Hamilton Sundstrand Corporation

United Technologies Corporation

Collins Engine Nozzles, Inc.

Delavan Inc.

Charles E Reuter

Todd Haugsjaahabink

Jason Allen Ryon

Brandon Phillip Williams

Murtuza Lokhandwalla

Gerald P Dyer

Kevin D Gibbons

Leo J Veilleux, Jr

Lubomir A Ribarov

Richard J Carpenter

Ryan Prescott Susca

Aaron F Rickis

Morgan O'Rorke

Jay W Kokas

Russell P Rourke

Michael Ferrarotti

Steve Doerner

Richard Hector Bostiga

Lev Alexander Prociw

Haralambos Cordatos

Francis P Marocchini

David S Behling

Naison E Mastrocola

Brian G Donnelly

Richard E Versailles

Ethan Flow

Jesse C Peters

Robert H Perkinson

Edward W Goy

William E Rhoden

Adrian L Stoicescu

August M Coretto

Matej Rutar

Gary L Miles

Brandon T Kovach

Satish Shantilal Shah

Zachary Allen Ray Le Duc

Sachin Ramprashad

Joseph Wetch

Joshua J Krecklow

David Wakefield

Scott J Beloncik

Timothy J Gaudet

Angelo Martucci

Robert A Bayles

Leroy R Rateike

John D Cannata

Aaron V Price

Michael D Schelonka

Paul K Seiler

Abiodun Okoya

Sara Dexter

Yukinori Sato

John J Wichowski

Kevin Gibbons

Sara E Pacella

William D Hodge

Christopher J Davis

David L Wakefield

Glen C Lemmers

A system includes an injector having a scheduling valve assembly and a nozzle in fluid communication with the valve assembly. The scheduling valve assembly is configured for regulation of flow from an inlet of the injector to the nozzle. An electromagnetic device is operatively connected to a hydromechanical valve spool of the valve assembly to selectively adjust position of the valve spool in the valve assembly.

Force modification of passive valve spools for control of nozzles

In accordance with at least one aspect of this disclosure, a fuel system can include, a fuel device, a fuel characterization device operatively connected to the fuel device configured to measure performance data of the fuel device before installation into an engine fuel system, and an electronic engine controller operatively connected to the fuel characterization device to receive the measured performance data of the fuel device on start up and calculate a metered mass flow based at least in part on the measured performance data of the fuel device. The electronic engine controller can be configured to control the fuel device to direct, meter, or pump fuel to the engine through the fuel device based on the calculated metered mass flow.

High accuracy fuel system

A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet in response to fuel pressure received at the fuel inlet. Primary and secondary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the primary circuit, adapted and configured to actively control fuel through the primary circuit in response to a control signal.

Variable restriction of a fuel circuit of a fuel nozzle

A fuel injector for a turbine engine includes a fuel scheduling valve configured for regulation of fuel flow from a fuel inlet, in response to fuel pressure received at the fuel inlet. Primary, secondary and auxiliary fuel circuits receive fuel from the scheduling valve, and an electrically-controlled valve is provided in fluid communication with the auxiliary circuit, which electrically-controlled valve is adapted and configured to actively control fuel through the auxiliary circuit in response to a control signal.

Proportional restriction of fuel nozzle with an auxiliary circuit

A system includes an injector having a scheduling valve assembly and a nozzle in fluid communication with the valve assembly. The scheduling valve assembly is configured for regulation of flow from an inlet of the injector to the nozzle. The injector includes two fluid circuits between the inlet of the injector and two respective outlets of the nozzle for staged flow output from the nozzle. A first one of the two fluid circuits is a primary circuit, and a second one of the two fluid circuits is a secondary circuit. A solenoid valve is connected in fluid communication with the scheduling valve assembly, wherein the solenoid valve is configured to adjust position of a hydromechanical valve spool of the valve assembly.

Force modification of passive spool for control of secondary nozzle circuits

Variable restriction of fuel nozzle with an auxiliary circuit

A fuel system can include a total flow line configured to receive a total flow and a primary flow line connected to the total flow line. The primary flow line can be in fluid communication with one or more primary fuel nozzles of a nozzle assembly. The fuel system can include a secondary flow line connected to the total flow line in parallel with the primary flow line, the secondary flow line in fluid communication with a plurality of secondary flow nozzles of the nozzle assembly. The fuel system can include a flow split system configured to control a flow split between a primary flow of the primary flow line and a secondary flow of the secondary flow line.

