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  • 11
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    Compliant Foil Seal Investigations (2004)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: Room temperature testing of an 8.5 inch diameter foil seal was conducted in the High Speed, High Temperature Turbine Seal Test Rig at the NASA Glenn Research Center. The seal was operated at speeds up to 30,000 rpm and pressure differentials up to 75 psid. Seal leakage and power loss data will be presented and compared to brush seal performance. The failure of the seal and rotor coating at 30,000 rpm and 15 psid will be presented and future development needs discussed.
    Keywords: Aircraft Propulsion and Power
    Type: 2003 NASA Seal/Secondary Air System Workshop, Volume 1; 127-138; NASA/CP-2004-212963/VOL1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Preliminary Test Results of a Non-Contacting Finger Seal on a Herringbone-Grooved Rotor (2009)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: The baseline non-contacting finger seal is a NASA patented design. The primary difference between it and Gul Aroras design patented by AlliedSignal is that there are no lift pads on the high pressure fingers. The baseline non-contacting finger seal is comprised of a back plate, aft spacer, aft (or low pressure) finger element, forward (or high pressure) finger element, forward spacer, and front plate. The components are held together with 20 flat head screws. A typical seal would have a back plate of approximately the same thickness as the front plate and would be riveted together. The thicker back plate allows use of threaded fasteners so that different finger elements can be tested without having to replace all the individual seal components. The finger elements are essentially washers made of thin sheet stock with multiple curved slots machined around the inner diameter to form the fingers. They are clocked so that the fingers of one cover the slots of the other. The aft finger element fingers have axial extensions or "lift pads" at the seal id that are concentric to the rotor. The fingers act as cantilever beams and flex in response to rotor dynamic motion and radial growth of the rotor due to centrifugal or thermal forces.
    Keywords: Mechanical Engineering
    Type: 2008 NASA Seal/Secondary Air System Workshop; 139-158; NASA/CP-2009-215677
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Overview of NASA Glenn Seal Project (2009)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: NASA Glenn is currently performing seal research supporting both advanced turbine engine development and advanced space vehicle/propulsion system development. Studies have shown that decreasing parasitic leakage by applying advanced seals will increase turbine engine performance and decrease operating costs. Studies have also shown that higher temperature, long life seals are critical in meeting next generation space vehicle and propulsion system goals in the areas of performance, reusability, safety, and cost. Advanced docking system seals need to be very robust resisting space environmental effects while exhibiting very low leakage and low compression and adhesion forces. NASA Glenn is developing seal technology and providing technical consultation for the Agencys key aero- and space technology development programs.
    Keywords: Mechanical Engineering
    Type: 2008 NASA Seal/Secondary Air System Workshop; 57-90; NASA/CP-2009-215677
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Overview of CEV Thermal Protection System Seal Development (2009)
    In:  CASI
    Details
    Publication Date: 2018-06-06
    Description: NASA GRC supporting design, development, and implementation of numerous seal systems for the Orion CEV: a) HS-to-BS interface. b) Compression pad. HS-to-BS Interface Seal System: a) design has evolved as a result of changes with the CEV TPS. b) Seal system is currently under development/evaluation. Coupon level tests, Arc jet tests, and Validation test development. Compression Pad: a) Finalizing design options. b) Evaluating material candidates.
    Keywords: Mechanical Engineering
    Type: 2008 NASA Seal/Secondary Air System Workshop; 253-269; NASA/CP-2009-215677
    Format: application/pdf
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  • 15
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    "Kicking Up Some Dust": An Experimental Investigation Relating Lunar Dust Erosive Wear to Solar Power Loss (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The exhaust from retrograde rockets fired by spacecraft landing on the Moon can accelerate lunar dust particles to high velocities. Information obtained from NASA's Apollo 12 mission confirmed that these high-speed dust particles can erode nearby structures. This erosive wear damage can affect the performance of optical components such as solar concentrators. Solar concentrators are objects which collect sunlight over large areas and focus the light into smaller areas for purposes such as heating and energy production. In this work, laboratory-scale solar concentrators were constructed and subjected to erosive wear by the JSC-1AF lunar dust simulant. The concentrators were focused on a photovoltaic cell and the degradation in electrical power due to the erosive wear was measured. It was observed that even moderate exposure to erosive wear from lunar dust simulant resulted in a 40 percent reduction in power production from the solar concentrators.
