Selecting the machining processes for slot arrays in gas-turbine disks

2008 ◽  
Vol 28 (5) ◽  
pp. 503-507
Author(s):  
V. F. Bez’yazychnyi ◽  
S. A. Volkov ◽  
R. N. Fomenko
Keyword(s):  
Gas Turbine ◽  
Machining Processes ◽  
Slot Arrays ◽  
Turbine Disks

A Numerical Analysis of Gas Turbine Disks Incorporating Rotating Heat Pipes

2000 ◽  
Author(s):  
Y. Cao ◽  
J. Ling ◽  
R. Rivir ◽  
C. MacArthur
Keyword(s):  
Heat Pipe ◽  
Gas Turbine ◽  
Heat Pipes ◽  
High Heat ◽  
Thermal Dissipation ◽  
High Heat Flux ◽  
Heating And Cooling ◽  
Turbine Disks ◽  
Higher Temperature ◽  
Lower Temperature

Abstract Radially rotating heat pipes have been proposed for cooling gas turbine disks working at high temperatures. A disk incorporating the heat pipe would have an enhanced thermal dissipation capacity and a much lower temperature at the disk rim and dovetail surface. In this paper, extensive numerical simulations have been made for heat-pipe-cooled disks. Thermal performances are compared for the disks with and without incorporating the heat pipe at different heating and cooling conditions. The numerical results presented in this paper indicate that radially rotating heat pipes can significantly reduce the maximum and average temperatures at the disk rim and dovetail surface under a high heat flux working condition. In general, the maximum and average temperatures at the disk rim and dovetail surface could be reduced by above 250 and 150 degrees, respectively, compared to those of the disk without the heat pipe. As a result, a disk incorporating radially rotating heat pipes could alleviate temperature-related problems and allow a gas turbine to work at a much higher temperature.

Investigation Performance of AlCrN_Based Coated Broaching Tool in Broaching of Gas Turbine Material X12CrMoWVNbN1011

2014 ◽  
Vol 1017 ◽  
pp. 361-366
Author(s):  
Zhi Qiang Liu ◽  
Ming Chen ◽  
Cheng Dong Wang ◽  
Qing Long An ◽  
Chun Xin Ge ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Cutting Temperature ◽  
High Hardness ◽  
Heavy Duty ◽  
Machining Processes ◽  
Tool Performance ◽  
Tool Coating ◽  
Tool Edge ◽  
Coated Tool ◽  
Heavy Duty Gas Turbine

Pull broaching fir-tree slots of gas turbine is one of the most productive precision machining processes when machining simple surfaces or complex contours. Tool edge chipping and wear of uncoated broaching tool become a serious problem in the currently broaching of gas turbine discs. Therefore, tool coating can be used to improve the wear resistance of broaching tool. AlCrN-based coatings have been developed as a high hardness coating for cutters due to excellent resistance to oxidation which is higher than that of conventional coatings. However, few researches had paid attention to investigating AlCrN-based coating tool performance in the broaching process, especially in machining of heat-resisting material of heavy-duty gas turbine discs. In this paper, experiments of broaching heat-resisting material X12CrMoWVNbN1011 were investigated. In order to obtain suitable and ideal broaching tool, the AlCrN coated or uncoated T15 broaching tools were also compared. Cutting force, cutting temperature, and tool wear were measured in the broaching experiments. Results showed that: (1) with a little changed cutting load and tool edge radius, AlCrN-based coating was found to have more significantly influence in improving the tool life as comparing to uncoated tool. The similar wear forms was observed by comparing coated tool and uncoated tool. The conclusions of the study can help to improve heavy-duty gas turbine disc broaching process and broaching tool. (2) Owing to AlCrN coating’s unique combination of heat resistance and hardness, broaching tool could reach higher cutting performance levels. AlCrN coated tool compared with uncoated tool have much better performance in term of cutting strains or cutting temperature.

