Tail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric AircraftSource: Journal of Turbomachinery:;2023:;volume( 146 ):;issue: 002::page 21004-1Author:Chen, Zhibo
,
Galbraith, Marshall C.
,
Spakovszky, Zoltán S.
,
Greitzer, Edward M.
,
Sabnis, Jayant S.
DOI: 10.1115/1.4063930Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: This article presents conceptual design guidelines and results for a tail-integrated propulsion system for a turbo-electric civil transport aircraft with boundary layer ingestion (BLI). The aerodynamic performance goal is separation-free and shock-free operation at cruise with fuel burn reduction, compared with a baseline conventional aircraft for the same mission. The assessment of BLI benefits is based on calculations using CFD and TASOPT software, both to characterize the design challenges and to establish the physical mechanisms for resolving these challenges. The guidelines include a “horseshoe” inlet to accept the non-uniform flow without incurring separation, a nacelle profile similar to supercritical airfoils to reduce shock strength, and an annular nozzle to eliminate flow separation between tail-BLI propulsors. The conceptual design has nine BLI propulsors with electric fans on an axisymmetric tail of a single-aisle aircraft. The fans are powered by twin underwing turbofans. The estimated benefit of the tail-BLI, twin underwing turbofan aircraft is 10.4% in Payload-Range Fuel Consumption (PRFC) at a cruise Mach number of 0.8, compared to a baseline twin underwing turbofan configuration. Sensitivity studies further show that a 1% increase in installed (i.e., with BLI) fan isentropic efficiency translates to 0.8% rise in PRFC benefit.
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contributor author | Chen, Zhibo | |
contributor author | Galbraith, Marshall C. | |
contributor author | Spakovszky, Zoltán S. | |
contributor author | Greitzer, Edward M. | |
contributor author | Sabnis, Jayant S. | |
date accessioned | 2024-04-24T22:49:25Z | |
date available | 2024-04-24T22:49:25Z | |
date copyright | 11/8/2023 12:00:00 AM | |
date issued | 2023 | |
identifier issn | 0889-504X | |
identifier other | turbo_146_2_021004.pdf | |
identifier uri | http://yetl.yabesh.ir/yetl1/handle/yetl/4295937 | |
description abstract | This article presents conceptual design guidelines and results for a tail-integrated propulsion system for a turbo-electric civil transport aircraft with boundary layer ingestion (BLI). The aerodynamic performance goal is separation-free and shock-free operation at cruise with fuel burn reduction, compared with a baseline conventional aircraft for the same mission. The assessment of BLI benefits is based on calculations using CFD and TASOPT software, both to characterize the design challenges and to establish the physical mechanisms for resolving these challenges. The guidelines include a “horseshoe” inlet to accept the non-uniform flow without incurring separation, a nacelle profile similar to supercritical airfoils to reduce shock strength, and an annular nozzle to eliminate flow separation between tail-BLI propulsors. The conceptual design has nine BLI propulsors with electric fans on an axisymmetric tail of a single-aisle aircraft. The fans are powered by twin underwing turbofans. The estimated benefit of the tail-BLI, twin underwing turbofan aircraft is 10.4% in Payload-Range Fuel Consumption (PRFC) at a cruise Mach number of 0.8, compared to a baseline twin underwing turbofan configuration. Sensitivity studies further show that a 1% increase in installed (i.e., with BLI) fan isentropic efficiency translates to 0.8% rise in PRFC benefit. | |
publisher | The American Society of Mechanical Engineers (ASME) | |
title | Tail-Integrated Boundary Layer Ingesting Propulsion Systems for Turbo-Electric Aircraft | |
type | Journal Paper | |
journal volume | 146 | |
journal issue | 2 | |
journal title | Journal of Turbomachinery | |
identifier doi | 10.1115/1.4063930 | |
journal fristpage | 21004-1 | |
journal lastpage | 21004-10 | |
page | 10 | |
tree | Journal of Turbomachinery:;2023:;volume( 146 ):;issue: 002 | |
contenttype | Fulltext |