Stator and multiple piece seal
A gas turbine engine is described comprising a compressor section, a combustor section and a turbine section arranged in flow series and defining an annular flow path extending axially from the compressor section through the turbine section, the engine further comprising a plurality of air passageways extending from the compressor section to a plenum in the turbine section so that the pressure in the plenum is greater than the pressure in a portion of the flow path disposed within the turbine section, the turbine section comprising a stator vane array upstream of a rotor blade array, the stator vane array having a plurality of vanes interposed in the turbine section flow path and mounted radially between a segmented outer end wall and a segmented inner end wall, each of the segments, of the inner and outer end walls, having a narrow gap there between, the gap being in fluid communication with the plenum and the turbine section flow path defining a pressure differential across the gap, the stator vane array further comprising a multiple piece seal inserted in each of the gaps, the multiple piece seal comprising a first sealing member having a thickness sufficiently small so that the first sealing member deforms into sealing contact across the gap when exposed to the pressure differential, and a second sealing member having a thickness sufficiently large to prevent both the first and second sealing members from buckling when the multiple piece seal is inserted into the gap the first and second sealing members being attached at one end.
- Assignee:
- Allied-Signal Inc., Morris Township, NJ (United States)
- Patent Number(s):
- US 5221096; A
- Application Number:
- PPN: US 7-899827
- OSTI ID:
- 6406502
- Resource Relation:
- Patent File Date: 16 Jun 1992
- Country of Publication:
- United States
- Language:
- English
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