Bolt-on radial bleed manifold

Abstract

A compressor radial bleed manifold and compressor case assembly includes a compressor case (34) having one or more bleed flow exit passages (44) therein; and a discrete bleed manifold (38) mounted on the compressor case and having one or more inlet passages (46) extending radially between a manifold plenum (48) and the one or more exit passages (44) in the mounting boss for bleeding compressor air into the manifold plenum.

Description

technical field [0001] The present invention relates to rotating machinery technology, and more particularly to a separate compressor discharge pipe which can be secured to an associated compressor casing. Background technique [0002] Reducing the radial clearance between the rotating compressor blades and the compressor casing in axial flow industrial gas turbines is critical to improving performance. Current industrial gas turbine compressor exhaust pipes are integral to the basic compressor casing structure. In other words, current industrial turbine housing design principles integrate the exhaust pipe with the compressor housing. However, this configuration is not conducive to reducing compressor clearances because a separate shroud or casing is required to carry the engine loads and maintain a tight flow path around the clearances. Typically, such tubes include axially extending and opposed vertical flanges, opposed duct sections connected by a plurality of transvers...

AI Technical Summary

Problems solved by technology

This current compressor discharge duct construction also adds to the challenge of good casing design as it disrupts the otherwise smooth load path, creating unsupported casing wall sections that cause the so-called "springboard" effect, limiting the location and into the resultant load of the casing, and creates a thermal response mismatch between the rotor and casing

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