Office Action 2: Ex Parte Quayle Action (2025-09-29)
Rejection types: 112 - Written Description/Enablement

CLAIMS:
In Reply to Office Action dated: June 18, 2025 AMENDMENT AND PRESENTATION OF CLAIMSThis listing of claims will replace all prior versions and listings of claims in the application.

1\. (Currently Amended) 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;
the third coupling device is configured to transfer third rotational energy between the first gearbox and the second gearbox; or a combination thereof.
2\. (Canceled)
3\. (Currently Amended) The system of claim 1,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\. (Currently Amended) The system of claim 1,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\. (Currently Amended) The system of claim 1,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\. (Currently Amended) The system of claim 1,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\. (Currently Amended) The system of claim 1,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\. (Currently Amended) The system of claim 1,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\. (Currently Amended) The system of claim 1,wherein:
the first electrical machine comprises a low pressure machine; and the second electrical machine comprises a high pressure machine.

10\. (Currently Amended) The system of claim 1,wherein:
the first electrical machine and the second electrical machine each comprise a low pressure machine.

11\. (Currently Amended) The system of claim 1,wherein:
the first electrical machine and the second electrical machine each comprise a high pressure machine.

12\. (Original) 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\. (Original) 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\. (Currently Amended) 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.

15\. (Canceled)

16\. (Currently Amended) The apparatus o claim 14,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\. (Currently Amended) The apparatus o claim 14,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\. (Currently Amended) The apparatus o claim 14,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\. (Currently Amended) The apparatus o claim 14,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\. (Currently Amended) The apparatus o claim 14,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.

21\. (New) A system comprising:
a first electrical machine;
In Reply to Office Action dated: June 18, 2025 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.
Page 9 of 14

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

APPLICANT REBUTTAL: REMARKS At present, claims 1, 3-14 and 16-21 are pending in the application. Based on the following remarks and forgoing amendments, reconsideration of the application is respectfully requested. In the present Ex Parte Quayle Action, the rejections under 35 USC 102 have been withdrawn, and claims 1, 3-14 and 16-21 are allowed. Applicant appreciates the indication of allowance of the claims. 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. These requirements being the only outstanding issues in this case, the Applicant respectfully requests passage of the application to issue. If there are any additional charges with respect to this Amendment or otherwise, please charge them to Deposit Account No. 08-0385. Respectfully submitted, Cantor Colburn LLP By SVG {EMBED HERE} 0.311.763 Registration No.: 71,006CANTOR COLBURN LLP 20 Church Street, 22nd Floor Hartford, CT 06103 Telephone: 860-286-2929 Facsimile: 860-286-0115 Customer No.: 87521 Date: October 2, 2025

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 .
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.
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

