Goodrich Pump & Engine Control Systems, Inc.

Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Pratt-whitney Canada Corp

Triumph Engine Control Systems, LLC

Mihir Desai

Xingen Dong

Govindaraj Kalyanasamy

Jeffrey S Mattice

Paul J Paluszewski

Tomasz J Stanecki

Andrew Lee

Mark Collett

Martin Kenneth Yates

Eric E Wilson

John Gebhard

Cristina Crainic

Josh Gear

Joshua Gear

A method of mitigating uncommanded or uncontrollable high thrust in a gas turbine engine is provided. The method may comprise pumping fuel to a combustor from a fuel tank, controlling a flow rate of the fuel to the combustor with a metering valve, spilling a portion of the fuel pumped by the pump with a primary spill valve, controlling a pressure of the fuel flowing to the combustor via a pressure valve, detecting a pressure differential across the pressure valve with a pressure transducer, determining the flow rate of the fuel based on the detected pressure differential and the positional feedback of the pressure valve opening, comparing the determined flow rate with a demand flow rate, and opening a secondary spill valve when the determined flow rate exceeds the demand flow rate.

Uncommanded or uncontrollable high thrust detection and mitigation

A method of monitoring a fuel system in a gas turbine engine. The method may comprise pumping fuel to a combustor from a fuel tank with a pump. The method may comprise controlling a flow of the fuel to the combustor with a metering valve disposed downstream of the pump and closing a spill valve disposed downstream of the pump, wherein the spill valve is closed in fixed increments and closing the spill valve increases a pressure in the fuel system. The method may comprise opening a pressure valve in response to the pressure in the fuel system being equal to or greater than a predetermined value, and capturing a degree of closing of the spill valve when the pressure valve opens.

Fuel unit health monitoring system

A lubrication system comprises a lubricant feed tank, a lubricant feed pump, one or more lubricant nozzles, a scavenge pump drive motor, and one or more scavenge pumps. The lubricant feed pump takes suction from the lubricant feed tank and pumps a lubricant feed as lubricant jets exiting the one or more lubricant nozzles. The lubricant feed pump has a rotating feed pump shaft coupled to a power source. The scavenge pump drive motor drives a rotating scavenge pump shaft that is coupled to the one or more scavenge pumps. The scavenge pumps return lubricant to the lubricant feed tank. The feed pump shaft and scavenge pump shaft rotate independently of each other.

Lubrication and scavenge system

A fuel pumping unit has a low pressure centrifugal pump and a high pressure centrifugal pump. In use, the low pressure pump supplies fuel at a boosted pressure to the high pressure pump for onward supply to a fuel metering unit. The pumping unit further has a drive input which drives the low and high pressure pumps. A gear arrangement is operatively located between the drive input and the low and high pressure pumps such that the low and high pressure pumps are driven at different speeds by the drive input.

Fuel pumping unit

A split discharge vane pump is disclosed having a pump body that includes an interior pumping chamber having a central axis and defining a continuous peripheral cam surface, the cam surface including four quadrantal cam segments, wherein diametrically opposed cam segments have identical cam profiles, and each cam segment defines an inlet arc, a discharge arc and two seal arcs. A rotor is mounted for axial rotation within the pumping chamber and a plurality of circumferentially spaced apart radially extending vanes are mounted for radial movement within the rotor, wherein the plurality of vanes define an equal number of circumferentially spaced apart buckets which extend between the rotor and the cam surface of the pumping chamber for carrying pressurized fluid.

Split discharge vane pump and fluid metering system therefor

A two-stage system for delivering fuel to a gas turbine including a first stage variable pump for serving as a primary source of fuel, a second stage fixed pump for selectively supplementing the variable pump, a bypass valve connected to the fixed pump for loading and unloading the fixed pump and a regulator valve assembly connected to the variable pump and the bypass valve for controlling operation of the variable pump and the bypass valve. Preferably, the two-stage system also includes a control valve connected to the regulator valve assembly for setting a pressure differential across the regulator valve assembly and, thereby, loading and unloading the fixed pump.

High efficiency 2-stage fuel pump and control scheme for gas turbines

An adaptive aero-thermodynamic engine model is disclosed which incorporates a plurality of model engine operating parameters, a plurality of nominal component efficiencies and corresponding efficiency modifier functions. The engine model is adapted by measuring a plurality of engine operating parameters corresponding to the plurality of model engine operating parameters during steady state operation of the engine over a plurality of data points, matching each of the model engine operating parameters to respective measured engine operating parameters by iteratively adapting each of the nominal component efficiencies using the corresponding efficiency modifier functions, estimating actual component efficiencies based upon the adapted nominal component efficiencies, and inputting the estimated actual component efficiencies into the engine model.

Adaptive aero-thermodynamic engine model

A power turbine speed control system for a helicopter is disclosed which includes components for generating a power turbine speed signal based upon a demanded rotor speed, a high-order filter for filtering the power turbine speed signal by effectuating a rapid attenuation of main and tail rotor torsional frequencies in the power turbine speed signal without compromising phase at low frequencies, and a governor for providing isochronous power turbine speed and rotor speed control based upon the filtered power turbine speed signal.

Growing community of inventors

Yorba Linda, CA, United States of America

Mihir Desai