Abstract: A gas turbine engine (10) includes a catalytic oxidation element (62). The catalytic oxidation element includes a pressure boundary element (24) receiving a first fluid flow (16). An opening (28) in an upstream portion (26) of the pressure boundary element allows fluid communication across the pressure boundary element between the first and a second fluid flow (20) to generate a combustion mixture flow (30). A catalytic surface (34) disposed on a downstream portion (32) of the pressure boundary element is exposed to the combustion mixture flow for at least partially combusting the combustion mixture flow.

Abstract: A catalytic combustor (28) includes a tubular pressure boundary element (90) having a longitudinal flow axis (e.g., 56) separating a first portion (94) of a first fluid flow (e.g., 24) from a second portion (95) of the first fluid flow. The pressure boundary element includes a wall (96) having a plurality of separate longitudinally oriented flow paths (98) annularly disposed within the wall and conducting respective portions (100, 101) of a second fluid flow (e.g., 26) therethrough. A catalytic material (32) is disposed on a surface (e.g., 102, 103) of the pressure boundary element exposed to at least one of the first and second portions of the first fluid flow.

Abstract: A catalytic oxidation module (28) for a gas turbine engine (10) includes a bundle (50) of tubular elements (30) separating a first fluid flow of a combustion mixture (24) from a second fluid flow (e.g., 26). Each of the tubular elements has an inlet end (42) and an outlet end (44) in fluid communication with a downstream plenum (36) and a respective end portion (60) comprising a plurality of spaced apart longitudinal fingers (58). The fingers of each tubular element are joined at abutting fingers of respective adjacent elements to retain the tubes at the respective end portions with sufficient flexibility to allow relative movement between the adjacent tubular elements. A catalyst (32) is disposed on respective surfaces of a plurality of the tubular elements exposed to at least one of the first fluid flow and second fluid flow.

Abstract: A catalytic combustor (28) includes a plurality of concentric tubular pressure boundary elements (46). The pressure boundary elements are arranged to form a first annular space (e.g., 50) conducting a first fluid flow (e.g., 60) and a second annular space (e.g. 49), separate from the first annular space, conducting a second fluid flow (e.g., 58). A catalytic material (32) is disposed on a surface (e.g., 64) of at least one of the pressure boundary elements and exposed to at least one of the fluid flows.

Abstract: A gas turbine engine (10) includes a catalytic oxidation element (62). The catalytic oxidation element includes a pressure boundary element (24) receiving a first fluid flow (16). An opening (28) in an upstream portion (26) of the pressure boundary element allows fluid communication across the pressure boundary element between the first and a second fluid flow (20) to generate a combustion mixture flow (30). A catalytic surface (34) disposed on a downstream portion (32) of the pressure boundary element is exposed to the combustion mixture flow for at least partially combusting the combustion mixture flow.

Abstract: A catalytic combustor (14) includes a first catalytic stage (30), a second catalytic stage (40), and an oxidation completion stage (49). The first catalytic stage receives an oxidizer (e.g., 20) and a fuel (26) and discharges a partially oxidized fuel/oxidizer mixture (36). The second catalytic stage receives the partially oxidized fuel/oxidizer mixture and further oxidizes the mixture. The second catalytic stage may include a passageway (47) for conducting a bypass portion (46) of the mixture past a catalyst (e.g., 41) disposed therein. The second catalytic stage may have an outlet temperature elevated sufficiently to complete oxidation of the mixture without using a separate ignition source. The oxidation completion stage is disposed downstream of the second catalytic stage and may recombine the bypass portion with a catalyst exposed portion (48) of the mixture and complete oxidation of the mixture.

Abstract: A catalytic combustor includes a plurality of rectangular, tubular subassemblies having the catalyst coating on their outside surfaces. The subassemblies are held in spaced relationship within channels in support walls so that the catalyst coated surfaces of adjacent subassemblies define a catalyst-coated channel, and the interior of the tubular subassemblies defines uncoated channels. This structure permits precise location and support for the various subassemblies, provides wide flexibility in selecting the number and size of catalyst coated subassemblies, and provides for multiple possible flow paths for cooling air and fuel-air mixture through the catalytic combustor.

Abstract: A catalytic combustor includes a plurality of rectangular, tubular subassemblies having the catalyst coating on their outside surfaces. The subassemblies are held in spaced relationship within channels in support walls so that the catalyst coated surfaces of adjacent subassemblies define a catalyst-coated channel, and the interior of the tubular subassemblies defines uncoated channels. This structure permits precise location and support for the various subassemblies, provides wide flexibility in selecting the number and size of catalyst coated subassemblies, and provides for multiple possible flow paths for cooling air and fuel-air mixture through the catalytic combustor.