Research Papers

Development of a Turning Mid Turbine Frame With Embedded Design—Part II: Unsteady Measurements

[+] Author and Article Information
Emil Göttlich

e-mail: emil.goettlich@tugraz.at

Franz Heitmeir

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

1Currently at Whittle Laboratory, Department of Engineering, University of Cambridge.

2Currently at Dipartimento di Macchine, Sistemi Energetici e Trasporti, Universita di Genova.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 24, 2013; final manuscript received October 22, 2013; published online January 2, 2014. Editor: Ronald Bunker.

J. Turbomach 136(7), 071012 (Jan 02, 2014) (8 pages) Paper No: TURBO-13-1222; doi: 10.1115/1.4025950 History: Received September 24, 2013; Revised October 22, 2013

This paper, the second of two parts, presents a new setup for the two-stage two-spool facility located at the Institute for Thermal Turbomachinery and Machine Dynamics (ITTM) of Graz University of Technology. The rig was designed to reproduce the flow behavior of a transonic turbine followed by a counter-rotating low pressure stage such as those in high bypass aero-engines. The meridional flow path of the machine is characterized by a diffusing S-shaped duct between the two rotors. The role of wide chord vanes placed into the mid turbine frame is to lead the flow towards the low pressure (LP) rotor with appropriate swirl. Experimental and numerical investigations performed on this setup showed that the wide chord struts induce large wakes and extended secondary flows at the LP inlet flow. Moreover, large deterministic fluctuations of pressure, which may cause noise and blade vibrations, were observed downstream of the LP rotor. In order to minimize secondary vortices and to damp the unsteady interactions, the mid turbine frame was redesigned to locate two zero-lift splitters into each vane passage. While in the first part of the paper the design process of the splitters and the time-averaged flow field were presented, in this second part the measurements performed by means of a fast response probe will support the explanation of the time-resolved field. The discussion will focus on the comparison between the baseline case (without splitters) and the embedded design.

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Fig. 1

Schematic meridional section of the test setup with probe measurement planes D and F

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Fig. 2

Plane D—time-averaged distribution of the Mach number; splitter setup

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Fig. 3

Plane D—time-averaged distributions of the RMS of the stochastic fluctuations of the total pressure for the two configurations

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Fig. 4

Plane D—contour plots of the RMS of the deterministic fluctuations of the pressure for the two configurations

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Fig. 5

Plane F—time-resolved distribution of the Mach number and stochastic fluctuations of total pressure. The LP rotor phase.

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Fig. 6

Plane F—RMS of the coherent fluctuations of the flow yaw angle computed from the RSA

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Fig. 7

Plane F—RMS of the coherent fluctuations of the total pressure




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