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Research Papers

DDES Analysis of the Wake Vortex Related Unsteadiness and Losses in the Environment of a High-Pressure Turbine Stage

[+] Author and Article Information
Dun Lin

Mem. ASME
Key Laboratory for Thermal Science and
Power Engineering of Ministry of Education,
Tsinghua University,
Beijing 100084, China
e-mail: lindun91@gmail.com

Xinrong Su

Mem. ASME
Key Laboratory for Thermal Science and
Power Engineering of Ministry of Education,
Tsinghua University,
Beijing 100084, China
e-mail: suxr@mail.tsinghua.edu.cn

Xin Yuan

Professor
Mem. ASME
Key Laboratory for Thermal Science and
Power Engineering of Ministry of Education,
Tsinghua University,
Beijing 100084, China
e-mail: yuanxin@mail.tsinghua.edu.cn

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 23, 2017; final manuscript received November 17, 2017; published online January 3, 2018. Editor: Kenneth Hall.

J. Turbomach 140(4), 041001 (Jan 03, 2018) (12 pages) Paper No: TURBO-17-1133; doi: 10.1115/1.4038736 History: Received August 23, 2017; Revised November 17, 2017

In this work, the flows inside a high-pressure turbine (HPT) vane and stage are studied with a delayed detached eddy simulation (DDES) code. The fundamental nozzle/blade interaction is investigated with special attention paid to the development and transportation of the vane wake vortices. There are two motivations for this work. First, the extreme HPT operation conditions, including both transonic Mach numbers and high Reynolds numbers, impose a great challenge to modern computational fluid dynamics (CFD), especially for scale-resolved simulation methods. An accurate and efficient high-fidelity CFD solver is very important for a thorough understanding of the flow physics and the design of more efficient HPT. Second, the periodic wake vortex shedding is an important origin of turbine losses and unsteadiness. The wake and vortices not only cause losses themselves, but also interact with the shock wave (under transonic working condition), pressure waves, and have a strong impact on the downstream blade surface (affecting boundary layer transition and heat transfer). Based on one of our previous DDES simulations of a HPT vane, this work further investigates the development and length characteristics of the wake vortices, provides explanations for the length characteristics, and reveals the transportation of the wake vortices in the downstream rotor passages along with its impact on the downstream aero-thermal performance.

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Figures

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Fig. 1

HPT vane and blade geometries and loadings: (a) HPT vane VKI LS89 and (b) HPT blade PBD01

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Fig. 2

Computational domain for HPT stage

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Fig. 3

Details of the mesh at the leading and trailing edges (every two points are shown) (a) vane leading edge, (b) vane trailing edge, (c) blade leading edge, and (d) blade trailing edge

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Fig. 4

Contour of index of resolution quality: (a) vane and (b) blade

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Fig. 5

Velocity power spectral densities at three monitoring points of case vane

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Fig. 6

Velocity power spectral densities at four monitoring points of case stage

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Fig. 7

Isentropic Ma distributions along the vane surface of case vane

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Fig. 8

Isentropic Ma distributions along the vane surface of case stage

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Fig. 9

Numerical Schlieren of case vane

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Fig. 10

Numerical Schlieren of case stage

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Fig. 11

The length characteristics of the vane wake vortices (Ma contour and iso-surfaces of the Q–criterion colored by Ma of case vane)

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Fig. 12

The division of the suction side wake vortex (pressure contour slice and iso-surfaces of Q–criterion colored by pressure): (a) case vane and (b) case stage

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Fig. 13

Development of the vortices without downstream blade

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Fig. 14

Development of the vortices with downstream blade

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Fig. 15

Transportation of the wake vortices: (a) t=(1/5)Trot, (b) t=(2/5)Trot, and (c) (4/5)Trot

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Fig. 16

Two modes of the crash of vortex pair 6 on the leading edge of rotor: (a) mode 1 with pressure side vortex of vortex pair 6 divided into halves and (b) mode 2 without pressure side vortex of vortex pair 6 divided into halves

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Fig. 17

Transportation of the vane wake vortices

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Fig. 18

Unsteady effects of the wake vortices transportation on the loading and heat transfer of the rotors (corresponding to Fig. 14). (a) Pressure on the rotor surface and (b) temperature near the rotor surface (slice on the second layer).

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Fig. 19

Dissipation contours of case vane: (a) viscous dissipation S˙visc contour and (b) thermal loss S˙therm contour

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Fig. 20

Dissipation contours of case stage: (a) viscous dissipation S˙visc contour and (b) thermal loss S˙therm contour

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