Baffled passage casing treatment for compressor blades

A tip shroud assembly for an axial flow gas turbine engine, said tip shroud assembly comprising

• an annular shroud extending circumferentially about a reference axis, said shroud including a plurality of arcuate segments, each segment having a length, the sum of said lengths defining the circumference of said annular shroud, each segment comprising
• a first arcuate member having a first radially inner surface and a circumferentially extending channel extending radially outward therefrom the length of the segment, said channel including a first wall, a second wall and a radially outer channel wall connecting said first wall to said second wall, said first wall opposite said second wall,
• a second arcuate member, said second arcuate member having a second radially inner surface and a third wall and a fourth wall extending radially outward therefrom and a radially outer member wall connecting said third wall to said fourth wall, said second arcuate member received within the channel in spaced relation to the first arcuate member thereby defining a circumferentially extending passage therebetween, said third wall opposite said first wall and said fourth wall opposite said second wall, and
• a plurality of baffles located in the passage, each baffle extending from the radially outer member wall radially outward relative to said axis to said radially outer channel wall, each baffle fixed to the first and second arcuate members thereby preventing relative movement therebetween, each baffle terminating short of said first and second walls.