Skip to Content
Return to Search

SWIRLING MIDFRAME FLOW FOR GAS TURBINE ENGINE HAVING ADVANCED TRANSITIONS

United States Patent Application

*** PATENT GRANTED ***
20150167986
9,528,706
A1
View the Complete Application at the US Patent & Trademark Office
A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
Montgomery, Matthew D. (Jupiter, FL), Charron, Richard C. (West Palm Beach, FL), Rodriguez, Jose L. (Lake Mary, FL), Kusters, Bernhard W. (Jupiter, FL), Morrison, Jay A. (Titusville, FL), Beeck, Alexander R. (Orlando, FL)
14/ 105,313
December 13, 2013
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT [0001] Development for this invention was supported in part by Contract No. DE-FC26-05NT42644, awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.