United Technologies Corporation

Other

Hamilton Sundstrand Corporation

Raytheon Technologies Corporation

Rtx Corporation

Sikorsky Aircraft Corporation

Thomas Gregory Tillman

Frederick M Schwarz

Louis J Spadaccini

Robin Mihekun Miller

John L Kettle

Robert M Rukus

Nancy Mary Rey

Haralambos Cordatos

Brian Ernest Wake

Foster Philip Lamm

Hayden M Reeve

William T Cousins

He Huang

Alexander Chen

Charles C Coffin

Razvan Virgil Florea

Brian M Welch

Jacek F Gieras

Zaffir A Chaudhry

Wesley K Lord

Jon E Sobanski

James R Dunphy

Zidu Ma

Michael K Sahm

Catalin G Fotache

Neal R Herring

Scott F Kaslusky

Claude G Matalanis

Daniel R Sabatino

Louis Chiappetta, Jr

Luca Bertuccioli

Thomas A Wynosky

Stuart S Ochs

David D Pearson

Constantino V Loffredo

Byung-Young Min

James R Irish

John D Wolter

Jeremiah C Lee

Timothy D DeValve

Blake Almy Moffitt

Arindam Dasgupta

Harry Cordatos

Foster Phillip Lamm

Stephen R Jones

Robert L Bayt

Lou Chiappetta

James A Wilkinson

Peter G Smith

Craig R Bolt

David J Arend

Jonathan K Niemeyer

Kenneth C Dreitlein

Edwin M Worth

Alexander G Chen

An aircraft propulsion system includes a propulsive fan assembly configured for assembly into an aircraft structure, the propulsive fan assembly that includes a fan rotatable about a fan axis, an inlet duct assembly disposed within the aircraft fuselage, the inlet duct assembly that includes an upper inlet duct with an upper inlet opening and a lower inlet duct with a lower inlet opening. The upper inlet duct and the lower inlet duct merge into a common inlet duct forward of the propulsive fan assembly, and an outlet duct is disposed aft of the propulsive fan assembly.

Boundary layer ducted fan propulsion system

A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer.

Embedded engines in hybrid blended wing body

A gas turbine engine propulsion system and method of assembling such is disclosed. The gas turbine engine propulsion system comprises a gas turbine engine that includes a fan flow path. The fan flow path may extend from the fan inlet to the rear exhaust outlet of the bypass flow path. A portion of the fan flow path, proximal to the fan, is non-axisymmetric. The non-axisymmetric portion may be upstream or downstream of the fan.

Non-axisymmetric fan flow path

A fan section for an engine has a fan which rotates about an axis, the fan has an inlet for ingesting ambient air, and a non-axisymmetric nozzle for providing the fan with non-uniform back pressure.

Non-axisymmetric fixed or variable fan nozzle for boundary layer ingestion propulsion

A system for fuel and thermal management of fuel delivered to an engine is disclosed. The system includes a supply of fuel in fluid communication with a fuel inlet of the engine, and an oxygen sensor for measuring dissolved oxygen content in the fuel is in fluid communication with the fuel. The fuel is heated by transferring heat from engine oil in a heat exchanger. The temperature of the fuel is controlled by controlling engine oil flow and airflow through another heat exchanger upstream of the fuel/oil heat exchanger on the oil circulation path with engine oil.

Fuel and thermal management system

A boundary layer ingesting (BLI) blade having a span is provided and includes a root section connectable to a hub, a tip section disposable at a distance from the hub and having a pitch and a body extending in a spanwise dimension from the root section to the tip section. The root section has a local pitch from the root section to about a 70% span location, which is less than the pitch at the tip section, to thereby reduce local angles of attack in a boundary layer region defined in and around the root section.

Boundary layer ingesting blade

A multi-purpose protection system having a housing, an audio output device on the housing, an alarm activator on the housing, an external detector receptacle on the housing, an external audio output receptacle on the housing functioning to connect an external speaker and allows transmission of audio to the external speaker, a power switch on the housing, a power source housed in a battery compartment in the housing, a microprocessor operatively connected to each the alarm activator, the external detector receptacle, the audio output device, the power source, and the power switch, and a memory component operatively connected to the microprocessor having at least one audio file of a recording of a sound to be emitted when the alarm is activated.

