Aircraft propulsion system engine with multiple independent rotating structures

Patent metadata

Field	Value
Publication number	US-12428986-B2
Application number	US-202318217830-A
Country	US
Kind code	B2
Filing date	Jul 3, 2023
Priority date	Jul 3, 2023
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

A turbine engine is provided that includes a propulsor rotor and an engine core. The propulsor rotor is rotatable about a propulsor axis. The engine core is configured to power operation of the propulsor rotor. The engine core includes a core compressor section, a core combustor section, a core turbine section, a first rotating structure and a second rotating structure. The first rotating structure includes a first compressor rotor arranged within the core compressor section. The first rotating structure is rotatable about a first structure axis which is offset from the propulsor rotor axis. The second rotating structure includes a second compressor rotor arranged within the core compressor section. The second rotating structure is rotatable about a second structure axis which is offset from the propulsor rotor axis and the first structure axis.

First claim

What is claimed is:

1. A turbine engine, comprising:
a first rotating assembly including a propulsor rotor and a power turbine rotor configured to drive rotation of the propulsor rotor;
an engine core, the engine core comprising a first core rotating structure including a first compressor rotor, a second core rotating structure including a second compressor rotor and a turbine rotor, a combustor, and a flowpath extending sequentially across the first compressor rotor, the second compressor rotor, the combustor and the turbine rotor;
an electric machine configured to drive rotation of the first core rotating structure, the electric machine disposed axially between the first compressor rotor and the second core rotating structure,
an accessory gearbox coupling a second electric machine to the first rotating assembly; and
a geartrain coupling the propulsor rotor to the power turbine rotor;
wherein the first rotating assembly does not extend axially through the first core rotating structure or the second core rotating structure;
wherein the first core rotating structure does not extend axially through the second core rotating structure, and the first core rotating structure is mechanically independent of the second core rotating structure;
wherein the geartrain is disposed axially between and spaced from the accessory gearbox and the propulsor rotor;
wherein the accessory gearbox is axially forward of the power turbine rotor; and
wherein the propulsor rotor is axially between a forward upstream end of the turbine engine and the engine core.

2. The turbine engine of claim 1 , wherein
the first rotating assembly is rotatable about a propulsor axis;
the first core rotating structure is rotatable about a first structure axis;
the second core rotating structure is rotatable about a second structure axis; and
at least one of
the propulsor axis is offset from at least one of the first structure axis or the second structure axis; or
the first structure axis is offset from the second structure axis.

3. The turbine engine of claim 1 , wherein the first core rotating structure is configured to be solely rotatably driven by the electric machine.

4. The turbine engine of claim 1 , wherein the propulsor rotor is a ducted propulsor rotor.

5. The turbine engine of claim 1 , wherein the turbine engine comprises a turbofan engine, and the propulsor rotor comprises a fan rotor.

6. The turbine engine of claim 1 , wherein
the first rotating assembly is rotatable about a propulsor axis; and
the first core rotating structure is rotatable about a first structure axis that is parallel with the propulsor axis.

7. The turbine engine of claim 1 , wherein
the first rotating assembly is rotatable about a propulsor axis; and
the second core rotating structure is rotatable about a second structure axis that is parallel with the propulsor axis.

8. The turbine engine of claim 1 , wherein
the first core rotating structure is rotatable about a first structure axis; and
the second core rotating structure is rotatable about a second structure axis that is parallel with the first structure axis.

9. The turbine engine of claim 1 , wherein the electric machine is a first electric machine, and the turbine engine further comprises a second electric machine coupled to the first rotating assembly.

10. The turbine engine of claim 9 , wherein the second electric machine is disposed axially between the propulsor rotor and the power turbine rotor.

11. The turbine engine of claim 9 , wherein the second electric machine is an electric generator.

12. The turbine engine of claim 9 , further comprising a gearbox coupling the second electric machine to the first rotating assembly.

13. The turbine engine of claim 12 , further comprising a geartrain coupling the propulsor rotor to the power turbine rotor.

14. The turbine engine of claim 13 , wherein the geartrain is disposed axially between and spaced from the gearbox and the propulsor rotor.

15. A turbine engine, comprising:
a first rotating assembly including a ducted fan rotor and a power turbine rotor configured to drive rotation of the ducted fan rotor;
a first core rotating structure including a first compressor rotor;
a second core rotating structure including a second compressor rotor and a turbine rotor;
a combustor;
a flowpath extending sequentially across the first compressor rotor, the second compressor rotor, the combustor and the turbine rotor;
an accessory gearbox operatively coupled to the first rotating assembly; and
a geartrain coupling the ducted fan rotor to the power turbine rotor;
wherein the first rotating assembly does not extend axially through the first core rotating structure or the second core rotating structure;
wherein the first core rotating structure does not extend axially through the second core rotating structure, and the first core rotating structure is configured to rotate independent of the second core rotating structure,
wherein the geartrain is disposed axially between and spaced from the accessory gearbox and the ducted fan rotor;
wherein the accessory gearbox is axially forward of the power turbine rotor; and
wherein the ducted fan rotor is axially between a forward upstream end of the turbine engine and the first core rotating structure.

Assignees

• Raytheon Tech Corp
• Rtx Corp

Inventors

• Sobanski Jon E
• Evans Brandon M
• Evans Simon W

Classifications

• F02K3/06

  with front fan · CPC title

• B64D27/026

  comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33) · CPC title

• F02C7/36

  Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) · CPC title

• F05D2220/76

  an electrical generator · CPC title

• F02C3/13

  having variable working fluid interconnections between turbines or compressors or stages of different rotors {(controlling flow ratio between different flows of multi-flow jet-propulsion plant, e.g. ducted fan F02K3/075)} · CPC title