GAS TURBINE ENGINE, PART THEREOF, AND ASSOCIATED METHOD OF OPERATION
The gas turbine engine part can have a heat sink portion having a surface having a plurality of protrusions distributed over an area of the surface, the protrusions projecting away from the surface and including protrusions being adjacent to one another and collectively forming an identifier. A flow...
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| Format: | Patent |
| Sprache: | eng ; fre |
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| Zusammenfassung: | The gas turbine engine part can have a heat sink portion having a surface having a plurality of protrusions distributed over an area of the surface, the protrusions projecting away from the surface and including protrusions being adjacent to one another and collectively forming an identifier. A flow of cooling air can be directed to the protrusions forming the identifier to cool the part. |
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