure turbine rotor blades, and wherein the gas turbine engine further comprises:
a cooled cooling air system in fluid communication with the first stage of high pressure turbine rotor blades.
Regarding claim 16, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 17 of ‘037 teaches wherein the gas turbine engine is a turboprop engine further comprising:
a propeller assembly, wherein the propeller assembly comprises a propeller driven by the drive turbine shaft.
Regarding claim 17, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Claim 18 of ‘037 teaches further comprising:
a power gearbox, wherein the drive turbine shaft is driven by the turbomachine across the power gearbox.
Regarding claim 18, claim 20 of ‘037 teaches a gas turbine engine comprising:
a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine and defining an overall pressure ratio greater than 14:1 and less than or equal to 22:1; and
wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) greater than 600 degrees Celsius and less than 1000 degrees Celsius, an output power of at least 550 horsepower and up to 2,000 horsepower when operated at a rated speed, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein CSP is greater than 3.3 and less than 101 and is determined as follows:
T
O
U
T
A
D
T
E
x
i
t
2
*
E
G
T
A
H
P
C
E
x
i
t
*
10
-
11
.
Claim 1 of ‘037 is silent on wherein the gas turbine engine further comprises an inlet guide vane.
Olczak ‘577 teaches wherein the gas turbine engine (Figure 1) further comprises an inlet guide vane (Figure 2, 100).
Therefore it would have been obvious to one having ordinary skill in the art before the effective filing date of the claimed invention to modify ‘037 invention to include wherein the gas turbine engine further comprises an inlet guide vane in order to inhibit or mitigate ice formation as suggested and taught by Olczak ‘577 in paragraph 26.
Regarding claim 20, claim 1 of ‘037 in view of Olczak ‘577 teach the invention as claimed and described above. Olczak ‘577 further teaches wherein the gas turbine engine further includes a rotor shaft (Figure 2, 30) and an inlet guide vane (100), wherein the inlet guide vane includes a tip portion (106) that defines a radial gap (112) with the rotor shaft (Figure 2).
Claims 1-20 are rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 20 and 19 of U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above.
Claims 1-20 are rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 20 and 19 of U.S. Patent No. 12,392,290 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above.
Claims 1-20 are rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 8 and 15 of U.S. Patent No. 12,535,033 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 8 and 15 of copending Application No. 19/098,613 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 16 and 19 of copending Application No. 19/098,642 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 9 and 17 of copending Application No. 19/098,652 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-18 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1 and 18 of copending Application No. 19/180,378 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 17 and 20 of copending Application No. 19/180,421 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 16 and 19 of copending Application No. 19/180,742 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 11 and 20 of copending Application No. 19/194,856 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 16 and 20 of copending Application No. 19/194,896 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 21 of copending Application No. 19/194,975 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 21 of copending Application No. 19/194,999 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/299,724 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/317,285 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/317,457 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1 and 11 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1 and 16 of copending Application No. 19/317,584 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/358,481 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/445,929 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/457,294 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Claims 1-20 are provisionally rejected on the ground of nonstatutory double patenting as being unpatentable over claims 1, 12 and 20 of copending Application No. 19/661,807 in view of Olczak (US 2024/0318577) and U.S. Patent No. 12,196,131 in view of Olczak (US 2024/0369073) in the same manner as described above. This is a provisional nonstatutory double patenting rejection.
Conclusion
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/KATHERYN A MALATEK/Primary Examiner, Art Unit 3741
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