DETAILED 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 .
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.
Claim 1 is rejected under the judicially created doctrine of obviousness-type double patenting as being unpatentable over claim 50, of McCune et al (US 10,227,893 B2) in view of McCune et al – hereafter M246 – (US 20110130246 A1).
Although the claims are not identical, they are not patentably distinct from one another. The application claims are broader in at least one aspect and also recite additional features not claimed in the patent claims.
For claim 1:
Regarding the broadening aspect of the application claims, the following comparison between the patent claims and the application claims highlights (see underlined features in the patent claims) what elements have been excluded in the presentation of the application claims.
Patent claim 50
Application claim 1
A gas turbine engine, comprising:
a fan shaft driving a fan having fan blades;
a fan shaft support that supports said fan shaft;
a gear system connected to said fan shaft, said gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness;
a flexible support supporting said gear system and defining a flexible support lateral stiffness and a flexible support transverse stiffness; and wherein at least one of said flexible support lateral stiffness and said flexible support transverse stiffness is less than 8% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness;
further comprising a ring gear defines a ring gear lateral stiffness, wherein said gear mesh defines a gear mesh lateral stiffness, and said flexible support defines a flexible support lateral stiffness and said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness and said ring gear lateral stiffness is less than 12% of said gear mesh lateral stiffness.
A gas turbine engine, comprising:
a fan section having fan blades that drive air along a bypass flow path in a bypass duct;
a fan shaft drivingly connected to said fan section;
a turbine section including a turbine drive shaft;
a gear system connected to the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system, wherein there is at least one support supporting said gear system relative to a static structure; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said turbine drive shaft during operation and includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
Thus, it is apparent, for the broadening aspect, that patent claim 50 includes features that are not in application claim 1. Following the rationale in In re Goodman, cited above, where applicant has once been granted a patent containing a claim for the specific or narrower invention, applicant may not then obtain a second patent with a claim for the generic or broader invention without first submitting an appropriate terminal disclaimer. Since application claim 1 is anticipated by patent claim 50, with respect to the broadening aspect, then application claim 1 is obvious over patent claim 50 with respect to the broadening aspect.
With respect to the additional features recited in application claim 1, patent claim 50 fails to recite the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system. However, M246 teaches a gas turbine engine including a fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of a gear system and connected to a fan shaft on an output side of the gear system (Fig.1/2, note fan 32, bypass duct defined by inner surface of element 44, turbine section 20, turbine drive shaft 22 on an input side (via 46) of gear system 30, connected to fan shaft ¶9). Since the patent claim recites a gas turbine engine and M246 teaches the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system which is a well-known configuration for a geared gas turbine engine to increase engine thrust force output, it would have been obvious to one having ordinary skill in the art at the time the invention was made to modify the gas turbine engine in the patent claims so that the gas turbine engine includes fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system as taught by M246 for the purpose of increasing engine thrust force output.
Claim 1 is rejected under the judicially created doctrine of obviousness-type double patenting as being unpatentable over claim 4, of McCune et al (US 10,301,968 B2) in view of McCune et al – hereafter M246 – (US 20110130246 A1).
Although the claims are not identical, they are not patentably distinct from one another. The application claims are broader in at least one aspect and also recite additional features not claimed in the patent claims.
For claim 1:
Regarding the broadening aspect of the application claims, the following comparison between the patent claims and the application claims highlights (see underlined features in the patent claims) what elements have been excluded in the presentation of the application claims.
Patent claim 4
Application claim 1
A gas turbine engine comprising:
a fan shaft driving a fan having fan blades;
a frame which supports said fan shaft having a frame lateral stiffness and a frame transverse stiffness;
a plurality of gears in driving engagement with said fan shaft; and
a flexible support which supports said plurality of gears, said flexible support having at least one of a flexible support lateral stiffness and a flexible support transverse stiffness that is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness,
said plurality of gears includes a gear mesh, said gear mesh having a gear mesh lateral stiffness and a gear mesh transverse stiffness, and at least one of said flexible support lateral stiffness and said flexible support transverse stiffness is less than 8% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness,
a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle,
a ring gear having a ring gear lateral stiffness and a ring gear transverse stiffness and at least one of said ring gear lateral stiffness and said ring gear transverse stiffness is less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.
