Ge Aviation Systems Limited

Mra Systems, Inc.

Kelly Aerospace Thermal Systems, LLC

General Electric Company

Julian Alexander Opificius

David Patrick Calder

David Cenit Flosdorf

Stephen Craig Carlson

Erik Thomas Pederson

Kevin P Hallisey

Dominique Patrick Sautron

Lance F Miller

Jerry Dean Hielkema

Dale L Habbley

Benjamin Samuels, Jr

Rachael Huffman

Derek Dipietro

Bryan E Schwichtenberg

Paul Mitkusevitch

Benjamin Samuels

Dale Lee Habbley

Tyler Permenter

Jr Benjamin Samuel

Dave Cenit Flosdorf

A valve assembly including a valve body with an inlet port and an outlet port, a flow passage and a valve element disposed within the flow passage, an actuator and a lockout mechanism configured to maintain the position of the valve assembly in an opened position or a closed position. The lockout mechanism can include at least one screw.

Valve assembly and lockout mechanism

A method and apparatus for predicting conditions favorable for icing, includes sensing a value indicative of a thermal cycling period, comparing, the sensed thermal cycling period with a threshold value, determining, if the sensed thermal cycling period satisfies the threshold value, and indicating, by the controller module, that conditions favorable for icing are present when the sensed thermal cycling period satisfies the threshold value.

Method and apparatus for predicting conditions favorable for icing

An aircraft includes an environmental control system having a bleed air inlet, a gas turbine engine having a low pressure bleed air supply and a high pressure bleed air supply, and a turbo air cycle machine. The turbo air cycle machine includes a compressor fluidly coupled to the low pressure bleed air supply, as well as a turbine fluidly coupled to at least one of the low pressure bleed air supply or the high pressure bleed air supply.

Aircraft with environmental control system

A method of determining ice accretion on a surface of an aircraft can include supplying a known power to a heating element formed in a patch, wherein the patch includes a temperature sensor. A controller module can compare a sensed thermal signature with a threshold signature and determine the presence of ice accretion on the aircraft.

Method and apparatus for detecting ice accretion

An apparatus and method for deicing a surface upon which ice accumulates, on for example an aircraft wing. The apparatus and method for the deicing module include an actuating component, a casing, and a movable member. The movable member breaks ice that has accumulated on a surface of the wing.

Deicing module for an aircraft and method for deicing

A system and method for ice protection of a component, wherein the system is adapted to be adhesively bonded to a surface of the component. The system includes a heating element layer, at least one thermally conductive adhesive layer that adhesively bonds a first side of the heating element layer to the component, an insulation layer, at least one thermally insulating adhesive layer that adhesively bonds a second side of the heating element to the insulation layer, an electrical bus bar adapted to provide a connection between a power supply and the heating element layer, and at least one temperature sensor.

Aircraft ice protection system and method

A circuit and method of applying a three phase power source to a load such that each phase is applied to the load in a manner, such as a predetermined sequence, so as to reduce the electromagnetic interference (EMI) and heat generated in the switching devices during the application and removal of each phase to the load.

Circuit and method for applying a three phase power source to a three phase load

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Elk River, MN, United States of America

Julian Alexander Opificius