Office Action 1: Non-Final Rejection (2025-06-18)
Rejection types: 102 - Lack of Novelty, 112 - Written Description/Enablement

CLAIMS:
What is claimed is:
1\. A system comprising: a first electrical machine; a motor controller device coupled to the first electrical machine, wherein the motor controller device is configured to convert first power generated by the first electrical machine or provide second power to the first electrical machine; and a set of coupling devices configured to mechanically couple or decouple the first electrical machine and a turbine engine based on a mode of the system, wherein the set of coupling devices comprises: a first gearbox coupled to the first electrical machine; a first coupling device between the first gearbox and the turbine engine; a second gearbox; a second coupling device between the second gearbox and the turbine engine; and a third coupling device between the first gearbox and the second gearbox.
2\. The system of claim 1, wherein, based on the mode of the system: the first gearbox is configured to transfer first rotational energy between at least two of the turbine engine, the first electrical machine, or a second electrical machine; the second gearbox is configured to transfer second rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; the third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox; or a combination thereof.
3\. The system of claim 2, wherein, based on the mode of the system: the first coupling device, the second coupling device, and the third coupling device are each in an decoupling state; the first rotational energy is not transferred between any of the turbine engine, the first electrical machine, and the second electrical machine; the second rotational energy is not transferred between any of the turbine engine, the first electrical machine, and the second electrical machine; and the third rotational energy is not transferred between the first gearbox and the second gearbox.
4\. The system of claim 2, wherein, based on the mode of the system: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between the turbine engine and the first electrical machine; the second coupling device is in a decoupling state, and the second rotational energy is not transferred between any of the turbine engine, the first electrical machine, and the second electrical machine; and the third coupling device is in the decoupling state, and the third rotational energy is not transferred between the first gearbox and the second gearbox.
5\. The system of claim 2, wherein, based on the mode of the system: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between the turbine engine and the first electrical machine; the second coupling device is in the coupling state and is configured to transfer the second rotational energy between the turbine engine and the second electrical machine; and the third coupling device is in an decoupling state, and the third rotational energy is not transferred between the first gearbox and the second gearbox.
6\. The system of claim 2, wherein, based on the mode of the system: the first coupling device is in an decoupling state, and the first rotational energy is not transferred between the turbine engine and the first electrical machine; the second coupling device is in the decoupling state, and the second rotational energy is not transferred between the turbine engine and the second electrical machine; and the third coupling device is in a coupling state and is configured to transfer the third rotational energy between the first gearbox and the second gearbox.
7\. The system of claim 2, wherein, based on the mode of the system: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; the second coupling device is in an decoupling state, and the second rotational energy is not transferred between the turbine engine and the second electrical machine; and the third coupling device is in the coupling state and is configured to transfer the third rotational energy between the first gearbox and the second gearbox.
8\. The system of claim 2, wherein, based on the mode of the system: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; the second coupling device is in the coupling state and is configured to transfer the second rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; and the third coupling device is in the coupling state and is configured to transfer the third rotational energy between the first gearbox and the second gearbox.
9\. The system of claim 2, wherein: the first electrical machine comprises a low pressure machine; and the second electrical machine comprises a high pressure machine.
10\. The system of claim 2, wherein: the first electrical machine and the second electrical machine each comprise a low pressure machine.
11\. The system of claim 2, wherein: the first electrical machine and the second electrical machine each comprise a high pressure machine.
12\. The system of claim 1, further comprising a control device configured to, based on the mode of the system, control the set of coupling devices in association with at least one of: mechanically coupling or decoupling the first gearbox and the turbine engine; mechanically coupling or decoupling the second gearbox and the turbine engine; or mechanically coupling or decoupling the first gearbox and the second gearbox.
13\. The system of claim 1, wherein: the first coupling device is mechanically coupled to a first spool of the turbine engine; the second coupling device is mechanically coupled to a second spool of the turbine engine; and the first spool and the second spool are independent of one another.