A gas turbine engine, comprising:
a fan section having fan blades that drive air along a bypass flow path in a bypass duct;
a fan shaft drivingly connected to said fan section;
a turbine section including a turbine drive shaft;
a gear system connected to the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system, wherein there is at least one support supporting said gear system relative to a static structure; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said turbine drive shaft during operation and includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
Thus, it is apparent, for the broadening aspect, that patent claim 4 includes features that are not in application claim 1. Following the rationale in In re Goodman, cited above, where applicant has once been granted a patent containing a claim for the specific or narrower invention, applicant may not then obtain a second patent with a claim for the generic or broader invention without first submitting an appropriate terminal disclaimer. Since application claim 1 is anticipated by patent claim 4, with respect to the broadening aspect, then application claim 1 is obvious over patent claim 4 with respect to the broadening aspect.
With respect to the additional features recited in application claim 1, patent claim 4 fails to recite the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system. However, M246 teaches a gas turbine engine including a fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of a gear system and connected to a fan shaft on an output side of the gear system (Fig.1/2, note fan 32, bypass duct defined by inner surface of element 44, turbine section 20, turbine drive shaft 22 on an input side (via 46) of gear system 30, connected to fan shaft ¶9). Since the patent claim recites a gas turbine engine and M246 teaches the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system which is a well-known configuration for a geared gas turbine engine to increase engine thrust force output, it would have been obvious to one having ordinary skill in the art at the time the invention was made to modify the gas turbine engine in the patent claims so that the gas turbine engine includes fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system as taught by M246 for the purpose of increasing engine thrust force output.
Claim 1 is rejected under the judicially created doctrine of obviousness-type double patenting as being unpatentable over claim 2, of McCune et al (US 10,590,802 B2) in view of McCune et al – hereafter M246 – (US 20110130246 A1).
Although the claims are not identical, they are not patentably distinct from one another. The application claims are broader in at least one aspect and also recite additional features not claimed in the patent claims.
For claim 1:
Regarding the broadening aspect of the application claims, the following comparison between the patent claims and the application claims highlights (see underlined features in the patent claims) what elements have been excluded in the presentation of the application claims.
Patent claim 2
Application claim 1
A gas turbine engine, comprising:
a fan shaft driving a fan having fan blades;
a fan shaft support that supports said fan shaft defining a fan shaft support transverse stiffness;
a gear system connected to said fan shaft, wherein said gear system includes a gear mesh defining a gear mesh transverse stiffness;
a flexible support supporting said gear system defining a flexible support transverse stiffness; and
wherein said flexible support transverse stiffness is less than 11% of said fan shaft support transverse stiffness and less than 8% of said gear mesh transverse stiffness,
said gear mesh defines a gear mesh lateral stiffness and said gear system includes a ring gear defining a ring gear lateral stiffness and said ring gear lateral stiffness is less than 12% of said gear mesh lateral stiffness.
A gas turbine engine, comprising:
a fan section having fan blades that drive air along a bypass flow path in a bypass duct;
a fan shaft drivingly connected to said fan section;
a turbine section including a turbine drive shaft;
a gear system connected to the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system, wherein there is at least one support supporting said gear system relative to a static structure; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said turbine drive shaft during operation and includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
Thus, it is apparent, for the broadening aspect, that patent claim 2 includes features that are not in application claim 1. Following the rationale in In re Goodman, cited above, where applicant has once been granted a patent containing a claim for the specific or narrower invention, applicant may not then obtain a second patent with a claim for the generic or broader invention without first submitting an appropriate terminal disclaimer. Since application claim 1 is anticipated by patent claim 2, with respect to the broadening aspect, then application claim 1 is obvious over patent claim 2 with respect to the broadening aspect.
