Aero-thermodynamic Design of Jet Pump for A Turboprop Aircraft Engine in Pusher Configuration
IR@NAL: CSIR-National Aerospace Laboratories, Bangalore
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| Title |
Aero-thermodynamic Design of Jet Pump for A Turboprop Aircraft Engine in Pusher Configuration
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| Creator |
Vinay, CA
Bhaskar, Chakravarthy Malisetty Leela, Shankar |
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| Subject |
Aerodynamics
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| Description |
Engine oil cooling in ground idle condition is a problem area in pusher type turboprop aircraft due to non-availability of propeller slipstream into the nacelle. Therefore, it becomes necessary to induce air flow through the oil cooler by other suitable means. One such idea is the use of a jet pump (or ejector) aft of the oil cooler. However, this imposes additional demand on the compressor bleed air, over and above that required by the Environmental Control System (ECS) for cabin air. This paper describes the aero-thermodynamic considerations used for design of a jet-pump in one such application along with test results. Sample calculations have been presented for a typical jet-pump used in the oil cooling system of a pusher type turboprop engine aircraft. The calculations have been compared with the experimental results. The results obtained show that the design objectives are met and this design allows simultaneous operation of oil cooler and ECS.
Keywords: Ejectors, engine, pressure ratio, jet-pump
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| Date |
2014
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| Type |
Conference or Workshop Item
PeerReviewed |
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| Format |
application/pdf
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| Identifier |
http://nal-ir.nal.res.in/12471/1/cp323.pdf
Vinay, CA and Bhaskar, Chakravarthy and Malisetty Leela, Shankar (2014) Aero-thermodynamic Design of Jet Pump for A Turboprop Aircraft Engine in Pusher Configuration. In: 5th International and 41st National Conference on Fluid Mechanics and Fluid Power (FMFP-2014), 12 December 2014, IIT Kanpur. |
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| Relation |
http://nal-ir.nal.res.in/12471/
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