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Research Papers

Aerothermodynamics of a High-Pressure Turbine Blade With Very High Loading and Vortex Generators

[+] Author and Article Information
Reinaldo A. Gomes1

Institute of Jet Propulsion, University of the German Federal Armed Forces Munich, 85577 Neubiberg, Germanyreinaldo.gomes@unibw.de

Reinhard Niehuis

Institute of Jet Propulsion, University of the German Federal Armed Forces Munich, 85577 Neubiberg, Germanyreinhard.niehuis@unibw.de

1

Corresponding author.

J. Turbomach 134(1), 011020 (May 31, 2011) (9 pages) doi:10.1115/1.4003052 History: Received June 28, 2010; Revised July 20, 2010; Published May 31, 2011; Online May 31, 2011

AITEB-2 is a project where aerothermal challenges of modern high pressure turbine designs are analyzed. One of the scopes of the project is to allow for new gas turbine designs with less parts and lighter jet engines by increasing the blade pitch and therefore the aerodynamic blade loading. For transonic profiles, this leads to very high velocities on the suction side and shock induced separation is likely to occur. The total pressure loss increase due to flow separation and strong shocks, as well as the underturning of the flow, limits the increase of the blade pitch. In this paper, experiments using a linear turbine blade cascade with high aerodynamic loading are presented. The blade pitch is increased such that at design conditions, a strong separation occurs on the suction side. The experiments were run at high subsonic exit Mach numbers and at Reynolds numbers of 390,000 and 800,000. In order to reduce the flow separation and the aerodynamic losses, air jet vortex generators are used, which create streamwise vortices prior to the separation start. Since in high pressure turbine blades film cooling is widely used, also the influence of film cooling both with and without using vortex generators is analyzed. Film cooling is provided on the suction side by two rows of cylindrical holes. This paper provides an analysis of the influence of different main flow conditions, film cooling, and vortex generators on total pressure loss, heat transfer and film cooling effectiveness. The experiments show that the vortex generators, as well as the film cooling reduce flow separation and total pressure losses. The effects are also seen in the local heat transfer, especially with enhanced heat transport in the region with flow separation. The cases presented in this paper deal with complex flow phenomena, which are challenging to be predicted with modern numerical tools correctly. Therefore, the experimental data serve as a comprehensive database for validation of simulation tools in the AITEB-2 project.

Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

The high-speed cascade wind tunnel

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Figure 2

Schematic of the test section and cascade instrumentation (not to scale)

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Figure 3

Definition of the geometric data on the T120S cascade (not to scale)

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Figure 4

T120S blade with film cooling and AJVG rows (not to scale)

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Figure 5

Isentropic profile Mach number distribution without film cooling or AJVG for three operation points

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Figure 6

Isentropic profile Mach number distribution at Ma2,s=0.95; Re2,s=390,000 with and without film cooling or AJVG

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Figure 7

Integral primary and thermodynamic losses at Ma2,s=0.87; Re2,s=390,000 with and without film cooling or AJVG

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Figure 8

Integral primary and thermodynamic losses at Ma2,s=0.87; Re2,s=800,000 with and without film cooling or AJVG

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Figure 9

Integral primary and thermodynamic losses at Ma2,s=0.95; Re2,s=390,000 with and without film cooling or AJVG

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Figure 10

Heat transfer coefficient at Ma2,s=0.87; Re2,s=390,000 without film cooling or AJVG

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Figure 11

Heat transfer coefficient for the three operation points without film cooling or AJVG

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Figure 12

Heat transfer coefficient at Ma2,s=0.87; Re2,s=390,000; ptc/pt1=1.03

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Figure 13

Heat transfer coefficient at Ma2,s=0.87; Re2,s=390,000; ptc/pt1=1.03 with AJVG

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Figure 14

Heat transfer coefficient at Ma2,s=0.87; Re2,s=390,000; ptc/pt1=1.03 without AJVG

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Figure 15

Heat transfer coefficient at Ma2,s=0.95; Re2,s=390,000; ptc/pt1=1.06

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Figure 16

Adiabatic film cooling effectiveness at Ma2,s=0.87; Re2,s=390,000; ptc/pt1=1.03

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Figure 17

Adiabatic film cooling effectiveness at Ma2,s=0.87; Re2,s=390,000; ptc/pt1=1.03 With AJVG

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Figure 18

Adiabatic film cooling effectiveness at Ma2,s=0.95; Re2,s=390,000; ptc/pt1=1.06

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Figure 19

Heat transfer augmentation at Ma2,s=0.87; Re2,s=390,000; ptc/pt1=1.03

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Figure 20

Heat transfer augmentation at Ma2,s=0.95; Re2,s=390,000; ptc/pt1=1.06

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