Pratt-whitney Canada Corp

Honeywell International Inc.

Andrew Walz

Daniel Alecu

Simon John Hartropp

Ritchie Domingo

Steven Strecker

Mehmet Celal Tanju

Roger Lachance

Nicholas Ngoly

Donald A Tegart

Mehmet Tanju

An oil cooling system for an aircraft engine, a bypass valve and an associate method of cooling aircraft engine oil are provided. The oil cooling system includes a heat exchanger having an inlet and an outlet. The inlet is in fluid communication with a first oil conduit to receive a first oil flow from the first oil conduit. The heat exchanger facilitates heat transfer from the first oil flow to another fluid. A flow restrictor defining a constriction is operatively disposed to restrict the first oil flow through the heat exchanger. A second oil conduit receives the first oil flow from the heat exchanger. A bypass oil passage provides fluid communication between the first oil conduit and the second oil conduit to allow a second oil flow received from the first oil conduit to flow to the second oil conduit and bypass the heat exchanger.

Oil cooling system for aircraft engine

A fluid system for a gas turbine engine includes a first supply line, a hydraulic accessory actuable by a fluid, and a second supply line fluidly connected the hydraulic accessory and to the first supply line upstream of the component. An accumulator is fluidly connected to the second supply line upstream of the hydraulic accessory. The accumulator is operable to fill a reservoir with the fluid from the first supply line via the second supply line, and to deliver the fluid to the hydraulic accessory via the second supply line. The first supply line may be a fuel or lubricant main supply line of the engine. A method of actuating a hydraulic accessory is also disclosed.

Gas turbine engine fluid system with accumulator and hydraulic accessory

Methods and systems for controlling a pneumatic starter air valve of a gas turbine engine are described herein. The starter air valve is controlled in a first mode of operation by actuating a first solenoid of the starter air valve with a steady-state input signal. Passage of the steady-state input signal to a second solenoid of the starter air valve is allowed, to actuate the second solenoid and enable pressure regulation of the starter air valve. The starter air valve is controlled in a second mode of operation by actuating the first solenoid with a pulse-width modulation input signal. Passage of the pulse-width modulation input signal to the second solenoid is prevented, to disable the pressure regulation in the second mode of operation.

Method and system for controlling a pneumatic valve

A gas turbine fuel system including a main fuel line providing fuel flow from a fuel tank to a combustor, and at least one pump, including an ejector pump, pumping fuel from the fuel tank to the combustor via a fuel metering unit. The fuel metering unit directs a portion of the fuel into a motive flow line which returns a portion of the fuel to the ejector pump. First and second heat exchangers are disposed in serial flow communication within the main fuel line between the pump and the fuel metering unit. The first heat exchanger is a fuel-to-fuel heat exchanger.

Fuel system for a gas turbine engine

A rack system is disclosed that includes a plurality of electrical modules (), a frame () supporting the plurality of electrical modules () that includes a plurality of frame members () and a plurality of locations () for supportably receiving one of the plurality of electrical modules (), a first frame member () of the plurality of frame members including a first bore () for transporting a liquid along a length of the first frame member () and having a plurality of openings extending through the first frame member () between a sidewall of the bore () and an exterior surface of the frame member (), and a plurality of first connectors () mounted in the plurality of openings, wherein one of the plurality of electrical modules () includes a cooling liquid pathway () and at least one second connector () providing access to the cooling liquid pathway () detachably engaging the first connector () to provide fluid communication between the first bore () and the cooling liquid pathway () when the one of the plurality of electrical modules () is mounted at one of the plurality of locations ().

Electrical module and support therefor with integrated cooling

An electromagnetic device () includes a core () having first and second arms () connected by at least one body (), a first winding () having multiple turns () on the first arm () and a second winding () having multiple turns () on the second arm (), and a heatsink () having a first plurality of U-shaped heatsink elements () each including first and second legs () aligned with the first and second arms () and having a first thickness connected by a base () having a second thickness greater than the first thickness, the base () of each of the plurality of elements () being in contact with the base () of an adjacent heatsink element ().

Growing community of inventors

Toronto, Canada

Andrew Walz