Injector

A turbine containing system (10) is disclosed. The system includes an intake section (14), a compressor section (16) downstream from the intake section (14), a combustor section (20) having a primary combustion system (22) downstream from the intake section (14), a secondary combustion system (24) downstream from the primary combustion system (22), a turbine section (18), an exhaust section (26) and a load (28). The secondary combustion system (24) includes an injector for transversely injecting a secondary fuel into a stream of combustion products of the primary combustion system (22). The injector includes a coupling (30), a wall (34) defining an airfoil shape circumscribing a fuel mixture passage (36), and at least one exit (34) for communication between said fuel mixture passage (36) and said stream of primary combustion products.