Gas turbine engine flow duct having integrated heat exchanger

A flow duct for a gas turbine engine comprising:

• the flow duct disposed along a centerline of the gas turbine engine and defining a flow duct passage;
• a plurality of heat transfer components integrated in the flow duct and configured to have a variable geometry arrangement for adjusting static pressure in the flow duct passage downstream of the heat transfer components;
• and
• an adjustable nozzle positioned within the flow duct, the adjustable nozzle having a first nozzle wall assembly and a second nozzle wall assembly that define a nozzle span, such that air passing through the flow duct passes through the nozzle span;
• wherein:
• the first nozzle wall assembly includes a first nozzle wall and the second nozzle wall assembly includes a second nozzle wall;
• and
• the first and second nozzle wall assemblies are each adjustable to define the nozzle span between the first nozzle wall and the second nozzle wall;
• further comprising an adjustable diffuser positioned downstream of the adjustable nozzle, the adjustable diffuser including a first diffuser wall assembly and a second diffuser wall assembly, the first diffuser wall assembly having a first diffuser wall and the second diffuser wall assembly having a second diffuser wall, wherein the first and second diffuser wall assemblies are each adjustable to adjust a diffuser span between the first diffuser wall and the second diffuser wall;
• wherein each of the first and second nozzle wall assemblies are four-body linkages, each having pivotal joints that adjust the nozzle span between the first nozzle wall and the second nozzle wall;
• and
• wherein each of the first and second diffuser wall assemblies are four-body linkages, each having pivotal joints that adjust the diffuser span between the first diffuser wall and the second diffuser wall.

A method of adjusting pressure distribution in a flow duct for a gas turbine engine, the flow duct having heat exchangers comprising:

• providing fluid flow through a stream flow passage of the flow duct disposed along a centerline of the gas turbine engine;
• using first and second rows of heat exchangers disposed along the engine centerline of the gas turbine engine and integrated in the flow duct in fluid communication with the stream flow passage of the flow duct to adjust the pressure difference across the first and second rows of heat exchangers;
• adjusting airflow in the flow duct by passing air through an adjustable nozzle that is positioned within the flow duct, the adjustable nozzle having a first nozzle wall assembly and a second nozzle wall assembly that define a nozzle span;
• and
• adjusting the airflow by adjusting the nozzle span;
• wherein the first nozzle wall assembly includes a first nozzle wall and a second nozzle wall that define the nozzle span, the method further comprising:
• passing the air flow from the adjustable nozzle to an adjustable diffuser that is downstream of the adjustable nozzle, the adjustable diffuser including a first diffuser wall assembly and a second diffuser wall assembly, the first diffuser wall assembly having a first diffuser wall and the second diffuser wall assembly having a second diffuser wall, wherein the first and second diffuser wall assemblies are each adjustable to adjust a diffuser span between the first diffuser wall and the second diffuser wall, such that the air passing from the nozzle span passes into the diffuser span;
• and
• scooping air in a scoop that is positioned aft of the first nozzle wall and positioned to transfer air passing through the nozzle span to a location near a start of the adjustable diffuser.