14\. An apparatus comprising: a set of coupling devices configured to mechanically couple or decouple a first electrical machine and a turbine engine based on a mode associated with the apparatus, wherein the set of coupling devices comprises: a first gearbox coupled to the first electrical machine; a first coupling device between the first gearbox and the turbine engine; a second gearbox coupled; a second coupling device between the second gearbox and the turbine engine; and a third coupling device between the first gearbox and the second gearbox.
15\. The apparatus of claim 14, wherein, based on the mode associated with the apparatus: the first gearbox is configured to transfer first rotational energy between at least two of the turbine engine, the first electrical machine, or a second electrical machine; the second gearbox is configured to transfer second rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; the third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox, or a combination thereof.
16\. The apparatus of claim 15, wherein, based on the mode associated with the apparatus: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between the turbine engine and the first electrical machine; the second coupling device is in a decoupling state, and the second rotational energy is not transferred between any of the turbine engine, the first electrical machine, and the second electrical machine; and the third coupling device is in the decoupling state, and the third rotational energy is not transferred between the first gearbox and the second gearbox.
17\. The apparatus of claim 15, wherein, based on the mode associated with the apparatus: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between the turbine engine and the first electrical machine; the second coupling device is in the coupling state and is configured to transfer the second rotational energy between the turbine engine and the second electrical machine; and the third coupling device is in an decoupling state, and the third rotational energy is not transferred between the first gearbox and the second gearbox.
18\. The apparatus of claim 15, wherein, based on the mode associated with the apparatus: the first coupling device is in an decoupling state, and the first rotational energy is not transferred between the turbine engine and the first electrical machine; the second coupling device is in the decoupling state, and the second rotational energy is not transferred between the turbine engine and the second electrical machine; and the third coupling device is in a coupling state and is configured to transfer the third rotational energy between the first gearbox and the second gearbox.
19\. The apparatus of claim 15, wherein, based on the mode associated with the apparatus: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; the second coupling device is in an decoupling state, and the second rotational energy is not transferred between the turbine engine and the second electrical machine; and the third coupling device is in the coupling state and is configured to transfer the third rotational energy between the first gearbox and the second gearbox.
20\. The apparatus of claim 15, wherein, based on the mode associated with the apparatus: the first coupling device is in a coupling state and is configured to transfer the first rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; the second coupling device is in the coupling state and is configured to transfer the second rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine; and the third coupling device is in the coupling state and is configured to transfer the third rotational energy between the first gearbox and the second gearbox.

OFFICE ACTION:
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 .
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.
Drawings
The drawings are objected to as failing to comply with 37 CFR 1.84(p)(5) because they include the following reference character(s) not mentioned in the description: FIG. 1:221 & 44; FIG. 2:207& 208.  Corrected drawing sheets in compliance with 37 CFR 1.121(d), or amendment to the specification to add the reference character(s) in the description in compliance with 37 CFR 1.121(b) are required in reply to the Office action to avoid abandonment of the application. Any amended replacement drawing sheet should include all of the figures appearing on the immediate prior version of the sheet, even if only one figure is being amended. Each drawing sheet submitted after the filing date of an application must be labeled in the top margin as either “Replacement Sheet” or “New Sheet” pursuant to 37 CFR 1.121(d). If the changes are not accepted by the examiner, the applicant will be notified and informed of any required corrective action in the next Office action. The objection to the drawings will not be held in abeyance.
Claim Rejections - 35 USC § 102
The following is a quotation of the appropriate paragraphs of 35 U.S.C. 102 that form the basis for the rejections under this section made in this Office action:
A person shall be entitled to a patent unless –
(a)(1) the claimed invention was patented, described in a printed publication, or in public use, on sale, or otherwise available to the public before the effective filing date of the claimed invention.
Claims 1, 12-13 & 15 are rejected under 35 U.S.C. 102(a)(1) as being anticipated by Dalal (US 2018/0112599).
