Turbine disk interstage seal axial retaining ring

In a turbine engine of a type having a turbine section including first and second stage disks, an interstage seal located between said disks, said seal including a web portion having an aft arm extending from said web and having a peripheral rim adjacent said second stage disk, an interstage seal aft arm axial retention system comprising:

• a peripheral groove located in said peripheral rim;
• a plurality of tabs located on said second stage disk extending radially inwardly adjacent said peripheral rim;
• means located in said groove for forming a bayonet connection with said second stage disk tabs, wherein said bayonet connection means includes a split retaining ring having two ends and a plurality of radially outwardly extending tabs;
• and
• means for preventing circumferential rotation of said axial retention system, wherein said circumferential prevention means is a turbine blade.