Conjugate heat transfer analysis in high speed flows

Murty, Msr Chandra; Manna, P.; Chakraborty, Debasis

doi:10.1177/0954410012464920

Cited by 21 publications

(14 citation statements)

References 22 publications

(29 reference statements)

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“…The real-time-step size has a significant effect 36,37 on the accuracy of the fluid–thermal–structural simulation. Figure 20 illustrates the time evolution histories of the stagnation-point temperature with different real-time-step sizes ( Δt = 1×10 −4 s, 1 × 10 −3 s, 5 × 10 −3 s).…”

Section: Resultsmentioning

confidence: 99%

“…However, the calculations of the wall temperature and heat flux are separated artificially in the partitioned method; thus, the computational accuracy is highly dependent on the mesh size near the interface. The real-time-step size has a significant effect 36,37 on the accuracy of the fluid-thermal-structural simulation. Figure 20 illustrates the time evolution histories of the stagnation-point temperature with different real-timestep sizes (Át ¼ 1Â10 À4 s, 1 Â 10 À3 s, 5 Â 10 À3 s).…”

Section: Presentmentioning

confidence: 99%

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An integrated algorithm for hypersonic fluid–thermal–structural analysis of aerodynamically heated cylindrical leading edge

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The accurate and efficient prediction of the fluid–thermal–structural performance of thermal protection systems on hypersonic vehicles to protect against severe aerodynamic heating is attracting increasing worldwide attention. In this paper, a new integrated fluid-structural-thermal investigation based on the finite volume method is proposed to study the thermal behavior of aerodynamically heated cylinder leading edges in hypersonic flows. A unified integral equation system is developed based on the governing equations for the physical processes of aerodynamic heating and structural heat transfer, which is resolved by using an up-wind finite volume method and a new two-thermal-resistance model in one integrated, vectorized computer program. To demonstrate its capability and reliability, applications for steady/unsteady fluid–thermal–structural analysis are demonstrated on aerodynamically heated cylinder leading edges at Ma 6.47. The results show that the steady maximum temperature of the cylinder can reach approximately 648 K at the stagnation point, and the unsteady results are in good agreement with the experimental data and related references. Compared with the partitioned approach, the integrated method shows better computational stability with relatively small sensitivity to mesh scale and time step, reducing the computation time for the same unsteady case by approximately 50%. The present study indicates that the integrated approach has potential for significant improvements and efficiency in predicting long-endurance fluid-structural-thermal problems of hypersonic vehicles.

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Section: Resultsmentioning

confidence: 99%

Section: Presentmentioning

confidence: 99%

An integrated algorithm for hypersonic fluid–thermal–structural analysis of aerodynamically heated cylindrical leading edge

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Hence, conjugate heat transfer (CHT) studies are initiated to understand the SWBLI using the in-house developed CHT solver. 25,26 These studies would not only demonstrate the usefulness of CHT in the complex flow situation of SWBLI but also would recommend its necessity in analyzing the flow physics while arriving at the different interaction parameters. In view of this, the literature reported configuration and freestream conditions are considered along with different wall materials to undertake the CHT studies for SWBLI.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, it is necessary to consider the hypersonic fluid flow over an object of interest and the heat conduction through the same simultaneously. Hence, conjugate heat transfer (CHT) studies are initiated to understand the SWBLI using the in‐house developed CHT solver 25,26 . These studies would not only demonstrate the usefulness of CHT in the complex flow situation of SWBLI but also would recommend its necessity in analyzing the flow physics while arriving at the different interaction parameters.…”

Section: Introductionmentioning

confidence: 99%

Shock wave boundary layer interactions in hypersonic flows over a double wedge geometry by using conjugate heat transfer

2020

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“…The fluid and solid domains are independently solved during a global time step. This approach is recommended for unsteady problems, and it is all the more efficient in terms of computational expense because the global time step can be large, 14 which reduces the frequency of exchanges between the two solvers. Hence, the parallel approach is selected for the current simulations.…”

Section: Introductionmentioning

confidence: 99%

Numerical study of the internal flow field of a dual pulse solid rocket motor including conjugate heat transfer

Han

Chen

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical simulations were performed to study the influence of the inside diameter of the pulse separation device port on the flow features and the local heat transfer characteristics in a dual pulse solid rocket motor. A lower-upper symmetric Gauss-Seidel implicit dual time-stepping method was applied to address the problem of unsteady flow. A high-resolution upwind scheme (AUSMPWþ) and Menter's shear stress transport turbulence model were employed to solve the Reynolds-averaged Navier-Stokes equations. The conjugate heat transfer strategy was realized by enforcing a common temperature and heat flux at the fluid-solid interface. After validating the accuracy and reliability of the numerical algorithm by comparison with experimental cases, the internal flow of a dual pulse solid rocket motor was simulated. The results show that the magnitude of the velocity, the wall shear stress, and the turbulent kinetic energy downstream of the pulse separation device port decrease with increasing pulse separation device port diameter. The local heat transfer coefficient increases sharply downstream of the pulse separation device port, reaching a maximum within 1-2 diameters downstream of the pulse separation device port, before relaxing back to the fully developed pipe flow value. The peak value of the local heat transfer coefficient reduces as the pulse separation device port diameter increases. Meanwhile with an increasing pulse separation device port diameter, the position of the peak local heat transfer coefficient moves upstream to the head of the first pulse chamber, and appears upstream of the position of the reattachment point by an average of about 28.6%.

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Conjugate heat transfer analysis in high speed flows

Cited by 21 publications

References 22 publications

An integrated algorithm for hypersonic fluid–thermal–structural analysis of aerodynamically heated cylindrical leading edge

An integrated algorithm for hypersonic fluid–thermal–structural analysis of aerodynamically heated cylindrical leading edge

Shock wave boundary layer interactions in hypersonic flows over a double wedge geometry by using conjugate heat transfer

Numerical study of the internal flow field of a dual pulse solid rocket motor including conjugate heat transfer

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