With respect to the additional features recited in application claim 1, patent claim 2 fails to recite the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system. However, M246 teaches a gas turbine engine including a fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of a gear system and connected to a fan shaft on an output side of the gear system (Fig.1/2, note fan 32, bypass duct defined by inner surface of element 44, turbine section 20, turbine drive shaft 22 on an input side (via 46) of gear system 30, connected to fan shaft ¶9). Since the patent claim recites a gas turbine engine and M246 teaches the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system which is a well-known configuration for a geared gas turbine engine to increase engine thrust force output, it would have been obvious to one having ordinary skill in the art at the time the invention was made to modify the gas turbine engine in the patent claims so that the gas turbine engine includes fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system as taught by M246 for the purpose of increasing engine thrust force output.
Claim 1 is rejected under the judicially created doctrine of obviousness-type double patenting as being unpatentable over claim 3, of McCune et al (US 11,021,997 B2) in view of McCune et al – hereafter M246 – (US 20110130246 A1).
Although the claims are not identical, they are not patentably distinct from one another. The application claims are broader in at least one aspect and also recite additional features not claimed in the patent claims.
For claim 1:
Regarding the broadening aspect of the application claims, the following comparison between the patent claims and the application claims highlights (see underlined features in the patent claims) what elements have been excluded in the presentation of the application claims.
Patent claim 3
Application claim 1
A gas turbine engine, comprising:
a fan having fan blades;
an outer housing surrounding the fan, and a bypass flow path within said outer housing;
a fan shaft drivingly connected to said fan;
a frame supporting said fan shaft and defining a frame lateral stiffness;
a gear system connected to said fan shaft and driven through an input, said gear system includes a gear mesh defining a gear mesh lateral stiffness; and
a gear system flex mount arrangement, wherein said flex mount arrangement accommodates misalignment of said fan shaft and said input during operation and includes a flexible support which supports said gear system relative to a static structure and defines a flexible support lateral stiffness and said flexible support lateral stiffness is less than 11% of said frame lateral stiffness and said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness,
said frame defines a frame transverse stiffness and said flexible support defines a flexible support transverse stiffness that is less than 11% of said frame transverse stiffness,
said gear system includes a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
A gas turbine engine, comprising:
a fan section having fan blades that drive air along a bypass flow path in a bypass duct;
a fan shaft drivingly connected to said fan section;
a turbine section including a turbine drive shaft;
a gear system connected to the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system, wherein there is at least one support supporting said gear system relative to a static structure; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said turbine drive shaft during operation and includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
Thus, it is apparent, for the broadening aspect, that patent claim 3 includes features that are not in application claim 1. Following the rationale in In re Goodman, cited above, where applicant has once been granted a patent containing a claim for the specific or narrower invention, applicant may not then obtain a second patent with a claim for the generic or broader invention without first submitting an appropriate terminal disclaimer. Since application claim 1 is anticipated by patent claim 3, with respect to the broadening aspect, then application claim 1 is obvious over patent claim 3 with respect to the broadening aspect.
With respect to the additional features recited in application claim 1, patent claim 3 fails to recite the inclusion of the fan driving air along a bypass flow path in the bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system. However, M246 teaches a gas turbine engine including a fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of a gear system and connected to a fan shaft on an output side of the gear system (Fig.1/2, note fan 32, bypass duct defined by inner surface of element 44, turbine section 20, turbine drive shaft 22 on an input side (via 46) of gear system 30, connected to fan shaft ¶9). Since the patent claim recites a gas turbine engine and M246 teaches the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system which is a well-known configuration for a geared gas turbine engine to increase engine thrust force output, it would have been obvious to one having ordinary skill in the art at the time the invention was made to modify the gas turbine engine in the patent claims so that the gas turbine engine includes fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system as taught by M246 for the purpose of increasing engine thrust force output.
