Patent ID: 9333603
Filing Date: 2016-05-10
CPC Classification: B23K,F01D,F02C,F05D,Y10T

Claim Text:
1. A method for assembling a section of a gas turbine engine, the method comprising: inserting a plurality of vane arc segments in a radial direction into an assembled position that is axially between two rows of blades of a multi-row rotor drum, the multi-row drum formed of a single-piece body that has at least two rows of blades about a central axis; and joining circumferential end portions of adjacent ones of the vane arc segments, wherein the circumferential end portions are stronger than circumferential intermediate portions of the vane arc segments, and wherein the circumferential end portions are formed to resist deflection with a different material relative to circumferential intermediate portions, the different material making the circumferential end portions stronger than the circumferential intermediate portions.