Abstract: A method facilitates washing a gas turbine engine combustor. The method comprises coupling a nozzle assembly against the combustor, wherein the nozzle assembly includes an inlet end, a discharge end, a hollow nozzle body extending therebetween, and a centerbody positioned within the nozzle body, coupling the nozzle assembly to a fluid source, and discharging an annulus of fluid from the nozzle assembly into the combustor to facilitate removing particulate matter from the combustor.

Abstract: A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slots are formed in at least one of the annular portions. The outer annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of outer radial members connecting the outer annular portion and the middle annular portion are provided between adjacent windows therein. Similarly, the inner annular portion includes a plurality of circumferentially spaced windows of desired size formed therein, wherein a plurality of inner radial members connecting the inner annular portion and the middle annular portion are provided between adjacent windows therein.

Abstract: A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.

Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for film cooling a portion of the deflector portion to facilitate reducing an operating temperature and extending a useful life of the combustor.

Abstract: A one-piece deflector-flare cone assembly for a gas turbine engine combustor that facilitates extending a useful life of the combustor in a cost-effective and reliable manner is described. The one-piece assembly includes a deflector portion and a flare cone portion. The deflector portion includes an integral opening that extends through the deflector portion for receiving cooling fluid therein. The cooling opening extends circumferentially within the deflector portion. Cooling fluid discharged from the cooling opening is used for impingement cooling a portion of the flare cone portion to facilitate reducing an operating temperature and extending a useful life of the combustor.

Abstract: A combustor for a gas turbine engine includes a plurality of igniter tubes that facilitate reducing temperature gradients within the combustor in a cost effective and reliable manner. The combustor includes an annular outer liner that includes a plurality of openings sized to receive igniter tubes. Each igniter tube maintains an alignment of each igniter received therein, and includes an air impingement device that extends radially outward from the igniter tube. During operation, airflow contacting the air impingement device is channeled radially inward for impingement cooling of the igniter tubes and the combustor outer liner.