Granted Patent B2

US 12,378,895 · App. 18/075,148 · Granted Aug 5, 2025

Inventors: Viktor Kilchyk (Lancaster, NY); Brent J. Merritt (Southwick, MA)

Assignee: Hamilton Sundstrand Corporation

F01D15/12F25B9/004F25B9/06F25B11/02H02K21/24F04D25/024F04D25/026

Abstract

Claims (62)

1. An air cycle machine comprising:

a turbine section;

a compressor section; and

a powered axial flux magnetic gear system electromechanically coupling the turbine section to the compressor section, the powered axial flux magnetic gear system comprising:

a stator comprising a plurality of stator pole sections and oriented about a magnetic gear system axis such that the plurality of stator pole sections are distributed circumferentially about the magnetic gear system axis;

a first rotor comprising a first plurality of magnets arranged in a first plurality of polarity sections distributed circumferentially about the magnetic gear system axis in circumferential arcs of a first angular extent, the first rotor configured to interact with the stator such that the first rotor rotates at a first rotational speed when the first rotor is exposed to an electrical current;

a second rotor comprising a second plurality of magnets arranged in a second plurality of polarity sections distributed circumferentially about the magnetic gear system axis in circumferential arcs of a second angular extent, the second rotor configured to interact with the stator such that the second rotor rotates at a second rotational speed when the the second rotor is exposed to the electrical current; wherein the first and second rotational speeds depend on the electrical current, the first angular extent, and the second angular extent;

a winding system operable to stabilize a position of the first rotor and a position of the second rotor along the magnetic gear system axis;

a control module capable of supplying the electrical current to at least one of the winding system, the stator, the first rotor, and the second rotor, thereby driving rotation of the first rotor at the first rotational speed, and of the second rotor at the second rotational speed, about the magnetic gear system axis; and

a power source capable of supplying the electrical current to the control module or to at least one of the winding system, the first rotor, the stator, and the second rotor, thereby driving rotation of the first rotor at the first rotational speed, and the second rotor at the second rotational speed, about the magnetic gear system axis.

2. The air cycle machine of claim 1 , wherein the first rotational speed is greater than the second rotational speed.

3. The air cycle machine of claim 1 , wherein the second rotational speed is greater than the first rotational speed.

4. The air cycle machine of claim 1 , wherein the first rotor is operatively connected to a turbine of the air cycle machine and the second rotor is operatively connected to a compressor of the air cycle machine such that rotation of the turbine drives rotation of the first rotor and rotation of the second rotor drives rotation of the compressor.

5. The air cycle machine of claim 1 , further comprising a stabilization system for at least one shaft of the air cycle machine which stabilizes a position of the at least one shaft along a rotational axis of the at least one shaft.

6. The air cycle machine of claim 5 , wherein the stabilization system is a bearing system.

7. An air cycle machine comprising:

a turbine section comprising a plurality of turbine flow elements disposed about a turbine shaft;

a compressor section comprising a plurality of compressor flow elements disposed about a compressor shaft axially aligned with the turbine shaft; and

an electrical gearbox located between and electromechanically coupling the turbine shaft and the compressor shaft, the electrical gearbox comprising:

a gearbox housing; and

a powered axial flux magnetic gear system comprising disposed within the gearbox housing and comprising:

a stator comprising a plurality of stator pole sections oriented about a magnetic gear system axis such that the plurality of stator pole sections are distributed circumferentially about the magnetic gear system axis, and located between a first rotor and second rotor;

the first rotor, comprising a first plurality of magnets arranged in a first plurality of polarity sections distributed circumferentially about the magnetic gear system axis in circumferential arcs of a first angular extent, the first rotor configured to interact with the stator such that the first rotor rotates at a first rotational speed when the first rotor is exposed to an electrical current, wherein the first rotor is mechanically coupled to the turbine shaft;

the second rotor, comprising a second plurality of magnets arranged in a second plurality of polarity sections distributed circumferentially about the magnetic gear system axis in circumferential arcs of a second angular extent, the second rotor configured to interact with the stator such that the second rotor rotates at a second rotational speed when the second rotor is exposed to the electrical current, wherein the second rotor is mechanically coupled to the compressor shaft;

wherein the first and second rotational speeds depend on the electrical current, the first angular extent and the second angular extent;

a winding system operable to stabilize a position of the first rotor and a position of the second rotor along the magnetic gear system axis;

a control module capable of supplying the electrical current to at least one of the winding system, the stator, the first rotor, and the second rotor, thereby driving rotation of the first rotor at the first rotational speed, and of the second rotor at the second rotational speed, about the magnetic gear system axis; and

a power source capable of supplying the electrical current to the control module or at least one of the winding system, the first rotor, the stator, and the second rotor, thereby driving rotation of the first rotor at the first rotational speed, and the second rotor at the second rotational speed, about the magnetic gear system axis.

