A Study of Fan-Distortion Interaction Within the NASA Rotor 67 Transonic Stage

Fidalgo, V. Jerez; Hall, Cesare A.; Colin, Y.

doi:10.1115/1.4003850

Cited by 137 publications

(102 citation statements)

References 22 publications

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“…The first is that it requires full wheel simulations to capture the non-uniform flow caused by inlet separation; using traditional bladed full wheel simulations to model non-uniform flow is very computationally expensive. These bladed full wheel simulations can contain over 100 million cells for the internal flow alone, usually require 20-30 rotor revolutions to obtain statistically stationary results [2,3], and can take over two months to complete even with modern computing power. The second issue is that access to detailed fan stage geometry may not be possible and that most airframers lack the expertise or time required to reproduce this geometry.…”

Section: Introductionmentioning

confidence: 99%

Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 2: Comparison of Crosswind Separation Velocity with and without Detailed Fan 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 second part of a two part paper, we apply the fan gas path and body force model design process from Part 1 to the problem of predicting flow separation over an engine nacelle lip caused by crosswind. The inputs to the design process are based on NASA Stage 67. A body force model using the detailed Stage 67 geometry is also used to enable assessment of the accuracy of the design process based approach. In uniform flow, the model produced by the design process recreates the spanwise loading distribution of Rotor 67 with a 7% RMS error. Both models are then employed to predict crosswind separation velocity. The two approaches are found to agree in their prediction of the crosswind separation velocity to within 5%.

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Section: Introductionmentioning

confidence: 99%

Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 2: Comparison of Crosswind Separation Velocity with and without Detailed Fan Stage Geometry

Minaker

Defoe

2019

IJTPP

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“…In fig. 13, part-speed performance of isolated rotor is compared between current study, experimental results and numerical results (Fidalgo et al 2012). Simulations are done for 60%, 70%, 80%, 90% and 100% design speeds.…”

Section: Fig 10 Comparision Between Experimental and Numerical Resumentioning

confidence: 99%

A Developed Methodology in Design of Highly Loaded Tandem Axial Flow Compressor Stage

Eshraghi

Boroomand

Tousi³

2016

JAFM

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This study, primarily reports the development of a 3D design procedure for axial flow tandem compressor stages and then the method is used to design a highly loaded tandem stage. In order to investigate the effects of such arrangement, another stage with conventional loading with single blade for both rotor and stator rows is designed with similar specification. In order to ease the comparison of results, chord lengths and hub/shroud geometries are selected with the same dimensions. At the next stage a three dimensional numerical model is developed to predict the characteristic performance of both tandem and conventional stages. The model is validated with the experimental results of NASA-67 stage and the level of the accuracy of the model is presented. Employing the model to simulate the performance of both stages at design and offdesign operating points show that, tandem stage can provide higher pressure ratio with acceptable efficiency. In another word, tandem stage is capable having the same pressure ratio at lower rotational speed. The safe operation domain and loss mechanism in tandem stage are also discussed in this report.

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“…The result is a more uniform profile at the fan face. 54 The redistribution of mass flow in the distorted field leads to cross flows from the undistorted to distorted regions. The presence of a total pressure deficit in interaction with the fan leads to swirl.…”

Section: Fan-distortion Interactionmentioning

confidence: 99%

Progress in Boundary Layer Ingesting Embedded Engine Research

Ferrar¹,

O’Brien²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Modern aviation requirements for energy efficiency and environmental compatibility push air vehicle development toward highly integrated systems in which each component, and the system, is optimized for overall performance. Embedded engines and boundary layer ingesting propulsion systems have the potential to simultaneously improve fuel burn, noise, and emissions. Energizing the boundary layer of a drag-producing object has been recognized as a viable method to effectively reduce drag as part of the propulsion process for many years. For decades, investigators have suggested different methods for energizing boundary layers with propulsion systems. A wealth of publications forms a body of work including mathematical predictions of the effects of boundary layer ingestion and explanations of the physical basis for the process. This paper seeks to present a review of this work, in light of results from current research, to provide a reference and vision for the continuing development of boundary layer ingesting embedded engine technology.

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A Study of Fan-Distortion Interaction Within the NASA Rotor 67 Transonic Stage

Cited by 137 publications

References 22 publications

Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 2: Comparison of Crosswind Separation Velocity with and without Detailed Fan Stage Geometry

Prediction of Crosswind Separation Velocity for Fan and Nacelle Systems Using Body Force Models: Part 2: Comparison of Crosswind Separation Velocity with and without Detailed Fan Stage Geometry

A Developed Methodology in Design of Highly Loaded Tandem Axial Flow Compressor Stage

Progress in Boundary Layer Ingesting Embedded Engine Research

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