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research-article

Mach Number Distribution and Profile Losses for Low Pressure Turbine Profiles with High Diffusion Factors

[+] Author and Article Information
Roland Brachmanski

Institute of Jet Propulsion Universität der Bundeswehr München 85577 Neubiberg, Germany
roland.brachmanski@unibw.de

Reinhard Niehuis

Institute of Jet Propulsion Universität der Bundeswehr München 85577 Neubiberg, Germany
reinhard.niehuis@unibw.de

1Corresponding author.

ASME doi:10.1115/1.4036436 History: Received August 07, 2016; Revised March 05, 2017

Abstract

The present measurements for each low pressure turbine profile were conducted at midspan under a range of Reynolds- and exit Mach numbers. The exit Mach number was varied in a range covering low subsonic up to values where a transonic flow regime on the suction side of the blade could be expected. The variation of the exit Mach number was also used to create different locations of the maximum Mach number and to evaluate the resulting total pressure losses. This work focuses on two profiles with a diffusion factor between 0.18 ≤ DF ≤ 0.22. The integral total pressure losses were evaluated by wake traverses downstream of the profile. Numerical studies were also conducted to investigate further the influence of a reduced turbulence intensity on the boundary layer of the suction side of design B. The results show that the optimum of the integral total pressure losses are significantly dependent on the Reynolds number. Therefore a correlation between the maximum Mach number on the suction side and the integral total pressure losses has been successfully established. It also results in an equivalent change of the total pressure losses, which has been predicted by the trend line. However, the trend lines, which are based on the data of the integral total pressure losses of an attached boundary layer, are not able to predict the integral total pressure loss or the location of the maximum Mach number on the suction side of the blade since an open separation bubble occurs.

Copyright (c) 2017 by ASME
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