Fuel systems

A fluid injection system can include a main flow line, a primary flow line connected to the main flow line, and a primary flow valve disposed between the primary flow line and the main flow line and configured to allow injectant flow to the primary flow line from the main flow line in an open primary flow valve state, and to prevent injectant flow to the primary flow line from the main flow line in a closed primary flow valve state. The system can include a secondary flow line connected to the main flow line and a secondary flow valve disposed between the secondary flow line and the main flow line and configured to selectively allow injectant flow to the secondary flow line from the main flow line in an open secondary flow valve state, and to prevent injectant flow to the secondary flow line from the main flow line in a closed secondary flow valve state. The system can include a primary purge branch configured and a secondary purge branch configured to be in fluid communication with a purge gas line to receive a purge gas flow from the purge gas line.

Fluid injection systems having fluid line purging

A system includes a flow inlet conduit and a primary conduit that branches from the flow inlet conduit for delivering flow to a set of primary nozzles. An equalization bypass valve (EBV) connects between the flow inlet conduit and a secondary conduit for delivering flow to a set of secondary nozzles. The EBV is connected to an equalization conduit (EC). A pressure equalization solenoid is connected to the EC to selectively connect a servo supply pressure conduit and/or a return pressure (PDF) conduit into fluid communication with the EC. An EBV rate limiting orifice (RLO) is connected in the PDF conduit. A bypass conduit branches from the PDF conduit on a first side of the EBV RLO and reconnects to the PDF conduit on a second side of the EBV RLO. An orifice bypass valve (OBV) is connected to the bypass conduit and acts to selectively bypass the EBV RLO.

Flow divider valves with transient pressure limiting

Apparatus and associated methods relate to simultaneously pumping and measuring density of an aircraft fuel. The aircraft fuel is pumped by a centrifugal pump having an impeller. A rotational frequency of the impeller is determined while the centrifugal pump is pumping the aircraft fuel. Flow rate of the aircraft fuel through the centrifugal pump is sensed. Pressure of the aircraft fuel is measured at two different points within or across the centrifugal pump or a differential pressure is measured between the two different points while the centrifugal pump is pumping the aircraft fuel. Density of the aircraft fuel is determined based on a head-curve relation characterizing the centrifugal pump. The head-curve relation relates the fuel density to the rotational frequency, the flow rate, and pressures at the two different points or the differential pressure between the two different points.

Simultaneously pumping and measuring density of aircraft fuel

A fuel system including a fuel tank, a first pump fluidly coupled to the fuel tank configured for distributing fuel from the fuel tank throughout the fuel system, and a second pump fluidly coupled to the first pump by a pressure regulating valve and configured for driving fuel to an engine.

Metering pump system

Apparatus and associated methods relate to simultaneously pumping and measuring density of an aircraft fuel. The aircraft fuel is pumped by a centrifugal pump having an impeller. A rotational frequency of the impeller is determined while the centrifugal pump is pumping the aircraft fuel. Flow rate of the aircraft fuel through the centrifugal pump is sensed. Pressure of the aircraft fuel is measured at two different points within or across the centrifugal pump or a differential pressure is measured between the two different points while the centrifugal pump is pumping the aircraft fuel. Density of the aircraft fuel is determined based on an empirically-determined head-curve relation corresponding to the centrifugal pump. The head-curve relation is empirically determined during a characterization phase. The empirically-determined head-curve relation relates the density of the aircraft fuel to the rotational frequency, the flow rate, and the pressures at the two different points.

A method can include receiving, at a control module, first pump characteristic data from a data source associated with a pump, sensing second pump characteristic data from a flow system using one or more sensors, comparing the first pump characteristic data to the second pump characteristic data sensed in the flow system, and determining a health of the pump based on the comparison of the first pump characteristic data to the second pump characteristic data.

Pump health monitoring

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Granby, CT, United States of America

Charles E Reuter