General Electric Company

Ge Avio S.r.l.

General Electric Corporation Gmbh

Sanjeev Sai Kumar Manepalli

Bhaskar Nanda Mondal

Karthikeyan Sampath

Atanu Saha

Ravindra Shankar Ganiger

Thomas Ory Moniz

David Raju Yamarthi

Praveen Sharma

Monty Lee Shelton

Peeyush Pankaj

Adam Joseph Wangler

Mohan Kannaiah Raju

Santosh Kumar Pattnaik

Antonio Giuseppe D'Ettole

Ganesh Seshadri

Mahendran Manoharan

Randy Thomas Antelo

Shishir Paresh Shah

Anil Soni

N V Sai Krishna Emani

Ranganayakulu Alapati

Example thrust bearing apparatus includes: a thrust disk extending radially from the shaft, the thrust disk having a first side and a second side opposite the first side; a bearing housing surrounding the thrust disk and the shaft, the bearing housing having a first wall facing the first side of the thrust disk and a second wall facing the second side of the thrust disk; a first thrust pad coupled to the first wall of the bearing housing, the first thrust pad including a first plurality of serrations circumferentially arranged in a first pattern along the first thrust pad; and a second thrust pad coupled to the first side of the thrust disk, the second thrust pad including a second plurality of serrations circumferentially arranged in a second pattern along the second thrust pad.

Dual thrust bearing systems and methods for operating the same

A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, and a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with the fan and with a low pressure turbine of the turbine section. The low pressure turbine includes a rotating drum to which a first airfoil structure is connected and extends radially inward toward the rotary member. A torque frame connects the rotating drum to the rotary member and transfers torque from the first airfoil structure mounted to the rotating drum to the rotary member. The torque frame includes an inner disk mounted to the rotary member, an outer ring and a second airfoil structure formed separately from the outer ring and connected thereto by a releasable connecting structure. The second airfoil structure extends radially inward from the outer ring toward the inner disk.

Counter-rotating gas turbine engines including turbine sections with separable torque frames

A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor having a compressor discharge nozzle, a combustor coupled to the compressor, a turbine coupled to the combustor and the compressor, a fluid flow passage fluidly coupling the compressor and the turbine and bypassing the combustor, and a heat absorption device disposed fluidly along the fluid flow passage at a first predefined location. The heat absorption device includes a casing having an inlet and an outlet, a flow path within the casing and extending between the inlet and the outlet, wherein the flow path directs an input bleed flow diverted from a fluid stream discharged from the compressor, and a phase change material hermetically sealed within the casing. The phase change material is separated from the flow path. The heat absorption device is configured to exchange heat between the phase change material and the input bleed flow to generate an output bleed flow of a different temperature than the input bleed flow and discharge the output bleed flow to a second predefined location different from the first predefined location.

Gas turbine engine having a heat absorption device and an associated method thereof

A gas turbine engine, system, and method of severing at least one blade of a row of blades spaced about a rotor during an over speed condition are provided. The gas turbine engine includes a shaft rotatable about an axis of the shaft, a rotor coupled to the shaft and having a radially outer surface, and one or more rows of blades spaced axially along the outer portion. Each row of blades includes a plurality of blades spaced circumferentially around the radially outer surface. A gas turbine engine casing at least partially surrounds the one or more rows of blades. One or more rows of stationary vanes are spaced axially along the casing. Each row of stationary vanes includes a plurality of stationary vanes extending radially between the shaft and the gas turbine engine casing. The stationary vanes are coupled to the gas turbine engine casing using a fuse element.

Method and system for rotor overspeed protection

A gas turbine engine having a heat absorption device and an associated method are disclosed. The gas turbine engine includes a compressor, a combustor, a turbine, a bleed fluid cavity, and the heat absorption device. The combustor is coupled to the compressor. The turbine is coupled to the compressor and the combustor. The bleed fluid cavity is formed at a first predefined location in the compressor. The heat absorption device is disposed in the bleed fluid cavity and includes a casing, a flow path, and a phase change material. The casing includes an inlet and an outlet. The flow path is within the casing, extends between the inlet and the outlet, and directs an input bleed fluid separated from a fluid stream discharged from the compressor. The phase change material is filled in the casing, separated from the flow path.

Gas turbine engine having a heat absorption device utilizing phase change material

Growing community of inventors

Bengaluru, India

Sanjeev Sai Kumar Manepalli