Accession Number : ADA326922
Title : JTAGG II Brush Seal Test Results.
Descriptive Note : Technical memo.,
Corporate Author : NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
Personal Author(s) : Arora, Gul K. ; Proctor, Margaret P.
PDF Url : ADA326922
Report Date : JUL 1997
Pagination or Media Count : 18
Abstract : The Tri-services JTAGG II engine uses two identical brush seals, in tandem, located aft of the high pressure compressor. The engine operating conditions, at intermediate rated power (IRP), for this seal are estimated to be 50,000 rpm (899 ft/sec) speed, 175 psid air to air pressure differential and 1200 deg F air temperature. The testing was comprised of static air leakage, performance, seal offset, rotor run out tests and a 50 hr endurance test in the NASA Lewis seal rig. Based on the test results, it is concluded that the brush seal design should be able to meet the air leakage flow factor goal of less than 0.004 for the engine IRP operating conditions. As a comparison, a labyrinth seal in this location with a 0.005 in. typical radial clearance has an estimated leakage flow factor of 0.007. The long term seal life can not be predicted accurately due to the limited endurance testing of 50 hr. However, based on the excellent condition of the test seal and rotor after 50 hr of testing, it is anticipated that the seals should easily meet the JTAGG II engine test requirement.
Descriptors : *GAS GENERATOR ENGINES, TEST AND EVALUATION, VELOCITY, LEAKAGE(FLUID), HIGH PRESSURE COMPRESSORS, AIR PRESSURE, HYSTERESIS, SEALS(STOPPERS), BRUSHES, LABYRINTH SEALS.
Subject Categories : Hydraulic and Pneumatic Equipment
Test Facilities, Equipment and Methods
Distribution Statement : APPROVED FOR PUBLIC RELEASE