Reversible ring counter employing cascaded single SCR stages Patent
Reversible ring counter using cascaded single silicon controlled rectifier stages
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Reversible ring counter using cascaded single silicon controlled rectifier stages
Mode coupling and energy cascades in turbulent spectrum of thermal ionized plasma
Testing low reaction jet turbine stator blades in six-blade annular cascade
Two dimensional cascade test of jet flap turbine rotor blade
Radiation heat transfer characteristics of turbine vane airfoils in water-cooled cascade
Development of model for description of nucleon-nucleon and pion-nucleon collisions at high energy and Monte Carlo description of Nucleor Cascade
Fortran 4 computer program for design application of stagger angle replacing inlet flow angle for given blade cascade
Noise reduction studies involving variable geometry inlet guide vanes for choking using two-sector cascade apparatus with three inlet configurations
Three dimensional transonic shear flow structure in turbomachine cascade, using time dependent numerical solution
Low gain microwave amplifier cascade DC to RF conversion efficiency analysis
Lossless two-port cascade network synthesis using computer-oriented technique
Hanle cascade effects on atomic lifetime reliability from collisional excitation experiments
Supercavitating flow past straight cascade with arbitrary blade shapes, considering lift and drag coefficients, cavitation number, cavity shape and exit flow conditions
Lateral spread of nuclear-electromagnetic cascades in iron absorber from three-dimensional Monte Carlo simulation
Cascaded thermoelectric generator using Si-Ge and Pb-Te elements with heat pipe interstage coupling
A jet-flap blade was designed for a velocity diagram typical of the first-stage stator of a jet engine turbine and was tested in a simple two-dimensional cascade of six blades. The principal measurements were blade surface static pressure and cross-channel surveys of exit total pressure, static pressure, and flow angle. The results of the experimental investigation include blade loading, exit angle, flow, and loss data for a range of exit critical velocity ratios and three jet flow conditions.
Experimental flow and heat transfer data obtained for an air-cooled turbine vane tested in a static cascade at gas temperatures and pressures to 1644 K (2500 F) and 31 N/cm2 (45 psia), respectively, are presented. Average and local vane temperatures were correlated in several ways. Calculated and measured coolant flows and vane temperatures are compared. Potential allowable increases in gas temperature are also discussed.