Hamilton Sundstrand Corporation

The Stanley Works

Delavan Inc.

United Technologies Corporation

Bruce D Paradise

Leo J Veilleux, Jr

Ryan K Snyder

Eric J Heims

Vito Guardi

Jesse Ian Berube

Kari L Kisselbrack

Michael C O'Brien

Kofi Owusu

Ryan Timothy Matte

A cooling fluid valve having an actuator portion extending outwardly beyond an outer surface of an actuator housing. The cooling fluid valve actuator portion includes a plug force fit into an orifice in a valve housing. The plug blocks flow of cooling fluid from a cooling fluid inlet to a cooling fluid outlet. The cooling fluid outlet is connected to communicate cooling fluid to the component. The plug is formed of a material having a first coefficient of thermal expansion. A portion of the valve housing includes the orifice receiving the plug being formed of a material having a second coefficient of thermal expansion with the second coefficient of thermal expansion being higher than the first coefficient of thermal expansion, such that when the actuator portion of the valve is exposed to heat, the force fit may be eliminated as the valve housing expands at greater rate than the plug.

Fire activated cooling fluid valve

An aircraft engine pressure transducer includes a first pressure transducer channel and a second pressure transducer channel. The first pressure transducer channel is configured to sense a pressure of the aircraft engine over a first pressure range and a first temperature range. The second pressure transducer channel is configured to sense the pressure of the aircraft engine over a second pressure range and a second temperature range, the second pressure range being a subset of the first temperature range, and the second temperature range being a subset of the first temperature range.

Aircraft engine multi-channel pressure transducer

A sensor assembly is provided includes a sensor housing, a first sensor, and a second sensor. The sensor housing operatively connected to a body having a first end and a second end. The first sensor is disposed within the sensor housing. The second sensor is disposed within the sensor housing and is spaced apart from the first sensor. The first sensor and the second sensor face towards a first position feature and a second position feature that is disposed on a movable member that is received within the body.

Movable member assembly having a sensor assembly

A fuel nozzle for a gas turbine engine includes a feed arm including a fuel passage for issuing a spray of fuel. A nozzle assembly is fixed at an upstream end of the feed arm having a fuel inlet in fluid communication with the fuel passage. A fiber optic cable is configured to collect burner radiation for a pyrometer input and has a first end centered within an optical connector of the nozzle assembly and a second end exposed from the spray outlet. The fiber optic cable fitted within the feed arm and nozzle assembly has a permanent bend radius preformed in the fiber optic cable. The bend radius can be equal to or greater than the minimum bend radii for the fiber optic cable to serve as a wave guide in wavelengths for monitoring combustion.

Image conduit for fuel nozzle assemblies

An oil control module for a gas turbine engine is provided comprising a housing on which numerous components of a lubricating system are mounted. The components may include a variable oil reduction valve/shuttle valve, a main oil pressure sensor, a main oil temperature sensor, a main oil filter delta pressure sensor, an oil debris monitor, a lube filter, an active oil damper valve, a cool oil orifice, a knock down orifice and a lube trim orifice. By packing numerous lubricating system components onto or within a housing located adjacent to the gas turbine engine, the oil control module reduces cost and weight and simplifies the maintenance of the lubricating system.

Oil control module

A fluid flow control system includes a fluid inlet, a central chamber, a first nozzle extending from a first side of the central chamber and comprising a first throat, a second nozzle extending from a second side of the central chamber opposite the first side and comprising a second throat, and a flow control shuttle. The flow control shuttle includes a first needle having a first tapered portion positioned within the first throat for controlling flow through the first nozzle and a second needle having a second tapered portion positioned within the second throat for controlling flow through the second nozzle.

Fluid flow control device and method

A meter controller comprises a first input, a second input, and a processor. The processor is configured to receive first and second volumetric flow measurements and to calculate a quasi fluid density value required to cause the first volumetric flow measurement to equal the second volumetric flow measurement. The processor is further configured to subtract a first fluid density value from the quasi fluid density value for calculating a density correction factor. The density correction factor is subtracted from the first fluid density value to calculate a corrected second density value. The corrected second density value is applied to at least one of the first volumetric flow measurement and the second volumetric flow measurement for calculating a mass flow rate measurement.

