method of making superalloy turbine disks having graded

Material Selection Method in Design of Automotive Brake Disc

selecting the optimum combination of material and process is not a simple task rather gradually evolved processes during the different stages of material selection. In this investigation, the stages of material selection method are shown using a flow chart in Fig. 1.

Thermomechanical processing method for achieving

Method of making superalloy turbine disks having graded coarse and fine grains 1994-05-17 Mathey 148/676 5143563 Creep, stress rupture and hold-time fatigue crack resistant alloys 1992-09-01 Krueger et al. 148/410 5087305 Fatigue crack resistant nickel

Comparison of Additive Technologies for Gradient

The basic units of the turbines where nickel-based superalloys could be used are combustion chambers, guide blades in nozzles, rotor blades, and turbine disks. It is known that with the temperature rise by every 100 at the turbine inlet, the increase in efficiency is about 3–4%.

Efficient Distortion Prediction of Additively

All disks, excluding the 65 mm and 70 mm Ti–6Al–4V disks, had a cutoff value of 1 mm. Cutoff values of 1.1 mm and 1.6 mm were used for the 65 mm and 70 mm Ti–6Al–4V disks, respectively. Second, a lower bound for the recorded z coordinates was manually identified for each disk and used to remove points on the support structure.

Convergence Properties of the Nelder

(2021) Optimization-Based Methodology for Selection of Pump-as-Turbine in Water Distribution Networks: Effects of Different Objectives and Machine Operation Limits on Best Efficiency Point. Journal of Water Resources Planning and Management 147 :5, 04021019.

Investigation of Mechanical and Thermal Loading in Gas

M. Sujata, M. Madan, K. Raghavendra, M.A. Venkataswamy, S.K. Bhaumik,, Identification of failure mechanisms in nickel base, superalloy turbine blades through microstructural study 26 May 2010. Kyung Min Kim, Jun Su Park, Dong Hyun Lee, Tack Woon Lee, Hyung Hee Cho, Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages 8 March 2011.

Modular Coating for Flexible Gas Turbine Operation

The method was proven to be cost effective and a highly flexible solution, enabling fast compositional screening. A calculation method for final coating composition was defined and validated. The modular addition of ductility agent enabled increasing the coating ductility with up to factor 3 with only slight decrease of oxidation resistance.

List of new Gas Turbine patents technologies

A method for controlling a gas turbine engine having a constrained model based control (cmbc) system. The method including obtaining information about a current and previous states of the engine, updating model data information in the cmbc and a parameter

Establishing a Methodology for Thermo

Turbine inlet temperatures in Roll-Royce civilian engines 1940-2010 [Reprinted with permission from Roger C. Reed, The Superalloys, 2006, p. 5, Fig. 1-5] 39 PAGE 40 Figure 2-3. Nickel based superalloy microstructure [Reprinted with permission from Harshad

A Medley of Potpourri: Superalloy

Superalloy products that are subjected to high working temperatures and corrosive atmosphere (such as high-pressure turbine region of jet engines) are coated with various kinds of coating. Several kinds of coating process are applied: pack cementation process, gas phase coating (both are a type of chemical vapor deposition (CVD)), thermal spraying, and physical vapor deposition .

Method for making a compositionally graded gas turbine

What is claimed is: 1. A method for making a compositionally graded gas turbine disk, comprising the steps of providing an outer container having an interior; placing a slip case into the interior of the outer container to define a first portion of the interior, a second

Turbine blade

Turbine blade from a Turbo-Union RB199 jet engine. A turbine blade is the individual component which makes up the turbine section of a gas turbine or steam turbine. The blades are responsible for extracting energy from the high temperature, high pressure gas produced by the combustor. The turbine blades are often the limiting component of gas

Investigation on transient dynamic balancing of the power

2021/4/6In addition, a new balancing method is used to balance the power turbine rotor, and the results are compared with the influence coefficient method. Some conclusions can be summarized as follows: Through the analysis of the original unbalanced response data by Fast Fourier Transform (FFT) and wavelet decomposition, it is found that there is interference in the signal acquisition process.

Taguchi Design for Heat Treatment of Rene 65 Components

Rene 65 is a nickel-based superalloy used in aerospace components such as turbine blades and disks. The microstructure in the as-received condition of the superalloy consists of ~ 40% volume fraction of gamma prime precipitates, which gives such a high strength that thermomechanical processing is

Rotating apparatus disk

In a rotating apparatus disk embodiment, the graded added material 14 will migrate to form a rim region of the disk 32 having a graded material property across a radius of the disk. In one embodiment a graded layer 14 may be useful when applying a nickel-iron based superalloy material over a core ingot of a steel material such as 9Cr-1Mo steel or a NiCrMoV low alloy steel.

Establishing a Methodology for Thermo

Turbine inlet temperatures in Roll-Royce civilian engines 1940-2010 [Reprinted with permission from Roger C. Reed, The Superalloys, 2006, p. 5, Fig. 1-5] 39 PAGE 40 Figure 2-3. Nickel based superalloy microstructure [Reprinted with permission from Harshad

(PDF) Direct laser fabrication of superalloy cermet

Materials and Design 21 Ž2000. 63]73 Direct laser fabrication of superalloy cermet abrasive turbine blade tips Suman Das a,U, Timothy P. Fuesting b, Gregory Danyo a, Lawrence E. Brownb, Joseph J This superalloy cermet component is an integral part of the low-pressure turbine sealing system in a demonstrator engine.

The Characterization of Freckle Casting Defects in

NICKEL-BASE SUPERALLOY TURBINE BLADES By Erik M. Mueller August 2003 Chair: Dr. Michael Kaufman Major Department: Materials Science and Engineering The purpose of this project was to characterize equiaxed grains, or freckles, that appear on the

Superalloys made by conventional vacuum melting and a novel spray forming process Original

A key design property, minimum fatigue life, of superalloy disks is controlled by the presence of oxide inclusions which originate in the ingot remelt stock and the powder making process.' The most common approach to limiting inclusions is to screen the powder to the size of the maximum allowable defect.

US Patent for Method of improving the oxidation

12. A method of improving oxidation resistance of a nickel or cobalt based superalloy substrate, comprising: electroplating the substrate with a layer comprising platinum from an aqueous electroplating solution based on an alkali metal carbonate which is M 2 CO 3

Material Selection Method in Design of Automotive Brake Disc

selecting the optimum combination of material and process is not a simple task rather gradually evolved processes during the different stages of material selection. In this investigation, the stages of material selection method are shown using a flow chart in Fig. 1.

The Importance of Hot Corrosion and Its Effective

This chapter explains the critical issue of hot corrosion of superalloy components in gas turbine engines and methodologies to select appropriate materials and coatings for its prevention. It is followed by an assessment of current status of coatings, coating techniques and finally, some of the critical areas that need to be addressed for development of more efficient and smart coatings.

High

article{osti_413326, title = {High-temperature chemical stability of plasma-sprayed Ca{sub 0.5}Sr{sub 0.5}Zr{sub 4}P{sub 6}O{sub 24} coatings on Nicalon/SiC ceramic matrix composite and Ni-based superalloy substrates}, author = {Lee, W Y and Cooley, K M and Joslin, D L and Stinton, D P and Berndt, C C}, abstractNote = {The potential application of Ca{sub 0.5}Sr{sub 0.5}Zr{sub 4}P{sub

Why are turbine blades in jet engines made from single

Single crystals are used to mitigate creep. If you apply heat and a tensile load to a metal, it will creep, that is it will stretch slightly in the direction of the load, resulting in a permanent deformation. This is different to elastic deformati

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