8. The air cycle machine of claim 7 , wherein the first rotor is connected to the turbine shaft and the second rotor is connected to the compressor shaft such that rotation of the turbine drives rotation of the first rotor through rotation of the turbine shaft and rotation of the second rotor drives rotation of the compressor through rotation of the compressor shaft.

9. The air cycle machine of claim 7 , further comprising:

a primary heat exchanger;

a secondary heat exchanger;

a condenser;

a water collector; and

an air mixer.

10. The air cycle machine of claim 7 , further comprising a stabilization system for at least one of the turbine shaft and the compressor shaft, which stabilizes a position of the at least one of the turbine shaft and the compressor shaft along a rotational axis of the at least one of the turbine shaft and the compressor shaft.

11. The air cycle machine of claim 10 , wherein the stabilization system comprises a bearing system.

12. A method of operating an air cycle machine for an aircraft, the method comprising:

generating an electrical current with a power source;

supplying the electrical current to a powered axial flux magnetic gear system within an electrical gearbox of the air cycle machine, the powered axial flux magnetic gear system comprising a turbine shaft, a first rotor, a stator, a second rotor, and a compressor shaft, wherein the first rotor, the stator, and the second rotor are each oriented about a magnetic gear system axis such that the stator is located between the first rotor and the second rotor along the magnetic gear system axis;

rotating the compressor shaft of the air cycle machine using the powered axial flux magnetic gear system; and

conditioning an airflow for an aircraft cabin of the aircraft using the air cycle, wherein:

supplying the electrical current, with the power source, to the powered axial flux magnetic gear system within the electrical gearbox of the air cycle machine comprises supplying the electrical current to a control module or at least one of a winding system of the powered axial flux magnetic gear system, the stator of the powered axial flux magnetic gear system, the first rotor of the powered axial flux magnetic gear system, and the second rotor of the powered axial flux magnetic gear system, wherein:

the first rotor is configured to interact with the stator of the powered axial flux magnetic gear system such that the first rotor rotates about the magnetic gear system axis at a first rotational speed when the first rotor is exposed to the electrical current, wherein the stator comprises a plurality of stator pole sections and is oriented along the magnetic gear system axis;

the second rotor is configured to interact with the stator such that the second rotor rotates about the magnetic gear system axis at a second rotational speed when the second rotor is exposed to the electrical current; and

the winding system stabilizes a position of the first rotor and a position of the second rotor along the magnetic gear system axis; and

rotating the compressor shaft of the air cycle machine using the powered axial flux magnetic gear system comprises:

rotating the turbine shaft through operation of a turbine of the air cycle machine;

rotating the first rotor about the magnetic gear system axis through rotation of the turbine shaft, wherein the first rotor is mechanically coupled to the turbine shaft;

rotating the second rotor about the magnetic gear system axis; and

rotating the compressor shaft through rotation of the second rotor, wherein the second rotor is mechanically coupled to the compressor shaft.

13. The method of claim 12 , wherein conditioning the airflow for the aircraft cabin of the aircraft using the air cycle machine comprises:

receiving a flow of air which is bleed air from an engine of the aircraft;

directing the flow of air through a primary heat exchanger;

compressing the flow of air with a compressor of the air cycle machine which is connected to the compressor shaft;

directing the flow of air through a turbine of the air cycle machine; and

delivering the flow of air to the aircraft cabin.

14. The method of claim 13 , wherein conditioning the airflow for the aircraft cabin of the aircraft using the air cycle machine further comprises:

directing the flow of air through a secondary heat exchanger;

condensing water vapor in the flow of air using a condenser of the air cycle machine;

collecting water from the flow of air using a water collector of the air cycle machine; and

mixing the flow of air with bleed air from the engine before delivering the flow of air to the aircraft cabin.

Assignments (1)

Continuity (1)

References Cited (23)