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All sourcesNASA NTRSDOE OSTI
NASA NTRSDate not supplied

High-Fidelity Aerodynamic Analysis and Optimization of the SUSAN Electrofan Concept

Summary of Work - The LAVA flow solver is utilized to investigate the design trade space of the SUSAN Electrofan concept’s Propulsion-Airframe Integration (PAI) systems, which include the effects of aero-propulsive coupling and boundary-layer ingestion (BLI). - Simplified infinite wing models are used to study various distributed electric propulsion (DEP) system arrangements, such as over-wing, under-wing, and trailing-edge configurations.

Leonardo Machado↗
NASA NTRSDate not supplied

Thermal Management System Trade Study for SUSAN Electrofan Aircraft

Thermal management of power system components is one of the barriers identified towards the implementation of Electrified Aircraft Propulsion architectures. This paper documents the preliminary results of a trade space exploration of thermal management systems conducted for a new National Aeronautics and Space Administration regional transport aircraft concept called the SUbsonic Single Aft eNgine (SUSAN) Electrofan. Traditional methods of thermal management are evaluated alongside newer methods, which are still in development. Mass, power, and drag for traditional liquid / air heat exchangers were calculated, along with mass and area of oscillating heat pipes for outer mold line cooling. An initial assessment of the feasibility of using the fuel as part of the thermal management system was also conducted by evaluating the temperature over the full flight profile. Preliminary results and future work are discussed.

Nic Heersema↗
NASA NTRSDate not supplied

Conceptual Design of Propulsors for the SUSAN Electrofan Transport Aircraft

Conceptual designs of the propulsor modules for the SUSAN electro-fan aircraft are sought after. Shaft power requirement is reduced by using boundary layer ingesting propulsion technology. There are several obstacles to designing feasible BLI propulsion systems such as inlet distortion, flow blockage from ingesting low-momentum flow, strong coupling between airframe and propulsion systems. Thus, the high fidelity CFD tool is indispensable to assess the performance of the propulsion systems and evaluate the inlet profiles during the design process. Consequently, the CFD data is used to update the inputs for the NPSS model from the initial stage of the system design. Hence, the inlet sizing, fan design, and estimation of the power saving are carried out. Various installation concepts of the mail-slot nacelle, such as under-/over-wing and trailing edge configurations, are investigated for the wing-mounted turbo-electric distributed propulsor module, and their power-saving is evaluated. As for the tail-mounted turbofan engine, the fan diameter and inlet captured area is determined based on the CFD profiles. An appropriate area ratio of the bypass and core ducts is derived from meeting the target bypass ratio from the system design. The baseline fan stage is analyzed by full annulus URANS CFD to assess the efficiency penalty due to the ingested pressure and swirl distortions.

SUSAN Electro-Fan Aircraft↗
NASA NTRSDate not supplied

Conceptual Design of Propulsors for the SUSAN Electrofan Transport Aircrafts

Conceptual designs of the propulsor modules for the SUSAN electro-fan aircraft are sought after. Shaft power requirement is reduced by using boundary layer ingesting propulsion technology. There are several obstacles to designing feasible BLI propulsion systems such as inlet distortion, flow blockage from ingesting low-momentum flow, strong coupling between airframe and propulsion systems. Thus, the high fidelity CFD tool is indispensable to assess the performance of the propulsion systems and evaluate the inlet profiles during the design process. Consequently, the CFD data is used to update the inputs for the NPSS model from the initial stage of the system design. Hence, the inlet sizing, fan design, and estimation of the power saving are carried out. Various installation concepts of the mail-slot nacelle, such as under-/over-wing and trailing edge configurations, are investigated for the wing-mounted turbo-electric distributed propulsor module, and their power-saving is evaluated. As for the tail-mounted turbofan engine, the fan diameter and inlet captured area is determined based on the CFD profiles. An appropriate area ratio of the bypass and core ducts is derived from meeting the target bypass ratio from the system design. The baseline fan stage is analyzed by full annulus URANS CFD to assess the efficiency penalty due to the ingested pressure and swirl distortions.

Electric Aircraft↗
NASA NTRSDate not supplied

Thermal Management System Sizing and Mission Analysis for the SUSAN Electrofan Aircraft

This paper will detail the design, sizing, and mission analysis for the thermal management system (TMS) for the Subsonic Single Aft eNgine (SUSAN) aircraft. Previous work has defined key performance parameters (KPPs) for the electrical power system on SUSAN. These KPPs, efficiency and specific power, were assigned values for each power system component at minimum, nominal, and maximum levels of technology development. The values were based on NASA’s research in Electrified Aircraft Propulsion (EAP) technology. A similar approach was taken in this work, defining and assigning values for KPPs for each component of the TMS. These KPPs are used as inputs to the TMS analysis and sizing and establish targets for future technology development. The minimum level is based on the current state of the art, using available data on commercial off-the-shelf products from suppliers, datasheets, or testing. The nominal level is based on recent published research and on-going NASA-funded work. The maximum level represents a projection of technology performance into the future.

Electrified Aircraft↗
NASA NTRSDate not supplied

Thermal Management Key Performance Parameter Development and System Analysis for the SUSAN Electrofan Aircraft

A set of key performance parameters (KPPs) for thermal management system (TMS) components was developed for use in system sizing and analysis. These KPPs were defined at three different levels of performance corresponding to different ranges of Technology Readiness Levels. KPP values were determined based on a large dataset that includes analysis and testing data from literature, NASA-funded research, and commercial product datasheets. These KPPs were then used to perform a TMS sizing and analysis of the SUbsonic Single Aft eNgine (SUSAN) aircraft. Total TMS mass, power consumption, and drag is quantified at each KPP level, showing decreasing trends as the level of technology improves.

thermal management↗
NASA NTRSDate not supplied

High-Fidelity Aeropropulsive Optimization of a Mail-Slot Distributed Electric Propulsion System for the SUSAN Electrofan

Hybrid- and all-electric aircraft concepts use electric motors for power rather than a conventional jet engine. Electric propulsors open the door to new ways to synergistically integrate the propulsion system with the airframe. For example, many small electric propulsors can be distributed along the wing to increase the effective bypass ratio for better overall efficiency. Furthermore, these propulsors can be attached to the wing surface for boundary layer ingestion(BLI) to further the efficiency gains. However, these novel methods of aeropropulsive integration also create challenges such as nonuniform inflow and complex nacelle geometries. Here we use gradient-based aerodynamic shape optimization to address the design challenges of the wing-mounted distributed electric propulsion system of the Subsonic Single Aft Engine (SUSAN)concept. In doing so, we aim to more accurately benchmark the flow power of SUSAN’s mail slot propulsors relative to a conventional propulsion system in both an isolated and BLI configuration. Our preliminary results found relative to an optimized podded propulsor the optimized mailslot and BLI mailslot design required 8% and 17% more flow power respectively.The methods and key design insights also apply to other aircraft concepts that utilize distributed electric propulsion and boundary layer ingestion.

CAS↗
NASA NTRSDate not supplied

SUbsonic Single Aft eNgine (SUSAN) Electrofan: An Advanced Hybrid Electric Concept for Future Single-Aisle Aircraft

Address the aviation industry’s goal of achieving net-zero carbon emissions by 2050. Design an aircraft concept that can significantly reduce fuel burn and emissions in large regional transport aircraft carrying up to 180 passengers. Retain speed, size, and range in current commercial aircraft and utilize existing airport infrastructure and airspace management systems. Reduce operating costs while improving safety and efficiency.

Electrified Aircraft Propulsion (EAP)↗