Regarding Claim 1, Dalal discloses a system comprising:
(a) a first electrical machine [18] (FIG. 2);
a motor controller device [40] coupled to the first electrical machine [18], wherein the motor controller device [40] is configured to convert first power generated by the first electrical machine [18] OR (FIG. 2, [0022]; Also as shown, the first and second ICCs 40, 42 can be selectively connected with the power distribution bus 44 by way of respective selectively coupling links 46. As described herein, an ICC can be configured to operably enable or selectively implement inverting, converting, controlling, or the like, a first power received by the ICC to a second power supplied by the ICC); and
a set of coupling devices configured to mechanically couple or decouple the first electrical machine [18] and (b) a turbine engine [48] based on a mode of the system (FIG. 2),
wherein the set of coupling devices comprises:
(c) a first gearbox [52] coupled to the first electrical machine [18] (FIG. 2);
(d) a first coupling device [starter] between the first gearbox [52] and the turbine engine [12] (FIG. 2, ¶ [0020]);
(e) a second gearbox [54];
(f) a second coupling device [starter] between the second gearbox [54] and the turbine engine [12] (FIG. 2, ¶ [0020]); and
(g) a third coupling device [96] between the first gearbox [52] and the second gearbox [54] (FIG. 2, ¶ [0027]).
Regarding Claim 12, Dalal discloses the system of claim 1, further comprising a control device configured to, based on the mode of the system, control the set of coupling devices in association with at least one of:
mechanically coupling or decoupling the first gearbox [52] and the turbine engine [48] (FIG. 2, ¶ [0015]; While “a set of” various elements will be described, it will be understood that “a set” can include any number of the respective elements, including only one element. Connection references (e.g., attached, coupled, connected, decoupled, disconnected, and joined) are to be construed broadly and can include intermediate members between a collection of elements and relative movement between elements unless otherwise indicated).
Regarding Claim 13, Dalal discloses the system of claim 1, wherein:
the first coupling device [starter in 52] is mechanically coupled to a first spool of the turbine engine (¶ [0017]; In the aircraft 10, the operating left and right engines 12, 14 provide mechanical energy which can be extracted, typically via a spool or set of spools, to provide a driving force for the generators 18, 19, 36, 38);
the second coupling device [starter in 54] is mechanically coupled to a second spool of the turbine engine (¶ [0017]; In the aircraft 10, the operating left and right engines 12, 14 provide mechanical energy which can be extracted, typically via a spool or set of spools, to provide a driving force for the generators 18, 19, 36, 38); and
the first spool and the second spool are independent of one another (FIG. 2 shows each 48, 52 &16 “independent” from 50, 54 & 19).
Regarding Claim 14, Dalal discloses an apparatus comprising:
a set of coupling devices configured to mechanically couple or decouple a first electrical machine [refer to rejected Claim 1, element “a”] and a turbine engine based on a mode associated with the apparatus [refer to rejected Claim 1,element “b”],
wherein the set of coupling devices comprises:
a first gearbox coupled to the first electrical machine [refer to rejected Claim 1, element “c”];
a first coupling device between the first gearbox and the turbine engine [refer to rejected Claim 1, element “d”];
a second gearbox coupled [refer to rejected Claim 1, element “e”];
a second coupling device between the second gearbox and the turbine engine [refer to rejected Claim 1, element “f”]; and
a third coupling device between the first gearbox and the second gearbox [refer to rejected Claim 1, element “g”].
Allowable Subject Matter
Claims 2-11, 14 & 16-20 would be allowable if rewritten to overcome the rejection(s) under 35 U.S.C. 112(b) or 35 U.S.C. 112 (pre-AIA ), 2nd paragraph, set forth in this Office action and to include all of the limitations of the base claim and any intervening claims.
Conclusion

APPLICANT REBUTTAL: REMARKS
In response to the Office Action mailed on June 18, 2025, Applicant respectfully requests reconsideration based on the above claim amendments and the following remarks. Applicant respectfully submits that the claims as presented are in condition for allowance.
Claims 1, 3-14, and 16-21 are pending, with claims 1, 14, and 21 being independent. Claims 1, 3-11, 14, and 16-20 are amended. Claim 21 is newly added. Claims 2 and 15 are canceled. No new matter is added.
Claim Numbering
Upon Applicant review of the pending claims in Patent Center and the US Pre-grant Publication for the present application, Applicant notes a typographical issue with respect to claim numbering appears to have resulted from a processing error related to the upload of the DOCX version of the claims as-filed, in which claims 9-14 are erroneously numbered as claims 3-8, respectively.
