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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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The development and practical introduction of a robot hot-stamping system for compressor blades in gas-turbine engines is discussed. The benefits of this system are noted.
The finishing of the flow sections of compressor blades is considered. A sequence of operations for this purpose in an automated cycle is proposed. The development of control programs for the grinding of flow sections of the blades is discussed, with allowance for the nonuniform distribution of the margin over the blade surface.
Combined compressor coolant injection and afterburning for turbojet engine thrust augmentation
Calculated performance of a mercury-compressor- jet powered aircraft using nuclear reactor as energy source
Cycle analysis of turbojet and turboprop engines - axial flow compressor requirements for gas turbine engines
Thermodynamic equations, solution, and experimental data for aerodynamic design of axial flow compressors
Steady state characteristics, stalling, and surge in axial flow compressors
Three-dimensional compressor flow theory and real flow effect
Design and measurement error effects on compressor performance
Compressor and gas turbine engine matching - power turbine, turbojet, and turboprop engines
Far field noise propagation of rotor-stator interaction in single stage axial flow research compressor
Single turning vane for elimination of flow separation in intake elbow of axial flow compressor
Elbow turning vane design for high recovery and Uniform distribution at exit of 90 deg intake elbow of axial flow compressor
Noise generation in axial flow compressors - acoustic data in form of noise radiation patterns from inlet-guide-vane-rotor-stator interactions
Advanced aerodynamic design and specifications of high efficiency Brayton cycle compressor for monatomic gas operation
Seal concepts evaluation for compressor end seals, stator interchange seals, and stator pivot seals in air breathing propulsion system
Brayton cycle 3.2 inch radial compressor performance evaluation over wide range of Reynolds numbers
Outlet angle in axial compressor cascades, accounting for effect of shear flows, Bernoulli surface rotation and flow separation