Granted Patent B2

US 12,736,012 · App. 18/927,490 · Granted Sep 15, 2026

Inventors: Charlie Molina (Brampton, CA); Alessio Salerno (Montreal, CA)

Assignee: Pratt & Whitney Canada Corp.

F02C9/263F02C7/14F23R3/36F05D2220/323

Abstract

Claims (67)

1 . An aircraft propulsion system comprising:

a combustor section including a combustor forming a first portion of a core flow path through the aircraft propulsion system;

an engine oil system including a fuel-oil heat exchanger;

a fuel system assembly including a jet fuel system, a hydrogen fuel system and a switching valve,

the jet fuel system connected in fluid communication with the combustor and the switching valve,

the hydrogen fuel system connected in fluid communication with the combustor and the switching valve, the hydrogen fuel system including a hydrogen fuel metering system and a liquid hydrogen source, the hydrogen fuel metering system connected in fluid communication between the liquid hydrogen source, the switching valve and the combustor,

the switching valve in fluid communication with and arranged between the jet fuel system, the hydrogen fuel system and the fuel-oil heat exchanger, and

a control system including an engine controller connected in signal communication with the switching valve, the engine controller including a first processing system, the first processing system including a first processor connected in signal communication with a non-transitory first memory storing first instructions which, when executed by the first processor, cause the first processor to:

operate the fuel system assembly in one of a first fuel mode or a second fuel mode; and

configure the switching valve with one of a first circuit flow path for the first fuel mode or a second circuit flow path for the second fuel mode,

the switching valve with the first circuit flow path configured to direct a jet fuel from the jet fuel system through the fuel-oil heat exchanger, and

the switching valve with the second circuit flow path configured to direct a hydrogen fuel from the hydrogen fuel system through the fuel-oil heat exchanger.

2 . The aircraft propulsion system of claim 1 , wherein the jet fuel system includes a jet fuel metering system connected in fluid communication between the switching valve and the combustor, the jet fuel metering system is connected in signal communication with the engine controller, and the first instructions, when executed by the first processor, cause the first processor to:

control the jet fuel metering system to direct the jet fuel to the combustor.

3 . The aircraft propulsion system of claim 1 , wherein:

the control system further includes a hydrogen controller connected in signal communication with the engine controller and the hydrogen fuel metering system, the hydrogen controller includes a second processing system, the second processing system includes a second processor connected in signal communication with a non-transitory second memory storing second instructions which, when executed by the second processor, cause the second processor to:

control the hydrogen fuel metering system to direct the hydrogen fuel to the combustor.

4 . The aircraft propulsion system of claim 3 , wherein the hydrogen fuel system includes a gaseous hydrogen source, and the hydrogen fuel metering system is connected in fluid communication with and between the gaseous hydrogen source, the switching valve, and the combustor.

5 . The aircraft propulsion system of claim 4 , wherein the hydrogen fuel metering system includes a pressure relief valve and a metering valve, the pressure relief valve is connected in fluid communication with and between the gaseous hydrogen source and a hydrogen inlet of the switching valve, and the metering valve is connected in fluid communication with and between a hydrogen outlet of the switching valve and the combustor.

6 . The aircraft propulsion system of claim 3 , wherein the hydrogen fuel system further includes pump connected in fluid communication with and between the liquid hydrogen source and the hydrogen fuel metering system, and the hydrogen fuel metering system is connected in fluid communication with and arranged between the pump, the switching valve, and the combustor.

7 . The aircraft propulsion system of claim 6 , wherein the hydrogen fuel metering system includes a pressure relief valve and a metering valve, the pressure relief valve is connected in fluid communication with and between the liquid hydrogen source and a hydrogen inlet of the switching valve, and the metering valve is connected in fluid communication with and between a hydrogen outlet of the switching valve and the combustor.

