scholarly journals Series-hybridisation, distributed electric propulsion and boundary layer ingestion in long-endurance, small remotely piloted aircraft: Fuel consumption improvements

2021 ◽  
pp. 107227
Author(s):  
Andrés Omar Tiseira Izaguirre ◽  
Luis Miguel García-Cuevas González ◽  
Pedro Quintero Igeño ◽  
Pau Varela Martínez
Keyword(s):  
Boundary Layer ◽  
Fuel Consumption ◽  
Electric Propulsion ◽  
Aircraft Fuel ◽  
Remotely Piloted Aircraft ◽  
Long Endurance

scholarly journals Computational Study of the Propeller Position Effects in Wing-Mounted, Distributed Electric Propulsion with Boundary Layer Ingestion in a 25 kg Remotely Piloted Aircraft

Drones ◽  
2021 ◽  
Vol 5 (3) ◽  
pp. 56
Author(s):  
José Serrano Cruz ◽  
Andrés Tiseira ◽  
Luis García-Cuevas ◽  
Pau Varela
Keyword(s):  
Boundary Layer ◽  
Electric Propulsion ◽  
Computational Study ◽  
Bending Moment ◽  
Vertical Position ◽  
Position Effects ◽  
Foreign Object Damage ◽  
Trade Offs ◽  
Remotely Piloted Aircraft ◽  
Interesting Approach

Distributed electric propulsion and boundary layer ingestion are two attractive technologies to reduce the power consumption of fixed wing aircraft. Through careful distribution of the propulsive system elements, higher aerodynamic and propulsive efficiency can be achieved, as well as a lower risk of total loss of aircraft due to foreign object damage. When used on the wing, further reductions of the bending moment on the wing root can even lead to reductions of its structural weight, thus mitigating the expected increase of operating empty weight due to the extra components needed. While coupling these technologies in fixed-wing aircraft is being actively studied in the big aircraft segment, it is also an interesting approach for increasing the efficiency even for aircraft with maximum take-off masses as low as 25 kg, such as the A3 open subcategory for civil drones from EASA. This paper studies the effect of changing the propellers’ position in the aerodynamic performance parameters of a distributed electric propulsion with boundary layer ingestion system in a 25 kg fixed-wing aircraft, as well as in the performance of the propellers. The computational results show the trade-offs between the aerodynamic efficiency and the propeller efficiency when the vertical position is varied.

scholarly journals Advanced Turboprop Engines for Long Endurance Naval Patrol Aircraft

1982 ◽  
Author(s):  
R. Hirschkron ◽  
R. H. Davis
Keyword(s):  
Pressure Drop ◽  
Fuel Consumption ◽  
Pressure Ratio ◽  
Specific Fuel Consumption ◽  
Performance Requirements ◽  
The Future ◽  
Weight Design ◽  
Long Endurance

Long endurance naval patrol aircraft of the future will require more efficient advanced turboprop powerplants. Engines used in this kind of application will have performance requirements emphasizing prolonged endurance and very low specific fuel consumption for cruise and part-power loiter operation. Regenerative, regenerative/intercooled and advanced conventional cycle screening studies were carried out to select the cycle pressure ratio and turbine temperature for each type, considering the effects on installed performance and weight. Design and cycle choices were studied in each engine category including recuperator types, effectiveness, pressure drop, bypass bleed and variable area turbine nozzle. The engine characteristics of each type were then compared using a representative mission. The advanced conventional engine showed the largest potential, the regenerative second and the regenerative/intercooled the least promise for lower installed fuel consumption and improved mission performance.

Marine Gas Turbine Performance Model for More Electric Ships

2011 ◽  
Author(s):  
George M. Koutsothanasis ◽  
Anestis I. Kalfas ◽  
Georgios Doulgeris
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Diesel Engines ◽  
Gas Turbines ◽  
Electric Propulsion ◽  
Operating Conditions ◽  
Prime Mover ◽  
Creep Life ◽  
Hull Fouling ◽  
Turbine Performance

