Radial inflow combustor

Power plants – Combustion products used as motive fluid – Combined with regulation of power output feature

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60737, F02C 700, F23R 316

Patent

active

050690337

ABSTRACT:
In order to significantly reduce the carbon produced in a combustor, and thus reduce or eliminate carbon buildup on combustor walls, a gas turbine engine (10) has a radial compressor (12), an axial turbine (16), and a radial combustor (20). The radial combustor (20) includes a pair of axially spaced radially extending walls (62, 64) joined at radially outward extremes by a generally cylindrical wall (36). The walls (36, 62, 64) define a radial combustion space (24) in communication with both the radial compressor (12) and a turbine nozzle (22) and admit compressed air into the radial combustion space (24) in a manner avoiding formation of an air film on the generally cylindrical wall (36). The radial combustor (20) also includes a fuel injector (34) for injecting a liquid fuel into the radial combustion space (20) to impact the liquid fuel directly onto an inner surface (36a) of the generally cylindrical wall (36) to form a liquid fuel film (82) thereon. With this arrangement, the liquid fuel is centrifuged onto the inner surface (36a) of the generally cylindrical wall (36) to thereby produce a stabilized stratification within the radial combustion space in the form of the liquid fuel film (82), a gaseous fuel layer (80), a hot flame layer (84) and a cold air layer (86).

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