General Electric Company

Ling Yang

Robin Carl Schwant

Swami Ganesh

Robert V Falsetti

John Zhiqiang Wang

Francis Alexander Reed

Samuel Vinod Thamboo

Jeffrey Allen Hawk

Peter W Schilke

Disclosed herein is a method of treating a component comprising solution treating the component for a period of about 4 to about 10 hours at a temperature of about 1750 to about 1850&#xb0; F.; cooling the component to a temperature of about 1490 to about 1520&#xb0; F. at an average rate of 1&#xb0; F./min to about 25&#xb0; F./min; stabilizing the component at about 1450 to about 1520&#xb0; F. for a period of from about 1 to about 10 hours; cooling the component to room temperature; precipitation aging the component by heating the component to a first precipitation aging temperature of about 1275 to about 1375&#xb0; F. for about 3 to about 15 hours; cooling the component at an average rate of 50 to about 150&#xb0; F./hour to a second precipitation aging temperature of about 1100 to about 1200&#xb0; F. for a time period of about 2 to about 15 hours; and cooling the component.

Heat treatment method and components treated according to the method

Disclosed herein is a method of treating a component comprising solution treating the component for a period of about 4 to about 10 hours at a temperature of about 1750 to about 1850&#xb0;F.; cooling the component to a temperature of about 1580 to about 1650&#xb0;F. at an average rate of 1&#xb0;F./min to about 25&#xb0;F./min; stabilizing the component at about 1580 to about 1650&#xb0;F. for a period of about 1 to about 10 hours; cooling the component to room temperature; precipitation aging the component at a first precipitation aging temperature of about 1275 to about 1375&#xb0;F. for about 3 to about 15 hours; cooling the component at an average rate of 50 to about 150&#xb0;F./hour to a second precipitation aging temperature of about 1100 to about 1200&#xb0;F. for a time period of about 2 to about 15 hours; and cooling the component.

A method for heat treating a serviced turbine part to improve a hold time fatigue cracking resistance of the serviced turbine part is provided. The method includes positioning the serviced turbine part in a vacuum furnace configured to limit surface oxidation. The serviced turbine part is controllably heated to prevent distortion. A surface damage layer is recrystallized into a fine grain structure to prevent fatigue crack initiation. The serviced turbine part is controllably cooled to prevent distortion.

Method for heat treating serviced turbine part

A process for producing a rotor, the rotor formed thereby, as well as turbines in which such a rotor is installed. The rotor is formed by casting an ingot to have first and second regions formed of different alloys that intermix during casting to define a transition zone therebetween. The ingot is forged to yield a rotor forging that contains axially-aligned first and second alloy regions and a transition zone therebetween. The effects of the transition zone can be mitigated by modeling the transition zone and then off-center machining the forging so that the axis of rotation of the machined monolithic rotor is more centrally located with respect to the transition zone.

Process for producing a rotor

A method of processing a rotor. The rotor is formed by casting an ingot to have first and second regions formed of different alloys that intermix during casting to define a transition zone therebetween. The ingot is forged to yield a rotor forging that contains axially-aligned first and second alloy regions and a transition zone therebetween. A three-dimensional approximation of the transition zone is generated, which can be used to predict the effects of the transition zone on the dynamic performance of a rotor machined from the forging.

Method of processing a multiple alloy rotor

Multiple alloy rotor and method therefor

A monolithic rotor comprising first and second rotor regions axially aligned within the monolithic rotor and a transition zone therebetween. The first and second rotor regions are formed of different alloys and the transition zone having a composition that differs from and varies between the first and second rotor regions. The first rotor region is located within a high pressure region of the monolithic rotor and is formed from an alloy chosen from the group consisting of CrMoV low alloy steels, martensitic stainless steels containing about 11 to about 14 weight percent chromium, Fe&#x2014;Ni alloys, and nickel-base alloys. The second rotor region is located within a low pressure region of the monolithic rotor and is formed from an alloy chosen from the group consisting of NiCrMoV low alloy steels and martensitic stainless steels containing about 11 to about 14 weight percent chromium.

Multiple alloy rotor

A method to estimate the tensile properties of HIPed cast IN718 components at various grain sizes and different operating temperatures by using transfer functions to estimate ultimate tensile strength, yield strength, and elongation.

Method of estimating tensile properties of IN718 cast hiped components

A method and system for evaluating structural defects in metals is provided. In one embodiment, the method recognizes that the acceptability of a given defect is principally determined by the four basic parameters of operating temperature, operating stress, defect area, and defect shape. Ranges are established for each of these four basic parameters, and intermediate values within these ranges are selected to create a series of index value data sets. The method evaluates these index value data sets by calculating a life cycles estimate for each. Using statistical methods, the life cycles results are analyzed to determine the effect each of the four basic parameters has on the life of a component with a defect. Understanding the relationship between these four basic parameters and life cycles enables the method to provide an interpolation algorithm for finding the life cycles for any component having a defect.

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Niskayuna, NY, United States of America

Ling Yang