US 11,692,490 B2
Gas turbine inner shroud with abradable surface feature
Jae Bin Lee, Changwon (KR); David Ohlschwager, Loxahatchee, FL (US); and Gene Chong, Jupiter, FL (US)
Assigned to DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD., Changwon-si (KR)
Filed by DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD., Changwon-si (KR)
Filed on May 26, 2021, as Appl. No. 17/331,311.
Prior Publication US 2022/0381188 A1, Dec. 1, 2022
Int. Cl. F01D 11/12 (2006.01); F02C 7/28 (2006.01)
CPC F02C 7/28 (2013.01) [F01D 11/122 (2013.01); F05D 2220/32 (2013.01); F05D 2240/55 (2013.01)] 13 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a casing;
a plurality of outer shroud blocks having a forward lip and a rearward lip, each of the plurality of outer shroud blocks coupled to the casing by the respective forward lip and the respective rearward lip to form an annular array about a centerline of the gas turbine engine;
at least one inner shroud block coupled to each outer shroud block of the plurality of outer shroud blocks, each inner shroud block having an inner surface disposed towards the centerline of the gas turbine engine, and each side of the inner shroud block having a groove formed therein;
an impingement plate comprising a rearward lip, the impingement plate disposed between the outer shroud block and the at least one inner shroud block;
a plurality of turbine blades circumferentially spaced around the centerline of the gas turbine engine, the plurality of turbine blades configured to rotate in a first direction about the centerline of the gas turbine engine;
a plurality of ridges projecting radially inward from the inner surface, the plurality of ridges extending laterally across the inner surface in parallel to the first direction;
a first seal disposed between the rearward lip of the impingement plate and the at least one inner shroud block; and
a second seal extending from the groove of one inner shroud block to the groove of an adjacent inner shroud block.