Fluid mass flow measurement apparatus and method

A cooling system includes a housing having an aperture intersecting a passage that includes first and second passage portions. A plug is arranged in the aperture in an interference fit in a first position at a first temperature condition to block the passage and fluidly separate the first and second passage portions. A biasing element is arranged in the housing and is configured to move the plug from the first position to a second position at a second temperature condition to fluidly connect the first and second passage portions.

Aircraft fuel system cooling flow device

A fuel delivery system for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle, a first fuel nozzle and a second fuel nozzle. The fixed critical flow nozzle and the variable critical flow nozzle are connected to a fuel source in parallel. The fixed critical flow nozzle has an orifice throat with a fixed effective cross-sectional area. The variable critical flow nozzle has an orifice throat with a variable effective cross-sectional area. The first fuel nozzle is connected to the fixed critical flow nozzle for delivering fuel to the gas turbine engine, and the second fuel nozzle is connected to the variable critical flow nozzle for delivering fuel to the gas turbine engine.

Critical flow nozzle for controlling fuel distribution and burner stability

A magnetic flux position sensor includes a primary coil, a secondary coil, and a magnetic flux conductor. The primary coil generates a magnetic flux and the secondary coil senses magnetic flux. The primary and secondary coils are substantially concentric and spaced apart by an annular passage. The annular passage has first and second ends, and the magnetic flux conductor is slidable from the first end to the second end of the annular passage. The magnetic flux transferred from the primary coil to the secondary coil varies as a function of position of the magnetic flux conductor.

Magnetic flux oil level sensor for use in aircraft lubrication systems

A fuel delivery system for use, for example in a gas turbine engine system, includes a fuel metering unit including a main fuel inlet. The fuel metering unit includes fuel pressure and temperature sensors. A cavitating venturi is in fluid communication with the main fuel inlet and includes venturi characteristics such as throat diameter. A fuel nozzle is in fluid communication with the venturi for delivering fuel to the gas turbine engine. A controller is connected to the pressure temperature sensors and is operable to calculate a flow rate of fuel through the nozzle based upon the signals from the pressure and temperature sensors and the fuel and venturi characteristics. A variable cavitating venturi may be arranged within the throat to vary the area and adjust the flow rate through the venturi. The cavitating venturi can also be used at the fuel nozzle to further simplify the fuel delivery system.

Pressure-based fuel metering unit

According to one aspect of the invention, an ice separating apparatus for a gas turbine engine includes a can having a first end and a tangential inlet proximate the first end of the can to receive a fluid flow within the can, wherein the fluid flow includes fuel and ice. The apparatus also includes a first conduit within the can to receive a separated fuel flow proximate a second end of the can, wherein the fluid flow separates ice from fuel to form the separated fuel flow.

Apparatus and method for separating ice from fuel in a gas turbine engine

A cyclone separator includes a wall, a first passage, a second passage, and an oil debris monitor. The wall defines a cyclone cavity. The first passage has a first passage inlet positioned in the cyclone cavity and a first passage outlet at an exterior of the cyclone separator. The second passage has a second passage inlet positioned in the cyclone cavity and a second passage outlet at the first passage. The oil debris monitor detects debris flowing through the second passage.

Combined oil filter and debris monitor

A fuel delivery system uses a volumetric flow sensor and a densiometer to measure a mass flow rate of the fuel. A densiometer may be a coriolis mass flow sensor etched into a small circuit chip. As fuel flows past the densiometer a density of the fuel and characteristic slope as a function of temperature is determined. At least one temperature sensor is also located on the circuit chip to provide accurate temperature of the fuel to correspond to the fuel density reading. Piezoelectric crystals in the volumetric flow sensor generate and receive a sound wave. By analyzing the sound wave signals the volumetric flow rate of fluid through the volumetric flow sensor can be calculated. At least one temperature sensor is also placed on the volumetric flow sensor to correct for any thermal expansion of an inner diameter of the volumetric flow sensor and for final mass flow calculation. The density and temperature information from the densiometer and the volumetric flow and temperature information from the volumetric flow sensor are used to determine the density of the fuel at the volumetric flow sensor. By using the density calculated at the volumetric flow sensor and using the volumetric flow information an accurate mass flow rate of the fuel at the volumetric flow sensor can be calculated.

Growing community of inventors

Avon, CT, United States of America

Bruce D Paradise