It appears that the Examiner has recognized this processing error and treated claims 3-8 as claims 9-14 accordingly, which is appreciated by the Applicant. Applicant notes the Auxiliary PDF (filed July 16, 2024) of the present application as accessible via the USPTO Patent Center indicates the correct claim numbering of claims 1-20.
For purposes of the present response, Applicant refers to claims 1-20 as presented with the originally filed Application.
Allowable Subject Matter
Claims 2-11, 151 and 16-20 have been 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
1 Though the Office Action indicates at p. 6 that claims 2-11, 14 & 16-20 would be allowable, Applicant understands that claim 15 is allowable in view of the allowability of dependent claim 2 which recites similar features.
the base claim and any intervening claims. See Office Action, p. 6. Applicant appreciates the Examiner's indication of allowable subject matter.
Amendments to the Drawings
The drawings are objected to as failing to comply with 37 CFR 1.84(p)(5) for including the following reference character(s): FIG. 1:221 & 44; FIG. 2:207& 208.
Applicant has submitted replacement drawing sheets containing amended FIGS. 1 and 2.
Reference character 221 is deleted from FIG. 1, and components 207 and 208 are deleted from FIG. 2, in accordance with the guidelines provided in the Office Action. Reference character 44 is maintained in FIG. 1, as paragraph [0032] of the specification describes "a low pressure compressor 44."
Applicant respectfully submits that entry of the requested amendments to the drawings overcome the objections to the drawings. No new matter has been added. Therefore, applicants respectfully request withdrawal of the drawing objections.
X
102 Rejections
Claims 1 and 12-14 were rejected under 35 U.S.C. § 102(a)(1) as being anticipated by Dalal (U.S. Publication No. 2018/0112599, herein "Dalal"). See Office Action, pp. 3-5.
Independent claims 1 and 14
Applicant has amended independent claim 1 to include the allowable subject matter of claim 2. Applicant has also amended independent claim 14 to include the allowable subject matter of claim 15.
Dalal fails to teach or suggest the features recited in amended independent claims 1 and 14. Claims dependent from independent claims 1 and 14 are patentable for at least the same reasons.
Reconsideration and withdrawal of the 102 rejection applied against claims 1 and 12-14 is respectfully requested.
Independent claim 21
Newly added independent claim 21 incorporates the features of claim 1 and dependent claim 12. Dalal fail to teach or suggest at least the italicized features of claim 21.
21.   A system comprising:
a first electrical machine;
a motor controller device coupled to the first electrical machine, wherein the motor controller device is configured to convert first power generated by the first electrical machine or provide second power to the first electrical machine;
a set of coupling devices configured to mechanically couple or decouple the first electrical machine and a turbine engine based on a mode of the system; and
a control device,
wherein the set of coupling devices comprises:
a first gearbox coupled to the first electrical machine;
a first coupling device between the first gearbox and the turbine engine;
a second gearbox;
a second coupling device between the second gearbox and the turbine engine; and
a third coupling device between the first gearbox and the second gearbox, and
wherein the control device is configured to, based on the mode of the system, selectively control the set of coupling devices in association with:
selectively mechanically coupling or decoupling the first gearbox and the turbine engine; selectively mechanically coupling or decoupling the second gearbox and the turbine engine;
selectively mechanically coupling or decoupling the first gearbox and the second gearbox; or
a combination thereof.
The Office Action, p. 4, cites a high pressure (HP) spool 48 of the left engine 12 and a HP spool gearbox 52 in FIG. 2 of Dalal, and further, paragraph [0015] of Dalal as teaching the features of claim 12.
The portions of Dalal, however, fail to teach or suggest "control device is configured to, based on the mode of the system, selectively control the set of coupling devices in association with: selectively mechanically coupling or decoupling the first gearbox and the turbine engine; selectively mechanically coupling or decoupling the second gearbox and the turbine engine; selectively mechanically coupling or decoupling the first gearbox and the second gearbox; or a combination thereof," as recited in claim 21.
In view of the foregoing amendments and remarks, it is submitted that the application is
now in condition for allowance. Such action is therefore respectfully requested.
