US 12,264,587 B2
Integrated hybrid propulsion system
Joseph Lawrence Simonetti, Southbury, CT (US); Mark P. Eisenhauer, Milford, CT (US); and Michael Strauss, New Haven, CT (US)
Assigned to LOCKHEED MARTIN CORPORATION, Bethesda, MD (US)
Filed by Lockheed Martin Corporation, Bethesda, MD (US)
Filed on Oct. 16, 2023, as Appl. No. 18/487,771.
Application 18/487,771 is a continuation of application No. 17/154,515, filed on Jan. 21, 2021, granted, now 11,788,428.
Prior Publication US 2024/0060425 A1, Feb. 22, 2024
Int. Cl. F01D 15/10 (2006.01); H02K 7/18 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01)
CPC F01D 15/10 (2013.01) [H02K 7/1823 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F05D 2220/36 (2013.01); F05D 2260/404 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A hybrid propulsion system comprising:
an electrical power generator section configured to be driven by a power turbine;
an engine enclosure, wherein the engine enclosure is configured to circumferentially surround the power generator section; and
a shroud disposed between the power generator section and the engine enclosure, wherein the shroud comprises non-magnetic material;
wherein the power generator section comprises:
a low pressure compressor comprising at least three axial-flow compressor stage rotating members arranged along an output power shaft and wherein each of the at least three axial-flow compressor stage rotating members includes a magnetic portion; and
a conducting element mounted within the engine enclosure;
wherein rotation of the at least three axial-flow compressor stage rotating members relative to the conducting element generates a current transmissible by one or more coupled power output cables; and
wherein the shroud defines a clearance between the at least three rotating members and the engine enclosure, and wherein the shroud is disposed between the conducting element and the at least three axial-flow compressor stage rotating members.