SEAL ASSEMBLY INCLUDING GROOVES IN AN AFT FACING SIDE OF A PLATFORM IN A GAS TURBINE ENGINE
摘要
A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a stationary vane assembly and a rotating blade assembly axially upstream from the vane assembly. A platform of the blade assembly has a radially outwardly facing first surface, an axially downstream facing second surface defining an aft plane, and a plurality of grooves extending into the second surface such that the grooves are recessed from the aft plane. The grooves are arranged such that a circumferential space is defined between adjacent grooves. During operation of the engine, the grooves impart a circumferential velocity component to purge air flowing out of a disc cavity through the grooves to guide the purge air toward a hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.
申请公布号
EP3052761(A1)
申请公布日期
2016.08.10
申请号
EP20140776771
申请日期
2014.09.09
申请人
SIEMENS AKTIENGESELLSCHAFT
发明人
LEE, CHING-PANG;THAM, KOK-MUN;SCHROEDER, ERIC;JOHNSON, ERIK;MULLER, DUSTIN;COPPESS, STEVEN;SHIVANAND, MANJIT;MURIITHI, KAHWAI G.