ANNULAR COMBUSTOR

Assignee

Filed

Dec 21, 1989

Granted

Nov 15, 1994

Location

San Diego CA (SAIC/General Dynamics)

Abstract

The expense of fabricating an annular combustor (10) for a gas turbine is minimized by providing a combustor housing (12) including a generally axially extending sleeve (14) and an annular liner (18) disposed within the housing (12) and about the sleeve (14). The annular liner (18) has concentric inner and outer axially extending walls (20, 22) spaced from the sleeve (14 ) and the housing (12), respectively, and also has a radially extending wall (24) spaced from the housing (12 ) and interconnecting the inner and outer walls (20, 22) at one end to define a combustion chamber (26). The liner (18) is spaced from the housing (12 ) and the sleeve (14 ) to define a compressed air flow path (28) extending from a radially outer compressed air inlet (30) to a radially inner compressed air outlet (32) in communication with the combustion chamber (26) axially remote from the radially extending wall (24). The annular combustor (26) is provided with a plurality of air blast fuel injectors (42, 44) for injecting a fuel/air mixture into the liner (18 ) in a generally tangential direction adjacent the radially extending wall (24). The annular combustor (10) also includes a plurality of open ended elongated tubes (36) in the outer wall (22) adjacent the compressed air inlet (30) to provide dilution air at a point upstream of a turbine nozzle (40) and a plurality of open ended elongated tubes (34 ) in the outer wall (22) intermediate the dilution air tubes (36) and the radially extending wall (24) to provide air for combustion. With this arrangement, the combustion air tubes (34) are sized to admit sufficient combustion air to ensure completion of combustion upstream of the plane defined by the dilution air tubes (36) while forming a flame zone extending from a point adjacent the radially extending wall (24) to a point no further downstream than the dilution air tubes (36).

Source: Google Patents