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  • 1
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    Emittance and absorptance of the national aeronautics and space administration ceramic thermal barrier coating (1978)
    Elsevier
    Details
    Publication Date: 1978-09-01
    Print ISSN: 0040-6090
    Electronic ISSN: 1879-2731
    Topics: Physics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Tests of NASA ceramic thermal barrier coating for gas turbine engines (1979)
    Elsevier
    Details
    Publication Date: 1979-12-01
    Print ISSN: 0040-6090
    Electronic ISSN: 1879-2731
    Topics: Physics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    The significance of thermal contact resistance in two-layer thermal-barrier-coated turbine vanes (1980)
    Elsevier
    Details
    Publication Date: 1980-11-01
    Print ISSN: 0040-6090
    Electronic ISSN: 1879-2731
    Topics: Physics
    Published by Elsevier
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    PAPER CURRENT
  • 4
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    Miniature high temperature plug-type heat flux gauges (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: The objective is to describe continuing efforts to develop methods for measuring surface heat flux, gauge active surface temperature, and heat transfer coefficient quantities. The methodology involves inventing a procedure for fabricating improved plug-type heat flux gauges and also for formulating inverse heat conduction models and calculation procedures. These models and procedures are required for making indirect measurements of these quantities from direct temperature measurements at gauge interior locations. Measurements of these quantities were made in a turbine blade thermal cycling tester (TBT) located at MSFC. The TBT partially simulates the turbopump turbine environment in the Space Shuttle Main Engine. After the TBT test, experiments were performed in an arc lamp to analyze gauge quality.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: In: International Instrumentation Symposium, 38th, Las Vegas, NV, Apr. 26-30, 1992, Proceedings (A93-37851 15-35); p. 263-271.
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Progress in the measurement of SSME turbine heat flux with plug-type sensors (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Data reduction was completed for tests of plug-type heat flux sensors (gauges) in a turbine blade thermal cycling tester (TBT) that is located at NASA/Marshall Space Flight Center, and a typical gauge is illustrated. This is the first time that heat flux has been measured in a Space Shuttle Main Engine (SSME) Turbopump Turbine environment. The development of the concept for the gauge was performed in a heat flux measurement facility at Lewis. In this facility, transient and steady state absorbed surface heat flux information was obtained from transient temperature measurements taken at points within the gauge. A schematic of the TBT is presented, and plots of the absorbed surface heat flux measured on the three blades tested in the TBT are presented. High quality heat flux values were measured on all three blades. The experiments demonstrated that reliable and durable gauges can be repeatedly fabricated into the airfoils. The experiment heat flux data are being used for verification of SSME analytical stress, boundary layer, and heat transfer design models. Other experimental results and future plans are also presented.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 3-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Calibrator tests of heat flux gauges mounted in SSME blades (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Measurements of heat flux to space shuttle main engine (SSME) turbine blade surfaces are being made in the Lewis heat flux calibration facility. Surface heat flux information is obtained from transient temperature measurements taken at points within the gauge. A 100-kW Vortek arc lamp is used as a source of thermal radiant energy. Thermoplugs, with diameters of about 0.190 cm and lengths varying from about 0.190 to 0.320 cm, are being investigated. The thermoplug is surrounded on all surfaces except the active surface by a pocket of air located in the circular annulus and under the back cover. Since the thermoplug is insulated, it is assumed that heat is conducted in a one-dimensional manner from the hot active surface to the cooler back side of the thermoplug. It is concluded that the miniature plug-type gauge concept is feasible for measurement of blade surface heat flux. It is suggested that it is important to measure heat flux near the hub on the suction surface and at the throat on SSME blades rotating in engines because stress and heat transfer coefficients are high in this region.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 99-104
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Heat flux calibration facility capable of SSME conditions (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: There is a need to more thoroughly characterize the hostile space shuttle main engine (SSME) turbopump environment. It has been estimated that component surface heat flux in the hot-gas environment is about 10 MW/square meter, and this is about 50 times that encountered in aircraft engines. Also, material temperature transients can be as high as 1000 K in about 1 second. These transients can cause durability problems such as material cracking. Heat flux sensors placed in the turbopump components can partially characterize this environment by measuring surface heat flux. These heat flux data can be used to verify analytical-stress, boundary-layer, and heat-transfer design models. Preliminary plans were discussed at the first SSME durablity conference for designing and fabricating a new facility for the calibration and durability testing of prototype heat flux sensors for the SSME. This facility, which is necessary for assessment of new heat flux gauge concepts needed in the hostile SSME turbopump environment, is described.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Structural Integrity and Durability of Reusable Space Propulsion Systems; p 47-49
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Heat flux measurements (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper discusses a new automated, computer-controlled heat flux measurement facility. Continuous transient and steady-state surface heat flux values varying from about 0.3 to 6 MW/sq m over a temperature range of 100 to 1200 K can be obtained in the facility. An application of this facility is the development of heat flux gages for continuous fast transient surface heat flux measurement on turbine blades operating in Space Shuttle main engine turbopumps. The facility is also useful for durability testing at fast temperature transients.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: ASME PAPER 89-GT-107
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Permeability Variation of a Taper-rolled Wire Cloth (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-E56L10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Plug-type heat flux gauge (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A plug-type heat flux gauge formed in a material specimen and having a thermoplug integrally formed in the material specimen, and a method for making the same are disclosed. The thermoplug is surrounded by a concentric annulus, through which thermocouple wires are routed. The end of each thermocouple wire is welded to the thermoplug, with each thermocouple wire welded at a different location along the length of the thermoplug. The thermoplug and concentric annulus may be formed in the material specimen by electrical discharge machining and trepanning procedures.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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