Measurement of intrinsic burning rate of nitromethane

Y. C. Lu, E. Boyer, D. Koch, K. K. Kuo

Research output: Contribution to conferencePaper

Abstract

An optically accessible, high-pressure liquid propellant strand burner (LPSB) was designed and established to measure the intrinsic burning rates of liquid propellants over broad ranges of pressures and initial temperatures. Compared to other methods, the current setup minimizes undesirable effects introduced by gelling agents and LP-containing tubes that may modify LP burning behavior. A temperature conditioning system allowed temperature sensitivity to be examined as well. To determine the intrinsic burning rate, chamber pressure was varied to achieve a steady-state position of the LP burning surface at a set actuator feeding rate. Operation of the LPSB was demonstrated with nitromethane monopropellant. Burning rates at three different initial temperatures were determined in an air environment. Over a pressure range of 2.5 to 15 MPa (250 to 2200 psig), the intrinsic burning rate of nitromethane was determined as a power law of chamber pressure: rb, [mm/s] = 0.316 P1.02 [MPa] It was found that the burning rate of nitromethane was insensitive to the variation in initial temperatures tested (15 to 43 °C). The tube confinement encountered in conventional LP burningrate measurements was found to have non-negligible effects on the LP burning rate.

Original languageEnglish (US)
StatePublished - Jan 1 1997
Event33rd Joint Propulsion Conference and Exhibit, 1997 - Seattle, United States
Duration: Jul 6 1997Jul 9 1997

Other

Other33rd Joint Propulsion Conference and Exhibit, 1997
CountryUnited States
CitySeattle
Period7/6/977/9/97

All Science Journal Classification (ASJC) codes

  • Energy Engineering and Power Technology
  • Electrical and Electronic Engineering
  • Mechanical Engineering
  • Control and Systems Engineering
  • Aerospace Engineering

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    Lu, Y. C., Boyer, E., Koch, D., & Kuo, K. K. (1997). Measurement of intrinsic burning rate of nitromethane. Paper presented at 33rd Joint Propulsion Conference and Exhibit, 1997, Seattle, United States.