Abstract
A turbine arrangement and a gas turbine engine including a rim seal is configured with two cavities. The main fluid path, the two cavities, and a disc space are furthermore separated from another, but still in fluid communication with another, via three annular seal passages. The turbine arrangement also includes a plurality of cooling fluid injectors arranged underneath a radially inner vane platform. The rim seal is configured for an upstream guide vane and a downstream rotor blade.
| Original language | English |
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| Patent number | US2015354391 (A1) |
| Priority date | 28/01/13 |
| Publication status | Published - 2013 |