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COMUNICAÇÃO TÉCNICA ______________________________________________________________________________________________________________________________________________________________________________________________________
Nº176546
On the use of blade-section data in the propeller lifting-line theory José Rodolfo Chreim Marcos de Mattos Pimenta Fillipe Rocha Esteves GOEMS, Gustavo de Goes Gustavo Roque da Silva ASSI João Lucas Dozzi Dantas
Palestra apresentada no : ABCM INTERNATIONAL CONGRESS OF MECHANICAL ENGINEERING, 25., 2019, Uberlândia. 25 slides
A série “Comunicação Técnica” compreende trabalhos elaborados por técnicos do IPT, apresentados em eventos, publicados em revistas especializadas ou quando seu conteúdo apresentar relevância pública. ___________________________________________________________________________________________________
Instituto de Pesquisas Tecnológicas do Estado de São Paulo S/A - IPT
Av. Prof. Almeida Prado, 532 | Cidade Universitária ou Caixa Postal 0141 | CEP 01064-970
São Paulo | SP | Brasil | CEP 05508-901 Tel 11 3767 4374/4000 | Fax 11 3767-4099
www.ipt.br
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On the Use of Blade-Section Data in the Propeller Lifting-Line Theory
Jose Rodolfo Chreim Fillipe Rocha Esteves Gustavo de Goes Gomes Gustavo Roque da Silva Assi Joao Lucas Dozzi Dantas Marcos de Mattos Pimenta October, 2019
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2
Overview
Introduction
Mathematical Formulation
Results
Conclusion & Future Work
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3
Overview
Introduction
Mathematical Formulation
Results
Conclusion & Future Work
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4
Introduction
Knowledge in the emission estimates for greenhouse gases;
+ Efficient ships (propellers);
+ Compromise KT, KQ, 𝜎;
Tools for design and analysis; + Systematic series;
+ Lifting-line theory;
+ Lifting-surface theory;
+ CFD (Eulerian formulations);
Development of a novel Propeller Lifting-Line formulation;
+ Originally from Wing lifting-line;
+ Adapted to the propeller case; Complexity
Fid
elit
y
Not yet possible
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5
Overview
Introduction
Mathematical Formulation
Results
Conclusion & Future Work
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6
Mathematical Formulation I General
Novel Propeller LL; + Adaptations from modern
wing LL;
+ Close to Helical HSV;
Numerical expressions using superposition;
+ Force Equivalence + No flux (Pistolesi) Boundary Condition (PBC);
More general geometries;
Nonlinear (viscous) effects on KT, KQ, 𝛽𝑤;
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7
Mathematical Formulation II Horseshoe vortex
No analytical expression;
+ Series of straight segments (of velocity
𝑉𝑆𝑆,𝑖,𝑗
𝑏𝑖𝑏𝑗);
+ Velocity of each
horseshoe (𝑉𝐻𝑆,𝑖,𝑗
𝑏𝑖𝑏𝑗,)
𝑉𝐻𝑆,𝑖,𝑗
𝑏𝑖𝑏𝑗 = 𝑉𝑆𝑆,𝑖,𝑗
𝑏𝑖𝑏𝑗
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8
Mathematical Formulation III Pitch angle
HSV shed with pitch angle
𝛽𝐵𝑉,#,𝑖𝑏𝑖 .
Linear:
𝛽𝑖 𝑏𝑖 = tan−1
𝑉𝑃,𝑖 𝑏𝑖 ⋅ 𝑒 𝑎,𝑖
𝑏𝑖
𝑉𝑃,𝑖 𝑏𝑖 ⋅ 𝑒 𝑡,𝑖
𝑏𝑖
Nonlinear:
𝛽𝑖 𝑏𝑖 = 𝛼𝑒𝑓𝑓,𝑖
𝑏𝑖 − 𝜃𝑖
𝑅𝑖 𝑏𝑖tan 𝛽𝑖
𝑏𝑖 = 𝑅𝐵𝑉,#,𝑖𝑏𝑖 tan 𝛽𝐵𝑉,#,𝑖
𝑏𝑖