If a communication with Applicant's Attorneys would assist in advancing this case to allowance, the Examiner is cordially invited to contact the undersigned so that any such issues
may be promptly resolved.
The Commissioner is hereby authorized to charge any additional fees that may be
required for this amendment, or credit any overpayment, to Deposit Account No. 08-0385. In the event that an extension of time is required, or may be required in addition to that requested in a petition for extension of time, the Commissioner is requested to grant a petition for that extension of time that is required to make this response timely and is hereby authorized to charge any fee for such an extension of time or credit any overpayment for an extension of time to the above-identified Deposit Account.
Respectfully submitted, Cantor Colburn LLP

NEXT OFFICE ACTION: 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 .
Response to Arguments
Applicant’s arguments, filed 09/18/2025, with respect to 102 Rejections have been fully considered and are persuasive.  The 102 Rejections have been withdrawn.
Applicant's arguments regarding the Drawing Objections have been fully considered but they are not persuasive. NO new drawing sheet were submitted.
Drawings
The drawings are objected to as failing to comply with 37 CFR 1.84(p)(5) because they include the following reference character(s) not mentioned in the description: FIG. 1:221; FIG. 2:207& 208.  Corrected drawing sheets in compliance with 37 CFR 1.121(d), or amendment to the specification to add the reference character(s) in the description in compliance with 37 CFR 1.121(b) are required in reply to the Office action to avoid abandonment of the application. Any amended replacement drawing sheet should include all of the figures appearing on the immediate prior version of the sheet, even if only one figure is being amended. Each drawing sheet submitted after the filing date of an application must be labeled in the top margin as either “Replacement Sheet” or “New Sheet” pursuant to 37 CFR 1.121(d). If the changes are not accepted by the examiner, the applicant will be notified and informed of any required corrective action in the next Office action. The objection to the drawings will not be held in abeyance.
Allowable Subject Matter
Claims 1, 3-14 & 16-21 are allowed.
The prior art of record, alone or in combination, does not explicitly teach, suggest, or render obvious, at least to the skilled artisan in the context of other recited components of a system of Claim 1 specifically comprising, “the third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox; or a combination thereof”.
The prior art of record, alone or in combination, does not explicitly teach, suggest, or render obvious, at least to the skilled artisan in the context of other recited components of an apparatus of Claim 14 specifically comprising, “the third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox; or a combination thereof”.
The prior art of record, alone or in combination, does not explicitly teach, suggest, or render obvious, at least to the skilled artisan in the context of other recited components of a system of Claim 21 specifically comprising, “a third coupling device between the first gearbox and the second gearbox, and wherein the control device is configured to, based on the mode of the system, selectively control the set of coupling devices”.
REASONS FOR ALLOWANCE
With respect to Claim 1 and claims dependent thereon, the prior arts when considered, either alone or in combination, fails to teach or suggests –
A system comprising:
a first electrical machine;
a motor controller device coupled to the first electrical machine, wherein the motor controller device is configured to convert first power generated by the first electrical machine or provide second power to the first electrical machine; and
a set of coupling devices configured to mechanically couple or decouple the first electrical machine and a turbine engine based on a mode of the system,
wherein the set of coupling devices comprises:
a first gearbox coupled to the first electrical machine;
a first coupling device between the first gearbox and the turbine engine;
a second gearbox;
a second coupling device between the second gearbox and the turbine engine; and
a third coupling device between the first gearbox and the second gearbox, and
wherein, based on the mode of the system:
the first gearbox is configured to transfer first rotational energy between at least two of the turbine engine, the first electrical machine, or a second electrical machine;
the second gearbox is configured to transfer second rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine;
third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox; or a combination thereof.
With respect to Claim 14 and claims dependent thereon, the prior arts when considered, either alone or in combination, fails to teach or suggests –
An apparatus comprising:
a set of coupling devices configured to mechanically couple or decouple a first electrical machine and a turbine engine based on a mode associated with the apparatus,
wherein the set of coupling devices comprises:
a first gearbox coupled to the first electrical machine;
a first coupling device between the first gearbox and the turbine engine;
a second gearbox coupled;
a second coupling device between the second gearbox and the turbine engine; and
a third coupling device between the first gearbox and the second gearbox, and
wherein, based on the mode associated with the apparatus:
the first gearbox is configured to transfer first rotational energy between at least two of the turbine engine, the first electrical machine, or a second electrical machine;
the second gearbox is configured to transfer second rotational energy between at least two of the turbine engine, the first electrical machine, or the second electrical machine;
the third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox; or a combination thereof.
