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Hamilton Standard Q-fan demonstrator dynamic pitch change test program, volume 1Tests of a full scale variable pitch fan engine to obtain data on the structural characteristics, response times, and fan/core engine compatibility during transient changes in blade angle, fan rpm, and engine power is reported. Steady state reverse thrust tests with a take off nozzle configuration were also conducted. The 1.4 meter diameter, 13 bladed controllable pitch fan was driven by a T55 L 11A engine with power and blade angle coordinated by a digital computer. The tests demonstrated an ability to change from full forward thrust to reverse thrust in less than one (1) second. Reverse thrust was effected through feather and through flat pitch; structural characteristics and engine/fan compatibility were within satisfactory limits.
Document ID
19760022143
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Demers, W. J.
(Hamilton Standard Windsor Locks, CT, United States)
Nelson, D. J.
(Hamilton Standard Windsor Locks, CT, United States)
Wainauski, H. S.
(Hamilton Standard Windsor Locks, CT, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
HSER-6700-VOL-1
NASA-CR-134861
Report Number: HSER-6700-VOL-1
Report Number: NASA-CR-134861
Accession Number
76N29231
Funding Number(s)
CONTRACT_GRANT: NAS3-18513
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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