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Research Papers

Effect of Prediffuser Angle on the Static Pressure Recovery in Flow Through Casing-Liner Annulus of a Gas Turbine Combustor at Various Swirl Levels

[+] Author and Article Information
Prakash Ghose

Assistant Professor
Department of Mechanical Engineering,
KIIT University,
Bhubaneswar 751024, India
e-mail: prakashgbanu@yahoo.co.in

Amitava Datta

Professor
Department of Power Engineering,
Jadavpur University,
Salt Lake Campus, Kolkata 700098, India
e-mail: amdatta_ju@yahoo.com

Achintya Mukhopadhyay

Professor
Department of Mechanical Engineering,
Jadavpur University,
Kolkata 700032, India
e-mail: achintya.mukho@gmail.com

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received May 29, 2014; final manuscript received April 8, 2015; published online November 11, 2015. Assoc. Editor: Sumanta Acharya.

J. Thermal Sci. Eng. Appl 8(1), 011017 (Nov 11, 2015) (7 pages) Paper No: TSEA-14-1133; doi: 10.1115/1.4030734 History: Received May 29, 2014

A numerical study has been performed in an axisymmetric diffuser followed by a casing-liner annulus of a typical gas turbine combustor to analyze the flow structure and pressure recovery in the geometry. Static pressure recovery in a gas turbine combustor is important to ensure high pressure of air around the liner. However, the irreversible pressure losses reduce the static pressure recovery from the ideal value. The presence of swirl in the flow from compressor and prediffuser geometry before the dump diffuser influences the flow pattern significantly. In this study, flow structures are numerically predicted with different prediffuser angles and inlet swirl levels for different dump gaps. Streamline distributions and pressure plots on the casing and liner walls are analyzed. Static pressure recovery coefficients are obtained from the pressure distributions across the combustor. The effect of dump gap on the static pressure recovery has also been evaluated. It is observed that the best static pressure recovery can be obtained at optimum values of inlet swirl level and prediffuser angle. Dump gap is found to have significant influence on the static pressure recovery only at small prediffuser angle.

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References

Figures

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Fig. 1

Physical model of the combustor considered for computation

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Fig. 2

Comparison of the radial variation of predicted and measured [6] axial velocity at different axial locations (Re = 1.2 × 105): (a) X/Dc = 0.1, (b) X/Dc = 0.3, (c) X/Dc = 1.5, and (d) X/Dc = 2.1

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Fig. 3

Comparison of predicted and measured [6] wall pressure variation along the casing outer wall for nonswirling and swirling inlet conditions (Re = 1.2 × 105)

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Fig. 4

Streamline distributions within the diffuser and part of annulus at different prediffuser angles and without inlet swirl (Re = 1.2 × 105)

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Fig. 5

Streamline distributions within the diffuser and part of annulus at different prediffuser angles and with mild inlet swirl (SN = 0.178) (Re = 1.2 × 105)

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Fig. 6

Streamline distributions within the diffuser and part of annulus at different prediffuser angles and with higher inlet swirl (SN = 0.38) (Re = 1.2 × 105)

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Fig. 7

Wall pressure variation along the casing outer wall at different swirl number and prediffuser angle (Re = 1.2 × 105): (a) SN = 0, (b) SN = 0.178, and (c) SN = 0.38

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Fig. 8

Wall pressure variation along the liner wall at different swirl number and prediffuser angle (Re = 1.2 × 105): (a) SN = 0, (b) SN = 0.178, and (c) SN = 0.38

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Fig. 9

Variation of static pressure recovery coefficient with prediffuser angle at various inlet swirl numbers (Re = 1.2 × 105): (a) DG = 1.0 and (b) DG = 0.5

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