With respect to Claim 21 and claims dependent thereon, the prior arts when considered, either alone or in combination, fails to teach or suggests –
A system comprising:
a first electrical machine;
a motor controller device coupled to the first electrical machine, wherein the motor controller device is configured to convert first power generated by the first electrical machine or provide second power to the first electrical machine;
a set of coupling devices configured to mechanically couple or decouple the first electrical machine and a turbine engine based on a mode of the system; and
a control device,
wherein the set of coupling devices comprises:
a first gearbox coupled to the first electrical machine;
a first coupling device between the first gearbox and the turbine engine;
a second gearbox;
a second coupling device between the second gearbox and the turbine engine; and
a third coupling device between the first gearbox and the second gearbox, and
wherein the control device is configured to, based on the mode of the system, selectively control the set of coupling devices in association with:
selectively mechanically coupling or decoupling the first gearbox and the turbine engine;
selectively mechanically coupling or decoupling the second gearbox and the turbine engine;
selectively mechanically coupling or decoupling the first gearbox and the second gearbox;
or a combination thereof.
Conclusion

CITED REFERENCE SUMMARIES: Ref US20180112599A1: Claims:
An electrical power system architecture, comprising: a power distribution bus configured to receive power generated by a first engine having a first generator system and a second generator system; a first set of electrical buses connected with the power distribution bus and associated with the first engine; a second set of electrical buses configured to selectively connect with the power distribution bus, including at least an essential bus, and associated with a second engine; and a share regulator configured to provide a set of share ratios values to the first generator system and the second generator system, and configured to receive an operational status of the second engine; wherein, upon receipt of non-operational status of the second engine, the power distribution bus is configured to selectively disconnect the second set of electrical buses except for the essential bus, and the share regulator is configured to provide the set of share ratio values to the first generator system and second generator system selected to enabled the first and second generator systems to share allocation of power generation sufficient to energize the first set of electrical buses and the essential bus.
a power distribution bus configured to receive power generated by a first engine having a first generator system and a second generator system;
a first set of electrical buses connected with the power distribution bus and associated with the first engine;
a second set of electrical buses configured to selectively connect with the power distribution bus, including at least an essential bus, and associated with a second engine; and
a share regulator configured to provide a set of share ratios values to the first generator system and the second generator system, and configured to receive an operational status of the second engine;
wherein, upon receipt of non-operational status of the second engine, the power distribution bus is configured to selectively disconnect the second set of electrical buses except for the essential bus, and the share regulator is configured to provide the set of share ratio values to the first generator system and second generator system selected to enabled the first and second generator systems to share allocation of power generation sufficient to energize the first set of electrical buses and the essential bus.
The electrical power system architecture of claim 1 wherein the share regulator is configured to provide a desired power signal to at least one of the first generator system or the second generator system.
The electrical power system architecture of claim 2 wherein the at least one of the first or the second generator systems are configured to alter a power output in accordance with the desired power signal.
The electrical power system architecture of claim 3 wherein the at least one of the first or the second generator systems are configured to operate in overload mode in response to the desired power signal.
The electrical power system architecture of claim 1 wherein the second engine includes a third generator system.
The electrical power system architecture of claim 5 wherein the third generator system includes a starter/generator.
The electrical power system architecture of claim 6 wherein, upon receipt of non-operational status of the second engine, the share regulator is configured to provide the set of share ratio values to the first generator system and the second generator system, wherein the share ratio values are selected to enabled the first and second generator systems to share allocation of power generation sufficient to energize the starting of the second engine by way of the starter/generator system.
The electrical power system architecture according to claim 1 wherein at least one of the first or the second generator systems are mechanically connected to a high pressure spool in the first engine.
The electrical power system architecture according to claim 1 wherein at least one of the first or the second generator systems are mechanically connected to a low pressure spool in the first engine.
