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An anti-rotation system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk having a rearwardly extending aft shaft and a second stage disk. The interstage seal includes a rearwardly projecting conical arm mounted on the first stage

An anti-rotation system for an interstage seal located in a gas turbine engine of a type having a turbine section including a first stage disk having a rearwardly extending aft shaft and a second stage disk. The interstage seal includes a rearwardly projecting conical arm mounted on the first stage disk. The interstage seal anti-rotation system includes a key inserted within an opening formed between the aft shaft and the conical arm for preventing circumferential movement between the aft shaft and the conical arm by providing a double shear plane between the aft shaft and the conical arm. A circumferential wire is inserted within a slot formed in the conical arm and a groove on the key for preventing axial movement of the key.

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1. In a turbine engine of a type having a turbine section including first and second stage disks, and an interstage seal located between said disks, said seal including a web portion and a bore concentric with said first stage disk, an interstage seal anti-rotation system comprising: said bore an

1. In a turbine engine of a type having a turbine section including first and second stage disks, and an interstage seal located between said disks, said seal including a web portion and a bore concentric with said first stage disk, an interstage seal anti-rotation system comprising: said bore and said first stage disk having interconnecting bayonet means for preventing relative axial movement between said first stage disk and said seal; key means interconnected with said bayonet means and said first stage disk for preventing relative circumferential movement between said interstage seal and said first stage disk; and retaining means for preventing axial movement of said key means relative to said seal and said first stage disk, whereby said key means is retained in said interconnected position with said seal and said first stage disk; and wherein said key means includes a key having a radially outwardly extending boss which contacts an aft surface of an aft conical arm of said bore for proper axial positioning of said key relative to said conical arm. 2. In a turbine engine of a type having a turbine section including first and second stage disks, and an interstage seal located between said disks, said seal including a web portion and a bore concentric with said first stage disk, an interstage seal anti-rotation system comprising: said bore and said first stage disk having interconnecting bayonet means for preventing relative axial movement between said first stage disk and said seal; key means interconnected with said bayonet means and said first stage disk for preventing relative circumferential movement between said interstage seal and said first stage disk; and retaining means for preventing axial movement of said key means relative to said seal and said first stage disk, whereby said key means is retained in said interconnected position with said seal and said first stage disk; and wherein said bayonet means includes said first stage disk having an aft shaft including a plurality of spaced bayonet tabs; said bore having an aft conical arm including a plurality of complimentary bayonet tabs; said aft shaft bayonet tabs and said aft conical arm bayonet tabs having openings therebetween when said first stage disk and said seal interconnect; and said key means includes a key inserted into a first selected one of said openings. 3. The system of claim 2 wherein said conical arm and said key each include complementary grove means; and said retaining means includes a circumferential wire positioned in said groove means. 4. The system of claim 3 wherein said key includes a radially outwardly extending tab, positioned to abut said conical arm for proper alignment of said key relative to said conical arm. 5. The system of claim 4 wherein said wire includes a tab located on an end thereof for preventing rotation of said wire to a key release orientation. 6. The system of claim 5 wherein said conical arm includes a gap between said tabs thereon, and said wire tab is positioned in said gap, whereby said gap facilitates insertion and removal of said wire. 7. The system of claim 3 wherein said groove in said conical arm is shaped to receive said first stage disk bayonet tabs therein, whereby said wire is captured within said conical arm groove, and said conical arm bayonet tabs and said first stage disk bayonet tabs create a double shear plane with respect to said key.