General Electric Company

General Electric Company Polska Sp. Z O.o.

Eyitayo James Owoeye

Lana Maria Osusky

Bugra Han Ertas

Scott Alan Schimmels

William Morton

Ravindra Shankar Ganiger

William Dwight Gerstler

Daniel Jason Erno

Constantinos Minas

Adam Tomasz Pazinski

A rotatable heat exchanger includes a first manifold assembly, a second manifold assembly, and a core extending axially from the first manifold assembly to the second manifold assembly. The first manifold assembly, the core, and the second manifold assembly are formed to mount around and rotate with a shaft. The core includes a plurality of helical passages that extend from the first manifold assembly to the second manifold assembly. The plurality of helical passages includes a plurality of first-fluid passages fluidly coupled to the first manifold assembly and to the second manifold assembly, and a plurality of second-fluid passages fluidly coupled to the first manifold assembly and the second manifold assembly.

Rotatable heat exchanger for a gas turbine engine

A heat exchanger for a gas turbine engine includes an outer shell extending between a first end and a second end opposite the first end. The outer shell defines a first fluid chamber, a first fluid inlet adjacent the first end, and a first fluid outlet adjacent the second end. The outer shell also defines a first plurality of second fluid inlet openings located between the first end and the second end and a second fluid outlet adjacent the second end. The heat exchanger includes a manifold disposed within the outer shell. The manifold defines a second fluid chamber and a second plurality of second fluid inlet openings. The heat exchanger defines a first fluid pathway and a second fluid pathway.

Heat exchangers for gas turbine engines

A fuel cell assembly includes a plurality of fuel cells. The fuel cell includes a bipolar separator plate disposed between each fuel cell of the plurality of fuel cells. The bipolar separator plate includes one or more fuel cell sub-units each comprising a plurality of unit-cells. Each unit-cell in the plurality of unit-cells has an outer surface and defines an internal volume that extends in multiple directions between a plurality of openings defined on the outer surface. Each unit-cell in the plurality of unit-cells is disposed adjacent to a neighboring unit-cell in the plurality of unit-cells such that the plurality of unit-cells collectively define one or more channels.

Thermal management of a fuel cell assembly

A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 298.17 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m/mand 13,000 m/m.

Heat exchanger capacity for one or more heat exchangers associated with a power gearbox of a turbofan engine

A heat exchanger including a plurality of unit-cells, each unit-cell defined by a body having a plurality of faces and corners. The heat exchanger includes a first set of channels formed in the body and a second set of channels formed in the body and having corner openings on each of the corners including a distribution chamber located at the center.

Heat exchanger with a unit-cell

A heat exchanger is provided. The heat exchanger includes one or more exchanger units that each have a core and manifolds. The core of an exchanger unit is formed by multiple unit cells coupled together in flow communication to create a flow distribution grid. Each unit cell has at a first primary channel, a second primary channel, a first secondary channel in flow communication with the first primary channel, and a second secondary channel in flow communication with the second primary channel. The first secondary channel traverses through the second primary channel and the second secondary channel traverses through the first primary channel. Each manifold includes two chambers for separating fluids flowing through the heat exchanger, with one chamber being in flow communication with one of the primary channels and having one or more tubes traversing therethrough to provide flow communication between the other primary channel and the other chamber.

Heat exchanger for a gas turbine engine

A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals: and

Gas turbine engine having outlet guide vanes

A turbofan engine includes a fan, a core turbine engine having an exhaust section, and a hydrogen-exhaust gas heat exchanger in flow communication with the exhaust section and hydrogen flowing along a hydrogen supply line. The hydrogen-exhaust gas heat exchanger defines a load capacity factor determined by raising a product to a one-quarter power, the product being determined by multiplying a heat transfer surface area density associated with the hydrogen-exhaust gas heat exchanger by a process conductance parameter that relates characteristics of hydrogen, ambient air, and exhaust gas at takeoff, as well as a fan diameter of the fan and an overall pressure ratio of the turbofan engine. The load capacity factor is between 2.92 and 24 for the fan diameter being between 0.5 and 5 meters and the heat transfer surface area density being between 500 m/mand 13,000 m/m.

