Abstract: An apparatus is disclosed for injecting fluid coolant into a gas turbine engine combustion system at a location distal the fuel nozzle, such as at the primary or dilution orifices of the combustor. In one embodiment of the invention, the apparatus comprises a substantially hollow cylindrical tube adapted for insertion into a primary jet orifice of the combustor. A water nozzle is housed at the end of the tube opposite the primary jet orifice. The water nozzle is positionally adjustable relative to the inner liner. A pair of apertures is disposed along the tube between the primary jet orifice and the water nozzle so as to admit primary jet air from the plenum surrounding the combustion chamber into the tube. The apertures are configured to impart a swirling motion to the primary jet air as it enters the tube. Alternatively, at least one baffle may be housed within the tube proximal the aperture to impart a swirling motion to fluid communicated to the tube by the plenum.

Abstract: An air blast fuel nozzle includes a unitary structure which introduces not only axially swirling primary airflow into the primary zone of the combustor chamber, but also introduces radial inflow, coswirling, primary airflow into the premixing chamber immediately upstream of the primary zone of the combustor.

Abstract: An annular gas turbine engine combustor includes additional axial primary airflow openings, formed as arcuately segmented openings on opposite sides of each of the airblast fuel nozzles of the combustor, for reducing overall combustor diameter while maintaining flame stabilization and avoiding unacceptable thermal variations in the combustion process.

Abstract: A gas turbine engine has a low cost combustor liner cooling system combining the benefits of high internal heat removal with improved film cooling by employing a large number of strategically positioned, laser-drilled cooling passages. Cooling air flows through these specially tailored passages to absorb heat from the liner prior to injection as a protective film on the interior surface. The passages are set in staggered rows on a thickened portion of the liner and have a rough internal heat transfer surface and an exit with a steep injection angle to evenly distribute the cooling film along the interior surface of the liner.