Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

A gas supply system is provided herein. The gas supply system includes a fuel oxygen reduction unit having a circuit defining a gas flowpath for a flow of a stripping gas. A reservoir is in selective fluid communication with the fuel oxygen reduction unit and is configured to store a portion of the stripping gas from the circuit. The reservoir is further configured to be in selective fluid communication with the fuel system component when installed in a vehicle to provide the stored portion of the stripping gas to the fuel system component in response to detection of a purge condition.

The gas turbine engine can have an air mover configured for generating a flow of air around a rotation axis; a surface extending around the rotation axis delimiting a passage for the flow of air downstream of the air mover; an electric machine disposed within the passage and coupled to the air mover; a coolant circuit having: an evaporator circumferentially disposed around at least part of the electric machine and in thermal communication therewith; a condenser having a surface cooler circumferentially disposed at least partially around the surface and in thermal communication therewith; a first conduit fluidly connecting an upper region of the evaporator to an upper region of the condenser; and a second conduit fluidly connecting a lower region of the condenser to a lower region of the evaporator; and a coolant fluid in the coolant circuit.

The gas turbine engine can have an air mover configured for generating a flow of air around a rotation axis; a surface extending around the rotation axis delimiting a passage for the flow of air downstream of the air mover; an electric machine disposed within the passage and coupled to the air mover; a coolant circuit having: an evaporator circumferentially disposed around at least part of the electric machine and in thermal communication therewith; a condenser having a surface cooler circumferentially disposed at least partially around the surface and in thermal communication therewith; a first conduit fluidly connecting an upper region of the evaporator to an upper region of the condenser; and a second conduit fluidly connecting a lower region of the condenser to a lower region of the evaporator; and a coolant fluid in the coolant circuit.

A heat exchange system for an aircraft engine includes a heat exchanger, a main conduit directing fuel to a combustion chamber of the aircraft engine, and a pump connected to the main conduit. A return conduit receives excess fuel outputted by the pump and exceeding a fuel requirement of the combustion chamber. The return conduit, which is connected to a fuel conduit of the heat exchanger, has an inlet connected to the main conduit downstream of the pump and an outlet connected to the main conduit upstream of the pump. An actuator has an inlet connected to the main conduit downstream of the pump and an outlet connected to the main conduit upstream of the pump while bypassing the heat exchanger, wherein a pressure differential between the actuator inlet and the actuator outlet remains substantially unchanged with variations of a fuel flow through the heat exchanger.

In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.

In one aspect of the present disclosure, there is provided a gas turbine engine. The gas turbine engine includes a primary gas path having, in fluid series communication: an air inlet, a compressor fluidly connected to the air inlet, a combustor fluidly connected to an outlet of the compressor, and a turbine section fluidly connected to an outlet of the combustor section. In embodiments, a hydrogen expansion turbine is in fluid communication to receive hydrogen from the gaseous hydrogen outlet of the heat exchanger. In certain embodiments, the gas turbine engine includes a heat exchanger having a gas conduit fluidly connected to the primary gas path, and a fluid conduit in fluid isolation from the gas conduit and in thermal communication with the gas conduit.

A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.

A surface heat-exchanger for a turbojet engine nacelle between a fluid (C) to be cooled down and air (F) includes a circulation duct of the fluid (C) to be cooled down disposed in contact with air. The circulation duct includes a plurality of channels extending substantially in the same direction with a distance (D) between two adjacent channels between two and five times the width (L) of the channels, each channel having a wall with an area intended to be in contact with air and an area opposite to the area intended to be in contact with air.