General Electric Company

Nageswar Rao Ganji

Ravindra Shankar Ganiger

Hiranya Kumar Nath

Trevor Howard Wood

Ambika Shivamurthy

Giridhar Jothiprasad

Thomas Malkus

David Raju Yamarthi

Steven Douglas Johnson

Rahul Anil Bidkar

Narendra Anand Hardikar

Sripathi Mohan

Prateek Jalan

Arvind Namadevan

Dharmaraj Pachaiappan

Grant Robert Portune

Jonathan K Remer

Jeffrey D Carnes

Pratish Patil

Steven Mark Ballman

Srinivas Nuthi

Chandrashekhar Kandukuri

Charles Eric Lavender

Asim Ghosal

Ajith Jogi

Mallikarjun Metri

A dome-deflector assembly for a combustor of a gas turbine includes a dome portion having a dome-side swirler opening therethrough, and a deflector portion having a deflector-side swirler opening therethrough. The dome portion and the deflector portion are connected together to form a dome-deflector cavity therebetween. The deflector portion includes a first-side surface and a second-side surface, the second-side surface being arranged within the dome-deflector cavity, and the second-side surface including a plurality of stress-relief contours arranged in a pattern about the deflector-side swirler opening.

Dome-deflector assembly for a combustor of a gas turbine

This disclosure is directed to cooling systems for turbomachine seal assemblies. The seal assemblies include stationary and rotating components and at least one interface between the stationary and rotating components. During operation of the turbomachine, the components of the seal assemblies generate heat, which is removed from the seal assembly by the cooling systems of this disclosure. In some examples, the cooling system includes a reservoir of lubricant that is distributed to a face of one of the components of the seal assembly. In other examples, the cooling system includes a lattice structure capable of retaining lubricant against the components of the seal assembly, or a pressurized jet of lubricant directed against the components of the seal assembly. The cooling systems can further include a combination of deflectors, hairpin members, and channels for distributing the lubricant to the components of the seal assemblies.

Cooling system for seal assemblies

A lock lug for inhibiting movement of a plurality of rotor blades includes a body and an engagement mechanism. The body is sized and configured to be received within the rim slot of the rotor disk and defines a dovetail receiving aperture. The engagement mechanism extends from the body and has a retracted configuration configured to allow entry and exit of a dovetail of at least one or more of the plurality of rotor blades into and out of the dovetail receiving aperture and an extended configuration configured to block the dovetail from entering the dovetail receiving aperture.

Methods and apparatuses for blade locking

Aero-acoustically damped bleed valves are disclosed. An example variable bleed valve apparatus comprises a variable bleed valve door to actuate the variable bleed valve apparatus, and a variable bleed valve port including an upstream edge and a downstream edge, the VBV port to define a secondary flowpath, the VBV door to cover the VBV port in a closed position, and a vortex device at the upstream edge of the variable bleed valve port, the vortex device including a vorticity generating feature along the upstream edge of the variable bleed valve port.

Aero-acoustically dampened bleed valve

Example variable bleed valve assemblies for a gas turbine engine are disclosed herein, including a port extending radially outward from a compressor section of the gas turbine engine, the port defining a variable bleed valve cavity, the port to resonate at a resonant frequency based on an operating condition of the gas turbine engine, and an acoustic suppressor positioned on a wall of the port, the acoustic suppressor extending circumferentially along the wall by a length greater than a cross-sectional width of the acoustic suppressor, the acoustic suppressor defining a resonant cavity based on the length and the cross-sectional width, the acoustic suppressor including a perforated portion, the acoustic suppressor tuned to resonate at the resonant frequency based on the length and the perforated portion.

Variable bleed valve assemblies

A turbine engine is provided. The gas turbine engine defines a radial direction and includes: a rotor; a stator comprising a carrier; a seal assembly disposed between the rotor and the stator, the seal assembly comprising a plurality of seal segments, the plurality of seal segments having a seal segment, the seal segment having a seal face configured to form a fluid bearing with the rotor; and a seal support assembly, the seal support assembly comprises a pneumatic engagement assembly operable to bias the seal segment along the radial direction during operation of the turbine engine.

Seal support assembly for a turbine engine

Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.

Variable bleed valves with struts for aerodynamic stability

Variable bleed valves with inner wall controlled-flow circuits are disclosed. An example apparatus disclosed herein includes a casing segment defining a first flow path, a variable bleed valve port defining a second flow path, and a channel formed in the casing segment, the channel including a first opening into the first flow path, and a second opening into the second flow path, the channel defining a third flow path between the first opening and the second opening.

Variable bleed valves with inner wall controlled-flow circuits

Growing community of inventors

Bengaluru, India

Nageswar Rao Ganji