The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor

N. Z. Huang; X. Zhao; Y. H. Zhang

doi:10.1007/978-981-13-3305-7_18

The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor

N. Z. Huang, X. Zhao, Y. H. Zhang

School of Electronics and Information

Northwestern Polytechnical University Xian

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

Abstract

In order to understand the effects of axial sweep and tangential lean of blades on aerodynamic performance of transonic axial compressor NASA ROTOR 37, a systematic study was carried out. The optimal design method was developed and applied. The blade stacking line was described by Bezier polynomials. The optimization problem was to achieve the maximum rotor isentropic efficiency and pressure ratio at the design point, with a constraint on the mass flow rate. Commercial software Design 3D was employed for aerodynamic evaluation based on Navier–Stokes code. Simulation results were validated with experimental data in the literature. The optimization technique used in this paper is based on the concept of function approximation. This approximation helps to realize a rapid method available to evaluate rotor aerodynamic performance. The method requires the existence of a database containing several blade geometries and their associated aerodynamic performances. These database samples are used to construct the Artificial Neural Network. Finally, the optimal rotor configurations were obtained and compared to the original design. The effect of swept and leaned blade on the rotor performance was analyzed.

Original language	English
Title of host publication	The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Editors	Xinguo Zhang
Publisher	Springer Verlag
Pages	227-235
Number of pages	9
ISBN (Print)	9789811333040
DOIs	https://doi.org/10.1007/978-981-13-3305-7_18
State	Published - 2019
Event	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 - Chengdu, China Duration: 16 Oct 2018 → 18 Oct 2018

Publication series

Name	Lecture Notes in Electrical Engineering
Volume	459
ISSN (Print)	1876-1100
ISSN (Electronic)	1876-1119

Conference

Conference	Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Country/Territory	China
City	Chengdu
Period	16/10/18 → 18/10/18

Keywords

Aerodynamic performance
Optimal design
Sweeping-curving blade
Transonic flow

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10.1007/978-981-13-3305-7_18

Cite this

Huang, N. Z., Zhao, X., & Zhang, Y. H. (2019). The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor. In X. Zhang (Ed.), The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 (pp. 227-235). (Lecture Notes in Electrical Engineering; Vol. 459). Springer Verlag. https://doi.org/10.1007/978-981-13-3305-7_18

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title = "The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor",

abstract = "In order to understand the effects of axial sweep and tangential lean of blades on aerodynamic performance of transonic axial compressor NASA ROTOR 37, a systematic study was carried out. The optimal design method was developed and applied. The blade stacking line was described by Bezier polynomials. The optimization problem was to achieve the maximum rotor isentropic efficiency and pressure ratio at the design point, with a constraint on the mass flow rate. Commercial software Design 3D was employed for aerodynamic evaluation based on Navier–Stokes code. Simulation results were validated with experimental data in the literature. The optimization technique used in this paper is based on the concept of function approximation. This approximation helps to realize a rapid method available to evaluate rotor aerodynamic performance. The method requires the existence of a database containing several blade geometries and their associated aerodynamic performances. These database samples are used to construct the Artificial Neural Network. Finally, the optimal rotor configurations were obtained and compared to the original design. The effect of swept and leaned blade on the rotor performance was analyzed.",

keywords = "Aerodynamic performance, Optimal design, Sweeping-curving blade, Transonic flow",

author = "Huang, {N. Z.} and X. Zhao and Zhang, {Y. H.}",

note = "Publisher Copyright: {\textcopyright} Springer Nature Singapore Pte Ltd. 2019.; Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018 ; Conference date: 16-10-2018 Through 18-10-2018",

year = "2019",

doi = "10.1007/978-981-13-3305-7_18",

language = "英语",

isbn = "9789811333040",

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Huang, NZ, Zhao, X & Zhang, YH 2019, The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor. in X Zhang (ed.), The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. Lecture Notes in Electrical Engineering, vol. 459, Springer Verlag, pp. 227-235, Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018, Chengdu, China, 16/10/18. https://doi.org/10.1007/978-981-13-3305-7_18

The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor. / Huang, N. Z.; Zhao, X.; Zhang, Y. H.
The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018. ed. / Xinguo Zhang. Springer Verlag, 2019. p. 227-235 (Lecture Notes in Electrical Engineering; Vol. 459).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

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AU - Huang, N. Z.

AU - Zhao, X.

AU - Zhang, Y. H.

N1 - Publisher Copyright: © Springer Nature Singapore Pte Ltd. 2019.

PY - 2019

Y1 - 2019

N2 - In order to understand the effects of axial sweep and tangential lean of blades on aerodynamic performance of transonic axial compressor NASA ROTOR 37, a systematic study was carried out. The optimal design method was developed and applied. The blade stacking line was described by Bezier polynomials. The optimization problem was to achieve the maximum rotor isentropic efficiency and pressure ratio at the design point, with a constraint on the mass flow rate. Commercial software Design 3D was employed for aerodynamic evaluation based on Navier–Stokes code. Simulation results were validated with experimental data in the literature. The optimization technique used in this paper is based on the concept of function approximation. This approximation helps to realize a rapid method available to evaluate rotor aerodynamic performance. The method requires the existence of a database containing several blade geometries and their associated aerodynamic performances. These database samples are used to construct the Artificial Neural Network. Finally, the optimal rotor configurations were obtained and compared to the original design. The effect of swept and leaned blade on the rotor performance was analyzed.

AB - In order to understand the effects of axial sweep and tangential lean of blades on aerodynamic performance of transonic axial compressor NASA ROTOR 37, a systematic study was carried out. The optimal design method was developed and applied. The blade stacking line was described by Bezier polynomials. The optimization problem was to achieve the maximum rotor isentropic efficiency and pressure ratio at the design point, with a constraint on the mass flow rate. Commercial software Design 3D was employed for aerodynamic evaluation based on Navier–Stokes code. Simulation results were validated with experimental data in the literature. The optimization technique used in this paper is based on the concept of function approximation. This approximation helps to realize a rapid method available to evaluate rotor aerodynamic performance. The method requires the existence of a database containing several blade geometries and their associated aerodynamic performances. These database samples are used to construct the Artificial Neural Network. Finally, the optimal rotor configurations were obtained and compared to the original design. The effect of swept and leaned blade on the rotor performance was analyzed.

KW - Aerodynamic performance

KW - Optimal design

KW - Sweeping-curving blade

KW - Transonic flow

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Y2 - 16 October 2018 through 18 October 2018

ER -

The swept and leaned blade influence on the aerodynamic performance of a transonic axial compressor rotor

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