Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section

摘要

A midframe portion (213) of a gas turbine engine (210) is presented, and includes a compressor section (212) configured to discharge an air flow (211) directed in a radial direction from an outlet of the compressor section (212). Additionally, the midframe portion (213) includes a manifold (214) to directly couple the air flow (211) from the compressor section (212) outlet to an inlet of a respective combustor head (218) of the midframe portion (213).

主权项

1. A midframe portion of a gas turbine engine, comprising:
a compressor section comprising a last stage blade with a leading edge aligned with a leading edge of blades positioned upstream of the last stage blade, said last stage blade configured to discharge an air flow directed in a radial direction from an outlet of the compressor section; a plurality of discrete combustor heads circumferentially arranged around a rotor assembly of the gas turbine engine in an annular configuration; and a plurality of manifolds circumferentially arranged around the rotor assembly, wherein each manifold is configured to directly couple a respective portion of the air flow discharged from the compressor section to a respective combustor head; wherein the compressor section, the plurality of discrete combustor heads and the plurality of manifolds are positioned within a single casing to form a chamber; wherein an air flow is directed from an intermediate stage of the compressor section into the chamber to circulate stagnant air within the chamber.