The purpose of this paper is to describe the new facility design and operation improvements, and to demonstrate utility by providing typical results obtained as part of a typical measurement program. Since 2002 a number of experiments have been conducted to generate a broad database for tip rubs using two unique experimental facilities at the Gas Turbine Laboratory of The Ohio State University. Development of an in-ground spin-pit facility specifically designed to investigate rub-in-systems for jet engine components using real hardware rotating at representative engine speeds was reported several years ago. While the original smaller facility is still in use, more recently a much larger in-ground spin-pit facility for which the basic design and operation of the blade tip/shroud incursion technique is very different from the original facility design has been commissioned, and the results of a measurement program completed using a full-scale titanium-alloy fan blade rubbing an abradable casing are presented. The Large Spin-Pit Facility [LSPF] is designed to allow rotating engine hardware from low RPM [typically a few thousands] to 18,000 rpm, using two interchangeable spindle arrangements mounted above ground onto an in-ground containment tank. The LSPF is also designed to allow the progressive insertion of a casing segment into the path of a single-bladed or multiple-bladed disk. Segments extending 90 or 120 degrees are in use for different applications. For the configuration discussed in this paper, a 90-degree segment of a representative fan casing is forced to rub the tip of a titanium-alloy fan blade at a rotational speed in the vicinity of 6000 rpm.

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