Multi-Fidelity Simulation of a Turbofan Engine With Results Zoomed Into Mini-Maps for a Zero-D Cycle Simulation

Turner, Mark G.; Reed, John A.; Ryder, R. C.; Veres, Joseph P.

doi:10.1115/gt2004-53956

Cited by 44 publications

(33 citation statements)

References 20 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The USM3D flow solver, which will be discussed in subsequent sections, allows for the modeling of jet engines through the use of inflow, core outflow, and fan bypass outflow boundary conditions defined on the solid model geometry prior to grid generation. As the CRM model currently uses flow-through nacelles and does not have any engine geometry, a model based on publically available engine geometry for the GE90-115B, the PAX300, will be added to the CRM underwing nacelle 18 .…”

Section: Baseline Geometry and Engine Model Generation -Underwingmentioning

confidence: 99%

Computational Investigation of a Boundary Layer Ingestion Propulsion System for the Common Research Model

Blumenthal

Elmiligui

Geiselhart

et al. 2016

46th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

The present paper examines potential propulsive and aerodynamic benefits of integrating a Boundary-Layer Ingestion (BLI) propulsion system into a typical commercial aircraft using the Common Research Model (CRM) geometry and the NASA Tetrahedral Unstructured Software System (TetrUSS). The Numerical Propulsion System Simulation (NPSS) environment is used to generate engine conditions for CFD analysis. Improvements to the BLI geometry are made using the Constrained Direct Iterative Surface Curvature (CDISC) design method. Previous studies have shown reductions of up to 25% in terms of propulsive power required for cruise for other axisymmetric geometries using the BLI concept. An analysis of engine power requirements, drag, and lift coefficients using the baseline and BLI geometries coupled with the NPSS model are shown. Potential benefits of the BLI system relating to cruise propulsive power are quantified using a power balance method, and a comparison to the baseline case is made. Iterations of the BLI geometric design are shown and any improvements between subsequent BLI designs presented. Simulations are conducted for a cruise flight condition of Mach 0.85 at an altitude of 38,500 feet and an angle of attack of 2° for all geometries. A comparison between available wind tunnel data, previous computational results, and the original CRM model is presented for model verification purposes along with full results for BLI power savings. Results indicate a 14.4% reduction in engine power requirements at cruise for the BLI configuration over the baseline geometry. Minor shaping of the aft portion of the fuselage using CDISC has been shown to increase the benefit from Boundary-Layer Ingestion further, resulting in a 15.6% reduction in power requirements for cruise as well as a drag reduction of approximately eighteen counts over the baseline geometry.

show abstract

Section: Baseline Geometry and Engine Model Generation -Underwingmentioning

confidence: 99%

Computational Investigation of a Boundary Layer Ingestion Propulsion System for the Common Research Model

Blumenthal

Elmiligui

Geiselhart

et al. 2016

46th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

show abstract

“…The interesting aspect of this work was the coupling of the full computational fluid dynamics (CFD) simulation of the low-pressure system with a zero-dimensional cycle model of the core. Eventually, a full 3D CFD simulation of the GE90 engine was presented by this research group [14,15]. They developed an iterative approach for a full 3D CFD engine simulation even including the combustion system.…”

Section: Engine Modelmentioning

confidence: 99%

Optimization of Aero Gas Turbine Maintenance Using Advanced Simulation and Diagnostic Methods

Kraft

Sethi

Singh

2014

Journal of Engineering for Gas Turbines and Power

View full text Add to dashboard Cite

Engine maintenance costs are a major contributor to the direct operating costs o f aircraft. Therefore, the minimization of engine maintenance costs per flight-hour is a key aspect for airlines to operate successfully under challenging market conditions. Minimization can be achieved by increasing the on-wing time or by reducing the shop-visit costs. Com bining both provides optimum results and can only be achieved by thorough understand ing o f the engine. In the past, maintenance optimization was mainly an experience-based process. In this work, a novel analytical approach is presented to optimize the mainte nance o f commercial turbofan engines. A real engine fleet of more than 100 long-haul engines is used to demonstrate the application. The combination of advanced diagnostic and simulation methods with classical hardware-based failure analysis enables linking of overall engine performance with detailed hardware condition and, thus, an effective optimization of the overall maintenance process.

show abstract

“…To incorporate different fidelity models into automatic optimization design process, Variable Complexity Modeling (VCM) has been presented and followed by several further works. [9][10][11][12][13][14][15][16][17] All these works address use of variable fidelity at the disciplinary level, but this study focuses on variable fidelity in MDO systems or Multi-Level of Fidelity (Multi-LoF) MDO.…”

Section: Introductionmentioning

confidence: 99%

Multi-level of Fidelity Multi-Disciplinary Design Optimization of Small, Solid-Propellant Launch Vehicles

Roshanian

Jodei

Mirshams

et al. 2010

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

A new automated multi-level of fidelity Multi-Disciplinary Design Optimization (MDO) methodology has been developed at the MDO Laboratory of K.N. Toosi University of Technology. This paper explains a new design approach by formulation of developed disciplinary modules. A conceptual design for a small, solid-propellant launch vehicle was considered at two levels of fidelity structure. Low and medium level of fidelity disciplinary codes were developed and linked. Appropriate design and analysis codes were defined according to their effect on the conceptual design process. Simultaneous optimization of the launch vehicle was performed at the discipline level and system level. Propulsion, aerodynamics, structure and trajectory disciplinary codes were used. To reach the minimum launch weight, the Low LoF code first searches the whole design space to achieve the mission requirements. Then the medium LoF code receives the output of the low LoF and gives a value near the optimum launch weight with more details and higher fidelity.

show abstract

Multi-Fidelity Simulation of a Turbofan Engine With Results Zoomed Into Mini-Maps for a Zero-D Cycle Simulation

Cited by 44 publications

References 20 publications

Computational Investigation of a Boundary Layer Ingestion Propulsion System for the Common Research Model

Computational Investigation of a Boundary Layer Ingestion Propulsion System for the Common Research Model

Optimization of Aero Gas Turbine Maintenance Using Advanced Simulation and Diagnostic Methods

Multi-level of Fidelity Multi-Disciplinary Design Optimization of Small, Solid-Propellant Launch Vehicles

Contact Info

Product

Resources

About