Rosemount Aerospace Limited

Rosemount Inc.

Delavan Inc.

Rosemont Inc.

Douglas C Myhre

David Y Pui

William Kunik

John A Norlien

Mark Buenz

Wade Williams

Richard J O'Brien

Jerry Lee Goeke

Michael D Cornwell

David R Tushie

Thomas F Lenagh

Chuen-Jinn Tsai

Larry V Miller

Joachim H Scholz

Mark G Severtson

Steven M Lenertz

Christopher J Simones

O Harald Eriksen

Joseph R Michel

Odd Harald S Eriksen

Timothy Aadland

William G Kunik

Harald Steen Eriksen Odd

Mark J Buenz

Joseph R Miichel

Wade W Williams

A probe assembly for measuring the concentration of exhaust's emissions in a turbine engine. The probe assembly including a first probe member configured and operable to passively generate a beam of light wherein the wavelength of the beam of light is contingent upon the configuration of the first probe member. A second probe member positioned in the probe assembly to receive the beam of light generated by the first probe member, the second probe member configured and operable to attenuate the light passively generated from the first probe member contingent upon the gaseous species present in the exhaust emissions of the turbine engine.

Passive optical gaseous emissions sensor

A method of stabilizing combustion in a gas turbine engine includes the steps of observing a combustor flame from a location upstream from said flame to detect spectral characteristics indicative of a condition affecting combustion stability, and tuning the engine to stabilize combustion based upon an indicated condition affecting combustion stability.

Apparatus, system and method for observing combustion conditions in a gas turbine engine

A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with the fuel nozzle for observing combustor flame characteristics. The optical sensor array includes a plurality of sapphire rods positioned to be close enough to the combustor flame to oxidize soot deposits thereon.

Method for observing combustion conditions in a gas turbine engine

A seal assembly for an optical sensor employed in a high temperature environment is disclosed which includes an elongated metal guide tube having a distal end portion defining an open distal end and an inner rear wall, a sapphire window disposed within the distal end portion of the metal guide tube, the sapphire window having a rear end surface abutting the inner rear wall of the distal end portion of the metal guide tube, and a platinum mounting sleeve for securing the sapphire window to the metal guide tube, the platinum mounting sleeve having one portion joined to the metal guide tube and another portion joined to the sapphire window.

High temperature seal assembly for optical sensor

A fuel injector for a gas turbine combustor is disclosed which includes a fuel nozzle for issuing fuel into the combustor for combustion, at least one photodetector responsive to flame radiation indicative of an OH chemiluminescence peak, and at least one photodiode responsive to flame radiation indicative of a CH chemiluminescence peak.

Apparatus for observing combustion conditions in a gas turbine engine

A system is disclosed for actively controlling combustion in a gas turbine engine, which includes a fuel injector for issuing fuel into a combustion chamber of the gas turbine engine. The fuel injector has a dynamic pressure sensor for measuring acoustic pressure within the combustion chamber and a flame sensor for observing flame characteristics within the combustion chamber. The system further includes a high speed valve assembly for controlling flow of fuel to the injector and an electronic controller associated with the fuel injector for commanding the valve assembly to deliver fuel to the fuel injector at a commanded flow rate, based upon input from the sensors in the fuel injector.

Active combustion control system for gas turbine engines

The invention provides a temperature measurement system including a temperature sensor and means for biasing the temperature sensor in the direction of a thermal energy source in response to receiving thermal energy from the source. The invention also provides a continuous casting system including at least one temperature sensor disposed in the secondary cooling region and means for biasing the temperature sensor in the direction of the strand of metal in response to receiving thermal energy from the strand of metal.

Temperature measurement system

A wireless tire pressure sensing system for an aircraft comprises: dual resonant circuits mounted to a wheel of the aircraft, each resonant circuit comprising: a variable capacitance sensor and a wire loop of a predetermined inductance coupled thereto, one capacitance sensor for monitoring the pressure of a tire mounted to the wheel, and the other capacitance sensor operative as a reference to the one capacitance sensor; an interrogating circuit magnetically coupleable to the dual resonant circuits and operative to induce magnetically a variable frequency current in the dual resonant circuits, the one resonant circuit responding to the induced current with an E-field signal at a first resonant frequency commensurate with the capacitance of the one sensor, and the other resonant circuit responding to the induced current with an E-field signal at a second resonant frequency commensurate with the capacitance of the other sensor; a receiving circuit E-field coupleable to the dual resonant circuits and operative to receive the E-field signals at the first and second resonant frequencies and to generate first and second signals representative thereof, and a processing circuit coupled to the receiving circuit for processing the first and second signals to generate a compensated pressure reading of the tire. The pressure sensing system may be modified to provide and/or include wheel speed sensing.

