Office Action 2: Notice of Allowance (2025-07-08)

CLAIMS:
LISTING OF THE CLAIMS

In accordance with 37 C.F.R. § 1.121, a claim listing including the status and text of all claims as currently presented appears below.

1\. (Currently Amended) A gas turbine engine, comprising:
a fan section comprising a fan rotatable with a fan shaft;
a turbomachinery section comprising a turbine and a turbomachine shaft rotatable with the turbine;
a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft such that the fan shaft is rotatable by the turbomachine shaft across the power gearbox;
a grounded structure coupled to and supporting the power gearbox;
a torque monitoring system comprising a gearbox sensor, the gearbox sensor coupled to the grounded structure, the torque monitoring system configured to determine a torque across the power gearbox using the gearbox sensor; and
a controller operably coupled with the gearbox sensor, the controller configured to:determine a model torque based on received data indicative of one or more of a speed of the fan shaft, a pitch of fan blades of the fan, a Mach number of an aircraft in which the gas turbine engine is installed, an ambient temperature, or an altitude of the aircraft;
receive data indicative of the torque across the power gearbox;
determine the torque across the power gearbox is below the model torque using the received data indicative of the torque across the power gearbox; and
reduce a supply of fuel to the gas turbine engine in response to determining the torque across the power gearbox is below the model torque.

2\. (Original) The gas turbine engine of claim 1, wherein the power gearbox comprises an epicyclical power gearbox or a compound epicyclical power gearbox including a static member coupled to the grounded structure.

3\. (Original) The gas turbine engine of claim 1, wherein the power gearbox comprises:
a sun gear including a plurality of teeth, the sun gear drivingly coupled to the turbomachine shaft of the gas turbine engine;
a plurality of planet gears circumscribing the sun gear, each of the planet gears including a plurality of teeth meshing with the teeth of the sun gear such that rotation of the sun gear causes rotation of each planet gear of the plurality of planet gears;
a ring gear circumscribing the plurality of planet gears, the ring gear including a plurality of teeth meshing with the teeth of each of the planet gears such that the ring gear rotates relative to the plurality of planet gears; and
a planet carrier coupled to each planet gear of the plurality of planet gears and to the grounded structure such that the planet carrier supports the power gearbox relative to the grounded structure.
4\. (Original) The gas turbine engine of claim 3, further comprising:
a frame, wherein the grounded structure is coupled to the frame of the gas turbine engine.
5\. (Original) The gas turbine engine of claim 4, wherein the gearbox sensor is operable to sense data indicative of a deflection of the grounded structure to determine the torque across the power gearbox.
6\. (Currently Amended) The gas turbine engine of claim 1, wherein the controller is operably coupled with the gearbox sensor.
7\. (Currently Amended) The gas turbine engine of claim 6, wherein:
the fan comprises a fixed pitch fan; and
the controller is further configured to:receive data indicative of the torque across the power gearbox;
determine the torque across the power gearbox exceeds a lower torque threshold using the received data indicative of the torque across the power gearbox;
perform at least one corrective action in response to determining the torque across the power gearbox exceeds the lower torque threshold;

determine the torque across the power gearbox exceeds an upper torque threshold using the received data indicative of the torque across the power gearbox; and
reduce \[\[a\]\] the supply of fuel to the gas turbine engine in response to determining the torque across the power gearbox exceeds the upper torque threshold.

8\. (Original) The gas turbine engine of claim 7, wherein the at least one corrective action includes reducing a rotational speed of the fan shaft, reducing a flow of fuel to the gas turbine engine, or both.
9\. (Original) The gas turbine engine of claim 7, wherein the controller is further configured to:
determine the torque across the power gearbox is less than or equal to the upper torque threshold; and
determine the torque across the power gearbox is within a normal operating range using the received data indicative of the torque across the power gearbox in response to determining the torque across the power gearbox is less than or equal to the upper torque threshold.

10\. (Original) The gas turbine engine of claim 7, wherein the controller is further configured to:
determine the torque across the power gearbox is less than or equal to the upper torque threshold;
determine the torque across the power gearbox is outside a normal operating range using the received data indicative of the torque across the power gearbox in response to determining the torque across the power gearbox is less than or equal to the upper torque threshold; and
perform the at least one corrective action in response to determining the torque across the power gearbox is outside the normal operating range.

