The B. F. Goodrich Company

Goodrich Corporation

Hamilton Sundstrand Corporation

Michael John Giamati

Lubomir A Ribarov

Jin Hu

Mark R Gurvich

William A Veronesi

Tommy Maurice Wilson, Jr

David B Sweet

James C Putt

Kevin L Leffel

Terry Lee Sluss

Robert Willard Ray, Jr

Jeffrey J Siesel

Stephen Michael Bortoli

William E Seidel

Jon Shearer

James A Mullen

Charles A Lee

Alan John Fahrner

Kevin Edward Roach

George F Owens

David L Brittingham

Carl Aeschliman

Gregory C Hopkins

Mark Walter Corcoran

Kyle H Deiwert

Geoffrey D Fenelon

Joseph Winesdoerffer

Jason Gesner

James V Twisk

Tom Wilson

A runback system for receiving fluid from a deicing system may comprise a body and a first channel and a second channel defined by the body. A first end of the first channel may be spaced apart from a first end of the second channel. A second end of the first channel and a second end of the second channel may meet and form an outlet at an end of the body.

Pneumatic deicer with runback channels

A method of attaching a pneumatic de-icer to an aircraft wing includes using two pressure sensitive adhesive layers. A first pressure sensitive adhesive layer is attached to a primed aircraft wing, while a second pressure sensitive adhesive layer is attached to the pneumatic de-icer. The two pressure sensitive adhesive layers are attached to each other to create a high energy bond between the pneumatic de-icer and the aircraft wing.

Adhesive lay-up and method for attaching pneumatic de-icers

An air supply line includes an aluminum tube with a one inch diameter, a network of fins located within the aluminum tube to promote heat exchange, and a wall structure containing a heater wrapped around the aluminum tube to allow for temperature control and prevent freezing upstream of valves.

High efficiency air heater

A water supply system includes a water storage tank having a storage tank outlet, the water storage tank configured to store a volume of water at a first pressure. A pressure tank is in fluid communication with the water storage tank and is periodically fillable with water from the water storage tank. An air source is fluidly connected to the pressure tank to pressurize the volume of water in the pressure tank to a second pressure greater than the first pressure. A pressure tank output line is fluidly connected to the pressure tank to output water from the pressure tank.

Pressurized potable water system with conformal shape water storage tank

A ram air turbine movable between a stowed position and a deployed position is provided including a rotatable hub assembly. A hub face is arranged at a first end of the rotatable hub assembly. The hub face has a non-planar configuration such that a limited portion of a surface area of the hub face is arranged within a plane oriented perpendicular to a direction of travel of an airflow upstream from the hub face when the ram air turbine is in a deployed position.

Ice-shedding spinner for ram air turbine

A method of operating a monitored deicing system may comprise attempting, by a health monitor, to pass an electrical current through a signal wire disposed along a boot seam of a pneumatic deicer, evaluating, by the health monitor, a continuity of the signal wire in response to the electrical current, identifying, by the health monitor, that the signal wire lacks continuity in response to the evaluating, and determining, by the health monitor, that the boot seam has broken in response to the identification that the signal wire lacks continuity.

Health monitoring pneumatic deicer

A monitored deicing system is disclosed. The monitored deicing system may have a pneumatic deicer and a signal wire running through the pneumatic deicer. The signal wire may break in response to a failure of the pneumatic deicer, such as a torn boot seam. A health monitor may check the continuity of the signal wire in order to provide an alert upon detecting such a failure.

A drain mast includes a first fairing body defining a first fairing wall and a first drain portion. A second fairing body defines a second fairing wall and a second drain portion. The first and second fairing bodies are joined together as a fairing with the first and second fairing walls as opposed exterior fairing walls, and with the first and second drain portions joined to form a drain passage through the fairing from a drain passage inlet to a drain passage outlet.

Drain masts

One embodiment includes a high capacity water heater assembly. The assembly includes a vessel with an inlet and an outlet, with water delivered to the vessel through the inlet. Also included is a heating element attached to the vessel for heating the water delivered to the vessel, an active mixing valve in fluid connection with the outlet of the vessel, and a water temperature sensor attached to the vessel to communicate data used for powering on and off the heating element.

High capacity water heater

A drainmast which releases water into an airstream traveling in a fore-aft direction includes a water-discharging exit on its underside for communicating with the airstream, a post-exit stage on its underside situated aft of the water-discharging exit, where the water-discharging exit is vertically offset downward from the post-exit stage. The drainmast also includes a fairing having a mounting flange and a mast projecting downward from the mounting flange, the mast having a main body with a window and a door fastened to the main body to close the window.

Drainmast

An aircraft wing () comprising a structural member () forming the wing's leading edge skin, a Kreuger flap () which moves relative to the structural member () between a stowed position and a deployed position, and an electrothermal device () mounted (e.g., internally mounted) to the structural member (). An aft portion () of the structural member () is curved inwardly to form a recess (), and a fore portion () of the flap () fits within the notch () to form a joggle therebetween. The electrothermal device () is a deicing and/or anti-icing device which continuously provides heat to the curved aft portion () of the structural member () during icing conditions so as to prevent deployment-inhibiting ice buildup on the flap ().

Aircraft wing with electrothermal deicing and/or anti-icing device

A heater () for installation on a potable water tank (). The heater () comprises a blanket () including an electrical resistance heating element () and a connection pad () for electrically connecting the heating element () to lead lines () to an aircraft power source (). The water tank () is typically positioned under the cabin floor or other locations on an aircraft which are susceptible to cold temperatures, moisture invasion, and pressure drops/rises caused by changing altitudes. The heater () maintains the tank () at an acceptable temperature range and prevents freezing of the water.

Heater for aircraft potable water tank

An aircraft hot water supply system () comprising a group of water-use stations () each including a hot water line having a heater () which heats water at a heating rate dependent upon power provided thereto. A power manager () allocates different non-zero percentages of heater-dedicated power to different heaters () depending upon conditions at the corresponding water-use stations (). A network () is provided to establish peer-to-peer communication among the heaters' controllers ().

Aircraft hot water supply system

A deicer comprises a skin heating means immediately subjacent an outer skin overlying an apex of a leading edge, and a skin deflection means immediately subjacent the outer skin chordwise aft of the apex. The skin heating means prevents the formation of ice over the apex and the skin deflection means deflects the outer skin to expulse ice formed chordwise aft of the apex. A controller controls the heating and deflection cycles to minimize power consumption of the deicer.

Growing community of inventors

Akron, OH, United States of America

Michael John Giamati