AFT gear based engine with heat recovery system

Patent metadata

Field	Value
Publication number	US-12460577-B2
Application number	US-202418618098-A
Country	US
Kind code	B2
Filing date	Mar 27, 2024
Priority date	Mar 27, 2024
Publication date	Nov 4, 2025
Grant date	Nov 4, 2025

Abstract

A propulsion system for an aircraft includes a propulsor section that includes a fan with a plurality of fan blades that are rotatable about a fan axis, a core engine that is configured to generate a gas flow, a power turbine that is mechanically uncoupled from the core engine and rotatable independent of the core engine, the gas flow from the core engine is expanded through the power turbine to generate shaft power, a support structure where the power turbine is mounted relative the core engine, a fan drive gear system that is driven by the power turbine and at least partially mounted to the support structure, and a power turbine shaft that includes a first coupling to the fan drive gear system and a second coupling to the propulsor section.

First claim

What is claimed is:

1 . A propulsion system for an aircraft comprising:
a propulsor section including a fan with a plurality of fan blades rotatable about a fan axis; a core engine configured to generate a gas flow; a power turbine mechanically uncoupled from the core engine and rotatable independent of the core engine, wherein the gas flow from the core engine is expanded through the power turbine to generate shaft power; a support structure where the power turbine is mounted relative the core engine; a fan drive gear system driven by the power turbine and at least partially mounted to the support structure; and a power turbine shaft including a first coupling to the fan drive gear system and a second coupling to the propulsor section, wherein the support structure includes a fairing section including a plurality of fairings extending between a center portion and an outer portion, wherein each of the plurality of fairings is tangential to an outer periphery of the center portion and the center portion includes an aft portion that extends axially aft from the fairing section and the power turbine is attached to the aft portion.

2 . The propulsion system as recited in claim 1 , wherein an axial length of the power turbine shaft between the first coupling and the second coupling is greater than an axial length between the power turbine and the fan drive gear system.

3 . The propulsion system as recited in claim 1 , wherein the support structure extends axially between a fan exit guide vane and the core engine.

4 . The propulsion system as recited in claim 1 , wherein the fan drive gear system is attached to the aft portion between the power turbine and the fairing section.

5 . The propulsion system as recited in claim 1 , wherein the fan drive gear system comprises a first gearbox mounted in the propulsor section and a second gearbox mounted to the support structure.

6 . The propulsion system as recited in claim 1 , wherein the fan drive gear system comprises a first gearbox and a second gearbox both mounted to the support structure.

7 . The propulsion system as recited in claim 1 , wherein the propulsor section is forward of the power turbine and the core engine is disposed aft of the power turbine.

8 . The propulsion system as recited in claim 1 , wherein the core engine is centered on a core axis that is inclined relative to the fan axis.

9 . The propulsion system as recited in claim 1 , further comprising a nacelle surrounding the core engine and the propulsor section, the nacelle defining a bypass flow path through the nacelle and around the power turbine and the core engine.

10 . The propulsion system as recited in claim 9 , further comprising a heat recovery system at least partially supported by at least one of the support structure and the nacelle.

11 . An aircraft turbine engine assembly comprising:
a fan section including a fan with a plurality of fan blades rotatable about a fan axis; a core engine defining a core flow path where air is compressed in a compressor section, communicated to a combustor section, mixed with fuel, and ignited to generate a gas flow that is expanded through a main turbine section; a power turbine mechanically uncoupled from the core engine and rotatable independent of the core engine, wherein the gas flow from the core engine is expanded through the power turbine to generate shaft power; a support structure where the power turbine is mounted relative the core engine; a fan drive gear system driven by the power turbine and at least partially mounted to the support structure; and a power turbine shaft including a first coupling to the fan drive gear system and a second coupling to the fan, wherein an axial length of the power turbine shaft between the first coupling and the second coupling is greater than an axial length between the power turbine and the fan drive gear system, wherein the support structure includes a fairing section including a plurality of fairings extending between a center portion and an outer portion, wherein each of the plurality of fairings is tangential to an outer periphery of the center portion and the center portion includes an aft portion that extends axially aft from the fairing section and the power turbine is attached to the aft portion.

12 . The aircraft turbine engine assembly as recited in claim 11 , wherein the fan drive gear system comprises a first gearbox mounted in the fan section and a second gearbox mounted to the support structure.

13 . The aircraft turbine engine assembly as recited in claim 11 , wherein the fan drive gear system comprises a first gearbox coupled to a second gearbox with both mounted to the support structure.

14 . The aircraft turbine engine assembly as recited in claim 11 , wherein the core engine is centered on a core axis that is inclined relative to the fan axis.

15 . The aircraft turbine engine assembly as recited in claim 11 , further comprising a nacelle surrounding the core engine and the fan, the nacelle defining a bypass flow path through the nacelle and around the power turbine and the core engine.

16 . A method of operating an aircraft turbine engine assembly comprising:
generating a gas flow with a core engine; expanding the gas flow through a power turbine that is mechanically decoupled from the core engine; driving a gear system with the power turbine; driving a fan with a power turbine shaft driven by the gear system at a speed less than that of the power turbine, wherein the power turbine shaft is of an axial length that is greater than an axial length between the gear system and the power turbine; and supporting the gear system with a support structure including a fairing section including a plurality of fairings extending between a center portion and an outer portion, wherein each of the plurality of fairings is tangential to an outer periphery of the center portion and the center portion includes an aft portion that extends axially aft from the fairing section and the power turbine is attached to the aft portion.

Assignees

• Rtx Corp

Inventors

• Sobanski Jon Erik
• Morton Jeffrey T
• Breault Andrew E

Classifications

• F16H2057/02039

  Gearboxes for particular applications · CPC title

• F16H57/025

  Support of gearboxes, e.g. torque arms, or attachment to other devices · CPC title

• F02K3/06

  with front fan · 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

• F02C3/10 Primary

  with another turbine driving an output shaft but not driving the compressor · CPC title