Proceedings ArticleDOI
Instrumentation for Propulsion Systems Development
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TLDR
In this paper, the advantages and limitations of each instrument and technique are discussed and the possibility of modifying them for use in developing various propulsion systems is suggested, as well as the possibility to use them for propulsion systems.Abstract:
Apparatus and techniques developed or used by NASA-Lewis to make steady state or dynamic measurements of gas temperature, pressure, and velocity and of the temperature, tip clearance, and vibration of the blades of high-speed fans or turbines are described. The advantages and limitations of each instrument and technique are discussed and the possibility of modifying them for use in developing various propulsion systems is suggested.read more
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Experimental determination of time constants and nusselt numbers for bare- wire thermocouples in high-velocity air streams and analytic approximation of conduction and radiation errors
TL;DR: In this article, the results of experiments conducted to determine time constants of several bare-wire thermocouples mounted in cross flow to an air stream were presented, and the results regarding the time constants, Nusselt numbers, effective gas temperature and some numerical calculations were provided.
Journal ArticleDOI
Detection and study of compressor-blade vibration
TL;DR: In this paper, a new device capable of detecting rotor-blade vibration without contact is described, and the vibratory stresses generated must be experimentally determined, which is difficult to be done in practice.
Electrical Techniques for Compensation of Thermal Time Lag of Thermocouples and Resistance Thermometer Elements
TL;DR: In this article, basic electrical networks that compensate for the thermal time lag of thermocouple and resistance thermometer elements used in combustion research and in the control of jet power plants are described.
Recovery and radiation corrections and time constants of several sizes of shielded and unshielded thermocouple probes for measuring gas temperature
TL;DR: In this article, performance characteristics were experimentally determined for several sizes of a shielded and unshielded thermocouple probe design and the probes were tested through a Mach number range of 02 to 09, through a temperature range of room ambient to 1420 K, and through a total pressure range of 003 to 022 MPa (03 to 22 atm).
Study of Screeching Combustion in a 6-inch Simulated Afterburner
TL;DR: In this article, the authors investigated the mechanism of screech in a 6-inch-diameter simulated afterburner and developed a probe microphone to measure frequency, relative amplitude and relative phasing of the pressure oscillations at positions in a screeching combustor.