Patent ID: 9745920
Date: 2017-08-29
CPC Classifications: F01D,F02K,F05D

Claim:
1. A nozzle for a turbine section of a gas turbine engine, comprising: a band having an inner contour, a forward edge disposed opposite an aft edge, and a side edge extending from the forward edge to the aft edge; a seal slot within the side edge of the band; an airfoil extending from the band; a cavity within the airfoil, the cavity being defined by a leading sidewall of the airfoil, a trailing sidewall of the airfoil, and the inner contour of the band; and an embossment positioned at the inner contour of the band and extending into the cavity; wherein the leading sidewall of the airfoil extends from a leading edge of the airfoil to a trailing edge of the airfoil, the leading edge of the airfoil being located at a forward portion of the band proximate the forward edge of the band, the trailing edge of the airfoil being located at an aft portion of the band proximate the aft edge of the band, and a portion of the leading sidewall being located proximate the side edge of the band; and wherein the seal slot extends from the side edge of the band into the embossment.