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Research Papers

Effects of Hot Streak and Airfoil Clocking on Heat Transfer and Aerodynamic Characteristics in Gas Turbine

[+] Author and Article Information
Zhenping Feng

Institute of Turbomachinery,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: zpfeng@mail.xjtu.edu.cn

Zhaofang Liu, Zhiduo Wang

Institute of Turbomachinery,
Xi'an Jiaotong University,
Xi'an 710049, China

Yan Shi

State Nuclear Power Technology R&D Center,
Beijing 100190, China

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received February 17, 2015; final manuscript received October 9, 2015; published online November 3, 2015. Assoc. Editor: Li He.

J. Turbomach 138(2), 021002 (Nov 03, 2015) (10 pages) Paper No: TURBO-15-1025; doi: 10.1115/1.4031785 History: Received February 17, 2015; Revised October 09, 2015

The effects of the hot streak and airfoil clocking on the heat transfer and aerodynamic characteristics in a high pressure (HP) gas turbine have been investigated in this paper. The blade geometry is taken from the first 1.5 stage turbine of GE-E3 engine. To study the effect of hot streak clocking, three cases under nonuniform and uniform inlet temperature boundary conditions were simulated first. Subsequently, four clocking positions (CPs) of S2 (second stator) were arranged in these three cases to study the combined effect of hot streak and airfoil clocking. By solving the unsteady compressible Reynolds-averaged Navier–Stokes (RANS) equations, time-dependent solutions for the flow and heat transfer characteristics of the 1.5 stage turbine were obtained. The results indicate that impinged by different inlet temperature profiles, the heat flux distribution on S1 (first stator) blade varies significantly. Due to the separation of hot and cold fluid, more hot fluid flows toward pressure side (PS) of R1 (first rotor) and worsens the heat transfer environment there. The high heat flux on the R1 blade surface is controlled not only by the high heat transfer coefficient but also by the large temperature difference. By adjusting the CPs of S2, the hot streak fragments from the upstream could be guided to different places in S2 passage, to reduce the heat load on S2 blade surface. In view of the influence of the heat transfer characteristics, the nonadiabatic efficiency is calculated. The combined effects of the hot streak and airfoil clocking have been discussed, and the proper matching position for the two kinds of clocking could be selected for a higher nonadiabatic efficiency and lower heat load on S2 blade and end walls.

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Figures

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Fig. 1

Geometry of the first 1.5 stage of GE-E3 turbine

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Fig. 2

Circumferential mass-averaged total temperature distribution at the turbine inlet in the radial direction

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Fig. 3

Mark II cascade grid distribution

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Fig. 4

Heat transfer coefficient and relative pressure distributions on Mark II cascade midspan in simulation and experiment: (a) heat transfer coefficient and (b) relative pressure

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Fig. 5

Computational domain grids

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Fig. 6

Three cases under different inlet conditions

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Fig. 7

The time-averaged distributions of q and h on S1 blade surface in three cases (left is PS): (a) the distribution of q on S1 blade surface and (b) the distribution of h on S1 blade surface

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Fig. 8

Pressure distribution on R1 blade surface at midspan (AC: axial chord length)

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Fig. 9

Velocity magnitude at S1 outlet

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Fig. 10

The time-averaged distributions of q, h and Taw on R1 blade surface (right is PS)

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Fig. 11

T distribution at midspan in R1 and S2 passages

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Fig. 12

The time-averaged distribution of q on S2 surface (left is PS)

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Fig. 13

The time-averaged normalized heat flux ratio on blade surfaces and end walls

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Fig. 14

Four CPs of S2 for the three cases

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Fig. 15

Time-averaged S2 inlet total temperature and total pressure at −20% AC of S2

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Fig. 16

Time and space distribution of inlet temperature at mid span at −5% AC of S2

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Fig. 17

T distribution at midspan and t1 in S2 passage locating at different CPs

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Fig. 18

The time-averaged heat flux on S2 blade and end wall surfaces: (a) on blade, (b) on end wall, and (c) integrated

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Fig. 19

Nonadiabatic efficiency of 1.5 stage turbine

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