Claim 1 is rejected under the judicially created doctrine of obviousness-type double patenting as being unpatentable over claim 1, of McCune et al (US 11,021,996 B2) in view of McCune et al – hereafter M246 – (US 20110130246 A1).
Although the claims are not identical, they are not patentably distinct from one another. The application claims are broader in at least one aspect and also recite additional features not claimed in the patent claims.
For claim 1:
Regarding the broadening aspect of the application claims, the following comparison between the patent claims and the application claims highlights (see underlined features in the patent claims) what elements have been excluded in the presentation of the application claims.
Patent claim 1
Application claim 1
A gas turbine engine, comprising:
a fan shaft driving a fan having fan blades, wherein the fan delivers airflow to a bypass duct;
a fan shaft support that supports said fan shaft, said fan shaft support defining a fan shaft support lateral stiffness and a fan shaft support transverse stiffness;
a gear system connected to said fan shaft, said gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3, wherein at least one of said ring gear lateral stiffness and said ring gear transverse stiffness is less than 12% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness; and
a flexible support supporting said gear system defining a flexible support lateral stiffness and a flexible support transverse stiffness, wherein at least one of a flexible support lateral stiffness and said flexible support transverse stiffness is less than 11% of a respective one of said fan shaft support lateral stiffness and said fan shaft support transverse stiffness.
A gas turbine engine, comprising:
a fan section having fan blades that drive air along a bypass flow path in a bypass duct;
a fan shaft drivingly connected to said fan section;
a turbine section including a turbine drive shaft;
a gear system connected to the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system, wherein there is at least one support supporting said gear system relative to a static structure; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said turbine drive shaft during operation and includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
Thus, it is apparent, for the broadening aspect, that patent claim 1 includes features that are not in application claim 1. Following the rationale in In re Goodman, cited above, where applicant has once been granted a patent containing a claim for the specific or narrower invention, applicant may not then obtain a second patent with a claim for the generic or broader invention without first submitting an appropriate terminal disclaimer. Since application claim 1 is anticipated by patent claim 1, with respect to the broadening aspect, then application claim 1 is obvious over patent claim 1 with respect to the broadening aspect.
With respect to the additional features recited in application claim 1, patent claim 1 fails to recite the inclusion of a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system. However, M246 teaches a gas turbine engine including a fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of a gear system and connected to a fan shaft on an output side of the gear system (Fig.1/2, note fan 32, bypass duct defined by inner surface of element 44, turbine section 20, turbine drive shaft 22 on an input side (via 46) of gear system 30, connected to fan shaft ¶9). Since the patent claim recites a gas turbine engine and M246 teaches the inclusion of a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system which is a well-known configuration for a geared gas turbine engine to increase engine thrust force output, it would have been obvious to one having ordinary skill in the art at the time the invention was made to modify the gas turbine engine in the patent claims so that the gas turbine engine includes a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system as taught by M246 for the purpose of increasing engine thrust force output.
Claim 1 is rejected under the judicially created doctrine of obviousness-type double patenting as being unpatentable over claim 5, of McCune et al (US 11,698,007 B2) in view of McCune et al – hereafter M246 – (US 20110130246 A1).
Although the claims are not identical, they are not patentably distinct from one another. The application claims are broader in at least one aspect and also recite additional features not claimed in the patent claims.
For claim 1:
Regarding the broadening aspect of the application claims, the following comparison between the patent claims and the application claims highlights (see underlined features in the patent claims) what elements have been excluded in the presentation of the application claims.
