Pratt-whitney Canada Corp

Other

Pratt & Whitney Canada Corp.

Simon John Hartropp

Yusuf Razi Syed

Salvatore Calandra

Mark Iacobacci

Dariusz Chmiel

Frederic Giroux

Adrienne Bajaj

Martin Chabot

Andrew Walz

Roger Lachance

Michael Chun

Nicholas Ngoly

Mark Edward Feeney

Keith John Leslie

Yusuf Razl Syed

Shahin Shokatpour Torab

Keith J Leslie

Adrienne Balaj

A method and system for controlling fuel flow to an aircraft engine during start are provided. Following light-off, an actual value of at least one engine operating parameter is obtained. Based on a difference between the actual value and a target value, a first command is generated to cause fuel flow to be provided to the engine's combustor according to a computed fuel flow rate defined by a fuel schedule of the engine. When the computed fuel flow rate is within a fuel flow rate limit, the first command is output. Otherwise, a limiting factor is applied to the computed fuel flow rate to limit a reduction in fuel flow to the combustor and a limited fuel flow rate is obtained, and a second command is output to cause fuel flow to be provided to the combustor according to the limited fuel flow rate.

System and method for controlling fuel flow to an aircraft engine during start

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 for controlling an aircraft turbofan engine during icing of a temperature probe and devices for carrying out such methods are described. The methods may comprise: using one or more signals representative of temperature received from a heated temperature probe to generate one or more control signals for use in controlling the engine; determining that an icing condition associated with the probe exists; and using data representing one or more substitute signals in place of signals representative of temperature received from the heated temperature probe to generate the one or more control signals for use in controlling the engine.

Aircraft engine control during icing of temperature probe

A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.

Method of monitoring gas turbine engine operation

A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value Indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.

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Sainte-Adèle, Canada

Simon John Hartropp