Hydrogen-exhaust gas heat exchanger of a turbofan engine

A gas turbine engine is provided. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in a serial flow arrangement; and an air-to-air heat exchanger having an air-to-air heat exchanger potential defined by a product raised to a half power, the product being an effectiveness associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine, and wherein the air-to-air heat exchanger potential is between 0.028 and 0.067 for a bypass ratio associated with the gas turbine engine between 3 and 10 and the effectiveness being between 0.5 and 0.9 and is between 0.015 and 0.038 for a bypass ratio associated with the gas turbine engine between 10 and 20 and the effectiveness being between 0.3 and 0.9.

Air-to-air heat exchanger potential in gas turbine engines

A turbofan engine is provided. The turbofan engine includes a low pressure spool; a fan mechanically coupled with the low pressure spool; a high pressure spool; an accessory gearbox mechanically coupled with the high pressure spool; a hydraulic pump mechanically coupled with the accessory gearbox; and one or more heat exchangers tied to the accessory gearbox, the one or more heat exchangers having a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying an average heat exchanger effectiveness of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a hydraulic pump power of the hydraulic pump, a fan diameter of the fan, an engine length of the turbofan engine, and an overall pressure ratio of the turbofan engine.

Heat exchanger capacity for one or more heat exchangers associated with an accessory gearbox of a turbofan engine

A closed-loop cooling system for a gas turbine engine, comprising: a pump having a pump inlet and a pump outlet; a first plurality of stator vanes defining first cooling cavities therein; and a second plurality of stator vanes, defining second cooling cavities therein, wherein the pump drives a working fluid from the pump outlet, through the first cooling cavities of the first plurality of stator vanes, through the cooling cavities of the second plurality of stator vanes and back to the pump inlet.

Closed-loop cooling system for a gas turbine engine

A heat exchanger for a hydrogen fuel delivery system includes a tube bank including an inner-tube where a first portion of the inner-tube extends through an inlet region of the tube bank, a second portion of the inner-tube extends through a mid-region of the tube bank, and a third portion of the inner-tube extends through an outlet region of the tube bank. A thermal buffer at least partially surrounds the inner-tube. A first portion of the thermal buffer extends along the first portion of the inner-tube, a second portion of the thermal buffer extends along the second portion of the inner-tube, and a third portion of the thermal buffer extends along the third portion of the inner-tube. A plurality of fins is disposed along the inner-tube and extends radially outwardly from an outer surface of the thermal buffer.

Heat exchanger for a hydrogen fuel delivery system

An air-to-air heat exchanger in flow communication with a gas turbine engine is provided. The air-to-air heat exchanger has an air-to-air heat exchanger potential defined by a product raised to a half power, the product being a heat transfer surface area density associated with the air-to-air heat exchanger multiplied by an airflow conductance factor associated with the gas turbine engine. The air-to-air heat exchanger potential is between about 6.7 and 19.5 for a bypass ratio associated with the gas turbine engine between about 3 and 10 and the heat transfer surface area density being between about 3,000 m/mand 10,000 m/mand is between about 2.9 and 12.2 for a bypass ratio associated with the gas turbine engine between about 10 and 20 and the heat transfer surface area density being between about 1,000 m/mand 10,000 m/m.

A turbofan engine having one or more heat exchangers tied to an accessory gearbox is provided. The accessory gearbox is mechanically coupled with a spool, and a hydraulic pump is mechanically coupled with the accessory gearbox. The one or more heat exchangers have a heat exchanger capacity defined by a product raised to a half power, the product being determined by multiplying a resultant heat transfer surface area density of the one or more heat exchangers by a heat conductance factor that relates an accessory gearbox heat load, a power of the hydraulic pump, a diameter of a fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 23.9 and 97.7 for a rotational speed of the spool between 7,500 and 35,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 4,000 m/mand 13,000 m/m.

A contrail suppression system includes a shell having an exhaust gas inlet, an exhaust gas outlet, a condensate drain and a flow chamber in fluid communication with the exhaust gas inlet, the exhaust gas outlet and the condensate drain. The exhaust gas inlet is in fluid communication with a jet exhaust nozzle of a gas turbine engine. A first tube bundle is disposed within the flow chamber downstream from the exhaust gas inlet. The first tube bundle includes an inlet and an outlet. The inlet of the first tube bundle is fluidly connected to a first cooling medium source. A second tube bundle is disposed within the flow chamber downstream from the first tube bundle and upstream from the exhaust gas outlet. The second tube bundle includes an inlet and an outlet. The inlet of the second tube bundle is fluidly connected to a second cooling medium source.

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Houston, TX, United States of America

Eyitayo James Owoeye