Collins Engine Nozzles, Inc.

Hamilton Sundstrand Corporation

United Technologies Corporation

Sikorsky Aircraft Corporation

Richard E Versailles

Murtuza Lokhandwalla

Jay W Kokas

Brandon Phillip Williams

Todd Haugsjaahabink

Russell P Rourke

Michael Ferrarotti

Jason Allen Ryon

Charles E Reuter

Mark R Gurvich

Haralambos Cordatos

Bhalchandra R Tulpule

Michael Maynard

Peter L Jalbert

Robert D Klapatch

Kerry R Querns

Michael Ratchford

Thaddeus J Zebrowski

Andrew M Caldecutt

Jesse C Peters

Eric B Holmquist

Rajindar P Kaushik

James A Haesche

Edward R Brown

Richard W Crosset, Iii

Alan F Hunter

Rebecca R Stoner

Kevin Gibbons

Paul L Jalbert

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.

Proportional force modification of passive spool for control of secondary nozzle circuits

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. The auxiliary fuel circuit joins with the secondary fuel circuit for delivery to a fuel nozzle.

Proportional restriction of a secondary circuit of a fuel injector

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 method of forming a degassing system includes the step of forming a bundle of hollow tube membrane members by wrapping hollow tube membrane members to form the bundle at a temperature above 100° F. (38° C.). Another method of forming a degassing system includes the step of the inserting bundle into an outer canister at a temperature above 100° F. (38° C.). A fuel supply system made by these methods is also disclosed.

Membrane bundle for fuel deoxygenation with enhanced durability

A system includes a plurality of injectors each having a respective main circuit configured to be connected in fluid communication with one manifold for supplying fuel to each injector in the plurality of injectors. Each injector in the plurality of injectors includes a respective hydromechanical scheduling valve member configured to regulate fuel flow from a respective inlet to a respective nozzle of each injector of the plurality of injectors as a function of pressure input from the manifold to the respective main circuits. A valve block is connected in fluid communication with a respective auxiliary circuit in each injector in the plurality of injectors. The auxiliary circuit is operatively connected to adjust position of the respective scheduling valve member for actuating force modification of the scheduling valve member. The valve block is configured to control all of the injectors in the plurality of injectors as a block.

Banked force modification for fuel nozzles

A rotor blade measurement system includes a microwave source and a probe. A directional coupler is attached to the source and the probe. A detector is attached to the directional coupler. The probe directs a microwave signal toward a rotor such that during rotation the rotor blade will pass through the path of the microwave signal. As the rotor blade passes the microwave signal is reflected back to the probe. The directional coupler separates the original microwave signal and the reflected signal. The detector then determines the energy level of the reflected signal. As each rotor blade passes the microwave signal it generates a reflected signal that can be analyzed over time. From the length and shape of the waveform of the reflected signal the amount of twisting and flutter in a rotor blade can be determined.

System to measure time of arrival and thickness of rotor blades via microwave energy

An electric motor controller includes controller electronics configured to control an electric motor. The electric motor controller also includes a thermoelectric cooler in thermal communication with the controller electronics. The thermoelectric cooler is configured to receive a braking current associated with braking of the electric motor and provide cooling to the controller electronics.

Electric motor braking using thermoelectric cooling

A gas turbine engine includes a plurality of fuel injectors grouped operatively by stages in a multistage combustor. A fuel system for the gas turbine engine includes at least one fuel metering module per stage of the multistage combustor. Each fuel metering module includes a pump, a flow meter, a pressure sensor, a controller, and a motor, which work together to control fuel output.

Distributed aircraft engine fuel system

A Rotary Air-data System (RADS) periodically samples pressure data from a main rotor blade mounted pitot-scoop integrated with a high accuracy pressure sensor to compute a velocity vector that is resolvable into the aircraft's coordinate system. Mathematical techniques are employed which provide accurate computations of static pressure without a static pressure sensor. The RADS also computes the direction of the relative wind which is particularly useful when the pilot executes hover or low speed, low altitude maneuvers in restricted visibility. The availability of relative wind velocity information coupled with navigation data enhances the ability of rotary aircraft to perform accurate low altitude hover, fire control and other autopilot maneuvers.

Static pressure calculation from dynamic pressure for rotary air-data system and methodology therefor

A high fault coverage, instruction modeled self-test for a signal processor in a user environment is disclosed. The self-test executes a sequence of sub-tests and issues a state transition signal upon the execution of each sub-test. The self-test may be combined with a watchdog activity monitor (WAM) which provides a test-failure signal in the presence of a counted number of state transitions not agreeing with an expected number. An independent measure of time may be provided in the WAM to increase fault coverage by checking the processor's clock. Additionally, redundant processor systems are protected from inadvertent unsevering of a severed processor using a unique unsever arming technique and apparatus.

Watchdog activity monitor (WAM) for use wth high coverage processor

Flight parameter data is real time sampled in successive sample frames and temporarily stored in memory for one or more sample frame intervals, the stored sample values are examined to detect extremes in parameter values with time, periodic ones of the temporarily stored sample frames are permanently stored in memory at fixed frame intervals notwithstanding the presence or absence of extreme values in the sample set data, sampled frames intermediate to the fixed frames are stored only in the presence of extreme sample values amoung selected ones of the sensed flight parameters.

Growing community of inventors

New Hartford, CT, United States of America

Richard E Versailles