Multi-purpose protection system

A fuel deoxygenation system includes an oxygen permeable membrane having a porous membrane and an oleophobic layer. The porous membrane has pores that create a passage extending from a first side to an opposite second side of the porous membrane. The pores have an average pore diameter less than or equal to about 0.06 microns. The oleophobic layer and the porous membrane allow oxygen to cross the oxygen permeable membrane but substantially prevent fuel from crossing the oxygen permeable membrane. A method for removing dissolved oxygen from a fuel includes delivering fuel to an oxygen permeable membrane and removing oxygen from the fuel using the oxygen permeable membrane. A method for modifying a surface of a porous membrane includes depositing an oleophobic treatment agent on the porous membrane, removing solvent and heating the porous membrane to form an oleophobic layer on the porous membrane.

Fuel deoxygenation using surface-modified porous membranes

Vacuum pressure systems are provided. In this regard, a representative vacuum pressure system includes: an inlet; and a linear actuator having a permanent magnet, a coil, an inner ferromagnetic core and an outer ferromagnetic core, the outer ferromagnetic core surrounding at least a portion of each of the permanent magnet, the coil, and the inner ferromagnetic core; the linear actuator being operative to exhibit relative motion between the permanent magnet and the coil responsive to an electrical current being applied to the coil such that the linear actuator forms vacuum pressure and draws fluid into the inlet.

Vacuum pressure systems

A fuel gas removal system includes a venturi for reducing a pressure of the fuel, a bubble separator containing media to assist in the formation of gas bubbles within the fuel to separate the gas bubbles from the fuel, and a port to remove gas bubbles created by the reduction of pressure of the fuel and the bubble separator.

Pressure-based dissolved gas removal system

A fuel system for a gas turbine engine removes oxygen from fuel with a fuel stabilization unit (FSU). The FSU includes a first vacuum stage, where vacuum pressure is created by an ejector and a second vacuum stage where vacuum pressure is created by the ejector and a vacuum pump. The vacuum stream from the first vacuum stage and the second vacuum stage flow through the ejector. The vacuum stream from the second vacuum stage is all that passes through the vacuum pump.

Hybrid vacuum system for fuel deoxygenation

A fuel system for an energy conversion device includes a multiple of non-metallic fuel plates, gaskets, oxygen permeable membranes, porous substrate plates, and vacuum frame plates. Intricate 3-dimension fuel channel structures such as laminar flow impingement elements within the fuel channel dramatically enhance oxygen diffusivity in the FSU. The fuel plates are manufactured from a relatively soft non-metallic material. The non-metallic fuel plates and gasket arrangement provide an effective sealing interface between the fuel plate and oxygen permeable membrane, since compression may be applied to the plates without damaging the relatively delicate oxygen permeable membrane.

Fuel deoxygenation system with non-metallic fuel plate assembly

A fuel stabilization system includes a first deoxygenator and a second deoxygenator both for removing dissolved oxygen from a hydrocarbon fuel. The first and second deoxygenators are arranged in parallel or series to sequentially remove a portion of dissolved oxygen from the hydrocarbon fuel. The arrangement of several deoxygenators for a single fuel stream improves removal of dissolved oxygen and provides for scalability of the fuel system to meet application specific demands. The arrangement also provides for the preservation of partial system functionality in the event of the failure of one of the deoxygenator modules.

Modular fuel stabilization system

A deoxygenator includes a plurality of permeable membranes spirally wound about an exhaust tube for removing dissolved oxygen from a hydrocarbon fuel. The permeable membrane is spirally wrapped about the exhaust tube and defines fuel passages and exhaust passages. The fuel passages and exhaust passages alternate such that each fuel passage is bounded on each adjacent side by an exhaust passage. An oxygen partial pressure differential is generated across the permeable membrane to draw dissolved oxygen from fuel in the fuel passage. The dissolved oxygen is then communicated through openings about the circumference of the exhaust tube and out the deoxygenator.

Spiral wound fuel stabilization unit for fuel de-oxygenation

A gas turbine engine includes a variable area nozzle having a plurality of flaps. The flaps are actuated by a plurality of actuating mechanisms driven by shape memory alloy (SMA) actuators to vary fan exist nozzle area. The SMA actuator has a deformed shape in its martensitic state and a parent shape in its austenitic state. The SMA actuator is heated to transform from martensitic state to austenitic state generating a force output to actuate the flaps. The variable area nozzle also includes a plurality of return mechanisms deforming the SMA actuator when the SMA actuator is in its martensitic state.

Variable area nozzle for gas turbine engines driven by shape memory alloy actuators

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West Hartford, CT, United States of America

Thomas Gregory Tillman