This paper will discuss a study of an innovative design for an advanced turbine rotor that could have a great impact on future engines. The design challenge is to provide a minimum weight turbine rotor system that can withstand beyond state-of-the-art levels of (turbine annulus area multiplied by speed squared). An limit has been reached for high-pressure turbine (HPT) disks configured in conventional (single web) geometry with state-of-the-art nickel alloys. The problem has reached the point where increased has been declared a “break-through” technology. The twin-web disk has the potential to provide this break through. This paper will present the history of this turbine rotor design, analytical results, material/component processing, and concept validation results. All work was performed under an Air Force sponsored program entitled “Composite Ring Reinforced Turbine” (CRRT).
Twin Web Disk: A Step Beyond Convention
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Stockholm, Sweden, June 2–5, 1998; ASME Paper 98-GT-505. Manuscript received by the IGTI Division October 1997; final revision received by the ASME Headquarters March 1998. Associate Editor: R. Kielb.
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Cairo, R. R., and Sargent, K. A. (March 26, 2002). "Twin Web Disk: A Step Beyond Convention ." ASME. J. Eng. Gas Turbines Power. April 2002; 124(2): 298–302. https://doi.org/10.1115/1.1445440
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