Catalytic oxidation element for a gas turbine engine

1. A catalytic oxidation element for a gas turbine engine comprising:

a pressure boundary element having an inlet end receiving a first fluid flow and an outlet end;

an opening in an upstream portion of the pressure boundary element allowing fluid communication across the pressure boundary element between the first fluid flow and a second fluid flow to generate a combustion mixture flow;

a catalytic surface disposed on a downstream portion of the pressure boundary element and exposed to the combustion mixture flow for at least partially combusting the combustion mixture flow;

a support plate connected to the inlet end of the pressure boundary element; and

a first baffle disposed downstream of the support plate and upstream of the opening and comprising a first passageway allowing passage of the pressure boundary element therethrough, the first baffle further defining a first space between the support plate and the first baffle for distributing the second fluid flow;

wherein the pressure boundary element comprises a tube, wherein the opening is formed in the tube, and wherein the opening comprises a plurality of holes formed in the tube.

2. The catalytic oxidation element of claim 1 , the first baffle further comprising a first gap around the pressure boundary element sized to regulate passage of the second fluid flow through the first baffle around the pressure boundary element.

3. The catalytic oxidation element of claim 1 , further comprising a first manifold in fluid communication with the first space between the support plate and the first baffle, the first manifold receiving the second fluid flow and discharging the second fluid flow into the first space.

4. The catalytic oxidation element of claim 1 , further comprising a second baffle, comprising a second passageway allowing passage of the pressure boundary element therethrough, the second baffle disposed downstream of the opening in the pressure boundary element, the second passageway defining a second gap around the pressure boundary element for regulating the second fluid flow past the second baffle.

5. The catalytic oxidation element of claim 4 , further comprising a second manifold in fluid communication with a second space between the first and second baffles, the second manifold receiving a portion of the first fluid flow and discharging the portion of the first fluid flow into the second space.

6. The catalytic oxidation element of claim 5 , further comprising a second boundary element conducting the portion of the first fluid flow from an upstream side of the support plate to the second space to bypass the first space.

7. The catalytic oxidation element of claim 1 , wherein the first fluid flow comprises a cooling fluid.

8. The catalytic oxidation element of claim 7 , wherein the cooling fluid contains no combustible fuel.

9. The catalytic oxidation element of claim 1 , wherein the second fluid flow comprises a combustible fuel.

10. The catalytic oxidation element of claim 9 , wherein the combustible fuel contains no oxidizer.

11. The catalytic oxidation element of claim 1 , wherein the catalytic surface comprises a surface of the pressure boundary element.

12. A catalytic combustor for a gas turbine engine comprising:

a plurality of catalytic oxidation elements circumferentially disposed about a central axis, each catalytic oxidation element providing at least partial mixing of a first portion of a compressed air flow and at least a first portion of a combustible fuel flow to generate a combustion mixture flow and at least partially combusting the combustible fuel in the combustion mixture flow, each catalytic oxidation element discharging a partially combusted mixture flow and a second portion of the compressed air flow;

a first annular fuel manifold circumferentially disposed radially outward of and proximate to respective inlet ends of the catalytic oxidation elements, the first annular fuel manifold in fluid communication with at least some of the catalytic oxidation elements;

a combustion completion chamber disposed downstream of the catalytic oxidation elements receiving respective partially combusted mixture flows and compressed air flows discharged from the catalytic oxidation elements and discharging a hot combustion gas from an outlet end; and

an annular shell disposed radially outward of the catalytic oxidation elements and completely surrounding the catalytic oxidation elements and the combustion completion chamber, the annular shell hermetically sealing the combustion completion chamber against passage of fluids not discharged from the catalytic oxidation elements into the combustion completion chamber and against passage of fluids not discharged from the outlet end out of the combustion completion chamber.

13. The catalytic combustor of claim 12 , wherein the manifold further comprises an air turning structure for directing at least the first portion of the compressed air flow into respective inlet ends of the catalytic oxidation elements.

14. The catalytic combustor of claim 12 , further comprising a second annular fuel manifold circumferentially disposed radially outward of and proximate to respective inlet ends of the catalytic oxidation elements, the second annular fuel manifold in fluid communication with different catalytic oxidation elements than the first annular fuel manifold to allow providing a second portion of the combustible fuel flow to the different catalytic modules.

15. A gas turbine engine comprising the catalytic combustor of claim 12 .