Fan Performance Scaling With Inlet Distortions

Defoe, Jeff; Etemadi, Majed; Hall, David K.

doi:10.1115/1.4039433

Cited by 16 publications

(6 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Moreover, the greater integration of the propulsor with the airframe is expected to increase the flow distortion levels at the intake. This flow distortion will propagate through the turbomachinery and penalize the overall system performance (Defoe et al , 2018; Gunn et al , 2013). The aerodynamic design of the exhaust system becomes critical, since small penalties on the exhaust performance can lead to higher specific fuel consumption in low specific thrust engines (Goulos et al , 2016).…”

Section: Introductionmentioning

confidence: 99%

“…An inviscid BFM based on the discrete turbomachinery element was originally proposed by Hall (2015). That approach was used to model boundary layer ingestion effects on the turbomachinery performance by Defoe et al (2018). Hall’s formulation was modified for viscous flows with an explicit formulation of the turbomachinery losses and compressibility effects by Thollet (2017).…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Aerodynamic optimization of the exhaust system of an aft-mounted boundary layer ingestion propulsor

Matesanz-García

Piovesan

MacManus

2022

HFF

View full text Add to dashboard Cite

Purpose Novel aircraft propulsion configurations require a greater integration of the propulsive system with the airframe. As a consequence of the closer integration of the propulsive system, higher levels of flow distortion at the fan face are expected. This distortion will propagate through the fan and penalize the system performance. This will also modify the exhaust design requirements. This paper aims to propose a methodology for the aerodynamic optimization of the exhaust for novel embedded propulsive systems. To model the distortion transfer, a low order throughflow fan model is included. Design/methodology/approach As the case study a 2D axisymmetric aft-mounted annular boundary layer ingestion (BLI) propulsor is used. An automated computational fluid dynamics approach is applied with a parametric definition of the design space. A throughflow body force model for the fan is implemented and validated for 2D axisymmetric and 3D flows. A multi-objective optimization based on evolutionary algorithms is used for the exhaust design. Findings By the application of the optimization methodology, a maximum benefit of approximately 0.32% of the total aircraft required thrust was observed by the application of compact exhaust designs. Furthermore, for the embedded system, it is observed that the design of the compact exhaust and the nacelle afterbody have a considerable impact on the aerodynamic performance. Originality/value This paper presents a novel approach for the exhaust design of embedded propulsive systems in novel aircraft configurations. To the best of the authors’ knowledge, this is the first detailed optimization of the exhaust system on an annular aft-mounted BLI propulsor.

show abstract

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aerodynamic optimization of the exhaust system of an aft-mounted boundary layer ingestion propulsor

Matesanz-García

Piovesan

MacManus

2022

HFF

View full text Add to dashboard Cite

show abstract

“…Therefore, assessment of the coupling effects between the destabilizing factors is an essential part of reasonably assigning stability margins to compressor and designing an advanced compressor. Extensive studies [5][6][7][8][9] in previous works have been carried out on the effects of temperature and pressure distortion combination, but less attention has been paid to the coupling of other factors. The coupling effects of total pressure distortion and low Reynolds number, two key factors affecting the stability of a compressor, occur frequently in the flight envelope.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigations of mass-flux redistribution and performance prediction model on coupling effects of total pressure distortion-low Reynolds number in axial compressor

Zhu

Pan

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

View full text Add to dashboard Cite

Stability assessment is one of the important subjects in airworthiness certification. Many destabilizing factors can deteriorate the performance and stability margin of the compressor, and there are coupling effects between the external factors. This paper applies a computational method to investigate the coupling effects of total pressure distortion and low Reynolds number on an axial transonic compressor. The study was carried out on NASA stage 67, in which extensive open experimental data is available. Full annulus, steady, three-dimensional CFD has been used to study the coupling effects of 180-deg inlet distortion at low Reynolds number. The assessment of the stability margin loss under coupling effects by traditional methods results in a relative error of 27%. The local operating point of the rotor at different passages has been tracked, and the results reveal the reasons for the failure of model predictions. Combined with the analysis of the flow field under coupling effects, development solutions for the traditional model are proposed. The modifications to the model agree well with the calculation results. Finally, the improved model was validated. And according to the analysis of the rotor passage working points, the rationality of the model modification was verified.

show abstract

“…The body force approach in fan/compressor simulations has been a remedy to decrease cost while maintaining accuracy in blade response to nonuniform inflow [5,6]. The body forces, implemented as source terms in the governing equations in the rotor/stator swept volumes, cause the flow turning and losses.…”

Section: Introductionmentioning

confidence: 99%

A New Loss Generation Body Force Model for Fan/Compressor Blade Rows: An Artificial-Neural-Network Based Methodology

Pazireh

Defoe

2021

IJTPP

View full text Add to dashboard Cite

Body force models of fans and compressors are widely employed for predicting performance due to the reduction in computational cost associated with their use, particularly in nonuniform inflows. Such models are generally divided into a portion responsible for flow turning and another for loss generation. Recently, accurate, uncalibrated turning force models have been developed, but accurate loss generation models have typically required calibration against higher fidelity computations (especially when flow separation occurs). In this paper, a blade profile loss model is introduced which requires the trailing edge boundary layer momentum thicknesses. To estimate the momentum thickness for a given blade section, an artificial neural network is trained using over 400,000 combinations of blade section shape and flow conditions. A blade-to-blade flow field solver is used to generate the training data. The model obtained depends only on blade geometry information and the local flow conditions, making its implementation in a typical computational fluid dynamics framework straightforward. We show good agreement in the prediction of profile loss for 2D cascades both on and off design in the defined ranges for the neural network training.

show abstract

Fan Performance Scaling With Inlet Distortions

Cited by 16 publications

References 11 publications

Aerodynamic optimization of the exhaust system of an aft-mounted boundary layer ingestion propulsor

Aerodynamic optimization of the exhaust system of an aft-mounted boundary layer ingestion propulsor

Numerical investigations of mass-flux redistribution and performance prediction model on coupling effects of total pressure distortion-low Reynolds number in axial compressor

A New Loss Generation Body Force Model for Fan/Compressor Blade Rows: An Artificial-Neural-Network Based Methodology

Contact Info

Product

Resources

About