Refine
Year of publication
Institute
- Fachbereich Luft- und Raumfahrttechnik (207) (remove)
Document Type
- Conference Proceeding (207) (remove)
Keywords
- hydrogen (4)
- solar sail (4)
- Eisschicht (3)
- Karosseriebau (3)
- MASCOT (3)
- Sonde (3)
- GOSSAMER-1 (2)
- Hydrogen (2)
- Micromix (2)
- NOx emissions (2)
- PCM (2)
- Spacecraft (2)
- Trajectory Optimization (2)
- combustor development (2)
- fuels (2)
- industrial gas turbine (2)
- multiple NEA rendezvous (2)
- small spacecraft (2)
- Aircraft design (1)
- Ansaugsystem (1)
- Antarctica (1)
- Asteroid Deflection (1)
- Attitude dynamics (1)
- Autofluoreszenzverfahren (1)
- Automated Optimization (1)
- Bumblebees (1)
- Capacity Building Higher Education (1)
- Correlations (1)
- Design rules (1)
- Drag (1)
- ESATAN (1)
- Electrical Flight (1)
- Emissions (1)
- Erasmus+ United (1)
- European Framework and South East Asia (1)
- Evolutionary Neurocontrol (1)
- Flame residence time (1)
- Flame temperature (1)
- Flight Mechanics (1)
- Flight Tests (1)
- Flight control (1)
- Fuel-flexibility (1)
- GEO (1)
- Gas turbine combustion (1)
- Geometry (1)
- Gossamer (1)
- Gossamer structures (1)
- Green aircraft (1)
- Guide Tube (1)
- Hybrid Propellants (1)
- Hybrid-electric aircraft (1)
- ITS (1)
- Inflight Regeneration, Recuperation (1)
- Infused Thermal Solutions (1)
- Interplanetary flight (1)
- Jupiter (1)
- Kalman filter (1)
- Karosserieleichtbau (1)
- LEO (1)
- Laminare Strömung (1)
- Laminarprofil (1)
- Leichtbau (1)
- Leichtbauwerkstoffe (1)
- Lichtstreuungsbasierte Instrumente (1)
- Lightweight car body construction (1)
- Low-Thrust Propulsion (1)
- MAV (1)
- Malaysian Automotive Industry (1)
- Malaysian automotive industry (1)
- Mars (1)
- Materialmischbauweise (1)
- Multiphase (1)
- NOx (1)
- Nozzle (1)
- Obstacle avoidance (1)
- Orbital dynamics (1)
- PEM fuel cells (1)
- PHILAE (1)
- Planetary Protection (1)
- Planetary exploration (1)
- Profilumströmung (1)
- Propeller Aerodynamics (1)
- RaWid (1)
- Reusable Rocket Engines (1)
- Sequence-Search (1)
- Small Solar System Body Lander (1)
- Small Spacecraft (1)
- Solar Power Sail (1)
- Solar Sail (1)
- Solar sail (1)
- Spacecraft Trajectory Optimization (1)
- Stahlblech-Leichtmetall Verbundguss (1)
- Stahlblech-Leichtmetall-Hybride (1)
- Statistics (1)
- Suction (1)
- TICTOP (1)
- Technology Transfer (1)
- UAV (1)
- UTeM Engineering Knowledge Transfer Unit (1)
- Unmanned Air Vehicle (1)
- Verbundguss (1)
- aircraft engine (1)
- asteroid lander (1)
- asteroid sample return (1)
- autofluorescence-based detection system (1)
- avalanche (1)
- aviation application (1)
- car body construction (1)
- combustion (1)
- combustor (1)
- contamination (1)
- control system (1)
- electrically driven compressors (1)
- electro mobility (1)
- emission (1)
- emission index (1)
- engine demonstration (1)
- flotilla missions (1)
- fuel cell (1)
- fuel cell systems (1)
- gas turbine (1)
- habitability (1)
- health management systems (1)
- heliosphere (1)
- hybrid laminar flow (1)
- ice moons (1)
- icy moons (1)
- internal combustion engine (1)
- ion propulsion (1)
- latent heat (1)
- lattice (1)
- life detection (1)
- light scattering analysis (1)
- low-thrust (1)
- low-thrust trajectory optimization (1)
- near-Earth asteroid (1)
- nitric oxides (1)
- operational aspects (1)
- passive thermal control (1)
- planetary defence (1)
- responsive space (1)
- sample return (1)
- small solar system body characterisation (1)
- small spacecraft asteroid lander (1)
- small spacecraft solar sail (1)
- snow (1)
- solar sails (1)
- solar system (1)
- space missions (1)
- star tracker (1)
- subglacial aquatic ecosystems (1)
- subroutine (1)
- subsurface ice (1)
- subsurface ice research (1)
- subsurface probe (1)
- suction structure (1)
- suction systems (1)
- system engineering (1)
- technology transfer (1)
- thermo-physical (1)
- underwater vehicle (1)
Kawasaki Heavy Industries, LTD. (KHI) has research and development projects for a future hydrogen society. These projects comprise the complete hydrogen cycle, including the production of hydrogen gas, the refinement and liquefaction for transportation and storage, and finally the utilization in a gas turbine for electricity and heat supply. Within the development of the hydrogen gas turbine, the key technology is stable and low NOx hydrogen combustion, namely the Dry Low NOx (DLN) hydrogen combustion.