A method for allocating power in an electrical power system architecture, comprising: determining an operational status of a first engine system; and in response to determining the first engine system is non-operational: selectively disconnecting a first set of electrical loads associated with the first engine system from a power distribution bus except for a subset of essential electrical loads associated with the first engine system; providing a set of share ratio values to a second operational engine system having at least a first generator and a second generator; and operating the first and the second generators in accordance with the set of share ratio values such that the first and the second generators allocate a desired combined power output to the power distribution bus sufficient to energize a second set of electrical loads associated with the second engine system and the subset of essential electrical loads associated with the first engine system.
determining an operational status of a first engine system; and
in response to determining the first engine system is non-operational:
selectively disconnecting a first set of electrical loads associated with the first engine system from a power distribution bus except for a subset of essential electrical loads associated with the first engine system;
providing a set of share ratio values to a second operational engine system having at least a first generator and a second generator; and
operating the first and the second generators in accordance with the set of share ratio values such that the first and the second generators allocate a desired combined power output to the power distribution bus sufficient to energize a second set of electrical loads associated with the second engine system and the subset of essential electrical loads associated with the first engine system.
The method of claim 10 wherein the providing includes providing a desired power signal corresponding to the desired combined power output.
The method of claim 11 wherein the operating includes altering the power output of at least one of the first or the second generators such that the first and the second generators allocate the desired combined power output based on the desired power signal.
The method of claim 10 , further including starting the non-operational first engine system having a starter/generator mechanically connected with the first engine system by selectively supplying a starting power from the power distribution bus to the starter/generator, and operating the starter/generator in a starting mode.
The method of claim 13 wherein the operating includes operating the first and the second generators such that the first and the second generators allocate a desired combined power output to the power distribution bus sufficient to supply the starting power to the starter/generator and operating the starter/generator in the starting mode.
The method of claim 14 wherein the method includes restarting a non-operational gas turbine on an aircraft during flight.
The method of claim 10 wherein the providing includes providing a set of share ration values based on a flight phase of an aircraft having the first engine and the second engine.
The method of claim 10 wherein operating the first and the second generator include operating at least one of the first or second generators in overload mode.
A method for restarting a non-operational engine of a flying aircraft, the method comprising: disabling a set of electrical loads associated with the non-operational engine from a power distribution bus except for a subset of essential electrical loads associated with the non-operational engine; selectively allocating a combined power output between at least two generator systems driven by at least one operational engine of the flying aircraft; and restarting the non-operational engine by way of a mechanically connected starter/generator supplied with at least a portion of the combined power output; wherein the selectively allocating the combined power output is based at least on the summation of a first power demand for a set of electrical loads associated with the operational engine, a second power demand for the subset of essential electrical loads associated with the non-operational engine, and a third power demand for the restarting the non-operational engine.
disabling a set of electrical loads associated with the non-operational engine from a power distribution bus except for a subset of essential electrical loads associated with the non-operational engine;
selectively allocating a combined power output between at least two generator systems driven by at least one operational engine of the flying aircraft; and
restarting the non-operational engine by way of a mechanically connected starter/generator supplied with at least a portion of the combined power output;
wherein the selectively allocating the combined power output is based at least on the summation of a first power demand for a set of electrical loads associated with the operational engine, a second power demand for the subset of essential electrical loads associated with the non-operational engine, and a third power demand for the restarting the non-operational engine.
The method of claim 18 wherein the selectively allocating the combined power output includes providing at least one of a set of share ratio values or a desired power signal corresponds to a desired combined power output to the at least two generator systems.
The method of claim 19 wherein the selectively allocating the combined power output is based upon the phase of flight of the aircraft.
Ref US20180112599: Claims:
1. An electrical power system architecture, comprising:
a power distribution bus configured to receive power generated by a first engine having a first generator system and a second generator system; a first set of electrical buses connected with the power distribution bus and associated with the first engine; a second set of electrical buses configured to selectively connect with the power distribution bus, including at least an essential bus, and associated with a second engine; and a share regulator configured to provide a set of share ratios values to the first generator system and the second generator system, and configured to receive an operational status of the second engine; wherein, upon receipt of non-operational status of the second engine, the power distribution bus is configured to selectively disconnect the second set of electrical buses except for the essential bus, and the share regulator is configured to provide the set of share ratio values to the first generator system and second generator system selected to enabled the first and second generator systems to share allocation of power generation sufficient to energize the first set of electrical buses and the essential bus.
