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Swirling midframe flow for gas turbine engine having advanced transitions

United States Patent

9,528,706
December 27, 2016
View the Complete Patent at the US Patent & Trademark Office
U.S. Department of Energy - Visit the Office of the Assistant General Counsel for Technology Transfer & Intellectual Property Website
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)
SIEMENS ENERGY, INC. (Orlando, FL)
14/ 105,313
20150167986
December 13, 2013
STATEMENT REGARDING FEDERALLY SPONSORED DEVELOPMENT 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.