An aircraft engine has a combustor supplied by a hydrogen fuel system and is configured to combust hydrogen and generate water vapor. A water vapor collector receives at least part of the water vapor. A condenser is in fluid communication with the water vapor collector to receive and cool in the condenser the at least part of the water vapor and thereby condense at least part of the at least part of the flow of water vapor. A spray nozzle is in fluid communication with the condenser and operable to spray the condensed part of the at least part of the flow of water vapor onto a component of the aircraft engine.

This steam turbine is provided with a rotor shaft which rotates about an axis, a plurality of rows of moving blades which are fixed to the outside, in the radial direction, of the rotor shaft, and which are disposed spaced apart in the axial direction along the axis, a casing disposed in such a way as to cover the rotor shaft and the plurality of rows of moving blades, and rows of stationary blades which are fixed to the inside, in the radial direction, of the casing, are disposed spaced apart in the axial direction, and which are disposed on a first side, in the axial direction, of each of the plurality of rows of moving blades, wherein the rows of stationary blades are provided with: a plurality of stationary blades which are disposed spaced apart in the circumferential direction, and each of which extends in the radial direction.

This steam turbine is provided with a rotor shaft which rotates about an axis, a plurality of rows of moving blades which are fixed to the outside, in the radial direction, of the rotor shaft, and which are disposed spaced apart in the axial direction along the axis, a casing disposed in such a way as to cover the rotor shaft and the plurality of rows of moving blades, and rows of stationary blades which are fixed to the inside, in the radial direction, of the casing, are disposed spaced apart in the axial direction, and which are disposed on a first side, in the axial direction, of each of the plurality of rows of moving blades, wherein the rows of stationary blades are provided with: a plurality of stationary blades which are disposed spaced apart in the circumferential direction, and each of which extends in the radial direction.

A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.

A gas turbine engine component assembly is provided. The gas turbine engine component assembly, comprising: a first component having a first surface, a second surface opposite the first surface, and a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate capture device attached to at least one of the first component and the second component, the particulate capture device configured to aerodynamically separate the airflow from the particulate.

A dirt blocker including a support structure disposed within a gas turbine engine, the support structure defining an upstream control volume proximate a forward portion of the gas turbine engine and a downstream control volume proximate an aft portion of the gas turbine engine, the downstream control volume being opposite the upstream control volume relative to the support structure, a flow passage formed through the support structure, the flow passage configured to fluidly couple the upstream control volume with the downstream control volume; a radial contact wall formed from the support structure in fluid communication with the upstream control volume, the radial contact wall configured to intercept debris entrained within cooling air within the gas turbine engine; and a stagnation zone fluidly coupled with the flow passage, the stagnation zone configured to reduce momentum of the debris.

A dirt blocker including a support structure disposed within a gas turbine engine, the support structure defining an upstream control volume proximate a forward portion of the gas turbine engine and a downstream control volume proximate an aft portion of the gas turbine engine, the downstream control volume being opposite the upstream control volume relative to the support structure, a flow passage formed through the support structure, the flow passage configured to fluidly couple the upstream control volume with the downstream control volume; a radial contact wall formed from the support structure in fluid communication with the upstream control volume, the radial contact wall configured to intercept debris entrained within cooling air within the gas turbine engine; and a stagnation zone fluidly coupled with the flow passage, the stagnation zone configured to reduce momentum of the debris.

A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.

A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.

A system for reducing debris in a gas turbine engine includes a component that defines a component cooling channel for receiving a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris evacuation door coupled to the casing and having an open state in which the debris can exit the casing and a closed state.