Bleed Air versus Electric Power Off-takes from a Turbofan Gas Turbine over the Flight Cycle

Slingerland, Ronald; Zandstra, Sijmen

doi:10.2514/6.2007-7848

Cited by 21 publications

(12 citation statements)

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“…This reduction is attributed to the added power extraction demand on the engine by the All-Electric and Hybrid systems. This is consistent with the results outlined in the work by Slingerland and Zandstra [27] . The Booster Hybrid ECS was found to result in the highest reduction in HPC stall margin, even though it draws 36% less power than the All-Electric architecture at cruise ( Figure 5.8).…”

Section: Figure 57: Hpc Stall Margin Comparison At Cruisesupporting

confidence: 93%

Hybrid Environmental Control System Integrated Modeling Trade Study Analysis for Commercial Aviation

Parrilla¹

2014

SAE Technical Paper Series

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Current industry trends demonstrate aircraft electrification will be part of future platforms in order to achieve higher levels of efficiency in various vehicle level subsystems. However electrification requires a substantial change in aircraft design that is not suitable for re-winged or re-engined applications as some aircraft manufacturers are opting for today. Thermal limits arise as engine cores progressively get smaller and hotter to improve overall engine efficiency [8] , while legacy systems still demand a substantial amount of pneumatic, hydraulic and electric power extraction. The environmental control system (ECS) provides pressurization, ventilation and air conditioning in commercial aircraft [7] , making it the main heat sink for all aircraft loads with exception of the engine. To mitigate the architecture thermal limits in an efficient manner, the form in which the ECS interacts with the engine will have to be enhanced as to reduce the overall energy consumed and achieve an energy optimized solution.This study examines a tradeoff analysis of an electric ECS by use of a fully integrated Numerical Propulsion Simulation System (NPSS) model that is capable of studying the interaction between the ECS and the engine cycle deck. It was found that a peak solution lays in a hybrid ECS where it utilizes the correct balance between a traditional pneumatic and a fully electric system. This intermediate architecture offers a substantial improvement in aircraft fuel consumptions due to a reduced amount of waste heat and customer bleed in exchange for partial electrification of the air-conditions pack which is a viable option for re-winged applications. iii iv Para Dayana, Isaac y Ofelia v vi Acknowledgements I would first like to thank my wife, Dayana, for all her encouragement, support and patience, without her this paper would have not been possible. Her love was ever present, driving me to successfully completing my dissertation, at much sacrifice, because failure was not an option. Gracias! Furthermore, this dissertation could not have been completed without the help of numerous people. I would like to thank my advisor, Dr. Awatef Hamed, for having trusted in my capabilities and facilitated the opportunity for me to join the Vehicle Energy Systems and Integrations group at GE Aviation, which made this work possible.

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Section: Figure 57: Hpc Stall Margin Comparison At Cruisesupporting

confidence: 93%

Hybrid Environmental Control System Integrated Modeling Trade Study Analysis for Commercial Aviation

Parrilla¹

2014

SAE Technical Paper Series

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“…Researchers continue to investigate the efficiency of different secondary-power systems configurations [13][14][15][16] and how this affects the whole aircraft performance [17].…”

Section: Introductionmentioning

confidence: 99%

Effects of Off-takes for Aircraft Secondary-Power Systems on Jet Engine Efficiency

Giannakakis

Laskaridis

Pilidis

2011

Journal of Propulsion and Power

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Power and bleed-air engine offtakes have a detrimental effect on the efficiency of the engine. This paper presents a thermodynamic analysis that relates the offtakes specific fuel-consumption penalties to the design parameters of the engine. A set of equations is derived in order to determine the fuel-consumption penalties of known power and bleedair offtakes. Their predictions are compared against numerical results performed with an in-house engine simulation tool. The equations include design parameters that are known in the early preliminary design stages and can be a useful tool for aircraft, engine, and secondary-systems designers. Furthermore, the analytical expressions offer physical insight on the parameters that drive the magnitude of the specific fuel-consumption penalties. It has been found that the main factor driving the magnitude of the penalties is the size of the offtakes relative to the core power. This leads to the conclusion that future engines with a lower specific thrust factor ST=V 0 , a more efficient fan and lowpressure turbine, and a higher power factor P po =T V 0 will face increased offtake penalties.

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“…Slingerland states that the largest difficulty in comparing bleed air systems to electric systems is the inability to compare the off-takes directly. However, through the use of a gas turbine simulation program Slingerland concludes that electrical engine off-takes are less efficient than pneumatic off-takes, but the electrical systems operate much more efficiently resulting in a 2% improvement of thrust specific fuel consumption over the equivalent pneumatic system (Slingerland & Zandstra, 2007).…”

Section: Literature Reviewmentioning

confidence: 99%

Modeling and Development of an Experimental Pneumatic Facility for Aircraft Bleed Air System Studies

Molenaar¹

2023

Preprint

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Research on aircraft bleed air systems has been performed at Ryerson University for the last eight years. During this time, the requirements of the test apparatus have been constantly expanding. This thesis work aims at developing a new reconfigurable rig that supports current and future research on aircraft bleed air control systems and takes advantage of lessons learned from previous test rigs. The new rig consists of two temperature control channels in a parallel arrangement to allow for flow sharing control, and a load tank with variable exhaust. Beyond the development of the test rig, research has been performed to improve mass flow measurement based on signals from traditional thermal mass flow and pressure sensors. The proposed method utilized these redundant means of indicating flow to obtain fast and accurate flow measurement through the use of a dynamically weighted average. This method has been experimentally investigated using the test rig.

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Bleed Air versus Electric Power Off-takes from a Turbofan Gas Turbine over the Flight Cycle

Cited by 21 publications

References 0 publications

Hybrid Environmental Control System Integrated Modeling Trade Study Analysis for Commercial Aviation

Hybrid Environmental Control System Integrated Modeling Trade Study Analysis for Commercial Aviation

Effects of Off-takes for Aircraft Secondary-Power Systems on Jet Engine Efficiency

Modeling and Development of an Experimental Pneumatic Facility for Aircraft Bleed Air System Studies

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