    Keywords: Lunar and Planetary Science and Exploration; Optics
    Type: NASA/TM-2013-218068 , E-18744 , Society of Tribologists and Lubrication Engineers (STLE) Annual Meeting; May 05, 2013 - May 09, 2013; Detroit, MI; United States
    Format: application/pdf
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  • 16
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    Continued Evaluation of Gear Condition Indicator Performance on Rotorcraft Fleet (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper details analyses of condition indicator performance for the helicopter nose gearbox within the U.S. Army's Condition-Based Maintenance Program. Ten nose gearbox data sets underwent two specific analyses. A mean condition indicator level analysis was performed where condition indicator performance was based on a 'batting average' measured before and after part replacement. Two specific condition indicators, Diagnostic Algorithm 1 and Sideband Index, were found to perform well for the data sets studied. A condition indicator versus gear wear analysis was also performed, where gear wear photographs and descriptions from Army tear-down analyses were categorized based on ANSI/AGMA 1010-E95 standards. Seven nose gearbox data sets were analyzed and correlated with condition indicators Diagnostic Algorithm 1 and Sideband Index. Both were found to be most responsive to gear wear cases of micropitting and spalling. Input pinion nose gear box condition indicators were found to be more responsive to part replacement during overhaul than their corresponding output gear nose gear box condition indicators.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2013-217876 , E-18675 , Airworthiness, Condition Based Maintenance (CBM), and Health and Usage Monitoring (HUMS) Conference; Feb 11, 2013 - Feb 13, 2013; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Integrating Condition Indicators and Usage Parameters for Improved Spiral Bevel Gear Health Monitoring (2013)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The objective of this study was to illustrate the importance of combining Health Usage Monitoring Systems (HUMS) data with usage monitoring system data when detecting rotorcraft transmission health. Six gear sets were tested in the NASA Glenn Spiral Bevel Gear Fatigue Rig. Damage was initiated and progressed on the gear and pinion teeth. Damage progression was measured by debris generation and documented with inspection photos at varying torque values. A contact fatigue analysis was applied to the gear design indicating the effect temperature, load and reliability had on gear life. Results of this study illustrated the benefits of combining HUMS data and actual usage data to indicate progression of damage for spiral bevel gears.
    Keywords: Aircraft Propulsion and Power
    Type: E-18665 , American Helicopter Society 69th Annual Forum; May 21, 2013 - May 23, 2013; Phoenix, AZ; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 18
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    2007 NASA Seal/Secondary Air System Workshop (2008)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The 2007 NASA Seal/Secondary Air System workshop covered the following topics: (i) Overview of NASA's new Orion project aimed at developing a new spacecraft that will fare astronauts to the International Space Station, the Moon, Mars, and beyond; (ii) Overview of NASA's fundamental aeronautics technology project; (iii) Overview of NASA Glenn s seal project aimed at developing advanced seals for NASA's turbomachinery, space, and reentry vehicle needs; (iv) Reviews of NASA prime contractor, vendor, and university advanced sealing concepts, test results, experimental facilities, and numerical predictions; and (v) Reviews of material development programs relevant to advanced seals development. Turbine engine studies have shown that reducing seal leakage as well as high-pressure turbine (HPT) blade tip clearances will reduce fuel burn, lower emissions, retain exhaust gas temperature margin, and increase range. Turbine seal development topics covered include a method for fast-acting HPT blade tip clearance control, noncontacting low-leakage seals, intershaft seals, and a review of engine seal performance requirements for current and future Army engine platforms.
    Keywords: Mechanical Engineering
    Type: NASA/CP-2008-215263/VOL1 , E-16554-1 , 2007 NASA Seal/Secondary Air System Workshop; Nov 13, 2007 - Nov 14, 2007; Cleveland, OH; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 19
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    Gear Tooth Wear Detection Algorithm (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Vibration-based condition indicators continue to be developed for Health Usage Monitoring of rotorcraft gearboxes. Testing performed at NASA Glenn Research Center have shown correlations between specific condition indicators and specific types of gear wear. To speed up the detection and analysis of gear teeth, an image detection program based on the Viola-Jones algorithm was trained to automatically detect spiral bevel gear wear pitting. The detector was tested using a training set of gear wear pictures and a blind set of gear wear pictures. The detector accuracy for the training set was 75 percent while the accuracy for the blind set was 15 percent. Further improvements on the accuracy of the detector are required but preliminary results have shown its ability to automatically detect gear tooth wear. The trained detector would be used to quickly evaluate a set of gear or pinion pictures for pits, spalls, or abrasive wear. The results could then be used to correlate with vibration or oil debris data. In general, the program could be retrained to detect features of interest from pictures of a component taken over a period of time.
    Keywords: Aeronautics (General)
    Type: NASA/TM-2015-218830 , E-19102
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    Performance Evaluation of an Actuator Dust Seal for Lunar Operation (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Exploration of extraterrestrial surfaces (e.g. moon, Mars, asteroid) will require durable space mechanisms that will survive potentially dusty surface conditions in addition to the hard vacuum and extreme temperatures of space. Baseline tests with lunar simulant were recently completed at NASA GRC on a new Low-Temperature Mechanism (LTM) dust seal for space actuator application. Following are top-level findings of the tests completed to date in vacuum using NU-LHT-2M lunar-highlands simulant. A complete set of findings are found in the conclusions section.Tests were run at approximately 10-7 torr with unidirectional rotational speed of 39 RPM.Initial break-in runs were performed at atmospheric conditions with no simulant. During the break-in runs, the maximum torque observed was 16.7 lbf-in. while the maximum seal outer diameter temperature was 103F. Only 0.4 milligrams of NU-LHT-2M simulant passed through the sealshaft interface in the first 511,000 cycles while under vacuum despite a chip on the secondary sealing surface.Approximately 650,000 of a planned 1,000,000 cycles were completed in vacuum with NU-LHT-2M simulant.Upon test disassembly NU-LHT-2M was found on the secondary sealing surface.
    Keywords: Lunar and Planetary Science and Exploration
    Type: NASA/TM-2013-216587 , E-18781 , GRC-E-DAA-TN10013
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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