Integrated Gas Turbine and Environmental Control System Pack Sizing and Analysis

AIAA Propulsion and Energy 2020 Forum

Cinar

et al. 2020

Self Cite

Under the NASA University Leadership Initiative (ULI) program, a team of universities are collaborating on the advancement of technologies a hybrid turboelectric regional jet, with an intent to enter service in the 2030 timeframe. In the previous studies of the ULI program, the in-service benefits of the technologies under development were analyzed by integrating the technologies of interest to a 2030 regional jet with a hybrid turbo-electric distributed propulsion system. As the program has progressed, the projected performances for each technology and subsystem have been updated. This paper presents an update in the sizing and performance analysis of the regional jet with the hybrid turbo-electric distributed propulsion system, by integrating the updated values of the technologies and subsystems to the vehicle. The updates in this paper include the DC/AC conversion links, efficiency of generator and cabling losses, weight of the wires, the battery cooling through the environmental control system, motor and inverter cooling by the thermal management system, and the redundancy strategy of the propulsion system. The updates of the results from the integrated model include the overall efficiency of the propulsion system, mission fuel savings, mission energy flow distribution, and the optimal hybridization rate in climb and cruise. The overall fuel saving benefit for the target 600-nmi mission is 19.9% compared to the baseline aircraft.

“…Details on the ECS can be found in the previous version of this paper [1]. The modeling approach of the ECS can be found in previous work [4]. The ECS architecture is illustrated in Fig.…”

Section: Fig 6 Architecture Of the Bus Multi-feeder Pgds E Thermal Ma...mentioning

confidence: 99%

An Update on Sizing and Performance Analysis of a Hybrid Turboelectric Regional Jet for the NASA ULI Program

Perullo

AIAA Propulsion and Energy 2020 Forum

Cinar

et al. 2020

Self Cite

“…The corresponding architecture is presented in Fig. 3, which was developed by the author [29]. The component TMS cools or heats a component, by rejecting (requiring cooling) or acquiring (requiring heating) heat through a local TMS.…”

Section: Scope Of the Methodologymentioning

confidence: 99%

“…Three different global TMS heat paths were generated for the further analysis while leaving the local TMS pre-selected and fixed. Shi investigated the impacts of two types of ECS on the engine performance and the aircraft missions [29,30]. One was the conventional pneumatic ECS which extracted the bleed from the engine as the supply air, while the other used the air compressed by an electric compressor.…”

Section: Introductionmentioning

confidence: 99%

A Systematic Methodology for Populating the Aircraft Thermal Management System Architecture Space

AIAA Scitech 2021 Forum

Gladin

Mavris

2021

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The aircraft thermal management system functions to provide suitable working conditions for pilot, crew, passengers, and the other aircraft systems. The additional weight, drag and power consumption caused by it greatly influences the performance of the aircraft. However, due to rising heat load of emerging novel aircraft concepts, traditional design approaches which rely on data and empirical equations may not apply to the future thermal management systems. Many existing literature which tried to identify the optimal thermal management system architectures only considered limited architecture space where the candidates were pre-selected in terms of experience or intuition. Therefore, viable but non-intuitive architectures may not be included in the design space. To fill this gap, this paper proposes a behavior-based backtracking methodology to systematically populate the architecture space by enumerating both intuitive and non-intuitive architectures. Thermal management requirements for traditional and novel configurations are used to generate the architectures. By comparing the generated architectures with existing ones, this paper validates that the proposed methodology is capable of generating both intuitive and non-intuitive architectures.

“…The air/oil heat exchanger (ACOC) is modeled using the ε-NTU relation, following the approach in Kays and London's book [20]. The detailed implementation can be found in Shi's previous paper [21].…”

Section: Fig 5 Gt-heat Functional Architecture B Modeling Methodology...mentioning

confidence: 99%

“…The pressure drop is generated as part of the fan bleed is extracted to cool the PAO and then is mixed back into the core flow stream. The pressure drop to the fan flow, the ACOC heat exchanger weight, and the PAO weight in the heat exchanger are calculated using the ACOC heat exchanger model, which was constructed in the previous work [21] based on the ε-NTU method [20]. An introduction of the modeling method will be briefly discussed in Sec.…”

Section: Fig 2 Architecture Of the Tmsmentioning

confidence: 99%

Design and Analysis of the Thermal Management System of a Hybrid Turboelectric Regional Jet for the NASA ULI Program

AIAA Propulsion and Energy 2020 Forum

Sanders

Alahmad

et al. 2020

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A team of researchers from multiple universities are collaborating on the demonstration of a hybrid turboelectric regional jet for 2030 under the NASA ULI Program. The thermal management is one of the major challenges for the development of such an electric propulsion concept. Existing studies hardly modeled the thermal management systems with the propulsion systems nor integrated it to the aircraft for system-and mission-level analyses. Therefore, it is very difficult to verify whether a design of the thermal management system is feasible and optimal based on current literature. To fill this gap, this paper presents a design of the thermal management system for the hybrid turboelectric regional jet under the ULI program and integrates it to the aircraft. The TMS is tested against the cooling requirements, where the thermal loads from the electric propulsion system are quantified through the whole mission. Potential solutions for peak thermal loads during takeoff and climb are also proposed and analyzed, where additional coolant or phase change materials are used. Moreover, the impacts of the TMS on the system-and missionlevel performance are investigated by the presented integration approach as well. It is discovered that a basic oil-air thermal management system cannot fully remove the heat during the early mission segments. Using additional coolant or phase change materials as heat absorption can handle such heating problem, but penalty due to additional weight is added. It is found that greater penalties in fuel burn and takeoff weight are added by additional coolant solution than the phase change material solution.