Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft

Vinay, C. A.; Narayanappa, Kumar Gottegere; Babu, Yepuri Giridhara

doi:10.1515/tjj-2022-0011

Cited by 2 publications

(2 citation statements)

References 12 publications

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“…Figure 6 shows a good exhaust duct design with longer cutback length, which favors flow turning at the inner radius, and thus improves performance for aircraft configuration. To design exhaust stubs for different aircrafts, special attention should be paid to the exhaust stub angle, for hot exhaust gas would impinge on aircraft surfaces and structures, and exhaust stubs should not create any additional external aerodynamic drag [11][12][13][14][15]. The design of internal flow ducts should minimize the pressure loss induced by the flow separation from the internal walls of the duct.…”

Section: Sizing Of Exhaust Stubmentioning

confidence: 99%

Engine Exhaust Stub Sizing for Turboprop Powered Aircraft

Vinay¹,

Narayanappa²,

Yepuri³

2023

PEET

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Turboprop engines are widely used in the commuter or light transport aircraft (LTA) turboprop engines, because they are more fuel efficient than the propeller, which has a low jet velocity, at flight velocities below 0.6 Mach. For short distances, turboprop engines are more fuel efficient than jet engines, because the light weight assures a high power output per unit of weight. In addition, turboprops are known for their efficiency at medium and low altitudes. Turboprop engines require an exhaust stub (or nozzle) to duct the engine exhaust flue gas outboard of the aircraft. The design of these exhaust stubs is dictated primarily by the aircraft configuration. During the exhaust stub design, full flow at bends and in diffusing sections must be realized by following the established practice for the design of internal flow ducts. Otherwise, the flow will separate from the wall, causing unnecessary pressure loss and reducing the effective flow area. This paper discusses some of the many variations in exhaust stub design, and examines how they influence the performance of the engine, the performance of the aircraft, and the manufacturing aspect. The authors carried out a detailed analysis on the influencing parameters, such as the location, orientation, flange dimension, and geometric effective area of exhaust port. On this basis, the authors determined the jet temperature at exhaust stub exit and temperature at exhaust stub exit plane and nacelle midsection were determined at both static and cruise condition, laying the data basis for further analysis on the exhaust temperature effects over the nacelle and aircraft surfaces.

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Section: Sizing Of Exhaust Stubmentioning

confidence: 99%

Engine Exhaust Stub Sizing for Turboprop Powered Aircraft

Vinay¹,

Narayanappa²,

Yepuri³

2023

PEET

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“…The entire domain enclosure is set to 5.6 D , where X is the length and D is the model’s diameter considered for analysis. A circular disk was enclosed around the propeller blades, referring to the rotating domain (Vinay et al , 2022).…”

Section: Geometry and Grid Generation Around The Computational Modelmentioning

confidence: 99%

Aero-thermal investigation of thermal interactions between turboprop engine exhaust and selected parts of the airplane skin for tractor configured aircraft

C.A.

G.N.

2022

AEAT

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Purpose Development or upgradation of airplanes requires many different analyses, e.g. thermal, aerodynamic, structural and safety. Similar studies were performed during configuration change design of commuter category aircraft equipped with pusher turboprop engines. In this paper, thermo-fluid analyses of interactions of the new propulsion system in tractor configuration with selected elements of airplane skin are carried out. This study aims to check the airplane skin material, and its geometry, including the Plexiglas passenger window material degradation, due to hot exhaust gas plume impingement. The impact of change in exhaust stub angle and asymmetric inboard-outboard stubs on the jet thrust at various flight operating conditions like minimum off-route altitude and cruise performance is assessed. Design/methodology/approach Commercial software-based numerical models were developed. In the first stage, heat and fluid flow analysis was performed over a twin-engine airplane’s nacelle, wing and center fuselage with its powerplant mounted in the high wing configuration. Subsequently, numerical simulations of thermal interactions between the hot exhaust gases, which leave the exhaust system close to the nacelle, flaps and the center fuselage, were estimated for various combinations of exhaust stub angles with asymmetry between inboard-outboard stubs at different airplane configurations and operating conditions. Findings The results of the simulations are used to recommend modifications to the design of the considered airplane in terms of material selection and/or special coatings. The importance and impact of exhaust jet thrust on the overall aircraft performance are investigated. Originality/value The advanced numerical model for the exhaust jet-airplane skin thermal interaction was developed to estimate the temperature effects on the propeller blades and aircraft fuselage surfaces during different flight operating conditions with multiple combinations of stub orientations.

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Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft

Cited by 2 publications

References 12 publications

Engine Exhaust Stub Sizing for Turboprop Powered Aircraft

Engine Exhaust Stub Sizing for Turboprop Powered Aircraft

Aero-thermal investigation of thermal interactions between turboprop engine exhaust and selected parts of the airplane skin for tractor configured aircraft

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