General Electric Company

Vaishnav Raghuvaran

Bhaskar Nanda Mondal

Raghuveer Chinta

Ravindra Shankar Ganiger

Atanu Saha

Gary W Bryant

Abhijit Sinha Roy

Vaibhav M Deshmukh

Srinivas Nuthi

Thomas Ory Moniz

Jeffrey Donald Clements

Scott Alan Schimmels

Rajesh Kumar

Gary Willard Bryant, Jr

Curtis Walton Stover

Michael Hogan

Sesha Subramanian

Vishnu Vardhan Venkata Tatiparthi

Sushilkumar Shevakari

Hari K Meka

Rakshit Tirumala

Andrew Mark Del Donno

Sai Raju Ippili

Daniel O'Brien

A turbine engine includes a spool with a compressor for providing a compressed air flow to a turbine, a shaft that connects the compressor and a turbine such that the compressor and the turbine rotate together, and a fuel supply. A combustor located downstream of the compressor receives and combusts the compressed air flow and the fuel supply, generating combustion gases. The combustion gases rotate the turbine, in turn rotating the spool. A balance piston for applying an axial force on the spool includes a rotating boundary portion and a fixed enclosure portion that does not rotate, defining a balance piston cavity. A water system provides water to the balance piston cavity, heat transfer from the balance piston to the water causes expansion of the water, the water in the balance piston cavity being balance piston fluid that is pressurized and applies an axial force to the spool.

Turbine engine including a water system

A fan assembly for an engine includes a fan disk, fan disk inserts, and fan blades. The fan disk includes disk posts extending in a radial direction from a central region of the fan disk. The disk posts include disk post pressure surfaces that define a first array of dovetail recesses. The fan disk inserts are retained within the first array of dovetail recesses. The fan disk inserts include fan disk insert pressure surfaces that define a second array of dovetail recesses. The fan blades are retained within the second array of dovetail recesses.

Fan assemblies with fan disk inserts and methods of assembling the same

A fan assembly includes a disk having a disk forward surface, a disk aft surface, and a radially outer surface. The disk defines a plurality of disk posts and a plurality of disk slots in the radially outer surface. At least one of the plurality of disk posts includes a post slot. The fan assembly also includes a fan having a plurality of fan blades and a plurality of platforms extending between adjacent fan blades of the plurality of fan blades. Each of the plurality of fan blades is received within one of the plurality of disk slots via a respective blade root. Further, the fan assembly includes at least one fan retention member having a body portion and a protrusion extending from the body portion. The protrusion is received within the post slot such that the at least one fan retention member supports one of the plurality of platforms.

Fan retention member for supporting a blade platform of a fan assembly

Disclosed herein are example variable flowpath casings for blade tip clearance control. An example casing for a turbine engine includes a first annular substrate extending along an axial direction; a second annular substrate positioned radially inward relative to the first annular substrate, the second annular substrate movably coupled to the first annular substrate; and an actuator coupled to the second annular substrate such that a force applied by the actuator moves the second annular substrate relative to the first annular substrate to adjust a tip clearance.

Variable flowpath casings for blade tip clearance control

Structures for reducing forward loads in compressors are described. A compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.

Forward load reduction structures for aft-most stages of high pressure compressors

A rotor disk for a gas turbine engine includes disk posts extending in a radial direction from a disk body. Each of the disk posts includes an insert receiving slot extending axially through the disk post and a disk post pressure surface. Disk post inserts are assembled within the insert receiving slots of each of the disk posts. A blade is retained by disk post pressure surfaces of each of the disk posts.

Rotor disks with disk post inserts and methods of assembling the same

A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

Air guide for a gas turbine engine

A gas turbine engine including a compressor section including a compressor and a turbine section located downstream of the compressor section. The turbine section including a high pressure turbine, a low pressure turbine, a sump positioned between the high pressure turbine and the low pressure turbine, and a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.

Sump arrangement for a gas turbine engine

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Bengaluru, India

Vaishnav Raghuvaran