CITED REFERENCE SUMMARIES: Ref US20090007569A1: Claims:
A turbine engine comprising: low and high spools; a high power take-off shaft coupled to the high spool; a first auxiliary component configured to be driven by the high power take-off shaft at a first speed; and a gearbox interconnecting the low spool to the first auxiliary component, the gearbox configured to drive the first auxiliary component at a second speed greater than the first speed.
low and high spools;
a high power take-off shaft coupled to the high spool;
a first auxiliary component configured to be driven by the high power take-off shaft at a first speed; and
a gearbox interconnecting the low spool to the first auxiliary component, the gearbox configured to drive the first auxiliary component at a second speed greater than the first speed.
The turbine engine according to claim 1 , wherein the first auxiliary component is a first generator.
The turbine engine according to claim 1 , comprising a low power take-off shaft coupled to the low spool and a second auxiliary component configured to be driven by the low power take-off shaft.
The turbine engine according to claim 3 , wherein the second auxiliary component is a second generator.
The turbine engine according to claim 3 , wherein the gearbox interconnects the low and high power take-off shafts.
The turbine engine according to claim 5 , wherein the gearbox includes an epicyclic gear train configured to receive a rotational input from the low power take-off shaft for increasing a rotational speed provided to the second auxiliary component.
The turbine engine according to claim 6 , wherein the epicyclic gear train includes a ring gear driven by the low power take-off shaft, the ring gear providing rotational input to planetary gears supported by a carrier, the carrier coupled to the high power take-off shaft, and a sun gear receiving rotational drive from the planetary gears, the sun gear providing rotational input to the second auxiliary component.
The turbine engine according to claim 7 , wherein the high power take-off shaft supports a gear for transmitting additional speed from the gearbox to the high power take-off shaft.
The turbine engine according to claim 8 , comprising an idler gear interconnecting the gear and a driven gear supported by the carrier.
The turbine engine according to claim 8 , comprising a third auxiliary component interconnecting the gear and a driven gear supported by the carrier.
The turbine engine according to claim 10 , wherein the third auxiliary component is a hydromechanical generator.
The turbine engine according to claim 4 , comprising a controller providing a command to the second generator for selectively rotating the high spool through the gearbox with the second generator in a start procedure.
A method of powering auxiliary components comprising the steps of: rotationally driving a first auxiliary component at a first speed with a high spool; rotationally coupling a low spool to the first auxiliary component; and increasing the first speed to a second speed in response to performing the rotationally coupling step.
rotationally driving a first auxiliary component at a first speed with a high spool;
rotationally coupling a low spool to the first auxiliary component; and
increasing the first speed to a second speed in response to performing the rotationally coupling step.
The method according to claim 13 , wherein the rotationally coupling step includes interconnecting low and high power take-off shafts with a gearbox.
The method according to claim 13 , wherein the first auxiliary component is a first generator.
The method according to claim 13 , comprising rotationally driving a second auxiliary component with the low spool.
The method according to claim 16 , wherein the second auxiliary component is a second generator.
The method according to claim 17 , comprising the step of rotationally driving the high spool with the second generator during a start procedure.
The method of claim 13 , comprising rotationally driving one of the low and high spools with a generator during engine operation.
Ref US20230250754A1: Claims:
An aircraft propulsion system, comprising: an aircraft system comprising at least one fuel tank and an aircraft-system heat exchanger; and an engine system comprising at least a main engine core, a high pressure pump, a fuel-air heat exchanger, and a turbo expander assembly, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section; wherein fuel is supplied from the at least one fuel tank through a fuel flow path, passing through the aircraft-system heat exchanger, the high pressure pump, the fuel-air heat exchanger, and selectively through the turbo expander assembly, prior to being injected into the burner for combustion, wherein the turbo expander assembly is operably coupled to at least two load sources through a selective coupler and configured to selectively drive operation of the at least two load sources.
an aircraft system comprising at least one fuel tank and an aircraft-system heat exchanger; and
an engine system comprising at least a main engine core, a high pressure pump, a fuel-air heat exchanger, and a turbo expander assembly, wherein the main engine core comprises a compressor section, a combustor section having a burner, and a turbine section;
wherein fuel is supplied from the at least one fuel tank through a fuel flow path, passing through the aircraft-system heat exchanger, the high pressure pump, the fuel-air heat exchanger, and selectively through the turbo expander assembly, prior to being injected into the burner for combustion,
wherein the turbo expander assembly is operably coupled to at least two load sources through a selective coupler and configured to selectively drive operation of the at least two load sources.
The aircraft propulsion system of claim 1 , wherein the turbo expander assembly consists of a single turbo expander operably coupled to the at least two load sources; and wherein the selective coupler comprises a clutch assembly configured to selectively connect the turbo expander to a first load source and a second load source of the at least two load sources.
wherein the turbo expander assembly consists of a single turbo expander operably coupled to the at least two load sources; and
wherein the selective coupler comprises a clutch assembly configured to selectively connect the turbo expander to a first load source and a second load source of the at least two load sources.
The aircraft propulsion system of claim 2 , wherein the first load source is continuously driven by the turbo expander and the second load source is decouplable from the turbo expander by a clutch.
The aircraft propulsion system of claim 1 , wherein the turbo expander assembly comprises a first turbo expander operably coupled to a first load source and a second turbo expander and operably coupled to a second load source.
The aircraft propulsion system of claim 4 , wherein the first load source and the second load source are electric generators having a combined power output of at least 300 kW of power.
The aircraft propulsion system of claim 4 , wherein each of the first load source and the second load source are electric generators each configured to generate at least 300 kW of power.
