Turbine engine combustor wall with aperture deflector

A combustor for a turbine engine, comprising:

• a combustor wall including a panel, a deflector, a cooling aperture and a wall aperture that extends along an aperture centerline through the combustor wall to an aperture outlet into a combustion chamber;
• a gas flow direction within the combustor extending along an axis, the gas flow direction extending from an upstream end of the combustor wall to a downstream end of the combustor wall;
• the panel extending axially along and circumferentially about the axis, the panel extending radially between a first panel surface and a second panel surface, and the first panel surface forming a peripheral boundary of the combustion chamber;
• the deflector projecting radially out from the panel into the combustion chamber to a deflector surface, the deflector partially forming the aperture outlet, the deflector surface sloping away from the first panel surface as the deflector extends longitudinally towards the aperture outlet, and the deflector surface sloping to the first panel surface as the deflector extends longitudinally from the aperture outlet;
• and
• the cooling aperture extending between the deflector surface and a cooling cavity, the cooling aperture having an upstream side and a downstream side, the cooling aperture having a cooling aperture centerline that is angularly offset from the panel by a constant non-zero acute angle, and the cooling aperture projecting through the entirety of the deflector at the constant non-zero acute angle along the cooling aperture centerline;
• wherein the upstream side of the cooling aperture is upstream of the downstream side of the cooling aperture along the gas flow direction;
• wherein the panel forms a trailing edge side of the aperture outlet relative to the gas flow direction within the combustion chamber;
• and
• wherein the deflector forms a leading edge side of the aperture outlet relative to the gas flow direction within the combustion chamber.