US 9,752,447 B2 · Angled rail holes

Abstract

A gas turbine engine combustor configured to cool a first vane platform by directing airflow through an aft combustor rail is disclosed. In various embodiments, a gas turbine engine combustor may comprise an aft combustor rail connected between an outer wall of an outer liner and an aft heat shield panel, and a plurality of holes in the aft combustor rail. The aft combustor rail may be positioned near an outer vane platform of a first vane stage of a turbine. Further, the plurality of holes may be designed to focus pass-through airflow onto the outer vane platform. In various embodiments, each hole of the plurality of holes may be angled between 20°-90° relative to the aft combustor rail. Additionally, the plurality of holes may be angled to converge the airflow to a focused area, such as a leading edge vane airfoil of the first vane stage.

Claims16

Dependent claims

A gas turbine engine combustor comprising:

an aft combustor rail connected between an outer wall of an outer liner and an aft heat shield panel, wherein the aft combustor rail is positioned near an outer vane platform of a first vane stage of a turbine;
and
a plurality of holes in the aft combustor rail, wherein the plurality of holes is configured to focus pass-through airflow onto the outer vane platform,
wherein each hole of the plurality of holes is angled between 20° and 90° in a circumferential direction relative to the aft combustor rail to converge the pass-through airflow to a focused area, wherein the focused area is a leading edge of a vane airfoil of the first vane stage.

1 more element

Dependencies are inferred from the claim text.

Angled rail holes

Life of this patent

Angled rail holes

Life of this patent

Abstract

Claims16