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Research Papers

Effects of Unsteady Wakes on the Secondary Flows in the Linear T106 Turbine Cascade

[+] Author and Article Information
Roberto Ciorciari

Institute of Jet Propulsion,
Universität der Bundeswehr München,
Werner-Heiseberg-Weg 39,
Neubiberg 85577, Germany
e-mail: roberto.ciorciari@unibw.de

Ilker Kirik, Reinhard Niehuis

Institute of Jet Propulsion,
Universität der Bundeswehr München,
Werner-Heiseberg-Weg 39,
Neubiberg 85577, Germany

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received February 28, 2014; final manuscript received March 31, 2014; published online May 2, 2014. Editor: Ronald Bunker.

J. Turbomach 136(9), 091010 (May 02, 2014) (11 pages) Paper No: TURBO-14-1029; doi: 10.1115/1.4027374 History: Received February 28, 2014; Revised March 31, 2014

In modern low pressure turbines the efforts to increase aerodynamic blade loading by increasing blade pitch and optimizing midspan performance in order to reduce weight and complexity can produce increased losses in the endwall region. Airfoils of high flow turning and high pressure gradients between the blades generate strong secondary flows which impair the global aerodynamic performance of the blades. In addition, the unsteady incoming wakes take influence on transition phenomena on the blade surfaces and the inlet boundary layer, and consequently affect the development and the evolution of the secondary flows. In this paper, the T106 cascade is used to identify the effect of unsteady wakes on the development of secondary flows in a turbine cascade. Numerical and experimental results are compared at different flux coefficients and Strouhal numbers, the relative differences and similarities are analyzed.

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Figures

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Fig. 1

Mesh and multiblock structure for the T40 configuration

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Fig. 2

Isentropic Mach number and cf for the cascade at midspan and at 18% span for the steady configuration

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Fig. 3

Nondimensional isobars on the endwall in the blade passage for the steady configuration

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Fig. 4

SVO, ω, and (Δpt/q2th)sec for the steady T106 cascade calculation at exit plane, 0.4 chord length downstream the trailing edge

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Fig. 5

Inflow angle variation, nondimensional velocity, and turbulence level of the incoming wake over time at midspan for the T80 20 configuration

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Fig. 6

Comparison between EXP and CFD of time-averaged Δβ2sec for steady and unsteady configurations

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Fig. 7

Comparison between EXP and CFD of time-averaged (Δpt/q2th)sec for steady and unsteady configurations

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Fig. 8

T40 20—comparison between EXP and CFD of Δβ2sec over time

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Fig. 9

T80 20—comparison between EXP and CFD of Δβ2sec over time

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Fig. 10

T80 40—comparison between CFD (Δpt/q2th)sec (top) and Δβ2s (bottom) over time

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Fig. 11

T40 20—comparison between SVO, ω, and (Δpt/q2th)sec in the MIN (left) and MAX (right) time instants

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Fig. 12

T80 20—comparison between SVO, ω, and (Δpt/q2th)sec in the MIN (left) and MAX (right) time instants (legend Fig. 11)

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Fig. 13

T80 40—comparison between SVO, ω, and (Δpt/q2th)sec in the MIN (left) and MAX (right) time instants (legend Fig. 11)

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Fig. 14

Comparison between instantaneous and time-averaged pitchwise averaged (Δpt/q2th)sec (top) and Δβ2s (bottom) for different configurations

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