General Electric Company

Unison Industries, Inc.

Ramana Reddy Kollam

Merin Sebastian

Bhaskar Nanda Mondal

Sandeep Kumar

Subrata Nayak

Emily Marie Phelps

Milind Chandrakant Dhabade

Gordon Tajiri

Shiloh Montegomery Meyers

Dattu G V Jonnalagadda

Vishnu Vardhan Venkata Tatiparthi

Dattu Guru Venkata Jonnalagadda

Saurya Ranjan Ray

Ravindra Shankar Ganiger

Darek Tomasz Zatorski

Christopher Charles Glynn

David Raju Yamarthi

Richard Ludwig Schmidt

David Allan Dranschak

Yanzhe Yang

Sharad Pundlik Patil

Peeyush Pankaj

Veeraraju Vanapalli

Pallavi Tripathi

Vinod Shashikant Chaudhari

Shashank Suresh Puranik

Rajendra Mahadeorao Wankhade

Parmeet Singh Chhabra

James Fitzgerald Bonar

Narendra Dev Mahadevaiah

Srinivasan Swaminathan

Steven Ryan Kerley

Michael John Simonetti

Rachamadugu Sivaprasad

Greedaran Kubendran Jankin

Michael Vadnais

Nishita Deshmukh

Mark Leslie Rickert

Mehmet Kilic

Prerna Mandal

An air turbine starter (ATS) for starting an engine, having a stator including a housing having an inlet, an outlet, and a flow path extending between the inlet and the outlet and a rotor including a turbine member defining a rotating axis and having a set of blades at least partially disposed within the flow path. The ATS further including a bearing support structure disposed between the rotor and the stator comprising a first bearing support having a first stiffness (K) and a second bearing support having a second stiffness (K).

Air turbine starter with bearing support structure

A gas turbine engine is provided. The gas turbine engine includes: a thermal management system having a thermal fluid member having a flow of thermal fluid therethrough during operation of the gas turbine engine and a heat exchanger assembly, the heat exchanger assembly including: a core section comprising a plurality of heat exchange members; and a heat exchange manifold including a first direction pressure vessel in fluid communication with the thermal fluid member and a second direction pressure vessel extending from the first direction pressure vessel, the first and second direction pressure vessels each extending in a reference plane, the second direction pressure vessel in fluid communication with the first direction pressure vessel and with at least one of the plurality of heat exchange members.

Thermal management system

An air turbine starter having a housing defining an interior with a primary inlet and a primary outlet to define a primary air flow path from the primary inlet to the primary outlet. A nozzle is located within the interior and has circumferentially spaced vanes. A shroud is also located within the interior and circumscribes at least a portion of the vanes. A retention mechanism constrains the axial movement of nozzle.

Air turbine starter with nozzle retention mechanism

An air turbine starter having a housing, a turbine, a drive shaft, and at least one vane. The housing having an inlet, an outlet and a curvilinear flow path extending between the inlet and the outlet. The at last one vane is located within a portion of the curvilinear flow path, and includes an outer wall extending between a root and a tip in a span-wise direction and between a leading edge and a trailing edge in a chord-wise direction. In one aspect, the vane is arranged to define an acute axial angle that is non-constant in the chord-wise or span-wise direction. In another aspect, the vane is arranged to define an acute tangential angle that is non-constant in the chord-wise or span-wise direction.

Air turbine starter with shaped vanes

An air turbine starter comprising a housing defining an inlet, an outlet, and a flow path, a turbine having a rotor with circumferentially spaced blades extending into the flow path, a drive shaft operably coupled to and rotating with the rotor, and at least one vane located within the flow path, upstream of the blades. The at least one blade being defined by an acute axial angle and an acute tangential angle.

A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.

OGV electroformed heat exchangers

A tube coupling assembly is disclosed, which comprises a first connector for connecting to a tube; a second connector for jointing with the first connector; a first member is adapted to mount on the first connector and operably affixable to the second connector; and a second member is adapted to mount on the second connector, and is capable of being engaged with the first member to prevent separation between the first connector and the second connector.

Tube coupling assembly

The present disclosure is directed to an outer drum rotor assembly for a gas turbine engine including a first outer drum and a second outer drum. Each outer drum defines a radially extended flange adjacent to one another. A plurality of outer drum airfoils is extended inward along the radial direction from between the first outer drum and the second outer drum at the flange.

Outer drum rotor assembly

The present disclosure is directed to a gas turbine engine including a first frame comprising a first bearing assembly, a second frame comprising a second bearing assembly, and a compressor rotor. A first stage compressor airfoil is defined at an upstream-most stage of the compressor rotor. The compressor rotor is rotatable via the first bearing assembly and the second bearing assembly. The first stage compressor airfoil is disposed between the first bearing assembly and the second bearing assembly.

Gas turbine engine arrangement with ultra high pressure compressor

A turbomachine includes a spool and a turbine section including a turbine and a turbine center frame. The turbine includes a first plurality of turbine rotor blades and a second plurality of turbine rotor blades alternatingly spaced along the axial direction and rotatable with one another. The turbomachine also includes a bearing assembly substantially completely supporting rotation of the turbine, the bearing assembly including a total of four bearings, each of the four bearings aligned with, or positioned aft of, the turbine center frame.

Turbomachine with alternatingly spaced turbine rotor blades

The present disclosure discloses a method of manufacturing a structure with a wall, comprising manufacturing a structure with a wall by using additive manufacturing technology, and dissolving a surface of the wall for reducing thickness of the wall.

Method of manufacturing a fin structure for heat exchanger

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Bengaluru, India

Ramana Reddy Kollam