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 fuel injector for use in a gas turbine engine includes an inlet stem with a bore formed therein and an insert disposed in the bore. The insert has a cavity formed therein for receiving a fuel filter. The use of the insert allows the upstream end of the inlet stem to be connected to a fuel manifold with a double seal fitting.

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.

Abstract: A combustor liner for use in a gas turbine engine includes a first annular panel section having a first cooling nugget formed at one end thereof and a second annular panel section having a second cooling nugget formed at one end thereof. A first row of cooling holes is formed in the first cooling nugget, and a second row of cooling holes is formed in the second cooling nugget. The second row of cooling holes is arranged in a preferential cooling pattern including a plurality of arrays, each array has a first set of cooling holes having a first diameter and a second set of cooling holes having a second diameter that is smaller than the first diameter. The cooling hole arrays are preferably arranged to minimize tooling set-ups and thereby reduce cost. At least one igniter tower is formed in the first annular panel section and is circumferentially aligned with one of the second sets of cooling holes.

Abstract: A gas turbine engine carburetor includes a fuel injector and a cooperating air swirler for injecting fuel and air into a combustor. The fuel injector includes a hollow body joined to a supporting stem for receiving fuel therein for flow through an injector tip slidingly mounted to the injector body for movement relative thereto. The air swirler surrounds the injector tip and is spaced form the injector body to define an air inlet, and is spaced from the injector tip to define an air outlet. A spring operatively engages the injector body and the injector tip and is preloaded for biasing the injector tip to an initial position. The spring is sized so that increasing pressure of the fuel in the injector body further loads the spring for moving the injector tip from the initial position to a displaced position, with movement of the injector tip modulating airflow through the swirler for in-turn modulating the ratio of discharged fuel and air.

Abstract: A gas turbine engine carburetor includes a fuel injector having a plurality of circumferentially spaced apart fuel outlets. A plurality of air swirlers (24) are circumferentially spaced apart around the fuel injector (22), with each swirler having a fuel inlet (24b) disposed in flow communication with a respective one of the fuel outlets for receiving fuel therefrom. Each swirler includes a plurality of swirl vanes to swirl air for mixing with the fuel from the fuel inlets. The multi-swirler carburetor having a common fuel injector increases injection points for reducing NO.sub.x emissions.

Abstract: A combustor includes radially spaced apart outer and inner liners joined together at upstream ends through an annular dome disposed coaxially about a longitudinal centerline axis. A plurality of circumferentially spaced apart fuel injectors are disposed adjacent to an arcuate a splashplate for injecting fuel thereagainst, the splashplate being arcuate about the centerline axis. Primary air is channeled along the splashplate for mixing with the injected fuel for forming a fuel/air mixture dischargeable from the splashplate into a combustion zone defined between the liners and the dome.

Abstract: A gas turbine engine combustor dome assembly includes a dome having a dome eyelet, a mounting ring fixedly joined to the dome around the eyelet, a baffle fixedly joined to the mounting ring, and a carburetor fixedly joined to the mounting ring. The carburetor is joined to the mounting ring for providing a fuel/air mixture through the mounting ring with a predetermined relationship to the baffle for controlling pattern factor. The mounting ring allows for assembly with reduced stackup clearances, and easy disassembly for servicing.

Abstract: An improved air swirler and fuel injector for a gas turbine combustor system employs primary fuel injection into a primary recirculation combustion zone supplied by an inner annulus of swirling air at high fuel-air ratio under low power conditions. A selectively staged secondary fuel flow is supplied into an outer annulus downstream of secondary air swirlers supplying a secondary recirculation zone for combustion at higher fuel flows but lower fuel-air ratios under high power conditions. The secondary fuel flow may be separately injected into the outer annulus through conduit means extending through the primary air swirler vanes. Alternatively, the secondary fuel flow may be combined with the primary fuel in the fuel injector body and the momentum due to mass flow used to inject the fuel into the outer annulus.