The aircraft propulsion system of claim 4 , further comprising a valve assembly arranged upstream of each of the first turbo expander and the second turbo expander, wherein the valve assembly is configured to selectively direct fuel to each of the first turbo expander and the second turbo expander.
The aircraft propulsion system of claim 4 , further comprising a valve assembly arranged upstream of each of the first turbo expander and the second turbo expander, wherein the valve assembly is configured to always supply fuel to the first turbo expander and to selectively direct fuel to the second turbo expander.
The aircraft propulsion system of claim 4 , further comprising a first gear box arranged between the first turbo expander and the first load source and a second gear box arranged between the second turbo expander and the second load source.
The aircraft propulsion system of claim 1 , wherein the turbo expander assembly comprises a plurality of turbo expanders and the at least two load sources comprises a number of load sources equal to the number of turbo expanders, wherein each turbo expander is selectively coupled to a respective load source.
The aircraft propulsion system of claim 1 , wherein the selective coupler is at least one of a valve assembly and a clutch assembly.
The aircraft propulsion system of claim 1 , wherein the fuel is hydrogen.
The aircraft propulsion system of claim 1 , wherein the turbo expander assembly comprises a first turbo expander operably coupled to a first load source through a first gear box and a second turbo expander operably coupled to a second load source through a second gear box, and wherein the selective coupler comprises a clutch arranged between the second turbo expander and the second load source.
wherein the turbo expander assembly comprises a first turbo expander operably coupled to a first load source through a first gear box and a second turbo expander operably coupled to a second load source through a second gear box, and
wherein the selective coupler comprises a clutch arranged between the second turbo expander and the second load source.
The aircraft propulsion system of claim 13 , further comprising a third turbo expander operably coupled to a third load source through a third gear box and the selective coupler comprises a second clutch arranged between the third turbo expander and the third gear box.
The aircraft propulsion system of claim 1 , wherein a first turbo expander of the turbo expander assembly is selectively coupled to a first load source by a clutch of the selective coupler; and wherein a second turbo expander of the turbo expander assembly is selectively coupled to a source of fuel through a valve assembly of the selective coupler.
wherein a first turbo expander of the turbo expander assembly is selectively coupled to a first load source by a clutch of the selective coupler; and
wherein a second turbo expander of the turbo expander assembly is selectively coupled to a source of fuel through a valve assembly of the selective coupler.
The aircraft propulsion system of claim 1 , wherein a first load source of the at least two load sources is an electric generator configured to generate a first power output and a second load source of the at least two load sources is an electric generator configured to generate a second power output that is different from the first power output.
A method of operating an aircraft propulsion system, the method comprising: coupling a turbo expander assembly to at least two load sources through a selective coupler; supplying, from at least one fuel tank, fuel through a fuel flow path comprising passing the fuel through an aircraft-system heat exchanger, a high pressure pump, a fuel-air heat exchanger, and selectively through a turbo expander assembly comprising at least one turbo expander, prior to injecting the fuel into a burner for combustion thereof, wherein the at least one turbo expander is rotationally driven by the fuel passing therethrough; detecting a throughflow of fuel through the turbo expander assembly; and controlling operation of the selective coupler to at least one of drive operation of the at least one turbo expander and selectively control operation of one or more of the operably connected load sources based on the detected throughflow.
coupling a turbo expander assembly to at least two load sources through a selective coupler;
supplying, from at least one fuel tank, fuel through a fuel flow path comprising passing the fuel through an aircraft-system heat exchanger, a high pressure pump, a fuel-air heat exchanger, and selectively through a turbo expander assembly comprising at least one turbo expander, prior to injecting the fuel into a burner for combustion thereof, wherein the at least one turbo expander is rotationally driven by the fuel passing therethrough;
detecting a throughflow of fuel through the turbo expander assembly; and
controlling operation of the selective coupler to at least one of drive operation of the at least one turbo expander and selectively control operation of one or more of the operably connected load sources based on the detected throughflow.
The method of claim 17 , wherein the turbo expander assembly consists of a single turbo expander operably coupled to the at least two load sources, the method further comprising: controlling the selective coupler to operate a clutch assembly to selectively connect the turbo expander assembly to a first load source and a second load source of the at least two load sources based on the detected throughflow.
controlling the selective coupler to operate a clutch assembly to selectively connect the turbo expander assembly to a first load source and a second load source of the at least two load sources based on the detected throughflow.
The method of claim 17 , wherein the turbo expander assembly comprises a first turbo expander operably coupled to a first load source of the at least two load sources and a second turbo expander and operably coupled to a second load source of the at least two load sources, the method further comprising: controlling the selective coupler to operate a valve assembly to selectively direct fuel to one or both of the first load source and the second load source based on the detected throughflow.
controlling the selective coupler to operate a valve assembly to selectively direct fuel to one or both of the first load source and the second load source based on the detected throughflow.
The method of claim 17 , wherein the turbo expander assembly comprises a first turbo expander operably coupled to a first load source of the at least two load sources and a second turbo expander and operably coupled to a second load source of the at least two load sources, the method further comprising: controlling the selective coupler to operate a clutch assembly to selectively couple one or both of the first turbo expander and the second turbo expander to the respective first load source and second load source based on the detected throughflow.
controlling the selective coupler to operate a clutch assembly to selectively couple one or both of the first turbo expander and the second turbo expander to the respective first load source and second load source based on the detected throughflow.