Test Slabs, Fluoroelastomer (FKM), 70-80 Hardness, for Improved Gas Turbine Engine Oil Compatibility

2017 ◽  
Author(s):  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Oil ◽  
Turbine Engine

Conditions for Scuffing Failure of Ground and Superfinished Steel Disks at High Sliding Speeds Using a Gas Turbine Engine Oil

1995 ◽  
Vol 117 (3) ◽  
pp. 482-489 ◽  
Author(s):  
M. J. Patching ◽  
C. C. Kweh ◽  
H. P. Evans ◽  
R. W. Snidle
Keyword(s):  
Experimental Investigation ◽  
Gas Turbine ◽  
Surface Finish ◽  
Axial Direction ◽  
Gas Turbine Engine ◽  
Hardened Steel ◽  
Engine Oil ◽  
Turbine Engine ◽  
Involute Gears ◽  
Scuffing Failure

This paper describes the results of an experimental investigation to compare the scuffing performance of conventionally ground and superfinished hardened steel disks operating at sliding speeds of up to 26 m/s and lubricated with a gas turbine engine oil at a temperature of 100° C. The ground disks were finished in the axial direction to simulate the orientation of surface finish found on involute gears. Superfinishing was found to give a significant increase in the load at which scuffing occurred. Frictional traction was also measured in the experiments and was found to be significantly lower for the superfinished disks in the loading stages preceding scuffing failure.

Lube Oil and Bearing Thermal Management System

2009 ◽  
Author(s):  
Karleine M. Justice ◽  
Jeffrey S. Dalton ◽  
Ian Halliwell ◽  
Stephen Williamson
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Thermal Management ◽  
Gas Turbine Engine ◽  
System Level ◽  
Engine Oil ◽  
Management Systems ◽  
Lubrication System ◽  
Turbine Engine ◽  
Heat Loads

Recent improvements in technology have enabled the development of models capable of capturing performance interactions in the thermal management of air vehicle systems. Such system level models are required for better understanding of integration constraints and interactions, and are becoming increasingly important because of the need for tighter coupling between the components of thermal management systems. The study described here integrates current engine modeling capabilities with an improved, more comprehensive thermal management simulation. More specifically, the current effort evaluates the heat loads associated with the lubrication system of a gas turbine engine. The underlying engine model represents a mid-size, two-spool, subsonic transport engine. The architecture of the model is adaptable to other two-spool turbine engines and missions. Mobil Avrex S Turbo 256 engine oil is used as the lubrication medium. The model consists of five bearing heat loads. Within the engine flowpath, local temperatures and the appropriate rotational speeds are the only parameters pertinent to the heat load calculations. General assumptions have been made to simplify the representation of the lubrication system. Fuel properties into the heat exchanger are assumed. A gear box attached to the high-speed shaft operates both supply pump and scavenge pump and sends compressed air to the oil reservoir. Once the oil is distributed to the bearings, the scavenge pump collects and sends it through a filter and a fuel/oil heat exchanger before it is remixed with the contents of the reservoir. A MATLAB/Simulink modeling environment provides a general approach that may be applied to the thermal management of any engine. As a result of this approach, the new model serves as a starting point for a flexible architecture that can be modified as more detailed specifications or data are made available. In this paper, results from the simple model are compared to a more comprehensive tribology-based analysis. The results demonstrate its successful application to a typical mission, based on very limited data. In general, these results will allow system designers to conduct preliminary analyses and trade studies of gas turbine engine thermal management systems.

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