Simulating Effects of High Angle of Attack on Turbofan Engine Performance

Liu, Yuan; Claus, Russell W.; Litt, Jonathan S.; Guo, Ten-Huei

doi:10.2514/6.2013-1075

Cited by 12 publications

(3 citation statements)

References 4 publications

(2 reference statements)

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“…As angle of attack gets larger, the fan performance deteriorates, resulting in reduced thrust and stability. 21 Upset conditions and unusual attitudes, including high angle of attack and sideslip, are far enough from nominal that real engine performance may be impacted, and the baseline model does not capture these effects.…”

Section: E Propulsion Systemmentioning

confidence: 99%

A Generic T-tail Transport Airplane Simulation for High-Angle-of-Attack Dynamics Modeling Investigations

Cunningham

Shah

Hill

et al. 2018

2018 AIAA Modeling and Simulation Technologies Conference

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A preliminary simulation of a generic T-tail transport airplane configuration has been developed at the National Aeronautics and Space Administration Langley Research Center. The primary purpose of this piloted simulation is to assess aerodynamic model fidelity requirements for training airline pilots to recognize and recover from full-stall flight conditions in a T-tail airplane. As a result, significant flexibility has been designed into the flight dynamics model. The flight dynamics model is based on newly acquired static and dynamic stability and control data from sources that include: wind tunnel, water tunnel, and computational fluid dynamics. Preliminary results for initial stall show an unstable stall pitch break (if the stick pusher is inhibited), un-commanded motions due to stall asymmetries, significantly reduced dynamic roll stability, and decreased control effectiveness. Preliminary studies indicated an insensitivity to the fidelity of the pitch damping model.

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Section: E Propulsion Systemmentioning

confidence: 99%

A Generic T-tail Transport Airplane Simulation for High-Angle-of-Attack Dynamics Modeling Investigations

Cunningham

Shah

Hill

et al. 2018

2018 AIAA Modeling and Simulation Technologies Conference

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“…The C-MAPSS40k simulations were modified to include the detrimental effect of inlet distortion due to high angle of attack on engine thrust output, which can be significant in a loss-of-control event. 22 This combination of aircraft and engine models provides a realistic, nonlinear, full-envelope aircraft simulation. Furthermore, the cockpit has a reasonably comprehensive, fully configurable pilot interface, which delivers an immersive environment for highly representative testing and evaluation.…”

Section: Experimental Test Bedmentioning

confidence: 99%

Piloted Simulation Evaluation of a Model-Predictive Automatic Recovery System to Prevent Vehicle Loss of Control on Approach

Litt

Liu

Sowers

et al. 2014

AIAA Atmospheric Flight Mechanics Conference

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This paper describes a model-predictive automatic recovery system for aircraft on the verge of a loss-of-control situation. The system determines when it must intervene to prevent an imminent accident, resulting from a poor approach. It estimates the altitude loss that would result from a go-around maneuver at the current flight condition. If the loss is projected to violate a minimum altitude threshold, the maneuver is automatically triggered. The system deactivates to allow landing once several criteria are met. Piloted flight simulator evaluation showed the system to provide effective envelope protection during extremely unsafe landing attempts. The results demonstrate how flight and propulsion control can be integrated to recover control of the vehicle automatically and prevent a potential catastrophe.

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“…Nevertheless, first tests and certifications on the use of biodiesel/airplane fuel (AVGAS) blends have been conducted for aviation piston engines [32] but also ethanol/Jet-A mixtures have been tested on piston aviation engines [33]. It has been determined that by using a new type of controller, the engine could overcome some drawbacks in terms of functioning characteristics.…”

Section: Introductionmentioning

confidence: 99%

Lab Scale Investigation of Gaseous Emissions, Performance and Stability of an Aviation Turbo-Engine While Running on Biodiesel Based Sustainable Aviation Fuel

Mirea,

Cican

2024

Inventions

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The research experimentally examines the viability of biodiesel obtained from pork fat (BP) as a sustainable aviation fuel (SAF) when mixed with kerosene (Ke)—Jet-A aviation fuel + 5% Aeroshell 500 oil. Various blends of biodiesel and kerosene (10, 20, and 30% vol. of BP added in Ke) were subjected to testing in an aviation micro turbo-engine under different operational states: idle, cruise, and maximum power. During the tests, monitoring of engine parameters such as burning temperature, fuel consumption, and thrust force was conducted. The study also encompassed the calculation of crucial performance indicators like burning efficiency, thermal efficiency, and specific consumption for all fuel blends under maximum power conditions. Combustion temperatures ahead of the turbines rise with an increase in biodiesel concentration, particularly in the idle regime, without compromising engine integrity. However, for regimes 2 and 3, the temperature in front of the turbine decreases with rising biodiesel concentration, accompanied by an increase in fuel flow rate. This phenomenon is reflected in the elevated specific consumption. Notably, for regime 3, there is a noticeable rise in specific consumption, starting from S = 0.0264 kg/Nh when the turbo-engine operates solely with Ke, to S = 0.0266 kg/Nh for Ke + 10% BP, S = 0.0269 kg/Nh for Ke + 20% BP, and S = 0.0275 kg/Nh for Ke + 30% BP. Physical–chemical properties of the blends, encompassing density, viscosity, flash point, and calorific power, were determined. Furthermore, elemental analysis and FTIR were used for chemical composition determination. The amount of CO2 produced during the stoichiometric combustion reaction with air showed variations. Initially, when using only Ke, it amounted to 3.12 kg per kilogram of fuel. Upon adding 10% BP, this value decreased to 3.09 kg, further reducing to 3.05 kg with 20% BP. The lowest value was observed with 30% BP, reaching 3.04 kg. Experimental assessments were performed on the Jet Cat P80® micro-turbo-engine, covering aspects such as starting procedures, sudden acceleration, sudden deceleration, and emissions of pollutants (NOx, CO, and SO2) during several engine operational phases. The outcomes reveal that the examined fuel blends exhibited stable engine performance across all tested conditions. This indicates that these blends hold promise as sustainable aviation fuels for micro turbo-engines, presenting benefits in terms of diminished pollution and a more ecologically sound raw material base for fuel production.

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Simulating Effects of High Angle of Attack on Turbofan Engine Performance

Cited by 12 publications

References 4 publications

A Generic T-tail Transport Airplane Simulation for High-Angle-of-Attack Dynamics Modeling Investigations

A Generic T-tail Transport Airplane Simulation for High-Angle-of-Attack Dynamics Modeling Investigations

Piloted Simulation Evaluation of a Model-Predictive Automatic Recovery System to Prevent Vehicle Loss of Control on Approach

Lab Scale Investigation of Gaseous Emissions, Performance and Stability of an Aviation Turbo-Engine While Running on Biodiesel Based Sustainable Aviation Fuel

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