BLEED FLOW PASSAGE
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United States of America Patent
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N/A
Issued Date -
May 1, 2014
app pub date -
Oct 10, 2013
filing date -
Nov 1, 2012
priority date (Note) -
Abandoned
status (Latency Note)
Importance
Abstract
A liner wall insert is provided for a compressor rotor stage of a gas turbine engine. Several liner wall inserts are provided radially outboard of the tips of the rotor blades. The liner wall inserts have bleed flow channels formed therein. The bleed flow channels are arranged to remove flow from a trailing edge region of the stage and re-inject the bleed flow at an upstream region. The re-injected bleed flow alters the flow field around the tips of the rotor blades, for example the tip leakage flow. Thus, the bleed flow is used to improve the efficiency of the compressor rotor stage, and thus of the gas turbine engine.
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