Turbine disk interstage seal system
In a turbine engine of a type having a turbine section including first and second stage disks mounted on a compressor shaft, an interstage seal system is described comprising: an outer, generally cylindrical housing having a forward arm engaging the first stage disk and a rearward arm engaging the second stage disk, the forward arm and the first stage disk including means forming a bayonet connection there between, and means forming an anti-rotation connection there between; the forward arm including a forwardly-facing axial stop abutting the first stage disk; and a radially outward-facing radial stop abutting the first stage disk, the axial and radial stop engagements preventing forward axial and outward radial deflection, respectively, of the forward arm; the bayonet connection includes the forward arm having a plurality of radially inward-extending teeth; and the first stage disk having a plurality of radially outwardly-extending tabs, the tabs being spaced apart from each other and from the first stage disk to receive the teeth between the tabs, and between the tabs and the first stage disk in the bayonet connection, whereby rearward axial movement of the forward arm relative to the first stage disk is prevented; and the first stage disk includes at least one blade having a tab projecting rearwardly from a root thereof: and the forward arm includes forwardly projecting tab means for meshing with the tab.
- Assignee:
- General Electric Co., Cincinnati, OH (United States)
- Patent Number(s):
- US 5236302; A
- Application Number:
- PPN: US 7-785404
- OSTI ID:
- 6241460
- Resource Relation:
- Patent File Date: 30 Oct 1991
- Country of Publication:
- United States
- Language:
- English
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