United Technologies Corporation

Raytheon Technologies Corporation

Other

Utc Fire and Security Corporation

Jeffrey Mark Cohen

Hongcheng Wang

James B Hoke

Matthew Robert Pearson

Zhongtao Dai

Lance L Smith

Catalin G Fotache

Alexander Chen

Donald J Hautman

Andrzej Banaszuk

Gregory S Hagen

Bryan Robert Siewert

William M Proscia

Jeffery A Lovett

May L Corn

Meredith Bright Colket, Iii

Kevin E Green

Gonzalo J Rey

Scott A Liljenberg

Kristin Kopp-Vaughan

Derk S Philippona

Prashant G Mehta

Clas A Jacobson

Michael R Carey

Nancy Mary Rey

Mike Lindsay

Raymond Mattfeld

William Proscia

Alexander G Chen

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector and an array of secondary plain jet fuel injectors.

Low emissions combustor assembly for gas turbine engine

A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.

Main mixer in an axial staged combustor for a gas turbine engine

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

Gas turbine engine combustor main mixer with vane supported centerbody

A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.

Mixer assembly for a gas turbine engine

A chemiluminescence imaging system that may be used for monitoring a combustor flame of a gas turbine engine includes a sensor array having a plurality of pixels operable to capture an image. A multispectral mask array and an attenuation filer array of the system may be generally placed in front of the sensor array and each have a plurality of cells that are generally align, respectively, to the plurality of pixels. Each cell is generally one of a plurality of band-pass filter types distributed randomly across the multispectral mask array and an image reconstruction algorithm is used to produce at least one image for evaluating properties of the flame.

Chemiluminescence imaging system and method of monitoring a combustor flame of a turbine engine

A combustor assembly includes a first wall, a second wall, a bulkhead and a plurality of fuel injectors. The bulkhead forms a combustion chamber with the first and the second walls. The fuel injectors are configured with the first wall in a unique and/or a fluctuating pattern.

Combustor assembly for a turbine engine

An exemplary fire suppression system includes a sprinkler nozzle. At least one conduit is connected to the nozzle for delivering a fire suppression fluid to the nozzle. The conduit and the nozzle establish a discharge path. A pneumatically driven pump is connected with the conduit for pumping fluid into the conduit. A gas source provides pressurized gas to the pump for driving the pump. The gas source also provides gas to the discharge path for achieving a desired discharge of the fluid from the nozzle. A controller selectively controls at least one of (i) the gas provided to the pump, which controls the fluid pressure in the conduit, or (ii) the gas provided to the nozzle or the conduit, which controls the gas pressure delivered to the nozzle.

Fire suppression system with variable dual use of gas source

A fuel-air premixer for a combustor of a gas turbine engine includes a central passage disposed along an axis and operable to communicate a first airflow and an outer annular passage about the axis operable to communicate a second airflow. The fuel-air premixer further includes an inner annular passage about the axis and between the central passage and the outer annular passage for communicating fuel flow. The inner annular passage including an inner exit angled for directing fuel flow toward the axis into a mixer passage downstream of the outer and inner exits for mixing the fuel flow with the first and second airflows.

Fuel-air pre-mixer with prefilmer

A mixer assembly for a gas turbine engine is provided, including a main mixer, and a pilot mixer having an annular housing in which a corner is formed between an aft portion of the housing and a bulkhead wall in which a corner recirculation zone is located to stabilize and anchor the flame of the pilot mixer. The pilot mixer can further include features to cool the annular housing, including in the area of the corner recirculation zone.

Mixer assembly for a gas turbine engine having a pilot mixer with a corner flame stabilizing recirculation zone

A method for controlling a temperature distribution within a combustor having a plurality of chamber sections comprising controlling a fuel-to-air ratio in the chamber sections. At least two chamber sections have different fuel-to-air ratios to create a non-uniform temperature distribution within the combustor to reduce thermoacoustic instabilities.

Method for control of thermoacoustic instabilities in a combustor

A fuel system includes a fuel deoxygenator for removing oxygen from a liquid fuel. A vaporizer is in fluid communication with the fuel deoxygenator. The vaporizer vaporizes at least a portion of the liquid fuel to produce vaporized fuel. At least a portion of the vaporized fuel pre-mixes with oxidizer to reduce formation of undesirable emissions.

Fuel system and method of reducing emission

A fuel injector has a number of groups of nozzles. The groups are generally concentric with an injector axis. Each nozzle defines a gas flowpath having an outlet for discharging a fuel/air mixture jet. There are means for introducing the fuel to the air. One or more groups of the nozzles are oriented to direct the associated jets skew to the injector axis.

Growing community of inventors

Hebron, CT, United States of America

Jeffrey Mark Cohen