Validation of Fan Source Term Model Constructed Without Blade Geometry

Sato, Sho; Spotts, Nathan; Gao, Xinfeng

doi:10.2514/6.2019-1448

Cited by 2 publications

(2 citation statements)

References 12 publications

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“…It should be noted that the model design approach did not produce realistic blade shapes, but increased the accuracy of the loading distribution of the body force model. This was a significant difference compared to the no blade information process used by Sato, Spotts, and Gao (2019) [8], as no real attempt was made to capture realistic chordwise loading in that paper.…”

Section: Blade Performance and Cambermentioning

confidence: 88%

“…Models such as those proposed by Hall et al (2017) [6] and Pazireh and Defoe (2019) [7] have been shown to work without the need for calibration; however, they still require the blade geometry (no thickness information needed in Hall's approach) and the gas path of the fan stage. The modelling approach of Sato et al (2019) [8] works without the need for fan blade geometries, but still requires information on the gas path and blade leading and trailing edge meridional profiles.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 1: Fan Body Force Model Generation without Detailed Stage Geometry

Minaker

Defoe

2019

IJTPP

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Modern aircraft engines must accommodate inflow distortions entering the engines as a consequence of modifying the size, shape, and placement of the engines and/or nacelle to increase propulsive efficiency and reduce aircraft weight and drag. It is important to be able to predict the interactions between the external flow and the fan early in the design process. This is challenging due to computational cost and limited access to detailed fan/engine geometry. In this, the first part of a two part paper, we present a design process that produces a fan gas path and body force model with performance representative of modern high bypass ratio turbofan engines. The target users are those with limited experience in turbomachinery design or limited access to fan geometry. We employ quasi-1D analysis and a series of simplifying assumptions to produce a gas path and the body force model inputs. Using a body force model of the fan enables steady computational fluid dynamics simulations to capture fan–distortion interaction. The approach is verified for the NASA Stage 67 transonic fan. An example of the design process is also included; the model generated is shown to meet the desired fan stagnation pressure ratio and thrust to within 1%.

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Section: Blade Performance and Cambermentioning

confidence: 88%