Reduced bleed air extraction for DC-10 cabin air conditioning

Newman, W. H.; Viele, Matthew; Hrach, F. J.

doi:10.2514/6.1980-1197

“…Bleed air is hot, compressed air taken from an aircraft engine, after the compressor stage(s) and before the fuel is injected in the burners. This high-pressure, hightemperature engine bleed air is commonly used within the aircraft after cooling in several ways, including de-icing (Yeoman, 1994), pressurizing the cabin (Newman, et al, 1980) and air conditioning for passengers and avionics equipment (Ensign & Gallman, 2006). However, engine bleed air cannot be used directly due to its high temperature, and it must be cooled to the desired temperature, to be utilized appropriately in the cabin or other low temperature areas.…”

Section: List Of Tablesmentioning

confidence: 99%

Fault detection and isolation in an aircraft engine bleed air system

Shang¹

2021

Preprint

0

View full text Add to dashboard Cite

High temperature pressurized bleed air generated in the engine compressor is used for air conditioning in a jetliner. The engine bleed air must be regulated to a target temperature in the bleed air temperature control system using cold ram air before it can be used in the cabin or other low temperature area. The bleed air system is a control system that consists of sensors, and valve actuators. Potential faults associated with these components need to be considered in the design of the control system. This dissertation focuses on fault detection and diagnosis of the bleed air temperature control system. The faults in temperature sensors and valve actuators are detected using two unscented Kalman filters. The source of a fault is identified using the squared residuals. Nonlinear governing equations for the engine bleed air temperature control system are derived in state space form. Convergence analysis of the proposed fault detection and diagnosis methods is conducted. Heat exchanger is another core component in the bleed air temperature control system. A common fault associated with a heat exchanger is fouling which reduces the heat transfer efficiency, introduces additional resistance to flow, and increases fuel consumption. This dissertation presents a heat exchanger fouling detection method based on the valve control command of an engine bleed air temperature control system. Heat exchanger fouling is monitored by estimating the deviation of valve control command. A simulated bleed air temperature control system has been designed and built. Experiments have been conducted for temperature sensor fault, valve actuator fault, and heat exchanger fouling. Computer simulations for each of these cases are conducted and compared to experimental results.

show abstract

“…Bleed air is hot, compressed air taken from an aircraft engine, after the compressor stage(s) and before the fuel is injected in the burners. This high-pressure, hightemperature engine bleed air is commonly used within the aircraft after cooling in several ways, including de-icing (Yeoman, 1994), pressurizing the cabin (Newman, et al, 1980) and air conditioning for passengers and avionics equipment (Ensign & Gallman, 2006). However, engine bleed air cannot be used directly due to its high temperature, and it must be cooled to the desired temperature, to be utilized appropriately in the cabin or other low temperature areas.…”

Section: List Of Tablesmentioning

confidence: 99%

Fault detection and isolation in an aircraft engine bleed air system

Shang¹

2021

Preprint

0

View full text Add to dashboard Cite

High temperature pressurized bleed air generated in the engine compressor is used for air conditioning in a jetliner. The engine bleed air must be regulated to a target temperature in the bleed air temperature control system using cold ram air before it can be used in the cabin or other low temperature area. The bleed air system is a control system that consists of sensors, and valve actuators. Potential faults associated with these components need to be considered in the design of the control system. This dissertation focuses on fault detection and diagnosis of the bleed air temperature control system. The faults in temperature sensors and valve actuators are detected using two unscented Kalman filters. The source of a fault is identified using the squared residuals. Nonlinear governing equations for the engine bleed air temperature control system are derived in state space form. Convergence analysis of the proposed fault detection and diagnosis methods is conducted. Heat exchanger is another core component in the bleed air temperature control system. A common fault associated with a heat exchanger is fouling which reduces the heat transfer efficiency, introduces additional resistance to flow, and increases fuel consumption. This dissertation presents a heat exchanger fouling detection method based on the valve control command of an engine bleed air temperature control system. Heat exchanger fouling is monitored by estimating the deviation of valve control command. A simulated bleed air temperature control system has been designed and built. Experiments have been conducted for temperature sensor fault, valve actuator fault, and heat exchanger fouling. Computer simulations for each of these cases are conducted and compared to experimental results.

show abstract

“…If air is hotter than required, the PHx can be used to cool the fresh air stream during flight. If no cooling is required the ram air stream can be controlled though the actuation of the exit or inlet doors [33] . In some cases the CAC might be producing more than the required cabin pressure just to generate enough heat in the system.…”

Section: Figure 32: Ecs Cold Day Operationmentioning

confidence: 99%

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

Parrilla¹

2014

SAE Technical Paper Series

View full text Add to dashboard Cite

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.

show abstract

Reduced bleed air extraction for DC-10 cabin air conditioning

Cited by 3 publications

References 1 publication

Fault detection and isolation in an aircraft engine bleed air system

Fault detection and isolation in an aircraft engine bleed air system

Fault detection and isolation in an aircraft engine bleed air system

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

Contact Info

Product

Resources

About