US 12,264,587 B2Granted

Integrated hybrid propulsion system

AssigneeLockheed Martin Corporation

InventorsJoseph Lawrence Simonetti, Mark P. Eisenhauer, Michael Strauss

Life of this patent

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Abstract

A hybrid propulsion system extracts electrical power using a combined heat engine and electrical generator. The propulsion system includes a gas generator, an electrical power generator disposed upstream of the gas generator 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 and power generator unit, an engine enclosure circumferentially surrounding the power generator, and a shroud disposed between the power generator and the engine enclosure. The electrical power generator includes at least one rotating member and a stationary conductive member, wherein the at least one rotating member includes a magnetic portion, and rotation of the at least one rotating member relative to stationary conductive member generates a current transmissible by one or more coupled power output cables.

Claims20

Dependent claims

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.

8 more elements

Dependencies are inferred from the claim text.

Facts

Application: 18/487,771Filed 16 Oct 2023 · continuation
Priority: 21 Jan 2021
Published: US 2024/0060425 A122 Feb 2024
Granted: 1 Apr 2025
Term ends: Not estimatedThe source records don’t support an estimate.

Classification19 codes

F01D 15/10
Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby: adaptations for driving, or combinations…
F01D 5/147
Form or construction: construction, i.e. structural features, e.g. of weight-saving hollow blades
F02C 6/20
Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use: adaptations…
F02C 9/28
Control of fuel supply: regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed

Family

Application17/154,515Parent of this continuation · filed 21 Jan 2021
US 2024/0060425 A1Pre-grant publication · published 22 Feb 2024
US 11,788,428 B2Parent of this continuation
US 2022/0228505 A1Published application
US 12,264,587 B2This patent

From the US filing history. Foreign family members aren’t listed.