Patent ID: 8313291

Claim:
A nozzle segment, comprising: an inner platform configured to be connected with a casing of a gas turbine engine; an outer platform configured to be connected with the casing, the outer platform being disposed apart from the inner platform in a radial direction of the gas turbine engine; and a plurality of blades disposed between the inner and outer platforms and connected thereto, each blade having a leading edge, a trailing edge, a suction side, and a pressure side, wherein one of an inside surface of the inner platform or an inside surface of the outer platform is scalloped outwardly along a radial direction extending from the leading edge of the blade past the trailing edge of the blade and into a portion of the inside surface of the inner or outer platform that is proximate the trailing edge of the blade to form a scalloped region, wherein the scalloped region extends from the pressure side of one of the plurality of blades to the suction side of an adjacent one of the plurality of blades in a uniform line having end points substantially equidistant from the rotation axis of the nozzle so as to increase a throat area of the nozzle segment; wherein the blades extend through the scalloped region to the inner platform and the outer platform.