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Mathematical Formulation IV Hub Model
Hub Influences Γ;
Image vortices;
𝑅𝐼𝑀,𝑖,𝑏𝑖=
𝑅ℎ2
𝑅𝑖,𝑏𝑖
Pressure Drag;
𝐷ℎ =𝜌
16𝜋log
𝑅ℎ
𝑅0+ 3 𝑁𝐵Γℎ
2
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Mathematical Formulation V Linear Scheme
No flux at each Control Point;
𝑉𝑃,𝑖𝑏𝑖 = 𝑉∞,𝑖
𝑏𝑖 + 𝑉𝑡,𝑖𝑏𝑖 + 𝑉
𝐻𝑆,𝑖,𝑗
𝑏𝑖𝑏𝑗𝑁
𝑗=1
𝑁𝐵
𝑏𝑗=1
u𝑛,𝑖 ⋅ 𝑉𝑃,𝑖𝑏𝑖 = 0 →
𝑛 𝑖 ⋅ 𝑉𝐻𝑆,𝑖,𝑗
𝑏𝑖𝑏𝑗𝑁
𝑗=1
𝑍
𝑏𝑗=1
= −𝑛 𝑖 ⋅ 𝑉∞,𝑖𝑏𝑖 + 𝑉𝑡,𝑖
𝑏𝑖
N × 𝑍 equations for ΓP;
𝕄PΓP = −𝑊∞𝑃
𝕄P =M11 ⋯ M1𝑁𝐵
⋮ M𝑏𝑖𝑏𝐽 ⋮M𝑁𝐵1 ⋯ M𝑁𝐵𝑁𝐵
ΓP =
Γ11
⋮Γ𝑁1
Γ12
⋮
Γ𝑁 𝑁𝐵
, 𝑊∞𝑃 =
W∞11
⋮W∞𝑁
1
W∞12
⋮
W∞𝑁 NB
Hydrodynamic Coefficients
𝐶𝑛,𝑝𝑜𝑡𝑏𝑖 =
𝜌Γi𝑏𝑖𝛿𝑙𝑖sin𝜃𝑖
𝑏𝑖
12 𝜌𝑉
𝑃,𝑖
𝑏𝑖𝛿𝐴𝑖
𝑏𝑖
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• CP moves to adjust 𝜕𝐶𝑛
𝜕𝛼= 𝐶𝑛𝛼
;
𝑥𝐶𝑃𝑖 =1
2
𝐶𝑛𝛼𝑖
2𝜋+
1
4𝑐𝑖
• 𝐶𝑛𝑃𝑜𝑡, 𝛽𝑠, 𝛼𝑒𝑓𝑓 updated;
𝛼𝑒𝑓𝑓𝑖 =𝐶𝑛𝑃𝑜𝑡𝑖
𝐶𝑛𝛼𝑖+ 𝛼𝐿0𝑖
• 𝐶𝑛𝑉𝑖𝑠from 2-D data;
𝐶𝑛𝑉𝑖𝑠𝑖 = 𝐶𝑛𝑉𝑖𝑠𝛼𝑒𝑓𝑓𝑖 , 𝑅𝑒𝑖
• 𝐶𝑛𝛼
updates;
𝐶𝑛𝛼𝑖 =𝐶𝑛𝑉𝑖𝑠𝑖
𝛼𝑒𝑓𝑓𝑖 − 𝛼𝐿0𝑖
𝐶𝑛𝛼𝑖 = Ω𝐶𝑛𝛼𝑖 + (1 − Ω)𝐶𝑛𝛼𝑉𝑖𝑠
𝑖
Mathematical Formulation VI Nonlinear Scheme
𝑪𝒏𝑷𝒐𝒕𝟏
𝑪𝒏𝑷𝒐𝒕𝟐
𝑪𝒏𝑽𝒊𝒔
𝜶𝒆𝒇𝒇𝟏 𝜶𝑳𝟎 𝜶𝒆𝒇𝒇𝟐
𝑪𝒏
𝜶
Change in 𝒙𝑪𝑷𝒊 (closer to the LE)
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Mathematical Formulation VII Flowchart
Begin 𝑀𝑃,𝑊𝑃 Lin ΓP , 𝛽 𝐶𝑛𝑃𝑜𝑡
𝐾𝑇 , 𝐾𝑄
𝐶𝑛𝛼 𝐶𝑛𝛼𝑉𝑖𝑠
𝑥 𝐶𝑃
𝛼𝑒𝑓𝑓 𝐶𝑛𝑉𝑖𝑠
End
tol NO
YES
YES
NO
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Overview
Introduction
Mathematical Formulation
Results
Conclusion & Future Work
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Convergence of 𝑉 – Single loop vortex;
Results I Previous work
⋯
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Convergence of 𝑉- number of helices;
Results II Previous work
⋯
⋮
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Results III Previous work
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Results IV – Previous work
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Results V Present work: influence of 2-D data
Assess the influence of the 2-D on the PLL; + Several sources
Theoretical: Thin Foil Theory
𝐶𝑛 = 2𝜋 𝛼 + 2 𝑓0𝑐
𝐶𝑐 = 0
Experimental: Brockett (1966)
𝐶𝑛 = 2𝜋 1 − 0.83𝑡0𝑐
𝛼 + 2 𝑓0𝑐
𝐶𝑐 = 0.0085
Numerical: CFD Simulations using Star-CCM+
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Results VI numerical 2-D data
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Results VII Comparison of 2-D data
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Results VIII Comparison of 2-D data
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Results IX – MOD5 Propeller
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Overview
Introduction
Mathematical Formulation
Results
Conclusion & Future Work
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Conclusion
Novel propeller LL formulation; + Strictly imposes PBC;
general geometries (rake and skew);
Viscosity (hydrofoil) and 𝛽𝑤;
Results; + Previous (OMAE 2018): Code and solution verification showed
satisfactory p (cosine);
+ Previous (PRADS 2019): Validation showed adequate adherence for a series of geometries and range of advance coefficients;
+ Present: The choice of 2-D data influences the results obtained, specially in terms of 𝐊𝐓; however, one must evaluate the costs for generating the 2-D data.
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THANK YOU
Questions?