Honeywell International Inc.

Thomas J Bronson

Frank Joseph Zupanc

Nagaraja S Rudrapatna

Donald G Godfrey

Rodolphe Dudebout

Paul Yankowich

A gas turbine engine combustor is provided. An inner liner has an upstream end and a downstream end and extends in an axial direction between the upstream and downstream ends. A dual wall outer liner has a hot wall, a cold wall at least partially surrounding the hot wall, an upstream end, and a downstream end. The outer liner extends in the axial direction between the upstream and downstream ends. A dome assembly is coupled between the upstream ends of the inner and outer liners to define a combustion chamber between the inner liner and the hot wall of the outer liner. Effusion cooling holes are disposed in the hot wall, including a first row disposed at a tangential angle of between about 70&#xb0; and about 90&#xb0; and a second row disposed at a tangential angle of between about 0&#xb0; and about 20&#xb0;.

Effusion cooled dual wall gas turbine combustors

A fuel injector assembly includes a fuel injector and a fuel injector shroud housing the fuel injector. The fuel injector includes a body and a nozzle coupled to the body. The fuel injector shroud includes a swirler device defining a center opening proximate to the nozzle of the fuel injector and a plurality of swirler holes surrounding the center opening, a body section with an air inlet configured to admit a flow of air into the fuel injector shroud and a dome section defining a mount for securing the swirler device to the body section, and at least one interior rib positioned on an interior surface of the dome section configured to direct the flow of air to the swirler holes of the swirler device such that the flow of air exiting through the swirler is mixed with the flow of fuel exiting the nozzle.

Gas turbine engines having fuel injector shrouds with interior ribs

A combustor for a turbine engine includes an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor further includes an inner liner circumscribed by the outer liner and forming a combustion chamber therebetween, the inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The combustor further includes a plurality of fuel injectors extending into the combustion chamber and configured to deliver an air-fuel mixture to the combustion chamber, each of the plurality of fuel injectors being associated with one of the outer liner regions and one of the inner liner regions. The first group within a respective outer liner region includes air admission holes that circumferentially alternate between approximately a first size and approximately a second size, the first size being different than the second size.

Quench jet arrangement for annular rich-quench-lean gas turbine combustors

A combustor for a turbine engine is provided. The combustor includes a first liner; a second liner positioned relative to the first liner to form a combustion chamber therebetween, the combustion chamber configured to receive a fuel-air mixture; an igniter positioned relative to the combustion chamber and configured to ignite the fuel-air mixture; a first group of air admission holes positioned in the first liner and forming a regular circumferential pattern around the first liner; and a second group of air admission holes positioned in the first liner at a first circumferential position corresponding to the igniter, the second group of air admission holes departing from the regular circumferential pattern.

Circumferentially varied quench jet arrangement for gas turbine combustors

A combustor may include an outer liner having a first group of air admission holes and defining a plurality of outer liner regions. The combustor may further include an inner liner having a second group of air admission holes and defining a plurality of inner liner regions. The first group of air admission holes within a respective outer liner region may include a first plunged air admission hole approximately axially aligned with the respective fuel injector, a second plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a first adjacent outer liner region, the first air admission hole being downstream of the second air admission hole, and a third plunged air admission hole approximately on the outer boundary line between the respective outer liner region and a second adjacent outer liner region.

Annular rich-quench-lean gas turbine combustors with plunged holes

A combustor may include an outer liner having a first row and a second row of circumferentially distributed air admission holes. The second row of the outer liner may be downstream of the first row of the outer liner, and the air admission holes of the first row of the outer liner may be larger than the air admission holes of the second row of the outer liner. An inner liner is circumscribed by the outer liner and has a third and fourth row of circumferentially distributed air admission holes. The air admission holes of the third row of the inner liner may be larger than the air admission holes of the fourth row of the inner liner. The inner and outer liners may form a combustion chamber, and at least a portion of the air admission holes of the first, second, third, or fourth rows may be plunged.

Plunged hole arrangement for annular rich-quench-lean gas turbine combustors

A combustor includes an inner liner; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; a combustor dome coupled to the inner and outer liners; and a plurality of heat shields coupled to combustor dome. Each of the heat shields includes a heat shield plate defined by a first edge facing the inner liner and a second edge facing the outer liner; and a plurality of baffles extending from the heat shield plate. Each of the plurality of baffles includes two ribs and a connection portion connecting the two ribs to form a closed portion and an opposite open portion. The open portion of each of the plurality of baffles faces the first edge or the second edge.

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Mesa, AZ, United States of America

Thomas J Bronson