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

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.

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

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

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.

Effect of Alloying Elements on the Strength Properties of Nickel Superalloys for Gas Turbine Disks

2021 ◽  
Vol 2021 (12) ◽  
pp. 1604-1611
Author(s):  
A. V. Logunov ◽  
Yu. N. Shmotin ◽  
R. V. Khramin ◽  
S. A. Zavodov ◽  
D. V. Danilov
Keyword(s):  
Gas Turbine ◽  
Strength Properties ◽  
Alloying Elements ◽  
Nickel Superalloys ◽  
Turbine Disks ◽  
Effect Of Alloying
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