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- W2015472805 abstract "other conditions for providing a system circuit flow and keeping hot spots from occurring, it is anticipated that the hydraulic system would probably use a series of bleeds. That is, high-pressure fluid is diverted to the low-pressure side to produce system circulation. Usually -J to gpm flows are sufficient to accomplish the desired system temperature stabilizations. These system bleeds are now being used in certain present subsonic turbine-powered aircraft. Although some present high-temperature systems are using the MLO-8200 series of fluids, it is felt that these disiloxane based fluids have lower lubricity values than the petroleum based fluids. More than 4000 hr of operation have been conducted in laboratory tests with the MLO-7277 fluid in the 550°F range. Of this time, more than 250 hr were conducted on one test pump. The fluid used for this high-speed transport will be required to have thermal stability, inasmuch as there may be as many as four thermal cycles, or four Mach 3 flights/ 24-hr period. Care must be given to eliminate both air and water from the system to provide the correct system response and eliminate any possibilit}^ of spongy system operation." @default.
- W2015472805 created "2016-06-24" @default.
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- W2015472805 date "1964-01-01" @default.
- W2015472805 modified "2023-09-27" @default.
- W2015472805 title "Analytical method for designing turbine nozzle partitions" @default.
- W2015472805 doi "https://doi.org/10.2514/3.43554" @default.
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