<p>An example gas turbine engine compressor includes a first compressor section. The first compressor section includes rotating stage that includes rotating blades and a stationary stage upstream thereof that includes stationary guide vanes. The stationary vanes controllably pivot about respective pivot axises for providing flow control into the rotating stage.</p>
申请公布号
EP2904218(A1)
申请公布日期
2015.08.12
申请号
EP20130844263
申请日期
2013.01.28
申请人
UNITED TECHNOLOGIES CORPORATION
发明人
BLAKE, SEAN DJ;TEMPELMAN, WILLIAM G.;TEICHOLZ, MATTHEW D.;GENDRON, JOHN R.;WOJCIK, KERRI A.;SPIESMAN, PAUL H.;HATCH, STEWART B.;DAENTL, WYATT S.;BARTKOWSKI, GLENN D.