2. The electrical power system architecture of claim 1 wherein the share regulator is configured to provide a desired power signal to at least one of the first generator system or the second generator system.
3. The electrical power system architecture of claim 2 wherein the at least one of the first or the second generator systems are configured to alter a power output in accordance with the desired power signal.
4. The electrical power system architecture of claim 3 wherein the at least one of the first or the second generator systems are configured to operate in overload mode in response to the desired power signal.
5. The electrical power system architecture of claim 1 wherein the second engine includes a third generator system.
6. The electrical power system architecture of claim 5 wherein the third generator system includes a starter/generator.
7. The electrical power system architecture of claim 6 wherein, upon receipt of non-operational status of the second engine, the share regulator is configured to provide the set of share ratio values to the first generator system and the second generator system, wherein the share ratio values are selected to enabled the first and second generator systems to share allocation of power generation sufficient to energize the starting of the second engine by way of the starter/generator system.
8. The electrical power system architecture according to claim 1 wherein at least one of the first or the second generator systems are mechanically connected to a high pressure spool in the first engine.
9. The electrical power system architecture according to claim 1 wherein at least one of the first or the second generator systems are mechanically connected to a low pressure spool in the first engine.
10. A method for allocating power in an electrical power system architecture, comprising:
determining an operational status of a first engine system; and in response to determining the first engine system is non-operational: selectively disconnecting a first set of electrical loads associated with the first engine system from a power distribution bus except for a subset of essential electrical loads associated with the first engine system; providing a set of share ratio values to a second operational engine system having at least a first generator and a second generator; and operating the first and the second generators in accordance with the set of share ratio values such that the first and the second generators allocate a desired combined power output to the power distribution bus sufficient to energize a second set of electrical loads associated with the second engine system and the subset of essential electrical loads associated with the first engine system.
11. The method of claim 10 wherein the providing includes providing a desired power signal corresponding to the desired combined power output.
12. The method of claim 11 wherein the operating includes altering the power output of at least one of the first or the second generators such that the first and the second generators allocate the desired combined power output based on the desired power signal.
13. The method of claim 10, further including starting the non-operational first engine system having a starter/generator mechanically connected with the first engine system by selectively supplying a starting power from the power distribution bus to the starter/generator, and operating the starter/generator in a starting mode.
14. The method of claim 13 wherein the operating includes operating the first and the second generators such that the first and the second generators allocate a desired combined power output to the power distribution bus sufficient to supply the starting power to the starter/generator and operating the starter/generator in the starting mode.
15. The method of claim 14 wherein the method includes restarting a non-operational gas turbine on an aircraft during flight.
16. The method of claim 10 wherein the providing includes providing a set of share ration values based on a flight phase of an aircraft having the first engine and the second engine.
17. The method of claim 10 wherein operating the first and the second generator include operating at least one of the first or second generators in overload mode.
18. A method for restarting a non-operational engine of a flying aircraft, the method comprising:
disabling a set of electrical loads associated with the non-operational engine from a power distribution bus except for a subset of essential electrical loads associated with the non-operational engine; selectively allocating a combined power output between at least two generator systems driven by at least one operational engine of the flying aircraft; and restarting the non-operational engine by way of a mechanically connected starter/generator supplied with at least a portion of the combined power output; wherein the selectively allocating the combined power output is based at least on the summation of a first power demand for a set of electrical loads associated with the operational engine, a second power demand for the subset of essential electrical loads associated with the non-operational engine, and a third power demand for the restarting the non-operational engine.
19. The method of claim 18 wherein the selectively allocating the combined power output includes providing at least one of a set of share ratio values or a desired power signal corresponds to a desired combined power output to the at least two generator systems.
20. The method of claim 19 wherein the selectively allocating the combined power output is based upon the phase of flight of the aircraft.