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Research Papers

Three Dimensional Clocking Effects in a One and a Half Stage Transonic Turbine

[+] Author and Article Information
O. Schennach

Institute for Thermal Turbomachinery and Machine Dynamics, Graz University of Technology, 8010 Graz, Austria

J. Woisetschläger

Institute for Thermal Turbomachinery and Machine Dynamics, Graz University of Technology, 8010 Graz, Austriajakob.woisetschlaeger@tugraz.at

B. Paradiso, G. Persico

Laboratorio di Fluidodinamica delle Macchine, Dipartimento di Energia, Politecnico di Milano, Milano 20156, Italy

P. Gaetani

Laboratorio di Fluidodinamica delle Macchine, Dipartimento di Energia, Politecnico di Milano, Milano 20156, Italypaolo.gaetani@polimi.it

J. Turbomach 132(1), 011019 (Sep 21, 2009) (10 pages) doi:10.1115/1.3072715 History: Received October 06, 2008; Revised November 03, 2008; Published September 21, 2009

This paper presents an experimental investigation of the flow field in a high-pressure transonic turbine with a downstream vane row (1.5 stage machine) concerning the airfoil indexing. The objective is a detailed analysis of the three-dimensional aerodynamics of the second vane for different clocking positions. To give an overview of the time-averaged flow field, five-hole probe measurements were performed upstream and downstream of the second stator. Furthermore in these planes additional unsteady measurements were carried out with laser Doppler velocimetry in order to record rotor phase-resolved velocity, flow angle, and turbulence distributions at two different clocking positions. In the planes upstream of the second vane, the time-resolved pressure field has been measured by means of a fast response aerodynamic pressure probe. This paper shows that the secondary flows of the second vane are significantly modified by the different clocking positions, in connection with the first vane modulation of the rotor secondary flows. An analysis of the performance of the second vane is also carried out, and a 0.6% variation in the second vane loss coefficient has been recorded among the different clocking positions.

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Figures

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Figure 1

Up: meridional section, LDV (ticks) and probe (circles) measurement positions in C2 and D1. Bottom: blade to blade overview with clocking positions.

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Figure 2

FRAPP phase-resolved flow field downstream of the rotor in plane C1, absolute frame

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Figure 3

FHP flow field in planes C1 (CP1) and C2 (CP1–CP6). From left: α, Tt, Cpt, and Cps.

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Figure 4

rms from FRAPP: Cpt, α, and Cps in plane C2 for CP1 (up) and CP6 (down)

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Figure 5

FRAPP phase-resolved flow field in plane C2 for clocking position CP1. From left: Cps, Cpt, α angle, and TKE.

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Figure 6

FRAPP phase-resolved flow field in plane C2 for clocking position CP6. From left: Cps, Cpt, α angle, and TKE.

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Figure 7

FHP flow field in planes D1 for CP1, CP3.5, CP6, and CP8.5. From top: α, ψ, and Cpt.

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Figure 8

TKE from LDV data in plane D1

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Figure 9

LDV phase-resolved flow field in plane D1 for clocking position CP6. From left: α angle, velocity magnitude, and TKE.

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Figure 10

LDV phase-resolved flow field in plane D1 for clocking position CP1. From left: α angle, velocity magnitude, and TKE.

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Figure 11

Pitchwise-averaged quantities: α angle and pressure loss coefficient Y

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