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Research Papers: Forced Convection

Numerical Simulation of Flow and Heat Transfer in a Square Rotating U-Duct Using Hydrocarbon Fuel

[+] Author and Article Information
Hongchuang Sun

Key Laboratory of Aerospace Thermophysics,
Ministry of Industry and
Information Technology,
School of Energy Science and Engineering,
Harbin Institute of Technology,
No.92, West Da-Zhi Street,
Harbin 150001, China
e-mail: sunhongchuang_v1@163.com

Jiang Qin

Key Laboratory of Aerospace Thermophysics,
Ministry of Industry and
Information Technology,
School of Energy Science and Engineering,
Harbin Institute of Technology,
No.92, West Da-Zhi Street,
Harbin 150001, China
e-mail: qinjiang@hit.edu.cn

Hongyan Huang

Key Laboratory of Aerospace Thermophysics,
Ministry of Industry and
Information Technology,
School of Energy Science and Engineering,
Harbin Institute of Technology,
No.92, West Da-Zhi Street,
Harbin 150001, China
e-mail: huanghy_04@hit.edu.cn

Peigang Yan

Key Laboratory of Aerospace Thermophysics,
Ministry of Industry and
Information Technology,
School of Energy Science and Engineering,
Harbin Institute of Technology,
No.92, West Da-Zhi Street,
Harbin 150001, China
e-mail: peigang_y@163.com

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received August 1, 2018; final manuscript received November 21, 2018; published online January 14, 2019. Assoc. Editor: Srinath V. Ekkad.

J. Heat Transfer 141(3), 031701 (Jan 14, 2019) (14 pages) Paper No: HT-18-1495; doi: 10.1115/1.4042299 History: Received August 01, 2018; Revised November 21, 2018

Air turbine power generation system is considered as a feasible power generation system for hypersonic aircraft with Mach 6. However, the incoming air with high temperature cannot be used as coolant while turbine has to be cooled. Since hydrocarbon fuel is the only cooling source onboard, the scheme of fuel cooling air turbine is put forward. In this paper, square cooling channel, including inlet part, outlet part and U-duct, is established based on the typical air turbine. The hydraulic diameter of the channel is 2 mm and four types of U-ducts are used to compare the performance with simulation using k-Epsilon turbulence model. The density and specific heat capacity of fuel are considered as constant as the temperature difference in this study is small. The Reynolds number varies from 2760 to 16,559 and rotating number ranges from 0 to 6.9. The results show that the pressure distribution in radial direction is proportional to the square of radial distance and the square of rotating speed. The regulations of velocity and normalized Nusselt number distributions depend on rotating number. Furthermore, the heat transfer is enhanced with fin while the pressure loss is also increased. The position of fins cannot significantly influence pressure loss but can influence heat transfer obviously. The normalized Nusselt number of inlet-fin U-duct is higher than the outlet-fin U-duct both on leading side surface and trailing side (TS) surface, while the pressure losses for the two types of ducts are almost same.

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Figures

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Fig. 1

Geometry and grid of the physics model

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Fig. 2

Comparison between CFD results using k-Epsilon model and experimental results for air rotating cooling: (a) experiment; average Nus = 3.2, (b) experiment; average Nus = 4.0, (c) CFD; average Nus = 3.1, and (d) CFD; average Nus = 3.8

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Fig. 3

Velocity and pressure distributions for Re=2760 under nonrotating condition: (a) smooth U-duct, (b) full-fin U-duct, (c) inlet-fin U-duct, and (d) outlet-fin U-duct

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Fig. 4

Variation of pressure loss coefficient with Re under nonrotating condition

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Fig. 5

Pressure distributions using smooth U-duct for Re=2760 under rotating conditions: (a) 10000 RPM, (b) 20000 RPM, and (c) 30000 RPM

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Fig. 6

Velocity distributions using smooth U-duct for Re=2760 under rotating conditions: (a) 10000 RPM, (b) 20000 RPM, and (c) 30000 RPM

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Fig. 7

Comparison of relative pressure between CFD results and theoretical formula under the condition of 30,000 RPM and 2.5 g/s

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Fig. 8

Development of vortexes in cooling channel under the condition of 30,000 RPM and 15 g/s

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Fig. 9

Pressure distribution using full-fin U-duct with Re=2760 for 10,000 RPM

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Fig. 10

Velocity distributions with the same Ro = 2.3 for different rotating speeds and mass flow rates: (a) 10000 RPM, 2.5 g/s, (b) 20000 RPM, 5 g/s, and (c) 30000 RPM, 7.5 g/s

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Fig. 11

Velocity and pressure distributions using inlet-fin and outlet-fin U-ducts for Re=2760 and Ro=2.3: (a) inlet-fin U-duct and (b) outlet-fin U-duct

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Fig. 12

Variation of pressure loss coefficient with the increase of Re

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Fig. 13

Schematic of U-duct unfolding (case: smooth U-duct, 30,000 RPM, 15 g/s)

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Fig. 14

Nus distributions using smooth U-duct under nonrotating conditions: (a) 2.5 g/s and (b) 15 g/s

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Fig. 15

Nus distributions of full-fin, inlet-fin and outlet-fin U-ducts for Re=2760 under nonrotating conditions

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Fig. 16

Nus distributions using smooth U-duct with a rotating speed of 30,000 RPM: (a) 2.5 g/s and (b) 7.5 g/s

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Fig. 17

Nus distribution using full-fin U-duct with a rotating speed of 30,000 RPM: (a) 2.5 g/s and (b) 7.5 g/s

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Fig. 18

Nus distributions using smooth U-duct for Ro=2.3: (a) 2.5 g/s and (b) 7.5 g/s

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Fig. 19

Nus distributions using smooth U-duct for Re=2760: (a) 10000 RPM and (b) 30000 RPM

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Fig. 20

Nus distribution using inlet-fin and outlet-fin U-ducts for Ro=2.3 and Re=8280: (a) inlet-fin and (b) outlet-fin

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Fig. 21

Average Nus on leading side and TS surfaces: (a) leading side and (b) trailing side

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