General Electric Company

General Electric Technology Gmbh

Sunil Rajagopal

Michael James Dutka

Marc Edward Blohm

Paul Griffin DeIvernois

Jeremy Peter Latimer

Joshy John

Michael Anthony Wondrasek

Andrew Paul Giametta

Prakash Bavanjibhai Dalsania

Siddaraja Mallikarjuna Devangada

Sendilkumaran Soundiramourty

Aaron David Williamson

Rajesh Mavuri

Sharan Shanti

Antanu Sadhu

Steven Lynn Huskins

Derek Paul Columbus

Vasantharuban S

Narasimha K V Rao

Timothy Edward DeJoris

Nandakumar A R

Jagdish Prasad Tyagi

Nancy Chaudhary

Amit Grover

Bala Muralidhar Singh B

Phillip Matthew Malloy

Turbomachine components and compressors are provided. The turbomachine component includes a platform and a mounting portion that extends from the platform. The mounting portion includes a dovetail received by a slot defined in the turbomachine. The slot includes a floor and a ceiling. The dovetail includes an inner surface and an outer surface. A hole is defined in the dovetail from an inlet at the inner surface to an end wall. The hole has a cylindrical portion and a tapered portion. A mechanical spring is disposed within the hole and in contact with the floor and the end wall such that the outer surface of the dovetail is forced into contact with the ceiling of the slot.

Turbomachine component retention

A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table I, Table II, Table III, Table IV, Table V, Table VI, Table VII, or Table VIII. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

Compressor stator vane airfoils

A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially-adjacent rotary components and an axial seal. Each of the rotary components includes a platform including a first side channel and an opposite second side channel, a shank extending radially inwardly from the platform, and a dovetail region extending radially inwardly from the shank. The axial seal is sized and shaped to be received in the first side channel of a first of the rotary components and the second side channel of a second of the rotary components, such that the axial seal sealingly interfaces with the first and second channels.

Sealing system for a rotary machine and method of assembling same

A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

Airfoil shape for seventh stage compressor rotor blade

Airfoil shape for sixth stage compressor rotor blade

Airfoil shape for ninth stage compressor stator vane

Airfoil shape for twelfth stage compressor stator vane

Growing community of inventors

Bengaluru, India

Sunil Rajagopal