Aerodynamic performance of a 4.59-inch modified radial-inflow turbine for a single-shaft Brayton cycle space power system
Aerodynamic characteristics of a stator modified gas turbine for single shaft Brayton cycle power system
Kofskey, M. G.↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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A nickel base alloy, WAZ-20, with improved strength in the 2000 deg to 2200 deg F range
Development and high temperature tests of high strength nickel alloy for stator vanes of gas turbine engines
Freche, J. C.↗
The analysis of geometry and design-point performance of axial-flow turbines using specified meridional velocity gradients. Part 2 - Design examples
Computer program for design of axial flow turbines with velocity distribution gradients at stator and rotor exits
Carter, A. F.↗
Variables in turbine erosion
Study of impact erosion in the operation of turbomachinery is undertaken to predict the results for particular designs. The test program investigates the effects of turbine stator blade shape, rotor blade shape, and variations in test conditions.
Baughman, J. R.↗
Computer program for the design of axial-flow turbines
Computer program, capable of analyzing single and multispool units, computes absolute and relative flow fields within the turbine at the first stator inlet, at each interblade row plane, and at the final rotor exit. No simplifying assumptions are made which would result in restrictive design.
Carter, A. F.↗
A computational study of rotational noise
Computed output graphs for blade loading and rotational noise generation by rotor stator interactions
Tana, H. K.↗
A new method for analysis of transonic flow
Finite difference method for transonic flow solution in axial stator
Katsanis, T.↗
A nickel base alloy, WAZ-20, with improved strength in the 2000 to 2200 F range
Nickel base alloy, WAZ-20 with improved strength in 2000-2200 F range for application to gas turbine engine stator vanes
Freche, J. C.↗
High temperature compounds for turbine vanes Final report
Mechanical properties of high temperature composites for use as turbine stator vanes
Cannon, R. M., Jr.↗
Analyses of cooled turbine airfoil configurations at conditions of supersonic flight
Analysis of first stage turbine stator vane and rotor blade cooling designs for application in highspeed aircraft
Stepka, F. S.↗
Experimental quiet engine program. Volume 2, phase 1 - Engine design report
Low pressure turbofan rotor, stator, frame, and exhaust nozzle designs for turbofan engine noise reduction including acoustics and engine tests
Source record↗
Experimental windage studies for high-speed alternators
Windage data for inert gas in high speed generators rotor-stator gap, investigating turbulent velocity profiles
Gorland, S. H.↗
Supersonic turbine design and performance
Methods for designing supersonic stator and rotor blading corrected for boundary layer displacement thickness are summarized. Computer programs based on these methods have been reported in NASA publications. Analytical blade losses for blading of this type are presented and design limitations resulting from consideration of flow separation and supersonic starting are discussed. In addition, a summary of the experimental performance of a single-stage turbine designed by these methods is given.
Goldman, L. J.↗
Variable geometry aft-fan for takeoff quieting or thrust augmentation of a turbojet engine
A concept is presented that combines the low-noise and high-thrust characteristics of a turbofan at takeoff, together with its high efficiency at subsonic flight speeds, with the high efficiency of a turbojet at supersonic cruise. It consists of a free turbine with tip fan mounted behind the turbine of a conventional turbojet engine. Fan air is supplied from blow-in doors or is ducted from the main engine inlet. At high flight speeds where fan augmentation is not desirable, the fan inlet is closed and the free turbine is stopped by adjustment of its variable-camber stators. Estimates of noise, cycle performance, and example configurations are presented for a typical supersonic transport application.
Weber, R. J.↗
Design and experimental results of a highly loaded, low solidity, jet flap rotor
The overall performance of a single-stage turbine with a low solidity jet flap rotor blade assembly was tested over a range of cavity pressure ratios, equivalent speeds, and expansion ratios. The rotor blades were designed with negative hub reaction and a mean-line axial chord solidity of 0.922. The results of the investigation are compared with the performance of a modified jet flap rotor blade which was designed to similar velocity diagrams but with a mean-section, axial chord solidity of 1.541. Both rotors were tested with the same stator.
Bettner, J. L.↗
Two-Stage Fan I: Aerodynamic and Mechanical Design
A two-stage, highly-loaded fan was designed to deliver an overall pressure ratio of 2.8 with an adiabatic efficiency of 83.9 percent. At the first rotor inlet, design flow per unit annulus area is 42 lbm/sec/sq ft (205 kg/sec/sq m), hub/tip ratio is 0.4 with a tip diameter of 31 inches (0.787 m), and design tip speed is 1450 ft/sec (441.96 m/sec). Other features include use of multiple-circular-arc airfoils, resettable stators, and split casings over the rotor tip sections for casing treatment tests.
Messenger, H. E.↗
Engine investigation of an air-cooled turbine rotor blade incorporating impingement-cooled leading edge, chordwise passages, and a slotted trailing edge
Experimental temperatures are presented for an air-cooled turbine rotor blade tested in an engine. The data were obtained for turbine stator inlet temperatures from 2000 to 2500 F and for turbine-inlet gas pressures from 32 to 46 psia. Average and local blade heat-transfer data are correlated. Potential allowable increases in gas temperature are also discussed.
Dengler, R. P.↗
Rotor windage losses for Lundell alternators
The Lundell alternator is being investigated for power system applications. At the high speeds required, power loss due to windage can become high and result in significant heating of the alternator. This loss must be incorporated in the cooling design. The velocity profiles expected in these alternators are highly turbulent, and the Reynolds numbers are well above the levels previously reported; the available data could only be extrapolated. For this reason, a range of experimental data was generated to permit accurate calculation of the windage power loss for Lundell alternator design. Windage tests were conducted on two concentric rotor-stator configurations in ambient air, producing Reynolds numbers as high as 100,000. Using the data obtained, a method was developed to calculate the windage loss for any Lundell alternator given the geometry and cavity conditions.
Gorland, S. H.↗