General Electric Company

Gas Research Institute

Consolidated Natural Gas Service Company, Inc.

Harjit Singh Hura

Bernard P Breen

Paul Hadley Vitt

Daniel Endecott Osgood

Aspi Rustom Wadia

James E Gabrielson

Brian Keith

Hukam Chand Mongia

James Neil Cooper

Frank Worthoff

Kenneth Edward Seitzer

Steven Joseph Lohmueller

Beverly Stephenson Duncan

Paul Edward Sabla

Jonathan Ong

James C McMichael

Raymond Gust Holm

Brett A Rich

Marie Myers

Jason Corey Slagle

Eric Pierre Masse

Nancy Haviland Morton

Connor Marie Shirley

Alison E Schulte

Michael David Gervasio

A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A turbine nozzle is arranged in the turbine section. Vanes of the turbine nozzle include a vane airfoil having cooling features formed in a trailing edge of the vane airfoil. Vanes of the turbine nozzle further include a baffle insert in a cavity of the vane airfoil. The baffle insert includes cooling holes.

Turbine engine with a nozzle having cooling features

A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.

Airfoil assembly with a scalloped flow surface

A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 30% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.

Gas turbine engine transition duct and turbine center frame

A booster compressor includes inlet guide vanes supported from a shroud. A shell surrounds the shroud and defines a manifold. A splitter nose includes a groove receiving a forward tang of the shroud with a clearance therebetween defining an outlet for the manifold. Hot air is channeled through the manifold and out the splitter nose for deicing thereof.

Booster compressor deicer

A two-stage fuel nozzle assembly for a gas turbine engine. The primary combustion region is centrally positioned and includes a fuel injector that is surrounded by one or more swirl chambers to provide a fuel air mixture that is ignited to define a first stage combustion zone. A secondary combustion region is provided by an annular housing that surrounds the primary combustion region, and it includes a secondary fuel injector having a radially outwardly directed opening and surrounded by an annular ring that includes openings for providing a swirl chamber for the secondary combustion region. Cooling air is directed angularly between the primary and secondary combustion zones to delay intermixing and thereby allow more complete combustion of the respective zones prior to their coalescing further downstream. The primary combustion region is activated during idle and low engine power conditions and both the primary and secondary combustion regions are activated during high engine power conditions.

Fuel nozzle assembly for reduced exhaust emissions

A combustor includes a fuel injector for injecting fuel into the combustor, a baseline air blast pilot splitter including a converging downstream side and a splitter extension. The splitter extension includes a diverging upstream portion attached to a baseline air blast splitter, a diverging downstream portion, and a converging intermediate portion extending between the upstream portion and the downstream portion.

Methods and apparatus for decreasing combustor emissions

In a furnace having a primary combustion zone for combustion of a fuel and oxidant, an in-furnace method for reducing nitrogen oxides in combustion products generated in the primary combustion zone in which at least one fluid fuel selected from the group consisting of natural gas, hydrogen, C,H,compounds, C,H,O,compounds and mixtures thereof in an amount in a range of about 2.0% to about 25% of a total heat input to the furnace and at least one nitrogenous compound selected from the group consisting of ammonia, amines, urea, cyanuric acid and mixtures thereof are injected into the furnace downstream of the primary combustion zone, forming an overall fuel-lean NO,-reduction zone.

Method and apparatus for NOx reduction in flue gases

A method of reducing NO.sub.x determines an NO.sub.x concentration profile within a zone of the furnace which is at a temperature below 2600.degree. F. A stream of fluid fuel is injected into at least one region of relatively high NO.sub.x concentration so that the fluid fuel mixes therein with the flue gas. The fluid fuel is natural gas, hydrogen, C.sub.x H.sub.y compounds, C.sub.x H.sub.y O.sub.z compounds or mixtures primarily of those compounds, in sufficient quantity to promote a reaction between nitrogen oxide in the flue gas and the fluid fuel, so as to substantially reduce nitrogen oxide content of the flue gas. The injector through which the fluid fuel is injected can be moveable and may have valves or deflectors to aid in directing the fluid fuel to regions of relatively high NO.sub.x concentration.

Apparatus and method for NO.sub.x reduction by selective injection of

A process and apparatus for combustion of a solid carbonaceous material, for example coal, in which a mixture of the solid carbonaceous material and combustion air is injected into a combustion chamber and ignited, thereby forming a fuel-lean primary combustion zone. A gaseous fuel is injected into the combustion chamber in a region downstream of the primary combustion zone, thereby forming a fuel-lean secondary combustion zone. Temperature in the secondary combustion zone is in the range of about 1800.degree. F. to 2400.degree. F.

Nitrogen oxide reduction by gaseous fuel injection in low temperature,

A fuel injector has an inner pipe within an outer pipe. The distal end of the inner pipe is set back from the distal end of the outer pipe to create a flame stabilization and mixing zone. A combustible gas and air mixture injected through the outer pipe forms a flame shroud around a gas stream injected through the inner pipe. This injector provides increased flame penetration and improved NO.sub.x reduction particularly when used to inject a flame shrouded gas stream into regions of the furnace at which the flue gas is at a temperature not greater than 2400.degree. F.

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Cincinnati, OH, United States of America

Harjit Singh Hura