Gas Turbine Engine Disk Retirement-for-Cause: An Application of Fracture Mechanics and NDE

1980 ◽  
Author(s):  
C. G. Annis ◽  
M. C. VanWanderham ◽  
J. A. Harris ◽  
D. L. Sims
Keyword(s):  
Fracture Mechanics ◽  
Gas Turbine ◽  
Life Cycle Cost ◽  
Energy Savings ◽  
Cost Savings ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Turbine Disks ◽  
Full Life ◽  
Engine Components

Historically, gas turbine engine disks are retired when they accrue an analytically determined lifetime where the first fatigue crack per 1000 disks could be expected. By definition then, 99.9 percent of these components are being retired prematurely. Retirement-for-Cause (RFC) is a procedure, based on Fracture Mechanics, which would allow safe utilization of the full life capacities of each individual disk. Since gas turbine disks are among the most costly of engine components, adopting a RFC philosophy could result in substantial systems life cycle cost savings. These would accrue from reduced replacement costs, conservation of strategic materials such as cobalt, and energy savings.

Gas Turbine Applications of Abrasive Flow Machining

1989 ◽  
Author(s):  
Winfield B. Perry ◽  
John Stackhouse
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Abrasive Flow Machining ◽  
Turbine Disks ◽  
Surface Improvement

Abrasive Flow Machining (AFM) is a non-traditional finishing method used for precision deburring, edge contouring, surface improvement and the removal of abusive machining and thermal recast layers. A firm-bodied abrasive laden compound is flowed at pressures of 75–500 psi (5–35 bar) across selective features of a fixtured workpiece. Gas turbine components benefited by this method include: axial and centrifugal rotors, stators, turbine blades, compressor and turbine disks, shafts, seals and other rotating parts. AFM process principles are explained and specific applications are reviewed.

Cracks in turbine disks of gas-turbine engines

1972 ◽  
Vol 4 (12) ◽  
pp. 1527-1531
Author(s):  
Ch. L. Svetlakov ◽  
A. G. Makhnev ◽  
V. F. Kozhevnikov
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Disks

Use of the adaptability theory in calculations for the strength of gas turbine disks

1988 ◽  
Vol 20 (11) ◽  
pp. 1527-1534 ◽  
Author(s):  
A. R. Belyakov ◽  
L. B. Getsov ◽  
V. K. Dondoshanskii ◽  
Yu. B. Shneerson
Keyword(s):  
Gas Turbine ◽  
Turbine Disks ◽  
Adaptability Theory

Convergent Zone-Refinement Method for Risk Assessment of Gas Turbine Disks Subject to Low-Frequency Metallurgical Defects

2006 ◽  
Vol 129 (3) ◽  
pp. 827-835 ◽  
Author(s):  
Harry R. Millwater ◽  
Michael P. Enright ◽  
Simeon H. K. Fitch
Keyword(s):  
Finite Element ◽  
Gas Turbine ◽  
Low Frequency ◽  
Federal Aviation Administration ◽  
Accurate Solution ◽  
Element Analysis ◽  
Refinement Method ◽  
Metallurgical Defects ◽  
Turbine Disks ◽  
Probability Of Fracture

Titanium gas turbine disks are subject to a rare but not insignificant probability of fracture due to metallurgical defects, particularly hard α. A probabilistic methodology has been developed and implemented in concordance with the Federal Aviation Administration (FAA) Advisory Circular 33.14-1 to compute the probability of fracture of gas turbine titanium disks subject to low-frequency metallurgical (hard α) defects. This methodology is further developed here to ensure that a robust, converged, accurate calculation of the probability is computed that is independent of discretization issues. A zone-based material discretization methodology is implemented, then refined locally through further discretization using risk contribution factors as a metric. The technical approach is akin to “h” refinement in finite element analysis; that is, a local metric is used to indicate regions requiring further refinement, and subsequent refinement yields a more accurate solution. Supporting technology improvements are also discussed, including localized finite element refinement and onion skinning for zone subdivision resolution, and a restart database and parallel processing for computational efficiency. A numerical example is presented for demonstration.

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