Radial inflow gas turbine engine with advanced transition duct

Patent · 17 March 2015

OSTI ID:1172766

Wiebe, David J

A gas turbine engine (10), including: a turbine having radial inflow impellor blades (38); and an array of advanced transition combustor assemblies arranged circumferentially about the radial inflow impellor blades (38) and having inner surfaces (34) that are adjacent to combustion gases (40). The inner surfaces (34) of the array are configured to accelerate and orient, for delivery directly onto the radial inflow impellor blades (38), a plurality of discrete flows of the combustion gases (40). The array inner surfaces (34) define respective combustion gas flow axes (20). Each combustion gas flow axis (20) is straight from a point of ignition until no longer bound by the array inner surfaces (34), and each combustion gas flow axis (20) intersects a unique location on a circumference defined by a sweep of the radial inflow impellor blades (38).

• Research Organization: Siemens Energy, Inc., Orlando, FL (United States)
• Sponsoring Organization: USDOE
• DOE Contract Number: FC26-05NT42644
• Assignee: Siemens Energy, Inc. (Orlando, FL)
• Patent Number(s): 8,978,389
• Application Number: 13/326,392
• OSTI ID: 1172766
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS