A system includes a combustor. The combustor has a combustor wall with a combustor dome at an upstream end of the combustor wall, and an outlet at a downstream end of the combustor wall opposite the upstream end. The combustor wall includes an inner wall portion and an outer wall portion defining an interior of the combustor therebetween. Each of the inner wall portion and outer wall portion extends from the combustor dome to the downstream end of the combustor wall. The combustor wall includes an air cooling passage embedded inside at least one of the inner wall portion and the outer wall portion. The air cooling passage extends from the upstream end of the combustor wall to the downstream end of the combustor wall.

A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

A turbo-expanding cracking assembly includes a plurality of stages each including a rotating blade coupled to an output shaft and a fixed stator, at least one heat exchanger configured to transfer heat to an ammonia containing fuel flow, and a catalyst that is configured to decompose an ammonia containing fuel flow into a flow containing hydrogen (H2).

System for chemical engine systems or air-breathing engine systems comprising: a catalytic combustion and/or addition of metallic additives, which can additionally adapt the combustion by homogeneous, respectively heterogeneous catalysts. The adaptation of combustion rate, combustion pressure, combustion temperature, latent heat and other conditions (e.g. heat reflections) can be used in a variety of technological ways. This enables optimization of combustion chamber geometry and, for example, reduction of profile losses. Lossy energy conversions are to be minimized, or specifically adapted (e.g. to a variable ambient pressure during vertical starts). To protect the adapted combustion, methods are named to avoid e.g. fouling, aging of the reactive surface, destructive pressure shocks and especially thermal damage. The potential through further technological additions, e.g. by means of contactless ignition or superordinate process concept is pointed out.

A gas turbine engine including a catalytic reactor and a combustor. The catalytic reactor is configured (i) to receive hydrogen fuel, (ii) to receive air containing oxygen, (iii) to catalytically react at least a portion of the oxygen in the air with at least a portion of the hydrogen in the hydrogen fuel to produce water, and (iv) to output diluent comprising the catalytically produced water. The combustor includes (a) a combustion chamber and (b) at least one nozzle that is fluidly coupled to the catalytic reactor to receive the diluent output by the catalytic reactor and configured to inject the diluent into the combustion chamber.

A gas turbine engine including a catalytic reactor and a combustor. The catalytic reactor is configured (i) to receive hydrogen fuel, (ii) to receive air containing oxygen, (iii) to catalytically react at least a portion of the oxygen in the air with at least a portion of the hydrogen in the hydrogen fuel to produce water, and (iv) to output diluent comprising the catalytically produced water. The combustor includes (a) a combustion chamber and (b) at least one nozzle that is fluidly coupled to the catalytic reactor to receive the diluent output by the catalytic reactor and configured to inject the diluent into the combustion chamber.

A gas turbine engine for an aircraft includes a turbine section and an exhaust section configured to receive an exhaust gas stream from the turbine section. The exhaust section includes a monolithic catalyst structure configured to remove nitrogen oxides (NO.sub.x) from the exhaust gas stream.

A gas turbine engine for an aircraft includes a turbine section and an exhaust section configured to receive an exhaust gas stream from the turbine section. The exhaust section includes a monolithic catalyst structure configured to remove nitrogen oxides (NO.sub.x) from the exhaust gas stream.

An exhaust gas purification device (26) for a gas turbine engine (10) comprises a catalyst chamber (64, 96) defined in an exhaust gas passage (22), a reduction agent container (32) containing a solid material that releases a reduction agent gas effective for NOx reduction when heated, a heating device (36, 38) for heating the solid material contained in the reduction agent container, and a reduction agent gas supply passage (48) for supplying the reduction agent gas released from the solid material into the catalyst chamber.

An exhaust gas purification device (26) for a gas turbine engine (10) comprises a catalyst chamber (64, 96) defined in an exhaust gas passage (22), a reduction agent container (32) containing a solid material that releases a reduction agent gas effective for NOx reduction when heated, a heating device (36, 38) for heating the solid material contained in the reduction agent container, and a reduction agent gas supply passage (48) for supplying the reduction agent gas released from the solid material into the catalyst chamber.