Honeywell International Inc.

Lowell Frye

Nagaraja S Rudrapatna

William Landram

Rodolphe Dudebout

Gregory O Woodcock

Terrel Kuhn

Philip Smalley

Sossity A Flamand

Terrel E Kuhn

A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The combustor further includes an insert having a body portion extending through the first liner and terminating at a tip, the body portion configured to direct air flow into the combustion chamber. The insert further includes a cooling hole defined in the body portion and configured to direct a first portion of the air flow toward the tip as cooling air.

Combustors with quench inserts

A combustor for a turbine engine is provided. The combustor includes a first liner and a second liner forming a combustion chamber with the first liner, the combustion chamber configured to receive an air-fuel mixture for combustion therein. The first liner defining an air admission hole for directing a first jet of pressurized air into the combustion chamber, and the air admission hole may have a non-circular shape. The combustor further includes an insert positioned within the air admission hole to guide the first jet through the air admission hole and into the combustion chamber.

A method of forming a plurality of shaped holes on a workpiece. The method may include rotating the workpiece about multiple axes relative to a laser beam, and positioning the laser at a first predetermined angle relative to the workpiece. The laser beam is pulsed to form a first plurality of trepan cuts defining a row of metering holes. The laser beam, after adjusting to a next predetermined angle and adjacent a previous row of trepan cuts, is pulsed to create a plurality of rows of trepan cuts wherein each cut in the previous row of trepan cuts is connected to a cut in said subsequent row of trepan cuts. The plurality of rows of trepan cuts are formed in a side-to-side sweeping formation and define a portion of each of the shaped holes. Next, the laser is pulsed in alignment with the metering hole to remove debris from therein.

Laser cutting shaped holes by trepanning on the fly

Methods are provided of forming a plurality of fan-shaped effusion holes on a combustor having a surface, each hole having an outlet on the combustor surface. The method may include rotating the combustor relative to a laser beam, and positioning the combustor to a first position where the laser beam is at a first predetermined angle relative to the combustor surface. The laser beam is pulsed at the combustor surface to form a first plurality of trepan cuts. The first predetermined angle is adjusted to a second position where the laser beam is at a second predetermined angle relative to the combustor surface. The laser beam is pulsed at each trepan cut of the first plurality of trepan cuts, to thereby form a cut for at least a portion of the fan shape of each effusion hole outlet, wherein each cut overlaps a trepan cut of the first plurality of trepan cuts.

Methods of forming fan-shaped effusion holes in combustors

A system and method for trepanning holes into a work piece as relative movement between the work piece and a pulsed laser occurs. As a cylindrical work piece rotates for example, a position controlled pulse laser fires a first series of timed pulses. During each subsequent rotation of said work piece another series of pulses is fired such that the periphery of a row of identical holes is cut into the cylindrical work piece.

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Chandler, AZ, United States of America

Lowell Frye