The Effect of Increase in Combustion-Air Inlet Temperature from 80 to 130 deg F on the Sea-Level Performance of a 22-Inch-Diameter Pulse-Jet Engine
Abstract
Data from a sea-level investigation of a 22-inch diameter pulse-jet engine installed on a thrust stand were analyzed to determine the effect on the engine performance of a change in combustion-air temperature from approximately 80 to 130 deg F. The tests at both combustion-air temperatures covered a range of simulated ram pressures from 19 to 58 inches of water for the fuel flow range of resonant operation. The results show that, when the combustion-air temperature was increased from 80 to 130 deg F for the same conditions of fuel flow and simulated ram pressure, the jet thrust was reduced about 6 to 10 percent, which is roughly equivalent to the percentage increase in absolute temperature of the combustion air. This reduction in jet thrust was accompanied by a reduction of only 0 to 4 percent in combustion-air flow thus indicating that the loss in engine performance with increase in combustion-air temperature is due to reduced engine thermal efficiency as well as decreased combustion air consumption.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1946
- Accession Number
- ADA801399
Entities
People
- Michael F. Valerino
- Richard F. Hughes
- Robert H. Essig
Organizations
- Glenn Research Center