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Low Noise Research Fan Stage DesignThis report describes the design of a Low Noise ADP Research Fan stage. The fan is a variable pitch design which is designed at the cruise pitch condition. Relative to the cruise setting, the blade is closed at takeoff and opened for reverse thrust operation. The fan stage is a split flow design with fan exit guide vanes and core stators. This fan stage design was combined with a nacelle and engine core duct to form a powered fan/nacelle, subscale model. This model is intended for use in aerodynamic performance, acoustic and structural testing in a wind tunnel. The model has a 22-inch outer fan diameter and a hub-to-top ratio of 0.426 which permits the use of existing NASA fan and cowl force balance designs and rig drive system. The design parameters were selected to permit valid acoustic and aerodynamic comparisons with the PW 17-inch rig previously tested under NASA contract. The fan stage design is described in detail. The results of the design axisymmetric analysis at aerodynamic design condition are included. The structural analysis of the fan rotor and attachment is described including the material selections and stress analysis. The blade and attachment are predicted to have adequate low cycle fatigue life, and an acceptable operating range without resonant stress or flutter. The stage was acoustically designed with airfoil counts in the fan exit guide vane and core stator to minimize noise. A fan-FEGV tone analysis developed separately under NASA contract was used to determine these airfoil counts. The fan stage design was matched to a nacelle design to form a fan/nacelle model for wind tunnel testing. The nacelle design was developed under a separate NASA contract. The nacelle was designed with an axisymmetric inlet, cowl and nozzle for convenience in testing and fabrication. Aerodynamic analysis of the nacelle confirmed the required performance at various aircraft operating conditions.
Document ID
19990095609
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Hobbs, David E.
(Pratt and Whitney Aircraft East Hartford, CT United States)
Neubert, Robert J.
(Pratt and Whitney Aircraft East Hartford, CT United States)
Malmborg, Eric W.
(Pratt and Whitney Aircraft East Hartford, CT United States)
Philbrick, Daniel H.
(Pratt and Whitney Aircraft East Hartford, CT United States)
Spear, David A.
(Pratt and Whitney Aircraft East Hartford, CT United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1995
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-9125
NASA-CR-195382
NAS 1.26:195382
Funding Number(s)
CONTRACT_GRANT: NAS3-26618
PROJECT: RTOP 538-03-11
Distribution Limits
Public
Copyright
Public Use Permitted.
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