This paper presents the benefits of the more electric vessels powered by hybrid engines and investigates the suitability of a particular prime-mover for a specific ship type using a simulation environment which can approach the actual operating conditions. The performance of a mega yacht (70m), powered by two 4.5MW recuperated gas turbines is examined in different voyage scenarios. The analysis is accomplished for a variety of weather and hull fouling conditions using a marine gas turbine performance software which is constituted by six modules based on analytical methods. In the present study, the marine simulation model is used to predict the fuel consumption and emission levels for various conditions of sea state, ambient and sea temperatures and hull fouling profiles. In addition, using the aforementioned parameters, the variation of engine and propeller efficiency can be estimated. Finally, the software is coupled to a creep life prediction tool, able to calculate the consumption of creep life of the high pressure turbine blading for the predefined missions. The results of the performance analysis show that a mega yacht powered by gas turbines can have comparable fuel consumption with the same vessel powered by high speed Diesel engines in the range of 10MW. In such Integrated Full Electric Propulsion (IFEP) environment the gas turbine provides a comprehensive candidate as a prime mover, mainly due to its compactness being highly valued in such application and its eco-friendly operation. The simulation of different voyage cases shows that cleaning the hull of the vessel, the fuel consumption reduces up to 16%. The benefit of the clean hull becomes even greater when adverse weather condition is considered. Additionally, the specific mega yacht when powered by two 4.2MW Diesel engines has a cruising speed of 15 knots with an average fuel consumption of 10.5 [tonne/day]. The same ship powered by two 4.5MW gas turbines has a cruising speed of 22 knots which means that a journey can be completed 31.8% faster, which reduces impressively the total steaming time. However the gas turbine powered yacht consumes 9 [tonne/day] more fuel. Considering the above, Gas Turbine looks to be the only solution which fulfills the next generation sophisticated high powered ship engine requirements.

scholarly journals A Study on Sustainable Consumption of Fuel—An Estimation Method of Aircraft

Energies ◽  
2021 ◽  
Vol 14 (22) ◽  
pp. 7559
Author(s):  
Lisha Li ◽  
Shuming Yuan ◽  
Yue Teng ◽  
Jing Shao
Keyword(s):  
Neural Network ◽  
Fuel Consumption ◽  
Influencing Factors ◽  
Carbon Emission ◽  
Estimation Method ◽  
Civil Aviation ◽  
Accurate Estimation ◽  
Low Carbon ◽  
Fuel Price ◽  
Aircraft Fuel

Though the development of China’s civil aviation and the improvement of control ability have strengthened the safety operation and support ability effectively, the airlines are under the pressure of operation costs due to the increase of aircraft fuel price. With the development of optimization controlling methods in flight management systems, it becomes increasingly challenging to cut down flight fuel consumption by control the flight status of the aircraft. Therefore, the airlines both at home and abroad mainly rely on the accurate estimation of aircraft fuel to reduce fuel consumption, and further reduce its carbon emission. The airlines have to take various potential factors into consideration and load more fuel to cope with possible negative situation during the flight. Therefore, the fuel for emergency use is called PBCF (Performance-Based Contingency Fuel). The existing PBCF forecasting method used by China Airlines is not accurate, which fails to take into account various influencing factors. This paper aims to find a method that could predict PBCF more accurately than the existing methods for China Airlines.This paper takes China Eastern Airlines as an example. The experimental data of flight fuel of China Eastern Airlines Co, Ltd. were collected to find out the relevant parameters affecting the fuel consumption, which is followed by the establishment of the LSTM neural network through the parameters and collected data. Finally, through the established neural network model, the PBCF addition required by the airline with different influencing factors is output. It can be seen from the results that the all the four models are available for the accurate prediction of fuel consumption. The amount of data of A319 is much larger than that of A320 and A330, which leads to higher accuracy of the model trained by A319. The study contributes to the calculation methods in the fuel-saving project, and helps the practitioners to learn about a particular fuel calculation method. The study brought insights for practitioners to achieve the goal of low carbon emission and further contributed to their progress towards circular economy.

Advanced Turbofan Engines for Low Fuel Consumption

1978 ◽  
Author(s):  
William Sens
Keyword(s):  
Fuel Consumption ◽  
Advanced Technology ◽  
Commercial Aircraft ◽  
New Production ◽  
Turbofan Engine ◽  
Fuel Savings ◽  
Turbofan Engines ◽  
Aircraft Fuel ◽  
Design Characteristics ◽  
Year 2000

The anticipated commercial aircraft fuel usage through the year 2000 is divided into three categories: that which will be consumed by existing engines, new production of current type engines, and new turbofan engines with advanced technology. Means of improving fuel consumption of each of these engine categories will be reviewed and the potential fuel savings identified. The cycle selection and design characteristics of an advanced turbofan engine configuration will be discussed and the potential improvements in fuel consumption and economics identified.

scholarly journals The impact of single engine taxiing on aircraft fuel consumption and pollutant emissions

