Abstract:
A combustor for a turbine engine includes an outer liner (34) having a row of circumferentially distributed outer combustion air holes and an inner liner (32) circumscribed by the outer liner (34) and having a row of circumferentially distributed inner combustion air holes. The inner and outer liners (32, 34) each include at least a major air hole (104) having a first hole size, an intermediate air hole (108) having a second hole size, and a minor air hole (106) having a third hole size. The first, second, and third hole sizes are all different from each other.
Abstract:
A catalyst conduit for a catalytic reactor (10) of a turbine combustor, the conduit comprising a tube (14) including an inlet (26) and an outlet (32), and a wall with an interior surface (34) and an exterior surface (36). The tube (14) contains a variation in its cross sectional area along at least a portion of its length to change a property of a fluid flowing adjacent the wall of the tube (14). An oxidation catalyst (44) is deposited on at least a portion of the tube (14).
Abstract:
A catalyst conduit (14) for a catalytic comprises a tube (14) including an inlet (26) and an outlet (28), an interior surface (34) and an exterior surface (36), and an insert (16) for modifying fluid flow mounted within the tube (14). An oxidation catalyst (44) is deposited on at least a portion of the tube (14).
Abstract:
A catalyst conduit for a catalytic reactor (10) of a turbine combustor, the conduit comprising a tube (14) including an inlet (26) and an outlet (32), and a wall with an interior surface (34) and an exterior surface (36). The tube (14) contains a variation in its cross sectional area along at least a portion of its length to change a property of a fluid flowing adjacent the wall of the tube (14). An oxidation catalyst (44) is deposited on at least a portion of the tube (14).
Abstract:
An article has a metallic substrate having a first emissivity. A thermal barrier coating atop the substrate may have an emissivity that is a substantial fraction of the first emissivity.
Abstract:
A combustor assembly (12) includes a convergent segment (34) followed by a divergent segment (36) to advantageously improve combustion. The combustor assembly includes a first segment (34) beginning at a forward end (24) that transitions to a second segment (36) past a transition segment (58) in a direction along a combustor axis (22) toward an aft end (26). The reduction in cross-sectional area within the first segment (34) provides desirable fuel and air mixing properties. The convergent first segment (34) in combination with the divergent second segment (36) decreases residence time of fuel-air mixture within the combustor chamber that decreases production of undesirable emissions from the combustor assembly.
Abstract:
A combustor liner assembly (10) includes an outer shell (14) made of a ceramic composite and an inner heat shell (16) that is supported within the outer shell (14). The inner heat shield (16) defines a surface that is exposed to combustion gases. The inner heat shield (16) is made of material that is compatible with the ceramic matrix composite and that provides favorable thermal gradient capability for a combustion chamber.