8 . The aircraft propulsion system of claim 1 , further comprising a compressor section forming a second portion of the core flow path, the compressor section includes an inlet guide vane assembly, the inlet guide vane assembly includes a plurality of inlet guide vanes, an inlet guide vane actuator (IGVA), and an IGVA servo, the plurality of inlet guide vanes are positionable to control an air flow direction of an air flow at the second portion of the core flow path, the inlet guide vane actuator is operably coupled with the plurality of inlet guide vanes, the IGVA servo is connected in fluid communication with the inlet guide vane actuator, and the jet fuel system is connected in fluid communication with the IGVA servo.

9 . The aircraft propulsion system of claim 8 , wherein the engine controller is connected in signal communication with the IGVA servo, and the first instructions, when executed by the first processor, further cause the first processor to:

control the IGVA servo to direct the jet fuel to the inlet guide vane actuator to control a position of the plurality of inlet guide vanes in the first fuel mode and the second fuel mode.

10 . The aircraft propulsion system of claim 1 , wherein the first instructions, when executed by the first processor, further cause the first processor to:

operate the fuel system assembly in one of the first fuel mode, the second fuel mode, or a third fuel mode; and

in the third fuel mode, configure the switching valve with both of the first circuit flow path and the second circuit flow path.

11 . An aircraft propulsion system comprising:

a combustor section including a combustor forming a first portion of a core flow path through the aircraft propulsion system;

a heat exchanger;

a fuel system assembly including a jet fuel system, a hydrogen fuel system, and a switching valve,

the jet fuel system including a jet fuel metering system connected in fluid communication with the combustor and the switching valve,

the hydrogen fuel system including a hydrogen fuel metering system and a liquid hydrogen source, the hydrogen fuel metering system connected in fluid communication between the combustor, the liquid hydrogen source and the switching valve, and

the switching valve in fluid communication with and upstream of the heat exchanger, the switching valve configured to switch between a first circuit flow path and a second circuit flow path, the first circuit flow path extending between the jet fuel system and the heat exchanger, and the second circuit flow path extending between the hydrogen fuel system and the heat exchanger; and

a control system including an engine controller connected in signal communication with the switching valve, the engine controller including a first processing system, the first processing system including a first processor connected in signal communication with a non-transitory first memory storing first instructions which, when executed by the first processor, cause the first processor to:

operate the fuel system assembly in one of a first fuel mode or a second fuel mode; and

configure the switching valve with one of the first circuit flow path for the first fuel mode or the second circuit flow path for the second fuel mode,

the switching valve with the first circuit flow path configured to direct a jet fuel from the jet fuel system through the heat exchanger and to the combustor through the jet fuel metering system, and

the switching valve with the second circuit flow path configured to direct a hydrogen fuel from the hydrogen fuel system through the heat exchanger and to the combustor through the hydrogen fuel metering system.

12 . The aircraft propulsion system of claim 11 , further comprising a compressor section forming a second portion of the core flow path, the compressor section includes an inlet guide vane assembly, the inlet guide vane assembly includes a plurality of inlet guide vanes, an inlet guide vane actuator (IGVA), and an IGVA servo, the plurality of inlet guide vanes are positionable to control an air flow direction of an air flow at the second portion of the core flow path, the inlet guide vane actuator is operably coupled with the plurality of inlet guide vanes, the IGVA servo is connected in fluid communication with the inlet guide vane actuator, and the jet fuel system is connected in fluid communication with the IGVA servo.

13 . The aircraft propulsion system of claim 12 , wherein the engine controller is connected in signal communication with the IGVA servo, and the first instructions, when executed by the first processor, further cause the first processor to:

control the IGVA servo to direct the jet fuel to the inlet guide vane actuator to control a position of the plurality of inlet guide vanes in the first fuel mode and the second fuel mode.

14 . The aircraft propulsion system of claim 11 , wherein the control system further includes a hydrogen controller connected in signal communication with the engine controller and the hydrogen fuel metering system, the hydrogen controller includes a second processing system, the second processing system includes a second processor connected in signal communication with a non-transitory second memory storing second instructions which, when executed by the second processor, cause the second processor to:

control, in the second fuel mode, the hydrogen fuel metering system to direct the hydrogen fuel to the combustor from the switching valve.