Wireless tire pressure and/or wheel speed sensing system for aircraft

A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is located within the fuel nozzle for observing combustion conditions within the combustor.

A wireless tire pressure sensing system for an aircraft comprises: dual resonant circuits mounted to a wheel of the aircraft, each resonant circuit comprising: a variable capacitance sensor and a wire loop of a predetermined inductance coupled thereto, one capacitance sensor for monitoring the pressure of a tire mounted to the wheel, and the other capacitance sensor operative as a reference to the one capacitance sensor; an interrogating circuit magnetically coupleable to the dual resonant circuits and operative to induce magnetically a variable frequency current in the dual resonant circuits, the one resonant circuit responding to the induced current with an E-field signal at a first resonant frequency commensurate with the capacitance of the one sensor, and the other resonant circuit responding to the induced current with an E-field signal at a second resonant frequency commensurate with the capacitance of the other sensor; a receiving circuit E-field coupleable to the dual resonant circuits and operative to receive the E-field signals at the first and second resonant frequencies and to generate first and second signals representative thereof; and a processing circuit coupled to the receiving circuit for processing the first and second signals to generate a compensated pressure reading of the tire. The pressure sensing system may be modified to provide and/or include wheel speed sensing.

Wireless tire pressure sensing system

A non-intrusive sensor for measuring mass flow of a medium flowing through a tube comprises: a probe having a predetermined length disposed along an external wall of the tube; a heater for heating the probe at a first point along the length thereof; a first temperature measuring device disposed at the first point for measuring a temperature of the probe and for generating a first signal Trepresentative thereof; a second temperature measuring device disposed at a second point along the length of the probe for measuring another temperature of the probe and for generating a second signal Trepresentative thereof; a third temperature measuring device disposed along the external wall of the tube a distance away from the probe for measuring an ambient temperature and for generating a signal Trepresentative thereof; and circuitry coupled to the first, second and third temperature measuring devices for generating a mass flow signal based on a ratio of temperature differential signals (T&#x2212;T)/(T&#x2212;T). A counterpart method is also disclosed.

Sensor and method of measuring mass flow non-intrusively

A mass flow sensor is disclosed comprising: a heated probe having a predetermined length for disposition in the path of mass flow; at least two first temperature measuring devices disposed at different points along the probe length for measuring temperatures of the heated probe at such points in the presence of the mass flow; a second temperature measuring device for disposition in the path of mass flow for measuring the temperature of the mass flow; and a processing unit for determining mass flow as a function of the temperature measurements of the first and second temperature measuring devices. A method of measuring mass flow is also disclosed comprising the steps of: disposing a probe of a predetermined length in the path of mass flow; heating the probe; measuring the heated probe temperature at at least two different points along its length in the presence of the mass flow; measuring the temperature of the mass flow; and determining mass flow as a function of the temperature measurements of the heated probe and mass flow. In one embodiment, the mass flow sensor includes at least three temperature measuring devices disposed in proximity to at least one probe for generating signals representative of the temperature of the heated probe along its length and the temperature of the mass flow. The at three temperature measuring devices are coupled together to generate at least two signals representative of temperature differentials in the vicinity of the at least one probe, and the processing unit processes at least one of the temperature differential signals to generate a signal representative of mass flow.

Method and sensor for mass flow measurement using probe heat conduction

A detector for use in a combustion system includes a probe having a tip adapted for placement through a singular aperture in the mixing area of a combustion system. First and second channels are derived from the probe output and are used to detect a flashback or flameout condition.

Apparatus for detecting flame conditions in combustion systems

A purging air flow system that causes air to pass over a pyrometer lens or window to keep it clean and free from particulate contaminants has an annular, continuous slot for air inlet around the periphery of the lens to permit flow of air across the lens without any obstructions in the path of flow inwardly from the outer edge of the lens. An asymmetric flow pattern is established across the lens surface, either by having a differential size slot at different peripheral portions of the peripheral edge of the lens or window, or by providing a radial swirl about the axis of the window so that when the air goes through the slot, the tangential velocity creates a moving asymmetric flow pattern on the window surface.

Growing community of inventors

Eden Prairie, MN, United States of America

Douglas C Myhre