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Title: Swirling midframe flow for gas turbine engine having advanced transitions

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.
Inventors:
; ; ; ; ;
Issue Date:
OSTI Identifier:
1337663
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL) NETL
Patent Number(s):
9,528,706
Application Number:
14/105,313
Contract Number:
FC26-05NT42644
Resource Relation:
Patent File Date: 2013 Dec 13
Research Org:
SIEMENS ENERGY, INC. Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS; 42 ENGINEERING

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