US 11,788,428 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 Jan. 21, 2021, as Appl. No. 17/154,515.
Prior Publication US 2022/0228505 A1, Jul. 21, 2022
Int. Cl. F01D 15/10 (2006.01); H02K 7/18 (2006.01); F02K 3/06 (2006.01); F02C 7/36 (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)] 18 Claims
OG exemplary drawing
 
1. A hybrid propulsion system comprising:
a gas generator section comprising a high-pressure compressor;
an electrical power generator section disposed upstream of the gas generator section and configured to be driven by a power turbine;
an output power shaft mated to the power turbine and extending through a central axis of the gas generator section and the power generator section;
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 the 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;
wherein the output power shaft is disposed concentrically within a turbine shaft located in the gas generator section, the output power shaft being structured to extend entirely through the gas generator section and the power generator section;
wherein the shroud is configured to reduce 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.