General Electric Company

James A Huffman

Dominic Stasio

Paul Stephen Manicke

Jeffrey Howard Nussbaum

Jeffrey Francis Wessels

Gary Edward Trewiler

Peter J Rock

Joseph Capozzi

Alan Glen Turner

Thomas A Baxter

Charles Kammer Christopherson

Murray L Dubin

Leslie M Pommer

Kenneth Allen Loehle

Jonathan A Rennert

Richard G Frenkel

Kenneth Loehle

Charles K Christopherson

Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Part span shrouded fan blisk

An igniter for a combustor of a gas turbine comprises a ground shell electrical conductor which provides the electrical ground path back to the spark source. The spark source connects to the conductor and a ground return path connects to the ground shell. Multiple ignition spark source electrical conductors are used in the single igniter. At least one insulator isolates the spark sources from each other and from the ground shell conductor. An electrical connection, typically a connector that would mate with an ignition source electrical lead having a source conductor, a ground conductor, and insulation to separate these conductors, mates with a spark source to operate the igniter.

Multiple electrode igniter

A control system and method provide thrust droop compensation in a gas turbine engine. A droop compensation signal is generated for increasing turbine exit temperature T.sub.5 based on a predetermined model, and is selectively reduced for limiting the increase in temperature T.sub.5 when the temperature T.sub.5 is above a predetermined threshold temperature for a predetermined time. The reduced droop signal is added as a bias signal into an error signal which effects thrust droop concentration in a variable area exhaust nozzle of the engine.

Thrust droop compensation method and system

A method and system are provided to bias a control subsystem of a gas turbine engine having a fan and compressor. The method includes the steps of measuring an operating parameter of the engine and differentiating this parameter over time to obtain a derivative thereof. A bias signal is generated in a predetermined bias schedule in response to the parameter derivative, and provided to the control subsystem for biasing the subsystem. The bias signal has a zero value for values of the parameter derivative from zero to a first value thereof at a first time. The bias signal has a maximum value for values of the parameter derivative between second and third values thereof corresponding with second and third times. And, the bias signal returns to a value of zero after a fourth time greater than the third time. In an exemplary embodiment, the operating parameter is fan speed, and the bias signal is provided to at least one, and preferably both, control subsystems of variable guide vanes regulating flow to the fan and a variable area exhaust nozzle regulating discharge flow area.

Method and system to increase stall margin

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Topsfield, MA, United States of America

James A Huffman