Turbine engine interstage seal
A seal structure is described for a turbine engine, the turbine engine including a housing surrounding a centrifugal compressor having a rotor, and a radial inflow turbine including a turbine rotor, the compressor rotor and the turbine rotor being disposed in back-to-back relation, the turbine rotor being drivingly connected with the compressor rotor and axially spaced therefrom to define an annular gap there between, the gap radially bounded at its outer periphery by the housing and at its inner periphery by an annular surface intermediate the compressor rotor and the turbine rotor an annular sealing member disposed in the gap to control air flow from the compressor toward the turbine; the annular sealing member the first axial direction, and a third annular wall portion joining with the second annular wall portion and extending inward therefrom towards the surface intermediate the compressor rotor and the turbine rotor, and biasing means cooperating with the housing for urging the seal structure toward the turbine rotor.
- Assignee:
- Allied-Signal Inc., Morris Township, NJ (United States)
- Patent Number(s):
- US 5233824; A
- Application Number:
- PPN: US 7-595158
- OSTI ID:
- 6304369
- Resource Relation:
- Patent File Date: 10 Oct 1990
- Country of Publication:
- United States
- Language:
- English
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