United Technologies Corporation

Rtx Corporation

Raytheon Technologies Corporation

Walter A Ledwith

Daniel Bernard Kupratis

Christopher J Hanlon

David Lei Ma

Joseph Brent Staubach

Neil J Terwilliger

Robert H Bush

William F Schneider

Benjamin Bellows

Sean Danby

A propulsion system for an air vehicle includes a fan system that includes a fan that is coupled to a fan drive electric motor for generating a fan discharge airflow, an augmentor where fuel is mixed with a portion of the fan discharge airflow to generate a propulsive flow in a first operating configuration, a bypass duct for directing the fan discharge airflow into the augmentor, a duct blocker for selectively closing the bypass duct to the fan discharge airflow, a liquid oxygen system that is configured to inject liquid oxygen into the augmentor to mix with the fuel when the fan discharge airflow is closed by the duct blocker, the mixture of fuel flow and liquid oxygen generates the propulsive flow in a second operating configuration, and an electric power generation system is coupled to drive the fan drive electric motor.

Hydrogen liquid oxygen combined cycle engine

A powerplant is provided that includes an engine and a water recovery system. The engine includes an engine combustor, an engine turbine, a flowpath and a fluid delivery system. The flowpath extends out of the engine combustor and through the engine turbine. The fluid delivery system includes a hydrogen reservoir and an oxygen reservoir. The hydrogen reservoir is configured to store fluid hydrogen as liquid hydrogen. The oxygen reservoir is configured to store fluid oxygen as liquid oxygen. The fluid delivery system is configured to provide the fluid hydrogen and the fluid oxygen for combustion within the engine combustor to produce combustion products within the flowpath. The water recovery system is configured to extract water from the combustion products. The water recovery system is configured to provide the water to a component of the powerplant.

Hydrogen-oxygen fueled powerplant with water and heat recovery

A powerplant is provided that includes a pre-burner, a combustor, a power turbine, a mechanical load and a propellant system. The combustor is fluidly coupled with and downstream of the pre-burner. The power turbine is fluidly coupled with and downstream of the combustor. The mechanical load is rotatably driven by the power turbine. The propellant system is configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner. The propellant system is also configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner.

Liquid hydrogen-liquid oxygen fueled powerplant

A gas turbine engine includes a core flowpath for flowing a core stream, a second flowpath located radially outward from the core flowpath for flowing a second stream, and an auxiliary flowpath located radially outward from the second flowpath for flowing an auxiliary stream. A heat exchanging device is constructed and arranged to divert a portion of the second stream into the auxiliary flowpath. A turbine exhaust case is constructed and arranged to flow the auxiliary stream into the core flowpath for mixing with the core stream.

Gas turbine engine and an airflow control system

Aspects of the disclosure are directed to an engine of an aircraft. The engine may include a first fan configured to output a first air flow, a second fan configured to receive a first portion of the first air flow and output a second air flow, a core configured to receive a first portion of the second air flow and generate a first stream, and at least one valve configured to assume one of at least three states in association with a generation of a second stream and a third stream based on at least one of the first air flow and the second air flow.

Engine bypass valve

A gas turbine engine includes low and high spools constructed and arranged to rotate about an engine axis. The low spool drives at least one leading stage of a fan section and the high spool drives an aft stage of the fan section. The aft stage may generally include a bypass duct for controllably flowing a bypass stream directly from the leading stage and controllably and/or selectively into an auxiliary flowpath and/or into a second flowpath both located radially outward from a core flowpath.

Gas turbine engine with a multi-spool driven fan

A gas turbine engine includes an auxiliary airflow control system to provide selective communication of a portion of a second stream from a second stream flow path into a third stream flow path, the auxiliary airflow control system in communication with a high temperature flow sourced from the turbine section.

Three-stream gas turbine engine architecture

A one-piece cylindrical drum of a drum rotor has a plurality of enlarged, axially spaced-apart, annular rim portions through which axial blade root slots are machined. The slots are curved along their length about an axis located radially outwardly of the rim. The rotor is preferably made from a plurality of bonded together cylinder-like sections. After bonding the sections together the curved blade root slots are machined using a circular broach.

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Marlborough, CT, United States of America

Walter A Ledwith