Turbine Air Seal with Full Backside Cooling.
Abstract
This patent application relates to air seals for use in turbo-machinery and, more particularly relates to an air seal assembly with increased cooling that is adapted to withstand elevated engine operating temperatures. The air seal comprises a full 360 degree seal ring that assemblies to the turbine by means of interlocking flanges. A two piece impingement plate which is positioned adjacent to the air seal controls and meters cooling air flow that cools ceramic seal. The backside of air seal is thereby fully cooled before heated cooling air is exhausted from the seal through holes at expansion slots and edge holes at the axial edges of the air seal.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 12, 1986
- Accession Number
- ADD012405
Entities
People
- George Liang
Organizations
- United States Department of the Air Force