Optimizing Subcritical-Flow Thrust-Vectoring of Converging-Diverging Nozzles

Wilson, Erich A.; Adler, Dan; Bal-Or, Benjamin Z.; Sherbaum, V.; Lichtsinder, Michael

doi:10.2514/2.5584

Cited by 8 publications

(2 citation statements)

References 5 publications

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“…It has been shown, however, that this scenario actually provides an increase of thrust in subsonic ow. 13 The algorithm presented in this work is speci cally intended for both xed-and variable-geometry axisymmetric convergingdiverging TV nozzles. It is also applicable to the two-dimensional nozzles through a minor geometrical transformation.…”

Section: Dynamic Tv Nozzle Control De Nitionsmentioning

confidence: 99%

Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Wilson

Adler

Bar‐Yoseph

2002

Journal of Propulsion and Power

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Nomenclature A = area, m 2 A j e =A j t = nozzle area control ratio @ j D E , G CD = ow coef cient at the nozzle throat M = Mach r = radius, m V c = effective nozzle expansion volume, m 3 W = gas ow rate, kg/s x = nozzle expansion length, m x n = length of divergent nozzle aps, m; x G = cos ® @ ± Gy;z D 0 ® = nozzle divergence angle, rad = nozzle convergence angle, rad ± = nozzle jet de ection angle, rad » = one-dimensionalradial elongation of r E t Subscripts c = control constant E = effective e = exit G = geometric i = variable (yaw or pitch) t = throat x = body-axis direction y = yaw direction z = pitch direction 7 = nozzle entrance station number 8 = nozzle throat station number ? = normal to A G t Superscript j = variable (effective or geometric)

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Section: Dynamic Tv Nozzle Control De Nitionsmentioning

confidence: 99%

Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Wilson

Adler

Bar‐Yoseph

2002

Journal of Propulsion and Power

Self Cite

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“…With the development of aeronautical technology, thrust vectoring nozzle has shown its advantages in many ways [1,2] .A series of investigations had been conducted to study the performance and flow characteristics of thrust vectoring nozzles [3][4][5][6][7][8] . Research results show that nozzle pressure ratios and geometric vectoring angle have significant influences on nozzles' performance.…”

Section: Introductionmentioning

confidence: 99%

Performance research of axisymmetric vectoring nozzle based on numerical simulations

Chang¹,

Qitai²,

Yang³

2015

Proceedings of the 2015 International Forum on Energy, Environment Science and Materials

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Keywords: axisymmetric vectoring nozzle； divergent angle； divergent wall length； numerical simulation Abstract. A series of numerical simulations had been conducted on nozzles with different divergent geometrical parameters, and each nozzle's flow field had been simulated under different working conditions. The effects of divergent angle and divergent wall length on nozzle performance had been analyzed. The results show that, divergent wall length and divergent angle affect nozzle performance in different ways and both should be taken into account when axisymmetric vectoring nozzle performance is investigated.

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Modeling and control schedule design of a two-dimensional thrust-vectoring nozzle and aeroengine

2020

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For advanced operational aircraft, the two-dimensional (2-D) thrust-vectoring (TV) nozzle effectively improves the flight mobility and post-stall manoevrability. However, its flow capacity decreases when deflecting and cooling air is injected, which impacts the engine’s operating state, including decreasing the fan surge margin and increasing the turbine inlet temperature. Therefore, in order to improve engine performance in the whole flight envelope, this paper studies the matching mechanism of the engine and the cooled 2-D TV nozzle, performance characterisation and control schedule of the nozzle, and an integrated aeroengine/nozzle modeling method is put forward. Based on these, an engine performance simulation model is modified to include a cooled 2-D TV nozzle. The testing results show that applying the nozzle control schedules recommended in this paper avoids the performance degradation when the nozzle deflects. This work advances the field of engine/nozzle integrated modeling, and helps to instruct the simulation and experimentation to better fit the needs of engine modeling and engineering applications.

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Optimizing Subcritical-Flow Thrust-Vectoring of Converging-Diverging Nozzles

Cited by 8 publications

References 5 publications

Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Geometric Evaluation of Axisymmetric Thrust-Vectoring Nozzles for Aerodynamic Performance Predictions

Performance research of axisymmetric vectoring nozzle based on numerical simulations

Modeling and control schedule design of a two-dimensional thrust-vectoring nozzle and aeroengine

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