Secondary first-stage blade for air compressor of high power combustion gas turbine
A secondary first-stage blade for an air compressor of a high power combustion gas turbine relates to a blade of the air compressor. The secondary first-stage blade aims at resolving the problem that an existing secondary first-stage blade is instable in quality, low in efficiency, short in service...
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Format: | Patent |
Sprache: | chi ; eng |
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Zusammenfassung: | A secondary first-stage blade for an air compressor of a high power combustion gas turbine relates to a blade of the air compressor. The secondary first-stage blade aims at resolving the problem that an existing secondary first-stage blade is instable in quality, low in efficiency, short in service life and capable of affecting safe running of the air compressor. The secondary first-stage blade is integrally formed by a blade working portion (1) and a blade root (2) from the top to the bottom, wherein a shaped line of the blade working portion (1) is a variable cross-section twisted blade. Geometry data of the section of the blade from the root to the top are that the cross section height H from section A-A to section DD-DD is -9.27 to 455.498 mm, the axial width B is 213.368 to 123.193 mm, the chord length b is 223.658 to 239.254 mm, the bending angle alpha is 17.667 degrees to 59.508 degrees, the maximum thickness Dmax of the shaped line is 25.383 to 7.140 mm, the thickness DE of an air outlet edge at the p |
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