General Electric Company

James Anthony Groeschen

Gilbert Farmer

Ronald Redden

Jason Paul Hoppa

Shaun Michael DeVane

Robert Paul Czachor

Mehmet Muhittin Dede

Daniel Lee Durstock

Douglas Marti Fortuna

Mark Gerard Rettig

Marwan Al-Roub

Stanford P Seto

Mark Patrick Kelsey

Neil S Rasmussen

Balena B Shorter

A method for assembling a gas turbine engine includes coupling a first structure within the gas turbine engine, wherein the first structure includes a plurality of sockets extending from a radially outer surface of the first structure, and coupling a second structure to the first structure by inserting a radial pin through the second structure and into each respective socket such that the first structure is aligned axially, circumferentially, and with respect to an engine centerline axis extending through the gas turbine engine, where the position of the pins relative to the second structure is adjustable.

Methods and apparatuses for assembling a gas turbine engine

A combustor liner is provided having first and second annular bands which define an overlapping circumferential joint area, wherein a weld is disposed in the joint area encompassing substantially all of the axial length of the joint area. A method for producing such a combustor liner is also provided.

Combustor linear and method for making thereof

A combustor for a gas turbine engine having a longitudinal axis extending therethrough, including an inner liner, an outer liner spaced radially from the inner liner, an annular dome connected to the inner and outer liners, a plurality of air/fuel mixers connected to the dome and circumferentially spaced within the dome, an outer cowl connected to the outer liner, and an inner cowl connected to the inner liner, wherein a combustion chamber is formed by the inner liner, the outer liner and the dome. The dome further includes a first end connected to a liner of the combustor, a second end spaced radially from the first end, a first portion extending rearwardly from the first end adjacent the liner, a second portion extending rearwardly from the second end and flaring radially outward from the longitudinal axis, and a nonlinear third portion connecting the first and second dome portions.

Combustor dome for gas turbine engine

A cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. A combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl.

Corrugated cowl for combustor of a gas turbine engine and method for configuring same

Combustor liner and method for making thereof

A nozzle for a gas turbine engine that includes an air circuit, a water circuit, and a swirler that facilitate reducing erosion within the nozzle is described. The air circuit is formed by a first conduit that extends along the nozzle. The water circuit is formed by a second conduit that also extends along the nozzle and is radially inward from the first conduit. Each circuit is in flow communication with a discharge opening. An air swirler adjacent the discharge opening discharges air into water spray exiting the water circuit to facilitate evaporating the water to lower engine operating temperatures.

Methods and apparatus for injecting water into gas turbine engines

A combustion apparatus for a gas turbine engine including a combustor structure having at least one combustion chamber, a dual cone fuel nozzle for injecting both fuel and water to the combustion chamber, and a swirl cup package upstream of and adjacent to the combustion chamber. The swirl cup package further includes a swirler and a venturi extending between the nozzle and the combustion chamber for mixing the fuel and water with air. The venturi is configured to have a non-uniform thickness from an upstream end to a downstream end resulting in a cross-sectional area which provides a heat transfer conduction path that reduces axial stresses imposed on the venturi when water impinges on an upstream portion of the venturi.

Venturi for use in the swirl cup package of a gas turbine combustor having water injected therein

A method for determining the appropriate hole parameters to achieve the desired airflow in a swirler with as-cast air jet holes includes the steps of determining the desired airflow through the holes and selecting a hole angle for the holes. Next, the ratio of the hole exit area to the hole inlet area is calculated based on the desired airflow and the selected hole angle using a regression equation. Then a value is determined for either of the hole exit area or the hole inlet area, and the other area is calculated from the known ratio. Once the hole angle, hole exit area and hole inlet area have been determined, then a swirler can be cast with as-cast holes using these hole parameters.

Growing community of inventors

Burlington, KY, United States of America

James Anthony Groeschen