11\. (Original) The gas turbine engine of claim 6, wherein:
the fan comprises a variable pitch fan; and
the controller is configured to:receive data indicative of the torque across the power gearbox;

determine the torque across the power gearbox exceeds a normal operating range using the received data indicative of the torque across the power gearbox;
in response to determining that the torque across the power gearbox exceeds the normal operating range, determine the torque across the power gearbox exceeds a lower torque threshold using the received data indicative of the torque across the power gearbox;
in response to determining that the torque across the power gearbox exceeds the lower torque threshold, perform a first corrective action; and
in response to determining that the torque across the power gearbox is less than or equal to the lower torque threshold, perform a second corrective action.

12\. (Currently Amended) The gas turbine engine of claim 11, wherein:
the first corrective action comprises adjusting \[\[a\]\] the pitch of one or more of the fan blades of the fan, increasing a rotational speed of the fan, or both; and
the second corrective action comprises reducing the rotational speed of the fan, reducing a flow of fuel to the gas turbine engine, adjusting the pitch of the one or more fan blades of the fan to a failsafe speed schedule, adjusting a flow of bleed air from a working gas flow path of the gas turbine engine via a variable bleed valve, or a combination thereof.

13\. (Original) The gas turbine engine of claim 11, wherein, in response to determining that the torque across the power gearbox exceeds the lower torque threshold, the controller is further configured to:
determine the torque across the power gearbox is less than or equal to a mid-torque threshold; and
in response to determining the torque across the power gearbox is less than or equal to the mid-torque threshold, determine the torque across the power gearbox is within the normal operating range.

14\. (Original) The gas turbine engine of claim 13, wherein, in response to determining the torque across the power gearbox is less than or equal to the mid-torque threshold, the controller is further configured to:
determine the torque across the power gearbox is outside the normal operating range;
perform the first corrective action;
determine the torque across the power gearbox is less than or equal to the mid-torque threshold; and
in response to determining the torque across the power gearbox is less than or equal to the mid-torque threshold, determine the torque across the power gearbox is within the normal operating range.

15\. (Original) The gas turbine engine of claim 13, wherein, the controller is further configured to:
determine the torque across the power gearbox exceeds the mid-torque threshold; and
in response to the torque across the power gearbox exceeding the mid-torque threshold, perform the second corrective action,
determine the torque across the power gearbox is less than or equal to an upper torque threshold, and
in response to the torque across the power gearbox being less than or equal to the upper torque threshold, determine the torque across the power gearbox is within the normal operating range.

16\. (Original) The gas turbine engine of claim 11, wherein, in response to determining that the torque across the power gearbox is less than or equal to the lower torque threshold and performing the second corrective action, the controller is further configured to:
determine the torque across the power gearbox is less than or equal to an upper torque threshold; and
in response to the torque across the power gearbox being less than or equal to the upper torque threshold, determine the torque across the power gearbox is within the normal operating range.

17\. (Original) The gas turbine engine of claim 16, wherein, the controller is further configured to:
determine the torque across the power gearbox exceeds the upper torque threshold; and
in response to the torque across the power gearbox exceeding the upper torque threshold,

reduce a flow of fuel to the gas turbine engine.

18\. (Original) The gas turbine engine of claim 16, wherein, the controller is further configured to:
determine the torque across the power gearbox is outside the normal operating range; and
in response to determining the torque across the power gearbox is outside the normal operating range,
reduce a rotational speed of the fan, reduce a flow of fuel to the gas turbine engine, or both reduce the rotational speed of the fan and reduce the flow of fuel to the gas turbine engine,
adjust a pitch of one or more blades of the fan to a failsafe speed schedule,
determine the torque across the power gearbox is less than or equal to the upper torque threshold, and
in response to the torque across the power gearbox being less than or equal to the upper torque threshold, determine the torque across the power gearbox is healthy.

19\. (Currently Amended) A method for a gas turbine engine including a fan section having a fan rotatable with a fan shaft, a turbomachinery section having a turbine and a turbomachine shaft rotatable with the turbine, and a power gearbox mechanically coupled to the fan shaft and the turbomachine shaft, the method comprising:
determining a model torque based on received data indicative of one or more of a speed of the fan shaft, a pitch of fan blades of the fan, a Mach number of an aircraft in which the gas turbine engine is installed, an ambient temperature, or an altitude of the aircraft;
receiving data indicative of a torque across the power gearbox;
determining the torque across the power gearbox is below the model torque using the received data indicative of the torque across the power gearbox; and
reducing a supply of fuel to the gas turbine engine in response to determining the torque across the power gearbox is below the model torque

.

