Effect of Overheating on Creep-rupture Properties of HS-31 Alloy at 1,500 Degrees F
Effect of Overheating on Creep-rupture Properties of HS-31 Alloy at 1,500 Degrees F

Author: John Paul Rowe

Publisher:

Published: 1957

Total Pages: 702

ISBN-13:

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An investigation of overheating HS-31 alloy to temperatures of 1,650 degrees, 1,800 degrees, 1,900 degrees, and 2,000 degrees F during the course of rupture tests 1,500 degrees F was carried out. The overheating was applied periodically for 2 minutes in most of the tests. The intent was to develop basic information on the effect of overheats on creep- rapture properties in order to assist in the evaluation of damage from overheats during gas- turbine operation.

Effect of Overheating on Creep-rupture Properties of S-816 Alloy at 1,500 Degrees F
Effect of Overheating on Creep-rupture Properties of S-816 Alloy at 1,500 Degrees F

Author: John P. Rowe

Publisher:

Published: 1957

Total Pages: 75

ISBN-13:

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The effects of overheats to temperatures of 1650, 1800, 1900, and 2000 F were evaluated in terms of the changes in creep-rupture characteristics at 1500 F of S-816 alloy under stresses within the range of rupture strengths of the alloy for 100 to 1000 hours. Overheat periods were predominantly of 2-minute duration and were applied cyclically at approximately 5- or 12-hour intervals. The possible damage from overheating was believed to include internal metal structure changes induced by exposure to the higher temperatures and loss of life by creep if stress was present during the overheats.

A Flight Evaluation and Analysis of the Effect of Icing Conditions on the ZPG-2 Airship
A Flight Evaluation and Analysis of the Effect of Icing Conditions on the ZPG-2 Airship

Author: William Lewis

Publisher:

Published: 1958

Total Pages: 648

ISBN-13:

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A series of test flights was conducted by the U. S. Navy over a 3-year period to evaluate the effects of icing on the operation of the ZFG-2 airship. In supercooled clouds, ice formed only on the forward edges of small protuberances and wires and presented no serious hazard to operation. Ice secretions of the glaze type which occurred in conditions described as freezing drizzle adversely affected various components to a somewhat greater extent. The results indicated a need for protection of certain components such as antennas, propellers, ad certain parts of the control system.