Numerical Study of Heat Transfer in a Rotating Detonation Combustor

Randall, Steven; Anand, Vijay; George, Andrew C. St.; Gutmark, Ephraim

doi:10.2514/6.2015-0880

Cited by 12 publications

(5 citation statements)

References 14 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…When the equivalent ratio is 0.77, the average heat flux of the inner cylinder is 1.02 × 10 6 W/m 2 , and the average heat flux of the outer cylinder is 3.4 × 10 5 W/m 2 . The possible reason for this phenomenon is that the high-temperature combustion products are closer to the inner wall, which is consistent with the numerical results in the literature [41,46]. Hence, the thermal protection of the inner wall needs to be paid more attention in the process of RDE operation over long periods.…”

Section: Average Heat Flux Of Inner and Outer Cylinderssupporting

confidence: 86%

“…Additionally, Roy et al [45] predicted that the outer-wall temperature could rise as much as 500 K after 3.5 s of operation and reach 1100 K in the detonation region. Randall et al [46] performed experimental and numerical studies to analyze the heat transfer of an RDE. The wall temperature was measured by inserting thermocouples into sensor ports at different depths of the outer wall, and an axisymmetric model was developed to predict wall temperature evolution.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Experimental Investigation of Thermal Prediction and Heat Transfer Characteristics of Two-Phase RDE during Long-Duration Operation

Wang,

Song,

Chen

et al. 2024

Energies

View full text Add to dashboard Cite

Accurately predicting the thermal characteristics and heat transfer distribution of the rotating detonation engine (RDE) and acquiring a clear understanding of the performance and mechanism of the rotating detonation are of great significance for achieving the safe and reliable long-duration operation of RDEs. Using RP-3 as fuel, a long-duration experimental study is performed on a 220 mm-diameter RDC to investigate the details with respect to the thermal environment. The heat flux at the typical location and the average heat flux of both the inner and outer cylinders are measured, respectively. Meanwhile, the peak pressure of the rotating detonation wave (RDW) and specific thrust are analyzed. When the ER is between 0.5 and 1 (oxidizer 2 kg/s), the stable rotating detonation mode is obtained, and the detonation duration is set as 40 s to accurately calculate the heat released by the detonation combustion. The heat flux in the upstream region of the RDW location ranges from 2.40 × 105 W/m2 to 3.17 × 105 W/m2, and the heat flux in the downstream area of the RDW location ranges from 1.05 × 106 W/m2 to 1.28 × 106 W/m2. The results demonstrate the important role of the detonation combustion zone, and the thrust performance of RDC can be improved by making the RDW move forward along the RDC axis, which is the optimal direction of detonation combustion. Through a comparison of average heat flux under different conditions, it is found that the heat released by the RDC is directly related to its thrust. In addition, the average heat flux of the inner cylinder is about three times that of the outer cylinder for the two-phase RDC with a Tesla valve intake structure, indicating that the high-temperature combustion product is closer to the inner wall. Therefore, more thermal protection should be allocated to the inner cylinder, and a more systematic analysis of the two-phase flow field distribution in the annular combustion chamber should be carried out to improve the thrust performance. In this paper, the average heat flux of the inner and outer cylinders of the RDC as well as the typical local heat flux of the outer cylinders is quantitatively measured by means of experiments, which not only deepens the understanding of RDC flow field distribution, but also provides quantitative boundary conditions for the thermal protection design of RDCs.

show abstract

Section: Average Heat Flux Of Inner and Outer Cylinderssupporting

confidence: 86%

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Thermal Prediction and Heat Transfer Characteristics of Two-Phase RDE during Long-Duration Operation

Wang,

Song,

Chen

et al. 2024

Energies

View full text Add to dashboard Cite

show abstract

“…Heat loads imposed on chamber walls are closely tied to injector design and this raises substantial complications when trying to assess the overall ability to cool the RDRE combustor. The airbreathing RDE community is significantly ahead of the rocket community with numerous publications [26][27][28][29][30][31][32] generally showing peak heat transfer at the end of the detonation region, but there are precious few results in the rockets realm with much higher temperature products and much stronger detonation fronts.…”

Section: Comparing Rdre and Cp Engine Thermal Loadsmentioning

confidence: 99%

Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines

et al. 2022

View full text Add to dashboard Cite

Rotating (also termed continuous spin) detonation technology is gaining interest in the global research and development community due to the potential for increased performance. Potential performance benefits, thrust chamber design, and thrust chamber cooling loads are analyzed for propellant applications using liquid oxygen or high-concentration hydrogen peroxide oxidizers with kerosene, hydrogen, and methane fuels. Performance results based on a lumped parameter treatment show that theoretical specific impulse gains of 3–14% are achievable with the highest benefit coming from hydrogen-fueled systems. Assessment of thrust chamber designs for notional space missions shows that both thrust chamber length and diameter benefits are achievable given the tiny annular chamber volume associated with the rotating detonation combustion. While the passing detonation front drastically increases local heat fluxes, global energy balances can be achieved if operating pressures are limited to be comparable to existing or prior space engines.

show abstract

“…The impingement cooling can quickly take away the heat accumulated on the wall and improve the heat transfer coefficient of the wall, so it has wide application in aero-engine. Detonation combustion instantaneously release a lot of heat, the results of the literature [2][3] show that the rotating detonation engine combustion chamber wall heat flux is very large. In the literature [4][5] , a rotating detonation engine with cooling structure was experimentally studied.…”

Section: Introductionmentioning

confidence: 98%

Numerical Study of Impingement Cooling Under Constant Heat Flux

Gao¹,

Lei²,

Jiang³

2017

Proceedings of the 2017 2nd International Conference on Automation, Mechanical Control and Computational Engineering (AMCCE 201

View full text Add to dashboard Cite

Abstract. Take the rotating detonation engine combustion chamber wall which under great heat flux as the research background. The characteristics of impingement cooling under different parameters were studied by numerical simulation, then analyzing and getting a better Impingement cooling structure. It is found that under the same air mass flow rate and constant heat flux,when the diameter of impingement hole is d=4mm, the impingement distance is H=4mm, the hole spacing is Xn=Yn= 35.168mm,the cooling effect is the best. With the cooling structure, the cooling of the heated wall with constant heat flux of 500000 W/m 2 was studied. The results show that when the Reynolds number is Re = 50000, the wall is cooled and the wall temperature is reduced to a reasonable range.

show abstract

Numerical Study of Heat Transfer in a Rotating Detonation Combustor

Cited by 12 publications

References 14 publications

Experimental Investigation of Thermal Prediction and Heat Transfer Characteristics of Two-Phase RDE during Long-Duration Operation

Experimental Investigation of Thermal Prediction and Heat Transfer Characteristics of Two-Phase RDE during Long-Duration Operation

Rotating Detonation Combustion for Advanced Liquid Propellant Space Engines

Numerical Study of Impingement Cooling Under Constant Heat Flux

Contact Info

Product

Resources

About