Patent ID: 8250870
Filing Date: 2012-08-28
Classification: F01D,F04D

Abstract:
1. A vortex reducer for the guidance of bleed airflows, which is arranged in an inter-disk chamber between two rotor disks of a compressor of a gas turbine, comprising: at least one ring having a plurality of circumferentially disposed hole passages, the hole passages including a plurality of first hole passages distributed evenly around a circumference of the ring and a plurality of second hole passages, the first hole passages and second hole passages positioned at outer radial positions; and a plurality of bleed air tubes respectively connected to the plurality of first hole passages for extending the respective first hole passages radially inward in an interior of the inter-disk chamber to open the first hole passages to the inter-disk chamber at inner radial positions radially inward of the outer radial positions, the second hole passages being free of bleed air tubes and opening to the inter-disk chamber at the outer radial positions at circumferential interspaces between the bleed air tubes; outer surfaces of the bleed air tubes guiding air flows from the second hole passages through the circumferential interspaces between the bleed air tubes to reduce swirl of the air flows from the second hole passages.