Analysis of combustion responses in liquid rocket engines

Woong-Sup Yoon, Y. S. Hwang, K. Y. Lee, H. Ko

Research output: Contribution to conferencePaper

Abstract

The combustion responses of the methanol and n-decane sprays reacting with air under the unstable waves are studied with a view to observing the oscillatory spray combustion, and investigating the effects of vaporization on the combustion instabilities. Navier-Stokes solutions for chemically reacting flows are used to calculate the flow variables, mass fractions and droplet histories, which in turn provide necessary data to detect the development of unstable waves. A preconditioned dual-time implicit algorithm is employed to simulate the low Mach flows with strong density variations inside the axisymmetric liquid propellant rocket combustor. Emphasized in the present study is the effect of vaporization-chemical interactions upon unstable waves. The results show that the droplets inside the flame strongly responds to the oscillating pressure, in return, flame is excited by amplifying fuel mass fluctuations. And pure vaporization without the interaction with flame, has much less contribution to amplify the unstable waves.

Original languageEnglish
Publication statusPublished - 1998 Jan 1
Event34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998 - Cleveland, United States
Duration: 1998 Jul 131998 Jul 15

Other

Other34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998
CountryUnited States
CityCleveland
Period98/7/1398/7/15

Fingerprint

Rocket engines
Vaporization
Liquids
Liquid propellants
Rockets
Combustors
Mach number
Methanol
Air

All Science Journal Classification (ASJC) codes

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

Cite this

Yoon, W-S., Hwang, Y. S., Lee, K. Y., & Ko, H. (1998). Analysis of combustion responses in liquid rocket engines. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.
Yoon, Woong-Sup ; Hwang, Y. S. ; Lee, K. Y. ; Ko, H. / Analysis of combustion responses in liquid rocket engines. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.
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year = "1998",
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Yoon, W-S, Hwang, YS, Lee, KY & Ko, H 1998, 'Analysis of combustion responses in liquid rocket engines' Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States, 98/7/13 - 98/7/15, .

Analysis of combustion responses in liquid rocket engines. / Yoon, Woong-Sup; Hwang, Y. S.; Lee, K. Y.; Ko, H.

1998. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.

Research output: Contribution to conferencePaper

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AU - Lee, K. Y.

AU - Ko, H.

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N2 - The combustion responses of the methanol and n-decane sprays reacting with air under the unstable waves are studied with a view to observing the oscillatory spray combustion, and investigating the effects of vaporization on the combustion instabilities. Navier-Stokes solutions for chemically reacting flows are used to calculate the flow variables, mass fractions and droplet histories, which in turn provide necessary data to detect the development of unstable waves. A preconditioned dual-time implicit algorithm is employed to simulate the low Mach flows with strong density variations inside the axisymmetric liquid propellant rocket combustor. Emphasized in the present study is the effect of vaporization-chemical interactions upon unstable waves. The results show that the droplets inside the flame strongly responds to the oscillating pressure, in return, flame is excited by amplifying fuel mass fluctuations. And pure vaporization without the interaction with flame, has much less contribution to amplify the unstable waves.

AB - The combustion responses of the methanol and n-decane sprays reacting with air under the unstable waves are studied with a view to observing the oscillatory spray combustion, and investigating the effects of vaporization on the combustion instabilities. Navier-Stokes solutions for chemically reacting flows are used to calculate the flow variables, mass fractions and droplet histories, which in turn provide necessary data to detect the development of unstable waves. A preconditioned dual-time implicit algorithm is employed to simulate the low Mach flows with strong density variations inside the axisymmetric liquid propellant rocket combustor. Emphasized in the present study is the effect of vaporization-chemical interactions upon unstable waves. The results show that the droplets inside the flame strongly responds to the oscillating pressure, in return, flame is excited by amplifying fuel mass fluctuations. And pure vaporization without the interaction with flame, has much less contribution to amplify the unstable waves.

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M3 - Paper

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Yoon W-S, Hwang YS, Lee KY, Ko H. Analysis of combustion responses in liquid rocket engines. 1998. Paper presented at 34th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 1998, Cleveland, United States.