Radiative heat transfer within a solid-propellant rocket motor

Pearce, B.

doi:10.2514/3.28003

Cited by 38 publications

(10 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…43 Here n is the percent of aluminum in the propellant, ρ is the local density of the combustion products (in units of lbm /ft 3 ), and D is the local diameter of the nozzle (in units of inches). The stream (combustion gases) is modeled as a 2D slab adjacent to the nozzle surface.…”

Section: Ivb1 Radiationmentioning

confidence: 99%

Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles

Cross

Boyd

2016

46th AIAA Thermophysics Conference

View full text Add to dashboard Cite

A new two-dimensional ablation analysis code ("MOPAR-MD") capable of modeling pyrolyzing thermal protection system materials is presented. Favorable agreement with analytical solutions and results from other (one-dimensional) ablation solvers for a wide range of test cases indicates a correct implementation consistent with other codes. This new material response code can be coupled to the "LeMANS" reacting flow solver. New capabilities required for modeling nozzle flow-fields are added to LeMANS, including the Menter BSL and SST turbulence models and a "two gas" method for capturing the thermodynamics of gas-particle flow found in many rocket nozzles. These updated codes are used to perform uncoupled simulations predicting the thermal and ablation response of the "HIPPO" nozzle test case. Radiation is found to have minimal impact on the response of the throat and downstream portions of the rocket nozzle, but remains significant for the motor chamber and upstream portions of the nozzle. Enthalpy conductance and surface recession of the nozzle are found to be quite sensitive to the assumed wall temperature, underscoring the need to perform coupled flow-field / ablation simulations in order to more accurately capture the convective heating environment. All simulations of the HIPPO nozzle predict substantially greater surface recession than measured experimentally. Several potential causes for this discrepancy are identified, many of which could be resolved by performing fully-conjugate, coupled flow-field / ablation simulations. NomenclatureA Area vector, m 2 B ′ Nondimensional mass flux E Activation energy, J /mol e Specific internal energy, J /kg g H Enthalpy conductance, kg /m 2 ·s g M Mass transfer conductance, kg /m 2 ·s h Specific enthlalpy, J /kg J Jacobian (sensitivity) matrix k Arrhenius pre-exponential factor, 1 /s M Gas mass content vector, kġ M Rate of change of gas mass content vector, kg /ṡ m ′′ Mass flux, kg /m 2 ·ṡ m ′′′ Volumetric mass source term, kg /m 3 ·s P Pressure, Pa Q Energy content vector, J Q Rate of change of energy content vector, W

show abstract

Section: Ivb1 Radiationmentioning

confidence: 99%

Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles

Cross

Boyd

2016

46th AIAA Thermophysics Conference

View full text Add to dashboard Cite

show abstract

“…is used to compute the stream emissivity. 43 Here n is the percent of aluminum in the propellant, ρ is the local density of the combustion products (in units of lbm /ft 3 ), and D is the local diameter of the nozzle (in units of inches).…”

Section: Ivb1 Radiationmentioning

confidence: 99%

Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles

Cross

Boyd

2017

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

A new two-dimensional ablation analysis code ("MOPAR-MD") capable of modeling pyrolyzing thermal protection system materials is presented. Favorable agreement with analytical solutions and results from other (one-dimensional) ablation solvers for a wide range of test cases indicates a correct implementation consistent with other codes. This new material response code can be coupled to the "LeMANS" reacting flow solver. New capabilities required for modeling nozzle flow-fields are added to LeMANS, including the Menter BSL and SST turbulence models and a "two gas" method for capturing the thermodynamics of gas-particle flow found in many rocket nozzles. These updated codes are used to perform uncoupled simulations predicting the thermal and ablation response of the "HIPPO" nozzle test case. Radiation is found to have minimal impact on the response of the throat and downstream portions of the rocket nozzle, but remains significant for the motor chamber and upstream portions of the nozzle. Enthalpy conductance and surface recession of the nozzle are found to be quite sensitive to the assumed wall temperature, underscoring the need to perform coupled flow-field / ablation simulations in order to more accurately capture the convective heating environment. All simulations of the HIPPO nozzle predict substantially greater surface recession than measured experimentally. Several potential causes for this discrepancy are identified, many of which could be resolved by performing fully-conjugate, coupled flow-field / ablation simulations. NomenclatureA Area vector, m 2 B ′ Nondimensional mass flux E Activation energy, J /mol e Specific internal energy, J /kg g H Enthalpy conductance, kg /m 2 •s g M Mass transfer conductance, kg /m 2 •s h Specific enthlalpy, J /kg J Jacobian (sensitivity) matrix k Arrhenius pre-exponential factor, 1 /s M Gas mass content vector, kġ M Rate of change of gas mass content vector, kg /ṡ m ′′ Mass flux, kg /m 2 •ṡ m ′′′ Volumetric mass source term, kg /m 3 •s P Pressure, Pa Q Energy content vector, J Q Rate of change of energy content vector, W

show abstract

“…The heat transfers between the high-temperature gas and the inner wall generally can be classified into convective, radiant and conductive. The forced convective heat is the most significant factor for the heat transfer [23][24][25][26].…”

Section: Introductionmentioning

confidence: 99%

“…radiation and conduction are ignored [23][24][25][26]. The mechanical erosion of the material and the ablation of the inner nozzle wall are also neglected [27,28].…”

Section: Introductionmentioning

confidence: 99%

Probabilistic Reliability Analysis of Carbon/Carbon Composite Nozzle Cones with Uncertain Parameters

Xie¹,

Yang²,

Meng³

et al. 2019

Journal of Spacecraft and Rockets

View full text Add to dashboard Cite

show abstract

Radiative heat transfer within a solid-propellant rocket motor

Cited by 38 publications

References 6 publications

Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles

Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles

Two-Dimensional Modeling of Ablation and Pyrolysis with Application to Rocket Nozzles

Probabilistic Reliability Analysis of Carbon/Carbon Composite Nozzle Cones with Uncertain Parameters

Contact Info

Product

Resources

About