US 12,460,577 B2
AFT gear based engine with heat recovery system
Jon Erik Sobanski, Glastonbury, CT (US); Jeffrey T. Morton, Manchester, CT (US); and Andrew E. Breault, Bolton, CT (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by RTX CORPORATION, Farmington, CT (US)
Filed on Mar. 27, 2024, as Appl. No. 18/618,098.
Prior Publication US 2025/0305455 A1, Oct. 2, 2025
Int. Cl. F02C 7/20 (2006.01); F02C 3/10 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01); F16H 57/02 (2012.01); F16H 57/025 (2012.01)
CPC F02C 7/20 (2013.01) [F02C 3/10 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F16H 2057/02039 (2013.01); F16H 57/025 (2013.01)] 16 Claims
OG exemplary drawing
 
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.