Gas turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same using additive manufacturing techniques

摘要

Disclosed in various exemplary embodiments are turbine engine combustors with effusion and impingement cooling and methods for manufacturing the same. In one exemplary embodiment, disclosed is a combustor for a turbine engine that includes an annular liner portion including a first metering hole positioned on a cold side annular surface of the annular liner portion and an impingement chamber positioned in the annular liner. The impingement chamber connects to an entry hole on the cold side annular surface and includes a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to an exit hole positioned on the hot side annular surface of the annular liner portion. The first metering hole is connected to the impingement chamber. The cooling air outlet passageway directs the air onto the hot side annular surface and spreads the airflow axially and laterally parallel to the hot side annular surface. Furthermore, a ratio of a radial thickness of the annular liner portion to a diameter of the entry hole is from about 2 to about 6.

主权项

1. A combustor for a turbine engine, comprising:
an annular liner portion comprising a first impingement hole positioned on a cold side annular surface of the annular liner portion; and an impingement chamber positioned in the annular liner portion, the impingement chamber comprising a chamber entry opening and a chamber exit opening, the impingement chamber connecting to a cooling air entry opening on the cold side annular surface via the first impingement hole and connecting to a cooling air outlet passageway that is angled with respect to a hot side annular surface of the annular liner portion and that connects to a cooling air exit opening positioned on the hot side annular surface of the annular liner portion, wherein the first impingement hole is connected to the impingement chamber at the chamber entry opening, wherein the cooling air outlet passageway is connected to the impingement chamber at the chamber exit opening, wherein the impingement chamber comprises an impingement surface disposed at a radially hot side end of the impingement chamber, and wherein the chamber exit opening is positioned radially outwardly toward to the cold side annular surface with respect to the impingement surface such that the chamber exit opening is disposed adjacent to a radially cold side end of the impingement chamber and is further oriented along the impingement chamber to allow cooling air to exit the impingement chamber in an axial direction, wherein the cooling air outlet passageway is configured to allow the cooling air onto the hot side annular surface, and wherein a ratio of a radial thickness of the annular liner portion to a diameter of the cooling air entry opening is from 2 to 6.