Supercritical Flows in High Aspect Ratio Cooling Channels

Wennerberg, Jason C.; Anderson, William E.; Jung, Hogirl; Merkle, Charles L.

doi:10.2514/6.2005-4302

Cited by 14 publications

(8 citation statements)

References 10 publications

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“…The CFD results presented for a 2D test case by Wennerberg et al 3 have been used to validate, on a quality level, the present code. In the literature, in fact, it is not easy to find numerical or experimental solutions of real fluid in a channel with a strong wall temperature gradient.…”

Section: Validationmentioning

confidence: 97%

“…The coupling of these processes is strongly non-linear because coolant and hot-gas heat transfer depend on the fluid pressure and temperature and on wall temperature. A further complication is that the flow in the cooling channels is strongly three-dimensional, [2][3][4] and that the coolant is not a perfect gas. In fact, in these systems the large pressure required in the combustion chamber is sufficient to ensure that the coolant remains supercritical (i.e., pressure and temperature over the critical point) along the entire length of the cooling passages, as it moves from a predominantly liquid-like regime (incompressible flow) at the manifold inlet to a predominantly gaseous like regime (compressible flow) at the chamber injectors or turbine; therefore the methods based on the assumption of perfect gas or perfect liquid cannot be used.…”

Section: Introductionmentioning

confidence: 99%

“…This implies that when a significant radial thermal stratification takes place, like in the case of HARCC, a significant error arises. 3 To circumvent these limitations a "quasi 2D" modification of a typical one-dimensional approach has been recently presented. 7 This approach consists in a computational tool able to describe the coupled hotgas/wall/coolant environment that occurs in most liquid rocket engines and to provide a quick and reliable prediction of thermal stratification phenomena in cooling channels.…”

Section: Introductionmentioning

confidence: 99%

“…If a more detailed fluid dynamic and thermal analysis of the coolant flow is necessary, it has to be considered that the temperature stratification of the cooling channels is a major 3D effect that occurs in this environment and it strongly influences the heat transfer efficiency of the coolant. 3 Another important 3D effect that characterize the HARCC channel flow is the presence of vortices in the channel cross section induced by the wall curvature of the converging-diverging combustor. 8 In the presence of temperature stratification, these vortices transport cool fluid from one side to the other side of the channel cross section, thereby increasing the heat transfer.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

A Numerical Model for Supercritical Flow in Rocket Engine Applications

Pizzarelli¹,

Nasuti²,

Paciorri³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: Validationmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A Numerical Model for Supercritical Flow in Rocket Engine Applications

Pizzarelli¹,

Nasuti²,

Paciorri³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…Today, these correlations are used in many engineering level computational analysis tools [1] for thrust chamber cooling system design, and cycle power-balance programs [2], which are increasingly being used in the design and evaluation of complete liquid rocket engine systems. In addition, these correlations are often used to aid the design of many of the experiments aimed at obtaining benchmark computational fluid dynamics data [3]. They are also used as validity checks of computational results.…”

mentioning

confidence: 99%

Study of Heat Transfer Correlations for Supercritical Hydrogen in Regenerative Cooling Channels

Locke

Landrum

2008

Journal of Propulsion and Power

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Understanding the cooling efficiency of supercritical hydrogen is crucial to the development of high-pressure thrust chambers for regeneratively cooled liquid-oxygen/liquid-hydrogen rocket engines. Available Nusselt number correlations are compared with an extensive data set of local heat transfer coefficients to determine the domains of validity for each correlation. The data set was compiled from previous heated straight-tube experiments with supercritical hydrogen. Results indicate that particular correlations perform better than others for certain regimes of fluid properties, with the accuracy of heat transfer coefficient predictions ranging from 23 to over 100%. Correlation uncertainty due to inherent uncertainties in the equation-of-state and transport properties of supercritical hydrogen is also evaluated. The property dependent uncertainty was found to range from 2 to 10%, and therefore is not the main contributor to the larger errors in the correlation predictions. A number of published correlations for nonhydrogen supercritical fluids are shown to achieve comparable performance with hydrogen.downstream from entrance x = any property = dynamic viscosity, kg=m s = kinematic viscosity, m 2 =s = density, kg=m 3 = standard deviation Subscripts b = property evaluated at bulk temperature reference c = critical condition calc = calculated value exp = experimental value f = property evaluated at film temperature reference pc = pseudocritical ref = reference temperature type s = condition at inner-wall surface R = property evaluated by integral method IntroductionA NALYTICAL performance predictions and design analyses for regeneratively cooled liquid rocket engines use correlations to predict the heat transfer from the combusting gas to the thrust chamber wall and from the wall into the cooling fluid. Today, these correlations are used in many engineering level computational analysis tools [1] for thrust chamber cooling system design, and cycle power-balance programs [2], which are increasingly being used in the design and evaluation of complete liquid rocket engine systems. In addition, these correlations are often used to aid the design of many of the experiments aimed at obtaining benchmark computational fluid dynamics data [3]. They are also used as validity checks of computational results. These semi-empirical heat transfer correlations are highly dependent on the fluid transport properties and the conditions at which the fluid is flowing [4-6]. Although a number of coolant-side correlations have been proposed for hydrogen [7][8][9][10][11][12][13][14][15], their ability to accurately predict heat transfer over a wide range of operating conditions has typically been limited.Improved thrust chamber design requires accurate correlations for different geometries, such as high aspect ratio rectangular channels and curvature, as well as asymmetric heating and varying heat flux. For correction factors and new correlations to have any merit, it is important to understand the limitations of current correlations for ...

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