초록 ▼

A method for assembling a section of a gas turbine engine is disclosed. The method involves a plurality of vane arc segments that together form a full vane ring, and a multi-row rotor drum that is formed of a single-piece body that has at least two rows of blades about a central axis. The method inc

A method for assembling a section of a gas turbine engine is disclosed. The method involves a plurality of vane arc segments that together form a full vane ring, and a multi-row rotor drum that is formed of a single-piece body that has at least two rows of blades about a central axis. The method includes inserting the plurality of vane arc segments in a radial direction into an assembled position that is axially between the two rows of blades.

대표청구항 ▼

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

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; andjoining 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. 2. The method as recited in claim 1, wherein the plurality of vane arc segments have equivalent arc lengths. 3. The method as recited in claim 1, wherein the plurality of vane arc segments have different arc lengths. 4. The method as recited in claim 1, further comprising providing an overlapping joint at an interface between two of the plurality of vane arc segments. 5. The method as recited in claim 1, further comprising providing a seal at an interface between two of the plurality of vane arc segments. 6. The method as recited in claim 1, wherein each of the plurality of vane arc segments includes a plurality of vanes in a vane support structure. 7. The method as recited in claim 1, wherein the multi-row rotor drum and the vane segments are in a high compressor section of a gas turbine engine. 8. The method as recited in claim 1, wherein the circumferential end portions of the adjacent ones of the vane arc segments include respective tabs, and the joining includes overlapping the respective tabs. 9. The method as recited in claim 1, wherein the circumferential end portions also have an increased thickness relative to the circumferential intermediate portions.