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Research Papers: Gas Turbines: Combustion, Fuels, and Emissions

Experimental Investigation Into the Efficiency of an Aero-engine Oil Jet Supply System

[+] Author and Article Information
Matthias B. Krug

Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology (KIT),
Karlsruhe 76131, Germany,
e-mail: matthias.krug@kit.edu

Davide Peduto, Wolfram Kurz, Hans-Jörg Bauer

Institut für Thermische Strömungsmaschinen,
Karlsruhe Institute of Technology (KIT),
Karlsruhe 76131, Germany

Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 9, 2014; final manuscript received July 16, 2014; published online September 3, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(1), 011505 (Sep 03, 2014) (7 pages) Paper No: GTP-14-1338; doi: 10.1115/1.4028255 History: Received July 09, 2014; Revised July 16, 2014

This paper presents results of investigations on the interaction between a targeted oil jet and a rotating shaft in an aero-engine typical bearing chamber. Measurements were performed at atmospheric temperature and pressure in order to study the influence of the operating conditions, nozzle diameters and impingement angles on the efficiency of such an oil supply system. The flow phenomena of the jet–shaft interaction were visualized. A qualitative analysis of the jet–shaft interaction revealed massive droplet generation due to the jet break-up in the air crossflow and its impact on the shaft. The latter could be reduced with shallower impingement angles. Measurements showed that the oil inflow rate, the shaft speed, and the nozzle diameter have a strong influence on the collected oil quantity, which is expressed as catch efficiency, i.e., the ratio of collected and supplied oil. The impingement angle was also identified to have a strong influence on the catch efficiency. The ratio of the momentum fluxes of supplied oil and chamber air flow is proposed as a parameter to correlate the catch efficiency to the operating conditions.

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Figures

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Fig. 1

Sectional view of the test rig

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Fig. 2

Modular setup of test configuration

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Fig. 3

Sectional view of rotor with feed holes

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Fig. 4

Schematics of nozzle setups

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Fig. 5

Influence of operating conditions with dnozzle=2d0, α = 70 deg, and lNT = 30 mm

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Fig. 6

Oil distribution for different nozzle diameters and impingement angles at V·l,in = 4 l/min

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Fig. 7

Influence of momentum flux ratio with α = 70 deg and lNT = 30 mm

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Fig. 8

Influence of nozzle diameter with α = 70 deg and lNT = 30 mm

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Fig. 9

Influence of impingement angle with lNT = 30 mm and dnozzle = d0, 1.3d0, 2d0

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Fig. 10

High speed images at V·l,in=6 l/min and nsh = 9000 rpm with dnozzle = 1.3d0 and lNT = 30 mm

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