KHI, Aachen University of Applied Science, and B&B-AGEMA have investigated the possibility of low NOx micro-mix hydrogen combustion and its application to an industrial gas turbine combustor. From 2014 to 2018, KHI developed a DLN hydrogen combustor for a 2MW class industrial gas turbine with the micro-mix technology. Thereby, the ignition performance, the flame stability for equivalent rotational speed, and higher load conditions were investigated. NOx emission values were kept about half of the Air Pollution Control Law in Japan: 84ppm (O2-15%). Hereby, the elementary combustor development was completed.
From May 2020, KHI started the engine demonstration operation by using an M1A-17 gas turbine with a co-generation system located in the hydrogen-fueled power generation plant in Kobe City, Japan. During the first engine demonstration tests, adjustments of engine starting and load control with fuel staging were investigated. On 21st May, the electrical power output reached 1,635 kW, which corresponds to 100% load (ambient temperature 20 °C), and thereby NOx emissions of 65 ppm (O2-15, 60 RH%) were verified. Here, for the first time, a DLN hydrogen-fueled gas turbine successfully generated power and heat.
This study investigates the influence of pressure on the temperature distribution of the micromix (MMX) hydrogen flame and the NOx emissions. A steady computational fluid dynamic (CFD) analysis is performed by simulating a reactive flow with a detailed chemical reaction model. The numerical analysis is validated based on experimental investigations. A quantitative correlation is parametrized based on the numerical results. We find, that the flame initiation point shifts with increasing pressure from anchoring behind a downstream located bluff body towards anchoring upstream at the hydrogen jet. The numerical NOx emissions trend regarding to a variation of pressure is in good agreement with the experimental results. The pressure has an impact on both, the residence time within the maximum temperature region and on the peak temperature itself. In conclusion, the numerical model proved to be adequate for future prototype design exploration studies targeting on improving the operating range.
Solar sails enable missions to the outer solar system and beyond, although the solar
radiation pressure decreases with the square of solar distance. For such missions, the solar sail may gain a large amount of energy by first making one or more close approaches to the sun. Within this paper, optimal trajectories for solar sail missions to the outer planets and into near interstellar space (200 AU) are presented. Thereby, it is shown that even near/medium-term solar sails with relatively moderate performance allow reasonable transfer times to the boundaries of the solar system.
The recovery of waste heat requires heat exchangers to extract it from a liquid or gaseous medium into another working medium, a refrigerant. In Organic Rankine Cycles (ORC) on Combustion Engines there are two major heat sources, the exhaust gas and the water/glycol fluid from the engine’s cooling circuit. A heat exchanger design must be adapted to the different requirements and conditions resulting from the heat sources, fluids, system configurations, geometric restrictions, and etcetera. The Stacked Shell Cooler (SSC) is a new and very specific design of a plate heat exchanger, created by AKG, which allows with a maximum degree of freedom the optimization of heat exchange rate and the reduction of the related pressure drop. This optimization in heat exchanger design for ORC systems is even more important, because it reduces the energy consumption of the system and therefore maximizes the increase in overall efficiency of the engine.
A new method for improved autoclave loading within the restrictive framework of helicopter manufacturing is proposed. It is derived from experimental and numerical studies of the curing process and aims at optimizing tooling positions in the autoclave for fast and homogeneous heat-up. The mold positioning is based on two sets of information. The thermal properties of the molds, which can be determined via semi-empirical thermal simulation. The second information is a previously determined distribution of heat transfer coefficients inside the autoclave. Finally, an experimental proof of concept is performed to show a cycle time reduction of up to 31% using the proposed methodology.
The utilization of phase change material (PCM) for latent heat storage and thermal control of spacecraft has been demonstrated in the past in few missions only. One limiting factor was the fact that all concepts developed so far envisioned the PCM to be applied as an additional capacitor, encapsulated in its own housing, leading to mass, efficiency and accommodation challenges. Recently, the application of PCM within the scan cavity of a GEOS type satellite has been suggested, in order to tackle thermal issues due to direct sun intrusion (Choi, M., 2014). However, the application of PCM in such complex mechanical structures is extremely challenging. A new concept to tackle this issue is currently under development at the FH Aachen University of Applied Sciences. The concept "Infused Thermal Solutions (ITS)" is based on the idea to 3D print metallic structures in their regular functional shape, but double walled with internal lattice support structures, allowing the infusion of a PCM layer directly into the voids and eliminating the need for additional parts and interfaces. Together with OHB System, FH Aachen theoretically studied the application of this technology to the Meteosat Third Generation (MTG) Infra-Red Sounder (IRS) instrument. The study focuses on the scan cavity and entrance baffling assembly (EBA) of the IRS. It consists of thermal analyses, 3D-redesign and bread boarding of a scaled and PCM infused EBA version. In the thermal design of the alternative EBA, PCM was applied directly into the EBA, simulating the worst hot case sun intrusion of the mission. By applying 4kg of PCM (to a 60kg baffle) the EBA temperature excursions during sun intrusion were limited from 140K to 30K, leading to a significant thermo-opto-elastic performance gain. This paper introduces the ITS concept development status.