Abstract: In order to avoid plugging the air passageways (42a) of fuel injectors (42) with carbon particles or lumps in a gas turbine engine (10), the gas turbine engine (10) includes an annular combustor (18) having radial dilution air injection. The gas turbine engine (10) also includes a rotor (12) having turbine blades (14) and a nozzle (16) adjacent the turbine blades (14) which is adapted to direct hot gases of combustion at the turbine blades (14) to cause rotation of the rotor (12). The annular combustor (18) is disposed about the rotor (12) and has an outlet (20) to the nozzle (16), spaced inner and outer walls (22 and 24), and a generally radially extending wall (26) connecting the inner and outer walls (22 and 24). The gas turbine engine (10) further includes a housing (28) substantially surrounding the annular combustor (18) in spaced relation to the inner, outer, and radially extending walls (22, 24 and 26) to define a dilution air flow path (30).

Abstract: In order to facilitate release of a filter by-pass valve (10) for filter element replacement in relatively inaccessible locations, the valve (10) includes a housing (12) defining a filter chamber (14) having an inlet (16) communicating with the filter chamber (14) at one end (18) of the housing (12) and an outlet (20) communicating with the filter chamber (14) at the other end (22) of the housing (12). An integral filter-valve assembly (24) is removably positionable within the housing (12) between the inlet (16) and outlet (20). The filter-valve asssembly (24) supports a filter element (26) within the filter chamber (14) in a manner defining a primary flow path from the inlet (16), through the filter element (26), and to the outlet (20). The filter-valve assembly (24) also includes a by-pass valve (28) defining a secondary flow path from the inlet (16) to the outlet (20).