15 . The aircraft propulsion system of claim 11 , wherein the first instructions, when executed by the first processor, further cause the first processor to:

operate the fuel system assembly in one of the first fuel mode, the second fuel mode, or a third fuel mode; and

in the third fuel mode, configure the switching valve with both of the first circuit flow path and the second circuit flow path.

16 . An aircraft propulsion system comprising:

a combustor section including a combustor forming a first portion of a core flow path through the aircraft propulsion system;

an engine oil system including a fuel-oil heat exchanger;

a fuel system assembly including a jet fuel system, a hydrogen fuel system and a switching valve,

the jet fuel system a low-pressure stage pump, a high-pressure stage pump, and a jet fuel metering system forming a jet fuel flow path, the jet fuel metering system connected in fluid communication with and between the high-pressure stage pump and the combustor,

the hydrogen fuel system including a hydrogen fuel flow path, the hydrogen fuel system including a hydrogen fuel source and a hydrogen fuel metering system forming the hydrogen fuel flow path, the hydrogen fuel metering system connected in fluid communication with and between the hydrogen fuel source, the switching valve, and the combustor, and

the switching valve configured to switch between a first circuit flow path and a second circuit flow path, the first circuit flow path extending between the jet fuel system and the fuel-oil heat exchanger, and the second circuit flow path extending between the hydrogen fuel system and the fuel-oil heat exchanger; and

a control system including an engine controller connected in signal communication with the switching valve, the engine controller including a first processing system, the first processing system including a first processor connected in signal communication with a non-transitory first memory storing first instructions which, when executed by the first processor, cause the first processor to:

operate the fuel system assembly in one of a first fuel mode or a second fuel mode; and

configure the switching valve with one of a first circuit flow path for the first fuel mode or a second circuit flow path for the second fuel mode,

the switching valve with the first circuit flow path configured to direct a jet fuel from the low-pressure stage pump, through the fuel-oil heat exchanger, and to the high-pressure stage pump along the jet fuel flow path, and

the switching valve with the second circuit flow path configured to direct a hydrogen fuel from the hydrogen fuel metering system, through the fuel-oil heat exchanger, and to the hydrogen fuel metering system along the hydrogen fuel flow path.

17 . The aircraft propulsion system of claim 16 , further comprising a compressor section forming a second portion of the core flow path, the compressor section includes an inlet guide vane assembly, the inlet guide vane assembly includes a plurality of inlet guide vanes, an inlet guide vane actuator (IGVA), and an IGVA servo, the plurality of inlet guide vanes are positionable to control an air flow direction of an air flow at the second portion of the core flow path, the inlet guide vane actuator is operably coupled with the plurality of inlet guide vanes, the IGVA servo is connected in fluid communication with the inlet guide vane actuator, and the jet fuel system is connected in fluid communication with the IGVA servo.

18 . The aircraft propulsion system of claim 17 , wherein the engine controller is connected in signal communication with the IGVA servo, and the first instructions, when executed by the first processor, further cause the first processor to:

control the IGVA servo to direct the jet fuel to the inlet guide vane actuator to control a position of the plurality of inlet guide vanes in the first fuel mode and the second fuel mode.

19 . The aircraft propulsion system of claim 16 , wherein the control system further includes a hydrogen controller connected in signal communication with the engine controller and the hydrogen fuel metering system, the hydrogen controller includes a second processing system, the second processing system includes a second processor connected in signal communication with a non-transitory second memory storing second instructions which, when executed by the second processor, cause the second processor to:

control, in the second fuel mode, the hydrogen fuel metering system to direct the hydrogen fuel to the combustor from the switching valve.

20 . The aircraft propulsion system of claim 16 , wherein the first instructions, when executed by the first processor, further cause the first processor to:

operate the fuel system assembly in one of the first fuel mode, the second fuel mode, or a third fuel mode; and

in the third fuel mode, configure the switching valve with both of the first circuit flow path and the second circuit flow path.

Assignments (1)

Continuity (1)

References Cited (11)