Research Papers

Experimental Analysis of the Interaction Between Rim Seal and Main Annulus Flow in a Low Pressure Two Stage Axial Turbine

[+] Author and Article Information
Heinz-Peter Schiffer

Large Scale Turbine Rig,
Department of Gas Turbines and
Aerospace Propulsion,
Technische Universität Darmstadt,
Darmstadt 64287, Germany

Manuscript received August 24, 2012; final manuscript received October 19, 2012; published online June 24, 2013. Editor: David Wisler.

J. Turbomach 135(5), 051003 (Jun 24, 2013) (9 pages) Paper No: TURBO-12-1179; doi: 10.1115/1.4023015 History: Received August 24, 2012; Revised October 19, 2012

The spoiling effects of rim seal flow are studied at the Large Scale Turbine Rig (LSTR) at Technische Universität Darmstadt. Detailed flow field measurements and efficiency measurements were performed for various ingress and egress setups and will be presented in this paper. Efficiency measurements show an efficiency decrease as the rim seal mass flow is increased. Five hole probe measurements upstream and downstream of the second stator row show that an increasing rim seal mass flow leads to an increased pressure loss across the stator, to altered incidence angles and to an intensification of secondary flow structures within the lower 50% span. Static pressure taps at the stator profile primarily show altered aerodynamic loading with increased rim seal air. In addition, the end wall profile pressure was measured at the stator 2 hub. It can be seen that seal air injection causes increased pressure fluctuations on the platform. Temperature measurements with a temperature difference between rim seal and main annulus flow show that rim seal air primarily enters the passage vortex.

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Fig. 1

Mixing losses due to seal air injection

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Fig. 2

General setup of the LSTR

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Fig. 3

Schematic of LSTR air flows and instrumentation positions

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Fig. 4

Efficiency measurements, design point

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Fig. 5

Definition of radial and yaw angle

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Fig. 6

Mach number distribution at MP03, upstream of the rim seal

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Fig. 7

Radial angle distribution at MP03, upstream of the rim seal

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Fig. 8

Pressure loss across stator row 2

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Fig. 18

Static pressure in wheelspace cavity and main annulus, MP03

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Fig. 17

Stator end wall pressure distribution

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Fig. 16

Profile pressure distribution at 20% span height

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Fig. 15

Profile pressure distribution at 5% span height

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Fig. 14

Radial angle distribution, MP04

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Fig. 13

Circumferentially averaged yaw angle at MP04

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Fig. 12

Yaw angle distribution, MP04

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Fig. 11

Circumferentially averaged Mach number distribution at MP04

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Fig. 10

Mach number distribution at MP04

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Fig. 9

Temperature measurement for different seal air temperatures; 1% seal air




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