Abstract: A method enables a gas turbine engine including a combustor to be operated. The combustor includes a mixer assembly including an air swirler, a premixer, a dome plate, and a heat shield. The method comprises discharging fluids from the air swirler into the premixer, and directing cooling fluids through a cooling opening defined in at least one of the swirler and the dome plate towards an upstream side of the heat shield for impingement cooling of the heat shield.

Abstract: An integrated engineering analysis system that determines at least one final output value in response to at least one initial input value. A first subprocesses provides at least one output value in response to the initial input value. A plurality of subprocesses provide a plurality of output values in response to the output values of the first subprocess. The plurality of output values and the output value of the first subprocess are inputted into at least one of the plurality of subprocesses. A command code executes each of the plurality of subprocesses in response to the output values and determines which one of the plurality of subprocesses to run and a final subprocess provides a final output. The final output is the result of a plurality of calculations executed by the plurality of subprocesses and the command code compares the final output with the initial input.

Abstract: A method enables a gas turbine engine including a combustor to be operated. The combustor includes a mixer assembly including an air swirler, a premixer, a dome plate, and a heat shield. The method comprises discharging fluids from the air swirler into the premixer, and directing cooling fluids through a cooling opening defined in at least one of the swirler and the dome plate towards an upstream side of the heat shield for impingement cooling of the heat shield.

Abstract: A fuel air mixer for a gas turbine engine combustor having a longitudinal axis therethrough, wherein the fuel air mixer is configured for use in a dome oriented substantially radial to the longitudinal axis. The fuel air mixer includes a fuel injection assembly having a first end, a second end, a fuel passage extending therethrough, and a flange portion having a plurality of spaced openings formed therein which extends from the first end. The fuel air mixer also includes a mixer assembly having a first end, a second end, a cavity formed in a central portion thereof, and a flange portion having a plurality of spaced openings formed therein which extends from the first end. The mixer assembly is configured to receive the fuel injection assembly in the cavity so that the fuel injection assembly and the mixer assembly are able to be connected to an outer casing of the combustor by means of the respective flange portions.

Abstract: An apparatus and method for minimizing compressor casing distortion due to bleed air extraction wherein the compressor casing includes an annular outer casing having at least one outlet duct, an annular inner casing disposed co-axially with the outer casing and spaced radially inwardly therefrom to define a plenum, two radial discs extending inwardly from the outer casing defining a plenum, a plurality of small area bleed openings located in the inner casing for imparting a radial velocity to the bleed air greater than the circumferential velocity entering the plenum, an air tube located over each bleed opening, and a baffle plate located on top of the air tubes and communicating with the radial discs for supporting the casings, whereby the bleed air impinges on the outer casing and controls distortion by sufficiently reducing the circumferential temperature gradient forming at the outer casing.