20\. (Original) The method of claim 19, wherein receiving data indicative of the torque across the power gearbox comprises:
receiving data indicative of the torque across the power gearbox from a gearbox sensor of a torque monitoring system, the gearbox sensor coupled to a grounded structure of the gas turbine engine, the grounded structure coupled to and supporting the power gearbox.

OFFICE ACTION:
Notice of Allowance
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 .
Reasons for Allowance
The following is an examiner’s statement of reasons for allowance: Examiner refers Applicant to Interview summary in the IFW under January 12, 2025. Examiner noted the current amendment overcame the prior art.  Further, per a consideration of the art, the amendment overcomes any prior art suitable for modifying Razaket (R1) or Moniz(M1) and Lee(L1) given that while measurements are made in some references (R1 and M1) and controls based on various levels are made in (L1) they do not coordinate with the fuel and torque control such that it makes a model torque and based on the received data, utilizes said model torque to perform the function.
Any comments considered necessary by applicant must be submitted no later than the payment of the issue fee and, to avoid processing delays, should preferably accompany the issue fee.  Such submissions should be clearly labeled “Comments on Statement of Reasons for Allowance.”
Conclusion

APPLICANT REBUTTAL: REMARKS Claims 1-20 are currently pending. Applicant respectfully requests reconsideration and allowance in view of the following remarks. I. Statement of the Interview Applicant wishes to thank the Examiner for the telephone interview held with Applicant's representative, Peter Keros, on February 6, 2025. Claim 1 was discussed, and Applicant presents the amendments based on the discussion. Applicant understands that further search and consideration would be performed. II. Rejections under 35 U.S.C. §§ 102 and 103 Claims 1-6 are rejected under 35 U.S.C. § 102 as allegedly anticipated by Razak (US20200088595). Claims 7-17 and 19-20 are rejected under 35 U.S.C. § 103 as allegedly unpatentable over Razak in view of Moniz (US20180171816) in view of Lee (US2678698). Claim 18 is rejected under 35 U.S.C. § 103 as allegedly unpatentable over Razak in view of Moniz, Lee, and Bacic (US201 10229319). Independent Claim 1 Claim 1 as amended recites, in part, to "determine a model torque based on received data indicative of one or more of a speed of the fan shaft, a pitch of fan blades of the fan, a Mach number of an aircraft in which the gas turbine engine is installed, an ambient temperature, or an altitude of the aircraft." Claim 1 further incorporates certain recitations from claim 6. Support for the amendment is found at least in T 68-73 and Figures 6A-6B. Razak discloses a thrust measuring apparatus that detects a force by a planet carrier on a static structure. Moniz discloses a gas turbine engine with a torque monitoring system that detects a torque of a power gearbox. Lee discloses a fuel and torque control apparatus for a gas turbine engine. However, none of the cited references teach or suggest "a model torque" as recited in claim 1 and described in the Specification. For at least these reasons, the rejection of claim 1 should be withdrawn. Independent Claim 19 For at least the reasons stated above for claim 1, the rejection of claim 19 should be withdrawn. Dependent Claims Applicant further submits that for at least the reasons relating to corresponding independent claims, the pending dependent claims are in condition for allowance. However, Applicant also notes that the patentability of the dependent claims certainly does not hinge on the patentability of independent claims. In particular, it is believed that some or all of these claims may possess features that are independently patentable, regardless of the patentability of the independent claims. III. Conclusion For the reasons set out above, Applicant respectfully submits that the application is in condition for allowance. Favorable reconsideration and allowance of the application are respectfully requested. If the Examiner believes that anything further is necessary to place the application in better condition for allowance, the Examiner is kindly asked to contact the undersigned at the telephone number or email below. Please charge any additional fees required by this Amendment to Deposit Account No. 07-0865. In accordance with MPEP 502.03, recognizing that Internet communications are not secure, the undersigned counsel hereby authorizes the USPTO to communicate concerning any subject matter of this application by electronic mail. Respectfully submitted, DORITY & MANNING, P.A. DATE: February 14, 2025 /Peter E. Keros/ SVG {EMBED HERE} 1.4372.763 Peter E. Keros Reg. No.: 72,539 P.O. Box 1449 Greenville, SC 29602-1449 (864) 271-1592