Carrier Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Hamilton Sundstrand Corporation

Scott A Liljenberg

Dennis M Moura

Duane C Mccormick

William M Proscia

William J Roy

Theodore R Strickland

Justin M Locke

Alan Matthew Finn

Anthony C Jones

Ziyou Xiong

Thomas J Martin

Jeffrey Mark Cohen

James C Napier

Catalin G Fotache

Jeffery A Lovett

Meredith Bright Colket, Iii

Louis Chiappetta, Jr

David R Polak

Derk S Philippona

Robert Hans Schlinker

Andrzej Banaszuk

Ray-Sing Lin

Serge L Shishkin

Meredith B Colket

Michael R Carey

Christopher T Chipman

Duane McCormick

Shiling Zhang

William Proscia

A gas turbine engine combustor section extends axially from a pre-diffuser at a forward end to an aft end relative to an engine axis. The gas turbine engine combustor section includes a combustor liner defining a combustion chamber and a combustor dome situated at a forward end of the combustor liner and affixed thereto. The gas turbine engine combustor section further includes an electrostatic particulate matter collector. The electrostatic particulate matter collector includes a first charged flow guide having an axially forward-most extent aligned with the pre-diffuser and widens radially with respect to the engine axis from the forward-most extent to the combustor dome. The electrostatic particulate matter collector further includes a fuel nozzle extending through the first charged flow guide into the combustor dome. The electrostatic particulate matter collector also includes a power supply electrically coupled to positively charge the first charged flow guide.

Electrostatic flow guide dirt collector

A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.

Reducing noise from a combustor of a gas turbine engine

A method for thermally-sensitive coating analysis of a component includes imaging the coated, exposed component over a range of distinct frequencies as selected by a narrowband variable filter; estimating parameters of non-uniformity correction (NUC) for every pixel at every wavelength; constructing a 2D temperature map on a pixel-by-pixel basis using the non-uniformity correction; and mapping the 2D temperature map to a 3D computer aided design (CAD) model.

Automated analysis of thermally-sensitive coating and method therefor

A gas burner for low NOgas furnaces is disclosed with improved flame carryover for igniting one or more adjacent burners. The burner includes a burner tube that receives a mixture of fuel and air. The burner tube is coupled to an outlet. The outlet includes a primary outlet opening which is in communication with at least one transverse slot for communicating a flame to at least one adjacent burner. The primary outlet opening may be elliptical and the outlet further may also include a concave outer face through which the primary outlet opening extends. The at least one slot may include a pair of oppositely directed transverse slots extending outward from the primary outlet opening along a semi-minor axis of the primary outlet opening.

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An improved induced draft gas burner assembly for low NOresidential and light commercial gas furnaces is disclosed. The improved burner includes an upstream assembly coupled to a fuel inlet and an air inlet. The air inlet is coupled to a neck extending between the air inlet and the outlet of the neck, both of which may be disposed within an optional chamber. If used, such a chamber also includes an outlet coupled to a burner. In practice, the chamber and neck behave as a Helmholtz resonator that can be tuned to provide an upstream impedance Zthat exceeds the downstream impedance Zof the components downstream of the burner assembly.

A burner for use with an induced draft furnace and which satisfies reduced nitrous oxide (NO) emission standards is disclosed. The burner may employ a mechanical swirler that introduces a rotational vector to the emitted air and fuel mixed by the burner. By introducing the rotational vector, the resulting flame is more stable and sustainable even with the relatively low air flow afforded by an induced system. Such flame stability can be enhanced by positioning the burner directly within an inlet to a heat exchanger and manufacturing the inlet with reception surfaces that form a frusto-conically shaped flame expansion zone. In doing so, a secondary source of air is avoided and NOemissions are reduced.

Induced-draft low swirl burner for low NOx emissions

An ignition system for a multi-burner heat exchanger assembly, a furnace, and a method using same are disclosed. The assembly may include a plurality of adjacent heat exchanger tubes, with a burner associated with each tube. All the burners may be lit with a single igniter and no source of secondary air. To do so, each of the burners may be provided so as to generate a swirling exit flow of combustion gases. One or more carryover tubes may also be connected between adjacent pairs of heat exchanger tubes or adjacent pairs of burners. The swirling flow generated by the burners causes hot combustion gases to move through the carryover tubes to thus carry the flame from one burner to the next. Not only can a single igniter be used, but a single flame sensor as well, while at the same time reducing nitrogen oxide emissions.

Racetrack carryover design for multi-burner ignition in induced draft heating system

A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies.

System for reducing compressor noise

An augmentor system minimizes acoustic pressure fluctuations on the heat release process within the augmentor by staggering the vanes therein. The alternating axial vane stagger pattern arranges the downstream set of vanes as baffles which prevent the propagation of tangential acoustic waves between the vanes to protect the upstream set of vanes from the effects of transverse acoustic velocity fluctuations which minimizes screech without substantially affecting augmentor performance.

Augmentor with axially displaced vane system

Growing community of inventors

Wethersfield, CT, United States of America

Scott A Liljenberg