General Electric Company

General Electric Renovables Espana, S.l.

Lana Maria Osusky

David Wayne Weber

Gregory Alexander Natsui

Gregory Thomas Foster

Eyitayo James Owoeye

Bugra Han Ertas

Harry Kirk Mathews, Jr

William Dwight Gerstler

Constantinos Minas

Daniel Jason Erno

Trevor Howard Wood

Kishore Ramakrishnan

Zachary John Snider

Hendrik Pieter Jacobus De Bock

Daniel Endecott Osgood

David Allan Torrey

Brian Magann Rush

Nicholas William Rathay

Corey Bourassa

Changjie Sun

Brian Gene Brzek

Thomas Earl Dyson

Naveenan Thiagarajan

Giridhar Jothiprasad

Michelle Jessica Iduate

Andrew Thomas Cross

Karthik Kumar Bodla

Gustavo Adolfo Ledezma

Thomas Malkus

Daniel Robert Burnos

Roelof Willem Schuring

Gary Mandrusial

Daniel Getsinger

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 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

Airfoil include a body extending along a spanwise direction between a root end and a tip end, the body comprising a plurality of acoustic cavities each having an inlet on the airfoil; and at least one cooling channel having an inlet section an outlet section and a middle section within the airfoil extending between the inlet section and the outlet section; and at least one porous face sheet positioned on at least one inlet of the plurality of acoustic cavities.

Airfoils for turbofan engines

An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.

Thermal bias control in turbomachines

A thermal management system for a gas turbine engine is provided. The gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, a turbine section, and an exhaust section arranged in serial flow order and together defining at least in part a core air flowpath; and a thermal management system comprising a supercritical carbon dioxide line thermally coupled to, or integrated into, a portion of the compressor section.

Thermal management system for a gas turbine engine

An engine component for a gas turbine engine, the engine component comprising a cooling architecture comprising at least one unit cell having a set of walls with a thickness, the set of walls defining fluidly separate conduits having multiple openings, each of the multiple openings having a hydraulic diameter; wherein the thickness (t) and the hydraulic diameter (D) relate to each other by an equation: to define a performance area factor (PAF).

Engine component with cooling architecture

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 48 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.

A generator, which may be used in a wind turbine, has a first stationary component carrying a first winding configuration and a second rotating component carrying a second winding configuration. The second rotating component includes a body portion and a plurality of teeth spaced around and extending radially from the body portion. The second winding configuration is arranged in slots defined between adjacent teeth. A housing is arranged around and rotates with the body portion. A heat exchange circuit is arranged on the second rotating component and includes a coolant channel defined in the teeth; a pump; and a heat exchanger arranged on the housing so as to rotate with the housing, the heat exchanger transverse to a rotational direction of the housing.

Rotating cooling system for wind turbine generator

A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.

System and method for near wall cooling for turbine component

A cooling assembly includes a body configured to be placed into thermal contact with a heat source and one or more non-planar, hermetic walls disposed within the body. The one or more non-planar hermetic walls extending around, enclosing, and defining a cooling channel configured to carry cooling fluid through the body such that the cooling fluid contacts internal surfaces of the cooling channel inside the body. The assembly including one or more enhancement structures disposed within the body and coupled with the one or more non-planar hermetic walls. The one or more enhancement structures shaped to change a flow path of the cooling fluid as the cooling fluid moves within the cooling channel and shaped to increase a surface area contacted by the cooling fluid within the cooling channel.

Additively manufactured cooling assemblies for thermal and/or mechanical systems, and methods for manufacturing the assemblies

A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the pressure and suction side cavities; and a second leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the second leading edge cavity located forward of the first leading edge cavity.

Cooling circuit for a multi-wall blade

A cooling circuit for a multi-wall blade according to an embodiment includes: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade, the first leading edge cavity located forward of the central cavity; a second leading edge cavity located forward of the first leading edge cavity; at least one impingement opening for fluidly coupling the first leading edge cavity to the second leading edge cavity; and at least one channel for fluidly coupling the central cavity to a tip of the multi-wall blade.

A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.

A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the first leading edge cavity with a second leading edge cavity.

Growing community of inventors

Rexford, NY, United States of America

Lana Maria Osusky