Coolable seal assembly for a gas turbine engine
This patent describes a gas turbine engine of the type having an axis A, an annular flow path for working medium gases, a flow path for cooling fluid spaced radially from the working medium flow path and arcuate seal segments extending circumferentially about the axis to bound the working medium flow path. The arcuate seal segments have at least one pair of arcuate seal segments which includes a first seal segment and a second seal segment that is spaced circumferentially from the first seal segment leaving a gap G therebetween that varies in size during operative conditions. The improvement described here comprises: an orifice plate disposed in the gap which extends axially between the pair of segments and across the gap G. It has an opening in flow communication with the flow path for cooling fluid for directing cooling air through the orifice plate and into the radial gap G at a location which is upstream of a portion of the orifice plate with a radial component of velocity, and means for variably restricting the flow through the opening which is adapted to variably overlap the opening under operative conditions and which has a position relative to the opening which is responsive to the size of the gap G.
- Assignee:
- United Technologies Corp., Hartford, CT
- Patent Number(s):
- US 4650394
- OSTI ID:
- 6652021
- Resource Relation:
- Patent File Date: Filed date 13 Nov 1984
- Country of Publication:
- United States
- Language:
- English
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