A simulative study on the erosive burning of solid rocket motors

Yamada, Kenjiro; Goto, Mirei; Ishikawa, Nobuyoshi

doi:10.2514/6.1975-1201

Cited by 6 publications

(10 citation statements)

References 4 publications

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“…Turbulence begins to penetrate into the primary flame zone at the point where the crossflow (axial) mass flux over the surface reaches about 750 kg/m 2 s, in agreement with the experimentally determined value for the onset of erosive burning. 20,23 The cross-flow velocity is a quantity closely related to the threshold behavior of erosive burning in solid propellants. The burning rate increases almost linearly with crossflow mass flux due to enhanced heat transfer by turbulence in the primary flame zone.…”

Section: Resultsmentioning

confidence: 99%

Transient combustion responses of homogeneous propellants to acoustic oscillations in axisymmetric rocket motors

Roh

Culick

1997

33rd Joint Propulsion Conference and Exhibit

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A numerical analysis of unsteady motions in solid rocket motors has been conducted. The formulation considers a 2-D axisymmetric combustion chamber and a choke nozzle, and treats the complete conservation equations accounting for turbulence closure and finiterate chemical kinetics in the gas phase and subsurface reactions. A fully coupled implicit scheme based on a dual time-stepping integration algorithm has been adopted to solve the governing equations and associated boundary conditions. Results of the steady-state calculations indicate that the distributions of pressure in the motor and Mach number in the nozzle are one-dimensional along the axial direction. Vorticity contours show similar pattern to those of Mach number in the combustion chamber. The nozzle has an influence on the flow and temperature fields in the combustion chamber. A narrow pressure pulse is imposed at the head end to simulate unsteady acoustic oscillations in the combustion chamber. When the front of the pulse reaches near the nozzle throat, pressure near the nozzle throat increases and blocks the hot gas flow from passing through the nozzle throat. Self-generated oscillations have similar frequencies to those of standing waves of the combustion chamber. Large vorticity fluctuations are observed in near surface region. The luminous flame zone responds to low-frequency pressure wave rather than highfrequency one. Temperature fluctuations in the primary flame zone of the head end oscillates independently of the imposed pressure oscillations while temperature fluctuations in downstream region show pressure-dependent oscillations.

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Section: Resultsmentioning

confidence: 99%

Transient combustion responses of homogeneous propellants to acoustic oscillations in axisymmetric rocket motors

Roh

Culick

1997

33rd Joint Propulsion Conference and Exhibit

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“…Furthermore, the often cited Taylor-Culick profile was repeatedly verified in a number of investigations. These start with the inventive tests reported by Taylor 2 and continue to those carried out in later years by way of computation ͑Dun-lap, Willoughby, and Hermsen; 3 Baum, Levine, and Lovine; 4 Sabnis, Gibeling, and McDonald 5 ͒, laboratory experiments ͑Yamada, Goto, and Ishikawa; 6 Dunlap et al 7 ͒, and theory ͑Clayton; 8 Balachandar, Buckmaster, and Short; 9 Majdalani and Roh; 10 Majdalani and Flandro 11 ͒. In short, a collective body of research has confirmed the suitability of the TaylorCulick model in approximating the bulk flow in a full-length cylindrical motor ͑Kuentzmann; 12 Traineau, Hervat, and Kuentzmann; 13 Apte and Yang 14 ͒.…”

Section: Introductionmentioning

confidence: 98%

The Taylor-Culick profile with arbitrary headwall injection

Majdalani

Saad

2007

Physics of Fluids

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Taylor's incompressible and rotational profile is extended to a porous cylinder with arbitrary headwall injection. This profile, often referred to as Culick's mean flow, is now generalized to permit the imposition of reactive headwall conditions. Starting with Euler's steady equations, the solution that we derive is approximate, being exact only at the sidewall, the centerline, or for similarity-conforming inlet profiles. Furthermore, the approximation is quasiviscous, being observant of the no slip requirement at the sidewall. Based on numerical experiments under inviscid flow conditions, the closed-form approximation that we obtain appears to be well suited to describe the bulk flow field in basic models of solid and hybrid rockets where uniform sidewall injection is imposed at the propellant surface. For similarity-nonconforming profiles, the approximation becomes more accurate as we move away from the headwall. Results are verified using computational fluid dynamics for several headwall injection patterns.

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“…Furthermore, we have reviewed the results of the simulative study by Yamada et al 2 and find no evidence or conclusion in regard to the nonexistence of the potential core or the production of turbulence near the centerline. In boundarylayer flows, it is well known that turbulence is produced mainly by mean shear in the near-wall region.…”

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confidence: 97%

Reply by Authors to R. L. Glick

Razdan

Kuo

1983

AIAA Journal

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W HETHER or not the potential flow region exists in real rocket motors will depend on factors such as initial conditions, grain geometry, and even igniter gas flow characteristics. However, in the case of high performance rocket motors, we believe that strong convective forces inside a rocket motor establish a boundary-layer flow over the propellant surface for which both developing boundary layer and the potential core region exist. Our model in Ref. 1 has been based on this physical picture. As far as experimental evidence on the nature of the flowfield cited by Click, it should be noted that these experiments were conducted under nonreactive *'simulative" flow conditions. However, the boundary layer in an actual grain port may be different due to differences in temperature, pressure, chemical reactions, etc.Furthermore, we have reviewed the results of the simulative study by Yamada et al. 2 and find no evidence or conclusion in regard to the nonexistence of the potential core or the production of turbulence near the centerline. In boundarylayer flows, it is well known that turbulence is produced mainly by mean shear in the near-wall region. This was also observed in the experiments of Ref. 2. Yamada et al. 2 further point out that the role of turbulence adjacent to a propellant surface is to enhance mixing rate of decomosed gases and increase the heat transfer. This is precisely what our model predicts and is also part of the erosive burning mechanism suggested by our study. It may be noted that our model can take into account a nonzero freestream turbulence level (which may be present as a result of initial conditions such as igniter gas flow characteristics) and its spread within the boundary layer through the boundary conditions, Eq. (27) Click speculates that the flowfield may contain four subdomains. The argument presented in regard to the interaction between negative erosive burning and the initial flow domains is not convincing. It is true that our model does not predict negative erosion. The reason we do not consider negative erosion is that for most propellants now being used nowadays, this phenomenon is not observed. Some older propellants using polyurethane binder do exhibit negative erosive burning. However, according to Langelle, 3 this is believed to be due to the covering of the AP particles by the molten binder at the surface and is related to the plateau strand-burning effect exhibited by those propellants. Furthermore, experiments of Marklund and Lake 4 show that the type of flowfield ("subdomains" (i)-(iii) and large scale turbulent surges) is not likely to be responsible for negative erosive burning. Indeed, their experiments conducted under clearly established boundary layer conditions, with no large scale turbulent surges present, showed negative erosive burning on a polyurethane propellant. Therefore, we disagree with Click's hypothesis that negative erosion is a result of the effects of initial flow "sub-domains" or turbulent surges.In regard to the comment on the theoretical work of Re...

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A simulative study on the erosive burning of solid rocket motors

Cited by 6 publications

References 4 publications

Transient combustion responses of homogeneous propellants to acoustic oscillations in axisymmetric rocket motors

Transient combustion responses of homogeneous propellants to acoustic oscillations in axisymmetric rocket motors

The Taylor-Culick profile with arbitrary headwall injection

Reply by Authors to R. L. Glick

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