Accession Number:

ADA350454

Title:

FAA T53-L-13L Turbine Fragment Containment Test

Descriptive Note:

Final rept.

Corporate Author:

NAVAL AIR WARFARE CENTER WEAPONS DIV CHINA LAKE CA

Personal Author(s):

Report Date:

1998-06-01

Pagination or Media Count:

16.0

Abstract:

The result of the FAA T53-L-13L engine turbine disk fragment containment test is presented in this report. A containment ring was designed and fabricated by Pepin Associates, Inc. and provided to the Naval Air Warfare Center, Weapons Division by the William J. Hughes Technical Center. This ring was fabricated with a 0.014-inch titanium inner and outer sleeve. One-inch-thick Kevlar 29 ballistic fabric made up the primary structure of the containment ring. The ring was reinforced with titanium rods inserted through the fabric and laser welded to the inner and outer sleeves. The engine and containment ring were installed in an UH-1 Huey helicopter. The second stage power turbine disk was notched so that the disk would rupture at approximately 20,400 rpm. The engine was started and immediately accelerated to minimize the chance of a premature rupture. The event was recorded on high-speed film at 4000 pictures per second. The disk ruptured as the engine accelerated through 19,629 rpm. The disk ruptured into three equal sections approximately 3.6 lbs. each. The result was a contained tri-hub burst with minor bulging of the containment ring and little sign of distress to the airframe. This test demonstrated the capability to contain a tri-hub burst on a medium sized turboshaft helicopter engine.

Subject Categories:

  • Helicopters
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE