MULTI-FLOW COOLING PASSAGE CHAMBER FOR GAS TURBINE ENGINE

摘要

A cooling chamber in a gas turbine engine includes a first side surface, a second side surface, a bottom surface, and a top surface defining a chamber therein. The second side surface is angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit. An inlet is located in one of the top surface or the bottom surface at the inlet end of the chamber. At least one divider is located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow. The at least one divider is angled at a second angle with respect to the first side surface.

主权项

1. A cooling chamber in a gas turbine engine, the cooling chamber comprising:
a first side surface, a second side surface opposing the first side surface, a bottom surface, and a top surface opposing the bottom surface, the surfaces defining a chamber therebetween, the second side surface angled at a first angle with respect to the first side surface, the chamber having an inlet end and an exit located downstream of the inlet end, wherein the chamber has a width that narrows from the inlet end toward the exit; an inlet located in one of the top surface or the bottom surface at the inlet end of the chamber; and at least one divider located within the chamber, the at least one divider configured to separate an airflow flowing from the inlet to the exit into a first airflow and a second airflow, wherein the at least one divider is angled at a second angle with respect to the first side surface.