2018 ◽  
Vol 122 (1258) ◽  
pp. 1967-1984 ◽  
Author(s):  
M. E. J. Stettler ◽  
G. S. Koudis ◽  
S. J. Hu ◽  
A. Majumdar ◽  
W. Y. Ochieng
Keyword(s):  
Fuel Consumption ◽  
Pollutant Emissions ◽  
Future Research ◽  
Reduce Fuel Consumption ◽  
Flight Data ◽  
Set Operations ◽  
Aircraft Fuel ◽  
Fuel Consumption And Emissions ◽  
The Impact

ABSTRACTOptimisation of aircraft ground operations to reduce airport emissions can reduce resultant local air quality impacts. Single engine taxiing (SET), where only half of the installed number of engines are used for the majority of the taxi duration, offers the opportunity to reduce fuel consumption, and emissions of NOX, CO and HC. Using 3510 flight data records, this paper develops a model for SET operations and presents a case study of London Heathrow, where we show that SET is regularly implemented during taxi-in. The model predicts fuel consumption and pollutant emissions with greater accuracy than previous studies that used simplistic assumptions. Without SET during taxi-in, fuel consumption and pollutant emissions would increase by up to 50%. Reducing the time before SET is initiated to the 25th percentile of recorded values would reduce fuel consumption and pollutant emissions by 7–14%, respectively, relative to current operations. Future research should investigate the practicalities of reducing the time before SET initialisation so that additional benefits of reduced fuel loadings, which would decrease fuel consumption across the whole flight, can be achieved.

Water drop runoff in aircraft fuel tank vent systems

2016 ◽  
Vol 231 (24) ◽  
pp. 4548-4563 ◽  
Author(s):  
Kwan Yee Chan ◽  
Joseph K-W Lam
Keyword(s):  
Boundary Layer ◽  
Water Drop ◽  
Air Flow ◽  
Fuel Tank ◽  
Pipe Surface ◽  
Hydrophobic Coating ◽  
Water Condensation ◽  
Flow Boundary ◽  
Run Off ◽  
Aircraft Fuel

Water condensation in aircraft fuel tank vent systems can run off to the fuel systems, where it can freeze to ice or support microbial growth in the fuel tanks. A laboratory scale test has been designed to investigate the ingress and runoff of water in the aircraft fuel tank vent pipes. The experiments are to determine the dual effects of air flow shear and hydrophobicity on water condensation in the vent pipes during descent from cruising altitudes. Results show only downslope runoff occurs and for large drop volumes where the height of the water drop is comparable with the height of the air flow boundary layer. Runoff is much more sensitive to drop volume and vent pipe inclination angle than air flow since the drops are within the air flow boundary layer. Downslope air flow has little effect on the runoff speeds. Downslope runoff speeds, where there is upslope air flow, exhibit large variations, when compared to those where there is downslope air flow. Upslope air flow can slow downslope runoff speeds of large volume drops by up to 400%. Runoff speeds may be up to 100 times greater with a hydrophobic coating than on the current inner vent pipe surface of anodised aluminium.

scholarly journals Two fast temperature sensors for probing of the Atmospheric Boundary Layer using small Remotely Piloted Aircraft (RPA)

2013 ◽  
Vol 6 (2) ◽  
pp. 3089-3127
Author(s):  
N. Wildmann ◽  
M. Mauz ◽  
J. Bange
Keyword(s):  
Boundary Layer ◽  
Atmospheric Boundary Layer ◽  
Low Cost ◽  
Measurement Range ◽  
Temperature Sensors ◽  
Resistance Thermometer ◽  
Remotely Piloted Aircraft ◽  
Measurement Principle ◽  
Wire Resistance ◽  
Radiation Error

Abstract. Two types of temperature sensors are designed and tested, a thermocouple and a fine wire resistance thermometer. The intention of this study is to figure out which kind of measurement principle is in general more suited for atmospheric boundary layer meteorology with small RPA. The sensors are calibrated in a NIST traceable climate chamber and validated in flight against tower measurements, radiosondes and remote sensing. The sensors have a measurement range of at least −10...50° C, an absolute RMS error of less than ±0.2 K which is stable over the lifetime of the sensors, and a resolution of about 0.01 K. Both devices are tested for typical errors like radiation error and adiabatic heating, as well as for their dynamic response. Spectral resolutions of up to approximately 10 Hz can be obtained with both sensors, which makes them suitable for turbulence measurements. Their low cost of less than 100 EUR in pure hardware is a major advantage for research with small RPA.

Sign in / Sign up

Export Citation Format

Share Document