Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
-
P. S. Premkumar
,
S. Bhaskar Chakravarthy
Abstract
Aircraft engines need a cooling system to keep the engine oil well within the temperature limits for continuous operation. The aircraft selected for this study is a typical pusher type Light Transport Aircraft (LTA) having twin turbo prop engines mounted at the aft end of the fuselage. Due to the pusher propeller configuration, effective oil cooling is a critical issue, especially during low-speed ground operations like engine idling and also in taxiing and initial climb. However, the possibility of utilizing the inflow induced by the propeller for oil cooling is the subject matter of investigation in this work. The oil cooler duct was designed to accommodate the required mass flow, estimated using the oil cooler performance graph. A series of experiments were carried out with and without oil cooler duct attached to the nacelle, in order to investigate the mass flow induced by the propeller and its adequacy to cool the engine oil. Experimental results show that the oil cooler positioned at roughly 25 % of the propeller radius from the nacelle center line leads to adequate cooling, without incorporating additional means. Furthermore, it is suggested to install a NACA scoop to minimize spillage drag by increasing pressure recovery.
Acknowledgements
Authors thank Director, NAL for his support to conduct the experiments on aircraft. And also gratefully acknowledge the support extended by Mr. M.S. Kamaleshiah, Head C-CADD, Dr. H.N.V. Dutt, Honorary consultant and Mr. M.S Chidananda, Former Head C-CADD and Dr. S. Elangovan, Head of the Department, Aeronautical Engineering, KCT. Authors express their gratitude to “Team LTA” for the support during flow measurements on the aircraft nacelle during EGR. The authors also acknowledge the support offered by CABS, DRDO for providing airflow sensors which supported the experiments.
References
1. Lathasree P, Pashilkar AA. Digital simulation model for a turboprop engine. Symposium on Applied Aerodynamics and Design of Aerospace Vehicle (SAROD 2011), Nov 2011.Search in Google Scholar
2. Know your PT6A Turboprop. Engine Introduction Manual, Pratt & Whitney Canada.Search in Google Scholar
3. Milley SJ, Ovens JK, Lawrence DL. An experimental investigation of the aerodynamics and cooling of a horizontally-opposed air-cooled aircraft engine installation. NASA Contractor Report 3405.Search in Google Scholar
4. ESDU86002 – Drag and pressure recovery characteristics of auxiliary air inlets at subsonic speeds, issued Apr 1986.Search in Google Scholar
5. ESDU66028 – Relationships between some common intake parameters, issued July 1966.Search in Google Scholar
6. Sóbester A. Tradeoffs in jet inlet design: a historical perspective. J Aircraft May–June 2007;44. DOI: 10.2514/1.26830.Search in Google Scholar
7. Dewey PE, Vick AR. An investigation of the discharge and drag characteristics of auxiliary-air outlets discharging into a transonic stream. NACA Technical Note 3466.Search in Google Scholar
8. Mossman EA. A comparison of two submerged inlets at subsonic and transonic speeds. NACA RM A9F16.Search in Google Scholar
9. Doebelin E. Measurement systems application and design. McGraw Hill, Columbus, U.S.A., 2003.Search in Google Scholar
© 2017 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Expanded R&D by Jet-engine-steering Revolution
- Scientific Paper
- Switching LPV Control with Double-Layer LPV Model for Aero-Engines
- On-Board Real-Time Optimization Control for Turbo-Fan Engine Life Extending
- Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
- Regulating Effect of Asymmetrical Impeller on the Flow Distributions of Double-sided Centrifugal Compressor
- Numerical Prediction of the Influence of Thrust Reverser on Aeroengine’s Aerodynamic Stability
- Performance Evaluation of an Experimental Turbojet Engine
- The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
- The Ignition of Two Phase Detonation by a Branching Detonation Tube
- Tab Geometry Effect on Supersonic Elliptic Jet Control
Articles in the same Issue
- Frontmatter
- Expanded R&D by Jet-engine-steering Revolution
- Scientific Paper
- Switching LPV Control with Double-Layer LPV Model for Aero-Engines
- On-Board Real-Time Optimization Control for Turbo-Fan Engine Life Extending
- Investigation of Engine Oil-cooling Problem during Idle Conditions on Pusher Type Turbo Prop Aircraft
- Regulating Effect of Asymmetrical Impeller on the Flow Distributions of Double-sided Centrifugal Compressor
- Numerical Prediction of the Influence of Thrust Reverser on Aeroengine’s Aerodynamic Stability
- Performance Evaluation of an Experimental Turbojet Engine
- The Design and Semi-Physical Simulation Test of Fault-Tolerant Controller for Aero Engine
- The Ignition of Two Phase Detonation by a Branching Detonation Tube
- Tab Geometry Effect on Supersonic Elliptic Jet Control
