Abstract: A method of making a dome plate for a gas turbine engine combustor includes forming an annular body and forming a plurality of swirler openings in the annular body. Then, an array of impingement cooling holes and an array of blow-off holes are electrically discharge machined into the annular body adjacent to each swirler opening. For each one of the plurality of swirler openings, the corresponding array of impingement cooling holes and the corresponding array of blow-off holes are machined in a single electrical discharge machining operation. This results in an annular dome plate having radially outer and inner curved corners that define a single radius of curvature. The blow-off holes are located in at least one of the outer and inner curved corners.

Abstract: A dome assembly for a gas turbine engine combustor includes an annular combustor dome with a substantially annular flat dome plate and at least one circular opening in the dome plate. A seal plate flange with a flat aft facing surface has a central ring circumscribed about a centerline axis and extends aftwardly from the seal plate flange. The central ring is disposed through the circular opening in the dome plate and the central ring includes a central bore coaxially aligned with the circular opening. A baffle has a cylindrical tubular mounting portion extending upstream through the central bore and is fixedly joined to the seal plate and a flare portion extending aft from the seal plate flange. A carburetor including an air swirler having an annular exit cone is joined to the baffle with the exit cone disposed within the cylindrical tubular mounting portion of the baffle. An aft end of the central ring is joined to the dome plate by a swage joint.