Patent claim 5
Application claim 1
A gas turbine engine, comprising:
a fan having fan blades;
an outer housing surrounding the fan, and a bypass flow path within said outer housing;
a fan shaft drivingly connected to said fan;
a frame supporting said fan shaft and defining a frame lateral stiffness and a frame transverse stiffness;
a gear system connected to said fan shaft and driven through an input defining an input lateral stiffness and an input transverse stiffness, said gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said input during operation and includes a flexible support which supports said gear system relative to a static structure and defines a flexible support lateral stiffness and a flexible support transverse stiffness;
wherein at least one of said flexible support lateral stiffness and said flexible support transverse stiffness is less than 8% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness; and
wherein at least one of said input lateral stiffness and said input transverse stiffness is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness,
at least one of said flexible support lateral stiffness and said flexible support transverse stiffness is less than 11% of a respective one of said frame lateral stiffness and said frame transverse stiffness,
at least one of said input lateral stiffness and said input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness,
a gear reduction ratio of greater than 2.3, a bypass ratio greater than ten (10), a fan pressure ratio of less than 1.45 measured across said fan blades alone, and a low pressure turbine with an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1, wherein said low pressure turbine pressure ratio is a ratio of a pressure measured prior to said inlet as related to a pressure at said outlet prior to any exhaust nozzle,
said gear system includes a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
A gas turbine engine, comprising:
a fan section having fan blades that drive air along a bypass flow path in a bypass duct;
a fan shaft drivingly connected to said fan section;
a turbine section including a turbine drive shaft;
a gear system connected to the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system, wherein there is at least one support supporting said gear system relative to a static structure; and
a gear system flex mount arrangement, wherein said gear system flex mount arrangement accommodates misalignment of said fan shaft and said turbine drive shaft during operation and includes a gear mesh defining a gear mesh lateral stiffness and a ring gear defining a ring gear lateral stiffness that is less than 12% of said gear mesh lateral stiffness.
Thus, it is apparent, for the broadening aspect, that patent claim 5 includes features that are not in application claim 1. Following the rationale in In re Goodman, cited above, where applicant has once been granted a patent containing a claim for the specific or narrower invention, applicant may not then obtain a second patent with a claim for the generic or broader invention without first submitting an appropriate terminal disclaimer. Since application claim 1 is anticipated by patent claim 5, with respect to the broadening aspect, then application claim 1 is obvious over patent claim 5 with respect to the broadening aspect.
With respect to the additional features recited in application claim 1, patent claim 5 fails to recite the inclusion of the fan driving air along the bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system. However, M246 teaches a gas turbine engine including a fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of a gear system and connected to a fan shaft on an output side of the gear system (Fig.1/2, note fan 32, bypass duct defined by inner surface of element 44, turbine section 20, turbine drive shaft 22 on an input side (via 46) of gear system 30, connected to fan shaft ¶9). Since the patent claim recites a gas turbine engine and M246 teaches the inclusion of the fan driving air along a bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system which is a well-known configuration for a geared gas turbine engine to increase engine thrust force output, it would have been obvious to one having ordinary skill in the art at the time the invention was made to modify the gas turbine engine in the patent claims so that the gas turbine engine includes fan driving air along the bypass flow path in a bypass duct, a turbine section including a turbine drive shaft, the turbine drive shaft on an input side of the gear system and connected to said fan shaft on an output side of the gear system as taught by M246 for the purpose of increasing engine thrust force output.
Allowable Subject Matter
Claims 2-30 are objected to as being dependent upon a rejected base claim, but would be allowable if rewritten in independent form including all of the limitations of the base claim and any intervening claims.
Conclusion
Any inquiry concerning this communication or earlier communications from the examiner should be directed to JUAN G FLORES whose telephone number is (571)272-3486. The examiner can normally be reached Monday - Friday, 8:30am - 5:30pm Pacific Time.
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If attempts to reach the examiner by telephone are unsuccessful, the examiner’s supervisor, Nathan E Wiehe can be reached at (571) 272-8648. The fax phone number for the organization where this application or proceeding is assigned is 571-273-8300.
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/JUAN G FLORES/Primary Examiner, Art Unit 3745