United Technologies Corporation

Carrier Corporation

Alexander Chen

Louis J Spadaccini

Donald W Kendrick

Jeffrey Mark Cohen

Thomas Gregory Tillman

Catalin G Fotache

Louis Chiappetta, Jr

Haralambos Cordatos

Foster Philip Lamm

Zidu Ma

Jules Ricardo Munoz

Charles C Coffin

James R Irish

Meredith B Colket

Stephen R Jones

Foster Phillip Lamm

Brian M Welch

Harry Cordatos

James A Wilkinson

Lou Chiappetta

Salvatore MacRi

Tiziano Conti

Young K Park

A catalytic reactor for a gas turbine engine comprising an air inlet, a premixing zone, a reacting zone comprising a reactive portion and a nonreactive portion, a post reaction mixing zone, a first fuel injection system for introducing fuel into the reactive portion, and a second fuel injection system for introducing fuel into the nonreactive portion.

Staging for rich catalytic combustion

A fuel delivery system includes a fuel stabilization unit that removes dissolved oxygen from liquid fuel to increase the temperature at which the liquid fuel can be elevated without substantial formation of insoluble products. At least a portion of the fuel with reduced amounts of dissolved oxygen is vaporized prior to entering a combustion device to improve mixing and combustor performance.

Flame stability enhancement

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 device for use in a fluid system includes a flow perturbation element within a fluid channel. The flow perturbation element has a gas permeable surface for removing dissolved gas from passing fluid. A gas permeable membrane is coated on the gas permeable surface and allows the dissolved gas transport out of passing fluid into a gas-removal channel. The gas permeable membrane may be coated on the fuel perturbation elements using any of a variety of methods.

Fuel deoxygenator with non-planar fuel channel and oxygen permeable membrane

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.

Nozzle

The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further has different fuel circuits for independently controlling the fuel flow rate for the nozzles in each of the arrays. Each of the nozzles include a fluid channel and one or more swirler vanes in the fluid channel for creating a swirling flow within the fluid channel. A method for injecting a fuel/air mixture into a combustor stage of a gas turbine engine is also described. At least one zone has a flame hot enough to stabilize the entire combustor flame.

Multi-point staging strategy for low emission and stable combustion

A fuel stabilization system includes a first deoxygenator and a second deoxygenator both for removing dissolved oxygen from a hydrocarbon fuel. The first and second deoxygenators are arranged in parallel or series to sequentially remove a portion of dissolved oxygen from the hydrocarbon fuel. The arrangement of several deoxygenators for a single fuel stream improves removal of dissolved oxygen and provides for scalability of the fuel system to meet application specific demands. The arrangement also provides for the preservation of partial system functionality in the event of the failure of one of the deoxygenator modules.

Modular fuel stabilization system

A deoxygenator includes a plurality of permeable membranes spirally wound about an exhaust tube for removing dissolved oxygen from a hydrocarbon fuel. The permeable membrane is spirally wrapped about the exhaust tube and defines fuel passages and exhaust passages. The fuel passages and exhaust passages alternate such that each fuel passage is bounded on each adjacent side by an exhaust passage. An oxygen partial pressure differential is generated across the permeable membrane to draw dissolved oxygen from fuel in the fuel passage. The dissolved oxygen is then communicated through openings about the circumference of the exhaust tube and out the deoxygenator.

Spiral wound fuel stabilization unit for fuel de-oxygenation

The fuel injector has a first means defining a number of flowpaths each having an inlet for receiving air and an outlet for discharging a fuel/air mixture. One or more arrays of vanes are each positioned to impart swirl to an associated one or more of the flowpaths. Second means are provided for introducing the fuel to the air.

Growing community of inventors

Ellington, CT, United States of America

Alexander Chen