scholarly journals Effect of Incoming Boundary-Layer Characteristics on Performance of a Distributed Propulsion System

2021 ◽  
pp. 1-12
Author(s):  
Puja Upadhyay ◽  
Khairul B. M. Q. Zaman
Keyword(s):  
Boundary Layer ◽  
Propulsion System ◽  
Distributed Propulsion

Aerodynamic benefits of boundary layer ingestion for distributed propulsion configuration

2019 ◽  
Vol 91 (10) ◽  
pp. 1285-1294 ◽  
Author(s):  
Jing Zhang ◽  
Wenwen Kang ◽  
Lingyu Yang
Keyword(s):  
Boundary Layer ◽  
Reference Value ◽  
Aerodynamic Characteristics ◽  
Comprehensive Analysis ◽  
Propulsion System ◽  
Analysis Method ◽  
Content Type ◽  
Model Based ◽  
Distributed Propulsion ◽  
Lift And Drag

Purpose Boundary layer ingestion (BLI) is one of the probable noteworthy features of distributed propulsion configuration (DPC). Because of BLI, strong coupling effects are generated between the aerodynamics and propulsion system of aircraft, leading to the specific lift and drag aerodynamic characteristics. This paper aims to propose a model-based comprehensive analysis method to investigate this unique aerodynamic. Design/methodology/approach To investigate this unique aerodynamics, a model-based comprehensive analysis method is proposed. This method uses a detailed mathematical model of the distributed propulsion system to provide the essential boundary conditions and guarantee the accuracy of calculation results. Then a synthetic three-dimensional computational model is developed to analyze the effects of BLI on the lift and drag aerodynamic characteristics. Findings Subsequently, detailed computational analyses are conducted at different flight states, and the regularities under various flight altitudes and velocities are revealed. Computational results demonstrate that BLI can improve the lift to drag ratio evidently and enable a great performance potentiality. Practical implications The general analysis method and useful regularities have reference value to DPC aircraft and other similar aircrafts. Originality/value This paper proposed a DPS model-based comprehensive analysis method of BLI benefit on aerodynamics for DPC aircraft, and the unique aerodynamics of this new configuration under various flight altitudes and velocities was revealed.

scholarly journals Installed Performance Assessment of a Boundary Layer Ingesting Distributed Propulsion System at Design Point

2016 ◽  
Author(s):  
Chana Goldberg ◽  
Devaiah Nalianda ◽  
Pericles Pilidis ◽  
David MacManus ◽  
James Felder
Keyword(s):  
Boundary Layer ◽  
Performance Assessment ◽  
Propulsion System ◽  
Design Point ◽  
Distributed Propulsion

Model-based analysis of boundary layer ingestion effect on lateral-directional aerodynamics using differentiated boundary conditions

2016 ◽  
Vol 231 (13) ◽  
pp. 2452-2463
Author(s):  
Jing Zhang ◽  
Xianfa Zeng ◽  
Lingyu Yang
Keyword(s):  
Boundary Layer ◽  
Boundary Conditions ◽  
Three Dimensional ◽  
Aerodynamic Characteristics ◽  
Propulsion System ◽  
Computational Method ◽  
Body Type ◽  
Detailed Model ◽  
Model Based ◽  
Distributed Propulsion

The noteworthy feature of aircraft with distributed propulsion configuration is the integration of a blended-wing-body type airframe and an embedded distributed propulsion system, thus inducing the specific boundary layer ingestion effect. Different boundary layer ingestion effects on the distributed engines may generate asymmetric flow fields on the airframe surface, and then lead to the unique lateral-directional aero-propulsive close coupling. To investigate the lateral-directional aerodynamics influenced by boundary layer ingestion, a new comprehensive computational method based on the differentiated boundary conditions is proposed. This method uses a synthetic three-dimensional computational model including the airframe and multi-engine to analyze the aerodynamic characteristics, and the essential boundary conditions can be extracted from the thermodynamic distributed propulsion system model to represent the different boundary layer ingestion intensities on the left and right engines. Subsequently, detailed model-based analyses of boundary layer ingestion influences on the lateral-directional aerodynamic characteristics are conducted, and the influence regularities under different flight states are revealed. All the results demonstrate that the differentiated boundary layer ingestion intensities on distributed engines can certainly affect the roll and yaw aerodynamic performance of the distributed propulsion configuration aircraft.

Thermal cycle analysis of turboelectric distributed propulsion system with boundary layer ingestion

2013 ◽  
Vol 27 (1) ◽  
pp. 163-170 ◽  
Author(s):  
Chengyuan Liu ◽  
Georgios Doulgeris ◽  
Panagiotis Laskaridis ◽  
Riti Singh
Keyword(s):  
Boundary Layer ◽  
Thermal Cycle ◽  
Propulsion System ◽  
Distributed Propulsion

Performance Analysis of a Distributed Propulsion System with Boundary Layer Ingestion

2015 ◽  
Author(s):  
Esteban A. Valencia ◽  
Chengyuan Liu ◽  
Laskaridis Panagiotis ◽  
Riti Singh ◽  
Devaiah Nalianda
Keyword(s):  
Boundary Layer ◽  
Performance Analysis ◽  
Propulsion System ◽  
Distributed Propulsion

scholarly journals Performance Assessment of a Boundary Layer Ingesting Distributed Propulsion System at Off-Design

2017 ◽  
Author(s):  
Chana Goldberg ◽  
Devaiah Nalianda ◽  
Pericles Pilidis ◽  
Riti Singh
Keyword(s):  
Boundary Layer ◽  
Performance Assessment ◽  
Propulsion System ◽  
Distributed Propulsion

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

2021 ◽  
pp. 095441002110253
Author(s):  
Babak Aryana
Keyword(s):  
High Performance ◽  
Static Condition ◽  
Propulsion System ◽  
Hybrid Propulsion ◽  
Pulse Detonation ◽  
Low Emission ◽  
Wide Range ◽  
Exit Nozzle ◽  
Distributed Propulsion ◽  
Detonation Process

This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

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