Browse Topic: Thermal runaway
Researchers at the National Aeronautics and Space Administration (NASA) have conducted a series of module-level tests on electric Vertical Take-off and Landing (eVTOL) Energy Storage Systems (ESS) for the generation of dynamic impact data to support standards developments. The tests were conducted on zero-state-of-charge Electric Power Systems (EPS) Electric Propulsion Ion Core (EPIC) modules at the National Institute for Aviation Research (NIAR), utilizing the NIAR outdoor drop test setup and personnel. Four total tests were conducted. For each test, the module was dropped at a specific orientation from a height of 50 feet while connected to a guided trolley in order to assess the effects of a 50-foot drop test on the ESS. The test velocities ranged between 46.9 and 52.8 ft/s with impact angles ranging between a flat, zero-degree impact and 18 degrees. Data were recorded in the form of temperatures, cell-level voltage, module level acceleration and digital image correlation from the tests. Accelerations were in the range of 1,500 g for a few millisecond duration, which were indicative of a shock type loading condition. No modules entered thermal runaway, and post-test inspections revealed a variety of internal deformations and damage present in the various modules tested, with specific damage occurring for specific orientations. The modules were ranked according to a custom developed scoring rubric developed by utilizing the test and post-test inspection results. The results were compiled, reported, and will be used to guide future ESS testing. Part 1 discusses the loading environments in the modules, while Part 2 will discuss the deformation and damage in the modules.
This paper presents experimental research aimed at developing novel low lubrication methods for rotorcraft and jet engines, focusing on sustaining minimal lubrication to prevent catastrophic bearing failure during loss of lubrication (LoL) events or to increase fuel consumption performance on once-through, fuel-oil bearing lubrication engines. Utilizing two high-speed bearing test rigs simulating low and high thrust class engine conditions, the study establishes lower bounds for oil flow rates necessary to maintain thermal stability and prevent thermal runaway in hybrid ball bearings. These findings inform the design of the Zulu Pod (ZPod), a passively driven, self-contained oil delivery system that uses engine compressor bleed air to precisely meter lubricant flow. Engine test stand results demonstrate that replacing traditional fuel-oil lubrication with the ZPod system reduces thrust specific fuel consumption (TSFC) by an average of 7%, with up to 11% savings, without compromising engine thrust or bearing health. The ZPod offers a simplified, efficient alternative to fuel-lubricated systems by eliminating fuel diversion for lubrication, enhancing fuel efficiency, and maintaining bearing performance in attritable or single-use engines. Additionally, the study highlights the potential of minimal lubrication supplied by the ZPod to extend operational life during LoL scenarios, enabling safer aircraft recovery. Future work will focus on extending testing to higher thrust classes and optimizing ZPod designs for broader applications.
xEVs involved in incidents present unique hazards associated with the high voltage system (including the battery system). These hazards can be grouped into three categories: chemical, electrical, and thermal. The potential consequences can vary depending on the size, configuration, and specific battery chemistry. Other incidents may arise from secondary events such as garage fires and floods. These types of incidents are also considered in the recommended practice (RP). This RP aims to describe the potential consequences associated with hazards from xEVs and suggest common procedures to help protect emergency responders, tow and/or recovery, storage, repair, and salvage personnel after an incident has occurred with an electrified vehicle. Industry design standards and tools were studied and where appropriate, suggested for responsible organizations to implement. Lithium ion (Li-ion) batteries used for vehicle propulsion power are the assumed battery system of this RP. This chemistry is the prevailing technology associated with high voltage vehicle electrification today and the foreseeable future. The hazards associated with Li-ion battery chemistries are addressed in this RP. Other chemistries and alternative propulsion systems including hydrogen fuel cells are not considered in this version of SAE J2990. Recommendations for hazards associated with hydrogen vehicles can be found in SAE J2990/1.
ABSTRACT Loss of the primary lubrication in a helicopter gearbox can result in a very rapid or immediate failure of the transmission system due to drastic reduction in heat removal and the degrading tribological performance of the highly loaded gear contacts. Current methods for predicting the gearbox life and performance under loss-of-lubrication condition are largely experimental and experience-based and thus provide limited insights into the underlying physics of the evolving tribology of gears and bearings. One of the major technical barriers that currently constrain the physics-based predictive capability is the limited understanding and quantitative modeling of the thermomechanical response of tooth surface after the loss of lubrication. The experimental portion of the effort described in this paper is a systematic study of the temperature rise and tooth surface evolution for a generic gearbox under loss-of-lubrication conditions. The overall thermal conditions of the gearbox are monitored through an infrared thermal imaging camera and the transient temperatures at multiple locations of gear and pinions are continuously measured with thermocouples. Tooth samples from different stages towards the final thermal runaway were examined to reveal the underlying physics of the surface evolution and failure after the loss of lubrication. In the modeling effort, FE modeling was combined with the transient thermal mixed-EHL model of gear meshing to simulate the gear thermal response and a sensitivity study was conducted with the validated thermal model to evaluate the potential underlying physics of the thermal runaway. The combined heat generation from frictional sliding and plastic deformation was also determined through the FE simulation of mesoscale sliding contact of tooth surface. The experimental and numerical results suggest that the potential mechanism of the final catastrophic failure is the adiabatic shear instability associated with severe plastic deformation and phase transformation.
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