Gas turbinen rotor blade
Number of patents in Portfolio can not be more than 2000
United States of America Patent
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-
Aug 22, 2017
Issued Date -
Jun 18, 2015
app pub date -
Nov 21, 2014
filing date -
Nov 27, 2013
priority date (Note) -
Abandoned
status (Latency Note)
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Abstract
A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.
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