PRESSURE REGULATED PISTON SEAL FOR A GAS TURBINE COMBUSTOR LINER

A seal assembly seals a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly includes a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (P-high) bypass airflow exiting a compressor to the cavity. The high-pressure (P-high) bypass airflow exerting a radial force on the piston ring. 一种密封组件，其用于在燃气涡轮中的燃烧器衬套和下游部件(例如第一级涡轮喷嘴)的界面处密封燃气涡轮热气体路径流。所述密封组件包括限定腔体的活塞环密封壳体以及设置在所述腔体内的活塞环。活塞环围绕燃烧器衬套周向地设置。活塞环响应调节压力以确保活塞环与燃烧器衬套的外表面的密封接合。密封组件包括一个或多个分段通槽、凸块或通道特征结构中的至少一种，以提供离开压缩机流到腔体的高压(P高)旁路空气流的流动通过。高压(P高)旁路空气流对