Numerical simulation of variable thrust engine combustion chamber

Tsung-Leo Jiang; Wei Tang Chiang; Shyh Dihng Jang

Numerical simulation of variable thrust engine combustion chamber

Tsung-Leo Jiang, Wei Tang Chiang, Shyh Dihng Jang

Research output: Contribution to conference › Paper › peer-review

Abstract

The combustion and aerodynamic processes of liquid bipropellants in the combustion chamber of a Variable Thrust Engine(VTE), to be used in the Orbital Maneuvering Vehicle(OMV), have been predicted at the choking condition of two different power level. The computation is conducted from the injector face down to the nozzle throat. Appropriate physical submodels are adopted to account for the two-phase interaction between bipropellant droplet flows and gas-phase flow. The nozzle throat conditions are determined by the mass con. servation and the thermodynamic relations. The optimal atomization condition is suggested V, considering the high combustion performance and the relatively cool chamber. Therefore, the conventional design concept linked with the corollary “the finer the spray, the better the efficiency” must be reassessed.

Original language	English
Publication status	Published - 1992 Jan 1
Event	AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 - Nashville, United States Duration: 1992 Jul 6 → 1992 Jul 8

Other

Other	AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992
Country	United States
City	Nashville
Period	92-07-06 → 92-07-08

All Science Journal Classification (ASJC) codes

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

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title = "Numerical simulation of variable thrust engine combustion chamber",

abstract = "The combustion and aerodynamic processes of liquid bipropellants in the combustion chamber of a Variable Thrust Engine(VTE), to be used in the Orbital Maneuvering Vehicle(OMV), have been predicted at the choking condition of two different power level. The computation is conducted from the injector face down to the nozzle throat. Appropriate physical submodels are adopted to account for the two-phase interaction between bipropellant droplet flows and gas-phase flow. The nozzle throat conditions are determined by the mass con. servation and the thermodynamic relations. The optimal atomization condition is suggested V, considering the high combustion performance and the relatively cool chamber. Therefore, the conventional design concept linked with the corollary “the finer the spray, the better the efficiency” must be reassessed.",

author = "Tsung-Leo Jiang and Chiang, {Wei Tang} and Jang, {Shyh Dihng}",

year = "1992",

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note = "AIAA/ASME/SAE/ASEE 28th Joint Propulsion Conference and Exhibit, 1992 ; Conference date: 06-07-1992 Through 08-07-1992",

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T1 - Numerical simulation of variable thrust engine combustion chamber

AU - Jiang, Tsung-Leo

AU - Chiang, Wei Tang

AU - Jang, Shyh Dihng

PY - 1992/1/1

Y1 - 1992/1/1

N2 - The combustion and aerodynamic processes of liquid bipropellants in the combustion chamber of a Variable Thrust Engine(VTE), to be used in the Orbital Maneuvering Vehicle(OMV), have been predicted at the choking condition of two different power level. The computation is conducted from the injector face down to the nozzle throat. Appropriate physical submodels are adopted to account for the two-phase interaction between bipropellant droplet flows and gas-phase flow. The nozzle throat conditions are determined by the mass con. servation and the thermodynamic relations. The optimal atomization condition is suggested V, considering the high combustion performance and the relatively cool chamber. Therefore, the conventional design concept linked with the corollary “the finer the spray, the better the efficiency” must be reassessed.

AB - The combustion and aerodynamic processes of liquid bipropellants in the combustion chamber of a Variable Thrust Engine(VTE), to be used in the Orbital Maneuvering Vehicle(OMV), have been predicted at the choking condition of two different power level. The computation is conducted from the injector face down to the nozzle throat. Appropriate physical submodels are adopted to account for the two-phase interaction between bipropellant droplet flows and gas-phase flow. The nozzle throat conditions are determined by the mass con. servation and the thermodynamic relations. The optimal atomization condition is suggested V, considering the high combustion performance and the relatively cool chamber. Therefore, the conventional design concept linked with the corollary “the finer the spray, the better the efficiency” must be reassessed.

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