Effects of gas temperature on nozzle damping experiments on cold-flow rocket motors

Sun, Bingbing; Li, Shipeng; Su, Wanxing; Li, Junwei; Wang, Ningfei

doi:10.1016/j.actaastro.2016.02.011

Cited by 15 publications

(3 citation statements)

References 29 publications

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“…The three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations are used for analyzing the combustion process with two realizable k − ɛ turbulence equations. The species transport model is solved the combustion physics of ideal gas with one-step irreversible chemical kinetics reaction model [26][27][28][29].…”

Section: Numerical Formulation and Simulation Methodsmentioning

confidence: 99%

“…To analyze the reaction rate of a hydrogen-air mixture, the one-step chemical reaction model is used, which follows ideal gas law [17]. The governing equations of continuity, momentum, and energy are solved simultaneously by the finite-volume method through commercial computational fluid dynamics (CFD) software ANSYS FLUENT 14.0 code [27][28][29][30][31][32][33][34]. A modified SIMPLEC scheme (Semi-Implicit Method for Pressure-Linked Equations-Consistent) is used to solve the Navier-Stokes equations.…”

Section: Mathematical and Combustion Modelingmentioning

confidence: 99%

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Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Alam

Sharma

Pandey

2019

J Braz. Soc. Mech. Sci. Eng.

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Pulse detonation engine is a new technique of supersonic wave propagation and stands for high impulsive thrust. The objective of the present investigation is to analyze the detonation wave characteristic of a hydrogen-air mixture in the pulse detonation engine (PDE) having obstacles of blockage ratio 0.5. The three-dimensional reactive Navier-Stokes equations with realizable k − ɛ turbulence model are used to simulate the propagation of combustion flame. The reaction rate of excess hydrogen and excess air is modeled by reduced single-step chemical reaction model and simulated using ANSYS software FLUENT 14.0 code. The simulation results of the shock wave overpressure, deflagration-to-detonation transition run-up distance of different flames and flame velocities are reported at initial boundary condition of 0.1 MPa pressure and 293 K temperature. It has been observed that the obstacles create turbulence in the propagating flame and form strong Mach stems of high temperature, resulting in reduction in accelerated flame run-up length. However, the normalized detonation flame run-up distance increases as the mass of fuel increases in the mixture. Thus, the performance of PDE combustor was observed 4.46% at high overpressure generated by excess fuel (ϕ = 1.3).

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Section: Numerical Formulation and Simulation Methodsmentioning

confidence: 99%

Section: Mathematical and Combustion Modelingmentioning

confidence: 99%

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Alam

Sharma

Pandey

2019

J Braz. Soc. Mech. Sci. Eng.

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“…According to these studies, there are many driving and damping factors that together determine the stability of a motor. The primary driving factors leading to an increase in fluid flow disturbance energy and thereby causing instability in the motor are pressure-coupled response [11] on the propellant surface, the velocity-coupled response [12], the vortexacoustic coupling [13,14], etc., whereas the main damping factors include the nozzle [15] and particles [16], etc., which tend to dissipate the energy causing perturbations to the flow, thereby exerting a stabilizing influence on a motor.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Wang,

Li,

et al. 2024

Aerospace

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A solid rocket motor (SRM) with a high aspect ratio that performs normally during ground tests may experience instability during flight. To address this issue, this study employs the pulse triggering method and the numerical approach of two-way fluid–structure interaction to investigate the mechanisms behind the SRM instability resulting from distinctions between on-ground and in-flight conditions. The results indicate that the main distinctions between the on-ground and in-flight conditions for SRMs are the strong constraints during the ground test, as well as aerodynamic forces and aerodynamic heating during flight. The strong constraints in the ground test effectively suppress structural vibrations by limiting displacements. In flight conditions, the aerodynamic heating reduces the strength of the SRM casing and aerodynamic forces provide sustained energy input for structural vibrations during flight. The mechanism for the ground/flight differences that induce SRM instability is that the structural natural frequencies are reduced by aerodynamic heating and the first-order acoustic frequency increased by the propellant regression approach reaches the resonance condition. Therefore, an instability factor Φ is proposed to represent the resonance relationship between the structural natural modes and the acoustic mode of SRMs. Furthermore, the closer the frequency of the aerodynamic forces is to the resonance frequency of the acoustic-structure coupling, the more pronounced the SRM instability.

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Influence of Multiple Parameters on the Efficiency of a Single Nozzle in a Heavy Gas Turbine Combustor

Hu,

Chen,

Meng

et al. 2024

Lecture Notes in Electrical Engineering

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Effects of gas temperature on nozzle damping experiments on cold-flow rocket motors

Cited by 15 publications

References 29 publications

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Numerical investigation of flame propagation and performance of obstructed pulse detonation engine with variation of hydrogen and air

Numerical Investigation on the Mechanism of Solid Rocket Motor Instability Induced by Differences between On-Ground and In-Flight Conditions

Influence of Multiple Parameters on the Efficiency of a Single Nozzle in a Heavy Gas Turbine Combustor

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