Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl

Aissaoui Mohammed Islem; Salaheddine Azzouz; Zakaria Mansouri

doi:10.31127/tuje.1802232

Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl

Abstract

The exhaust flow at the outlet of modern lean-burn combustors, which offer reduced NOx emissions for gas turbines, is characterized by hot streaks (HS) and residual swirl that affect the aerothermal performance of downstream high-pressure (HP) turbine nozzle guide vanes (NGVs). