Evaluation Of High Temperature Materials Systems With An Arc-Plasma-Jet
Report Number: ML TDR 64-73
Author(s): Smith, Howard E., Wurst, John C.
Corporate Author(s): Dayton Univ Ohio Research Inst
Laboratory: Air Force Materials Laboratory
Date of Publication: 1964-06
Pages: 202
Contract: AF 33(616)-7838
DoD Project: 7381
DoD Task: 738103
Identifier: AD0604418
Abstract:
A small arc-plasma-jet was suitably modified and utilized for the evaluation and screening of high temperature materials at heat flux levels ranging from 10 to 500 Btu/sq. ft-sec. A 'standard' evaluation procedure was employedto characterize a number of systems representing ablating, insulating, and heat sink type materials. Results of these tests are presented in terms of weight loss, density change, depth and volume of erosion, and front and back surface temperatures. A metallographic analysis of coating failures in the XLR-99 thrust chamber of the X-15 research aircraft and the subsequent development of a thermal shock test with the plasma-jet for sprayed ceramic coatings are discussed. The results of an extensive evaluation of protective coatings and the field test verification of these results are presented. Preliminary tests leading to the development of a dynamic oxidation test are discussed and the results of arc-plasma-jet tests of five silicide coatings on Mo-1/2% Ti are presented.
Provenance: Lockheed Martin Missiles & Fire Control
Author(s): Smith, Howard E., Wurst, John C.
Corporate Author(s): Dayton Univ Ohio Research Inst
Laboratory: Air Force Materials Laboratory
Date of Publication: 1964-06
Pages: 202
Contract: AF 33(616)-7838
DoD Project: 7381
DoD Task: 738103
Identifier: AD0604418
Abstract:
A small arc-plasma-jet was suitably modified and utilized for the evaluation and screening of high temperature materials at heat flux levels ranging from 10 to 500 Btu/sq. ft-sec. A 'standard' evaluation procedure was employedto characterize a number of systems representing ablating, insulating, and heat sink type materials. Results of these tests are presented in terms of weight loss, density change, depth and volume of erosion, and front and back surface temperatures. A metallographic analysis of coating failures in the XLR-99 thrust chamber of the X-15 research aircraft and the subsequent development of a thermal shock test with the plasma-jet for sprayed ceramic coatings are discussed. The results of an extensive evaluation of protective coatings and the field test verification of these results are presented. Preliminary tests leading to the development of a dynamic oxidation test are discussed and the results of arc-plasma-jet tests of five silicide coatings on Mo-1/2% Ti are presented.
Provenance: Lockheed Martin Missiles & Fire Control