Details
| Original language | English |
|---|---|
| Title of host publication | Cycle Innovations |
| Publisher | American Society of Mechanical Engineers(ASME) |
| ISBN (electronic) | 9780791887974 |
| Publication status | Published - 28 Aug 2024 |
| Event | 69th ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition, GT 2024 - London, United Kingdom (UK) Duration: 24 Jun 2024 → 28 Jun 2024 |
Publication series
| Name | Proceedings of the ASME Turbo Expo |
|---|---|
| Volume | 5 |
Abstract
A novel design for the cathode air supply system of a fuel cell-based aircraft propulsion system is presented in this study. Herein, the state-of-the-art Electrically driven Cathode air Supply system (ECS) is replaced by a H2-fuelled micro gas turbine (GTCS) with the main goals of 1) decreased total fuel cell power demand and, therefore, 2) reduced low temperature waste heat. Therefore, no parasitic power is required to drive the cathode air supply. The proposed system design is simulated for a regional, distributed propulsion aircraft. Adaptation to other aircraft layouts is easily possible. The operating characteristics of both systems are compared and advantages of the novel architecture are quantified. The advantages are, among others, a substantial reduction of the fuel cell waste heat as well as the reduction of the overall component size within the air supply system. For the most demanding operating point take-off, fuel cell waste heat can be reduced by 25% at maximum operating pressure while heat exchanger size is decreased by up to 16% and humidifier size by up to 20%. Further synergies from the novel architecture are the possibility to use up to 45% of hydrogen from the anode exhaust in the combustor instead of recirculating or venting it. This may lead to a substantial size reduction in the anode side recirculation cycle. Considering the overall system weight, the novel system can achieve a 26% lower weight than the state-of-the-art ECS system. The fuel consumption however is up 9.6% above the ECS system due to poor thermal efficiency of the core. However, it remains to be evaluated in the context of overall aircraft design whether the advantages in component size and weight due to reduced waste heat rejection requirements can outweigh the drawbacks in fuel consumption.
ASJC Scopus subject areas
- Engineering(all)
- General Engineering
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Cycle Innovations. American Society of Mechanical Engineers(ASME), 2024. v005t06a007 (Proceedings of the ASME Turbo Expo; Vol. 5).
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research › peer review
}
TY - GEN
T1 - Design and Performance Analysis of a Fuel Cell Propulsion System Driven by a Hydrogen-Fired Micro Gas-Turbine
AU - Lück, Sebastian
AU - Göing, Jan
AU - Nachtigal, Philipp
AU - Mimic, Dajan
AU - Friedrichs, Jens
N1 - Publisher Copyright: 1. INTRODUCTION: FUEL CELL PROPULSION SYSTEMS.
PY - 2024/8/28
Y1 - 2024/8/28
N2 - A novel design for the cathode air supply system of a fuel cell-based aircraft propulsion system is presented in this study. Herein, the state-of-the-art Electrically driven Cathode air Supply system (ECS) is replaced by a H2-fuelled micro gas turbine (GTCS) with the main goals of 1) decreased total fuel cell power demand and, therefore, 2) reduced low temperature waste heat. Therefore, no parasitic power is required to drive the cathode air supply. The proposed system design is simulated for a regional, distributed propulsion aircraft. Adaptation to other aircraft layouts is easily possible. The operating characteristics of both systems are compared and advantages of the novel architecture are quantified. The advantages are, among others, a substantial reduction of the fuel cell waste heat as well as the reduction of the overall component size within the air supply system. For the most demanding operating point take-off, fuel cell waste heat can be reduced by 25% at maximum operating pressure while heat exchanger size is decreased by up to 16% and humidifier size by up to 20%. Further synergies from the novel architecture are the possibility to use up to 45% of hydrogen from the anode exhaust in the combustor instead of recirculating or venting it. This may lead to a substantial size reduction in the anode side recirculation cycle. Considering the overall system weight, the novel system can achieve a 26% lower weight than the state-of-the-art ECS system. The fuel consumption however is up 9.6% above the ECS system due to poor thermal efficiency of the core. However, it remains to be evaluated in the context of overall aircraft design whether the advantages in component size and weight due to reduced waste heat rejection requirements can outweigh the drawbacks in fuel consumption.
AB - A novel design for the cathode air supply system of a fuel cell-based aircraft propulsion system is presented in this study. Herein, the state-of-the-art Electrically driven Cathode air Supply system (ECS) is replaced by a H2-fuelled micro gas turbine (GTCS) with the main goals of 1) decreased total fuel cell power demand and, therefore, 2) reduced low temperature waste heat. Therefore, no parasitic power is required to drive the cathode air supply. The proposed system design is simulated for a regional, distributed propulsion aircraft. Adaptation to other aircraft layouts is easily possible. The operating characteristics of both systems are compared and advantages of the novel architecture are quantified. The advantages are, among others, a substantial reduction of the fuel cell waste heat as well as the reduction of the overall component size within the air supply system. For the most demanding operating point take-off, fuel cell waste heat can be reduced by 25% at maximum operating pressure while heat exchanger size is decreased by up to 16% and humidifier size by up to 20%. Further synergies from the novel architecture are the possibility to use up to 45% of hydrogen from the anode exhaust in the combustor instead of recirculating or venting it. This may lead to a substantial size reduction in the anode side recirculation cycle. Considering the overall system weight, the novel system can achieve a 26% lower weight than the state-of-the-art ECS system. The fuel consumption however is up 9.6% above the ECS system due to poor thermal efficiency of the core. However, it remains to be evaluated in the context of overall aircraft design whether the advantages in component size and weight due to reduced waste heat rejection requirements can outweigh the drawbacks in fuel consumption.
UR - http://www.scopus.com/inward/record.url?scp=85204338942&partnerID=8YFLogxK
U2 - 10.1115/GT2024-124062
DO - 10.1115/GT2024-124062
M3 - Conference contribution
AN - SCOPUS:85204338942
T3 - Proceedings of the ASME Turbo Expo
BT - Cycle Innovations
PB - American Society of Mechanical Engineers(ASME)
T2 - 69th ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition, GT 2024
Y2 - 24 June 2024 through 28 June 2024
ER -