Add to ORKGAn analytical study was conducted on a bore entry cooled turbine disk for the first stage of the JT8D-17 high pressure turbine which had the potential to improve disk life over existing design. The disk analysis included the consideration of transient and steady state temperature, blade loading, creep, low cycle fatigue, fracture mechanics and manufacturing flaws. The improvement in life of the bore entry cooled turbine disk was determined by comparing it with the existing disk made of both conventional and advanced (Astroloy) disk materials. The improvement in crack initiation life of the Astroloy bore entry cooled disk is 87% and 67% over the existing disk made of Waspaloy and Astroloy, respectively. Improvement in crack propagation life ...
The next generation of subsonic commercial aircraft will require engines with improved efficiency an...
Recently, National Aeronautics and Space Administration (NASA) initiated a program to achieve the si...
Test rig for predicting thermal stress cracking in turbine stator or rotor blade
An analytical study was performed on a novel disk design to replace the existing high-pressure turbi...
Results of analytical studies to improve the low cycle fatigue lives and reliability of turbine disk...
Advanced disk structural concepts were employed to improve the cyclic lives and reliability of turbi...
Turbine disks are required to operate at a high temperature environment and rotate at high velocity ...
Turbine disks are required to operate at a high temperature environment and rotate at high velocity ...
Over the past decade, aircraft readiness rates have declined, spare parts have been in short supply,...
The JT8D high pressure turbine was revised to reduce leakage between the blade tip shrouds and the o...
An air-cooled turbine blade from an aircraft gas turbine engine chosen for its history of cracking w...
A full-scale J33 air-cooled split turbine rotor was designed and spin-pit tested to destruction. Str...
Two series of low cycle fatigue (LCF) test data for two groups of different aircraft gas turbine eng...
Environmental attack has the potential to limit turbine disk durability, particularly in next genera...
Recent activities of the Lewis Research Center are reviewed which are directed toward developing mat...
The next generation of subsonic commercial aircraft will require engines with improved efficiency an...
Recently, National Aeronautics and Space Administration (NASA) initiated a program to achieve the si...
Test rig for predicting thermal stress cracking in turbine stator or rotor blade
An analytical study was performed on a novel disk design to replace the existing high-pressure turbi...
Results of analytical studies to improve the low cycle fatigue lives and reliability of turbine disk...
Advanced disk structural concepts were employed to improve the cyclic lives and reliability of turbi...
Turbine disks are required to operate at a high temperature environment and rotate at high velocity ...
Turbine disks are required to operate at a high temperature environment and rotate at high velocity ...
Over the past decade, aircraft readiness rates have declined, spare parts have been in short supply,...
The JT8D high pressure turbine was revised to reduce leakage between the blade tip shrouds and the o...
An air-cooled turbine blade from an aircraft gas turbine engine chosen for its history of cracking w...
A full-scale J33 air-cooled split turbine rotor was designed and spin-pit tested to destruction. Str...
Two series of low cycle fatigue (LCF) test data for two groups of different aircraft gas turbine eng...
Environmental attack has the potential to limit turbine disk durability, particularly in next genera...
Recent activities of the Lewis Research Center are reviewed which are directed toward developing mat...
The next generation of subsonic commercial aircraft will require engines with improved efficiency an...
Recently, National Aeronautics and Space Administration (NASA) initiated a program to achieve the si...
Test rig for predicting thermal stress cracking in turbine stator or rotor blade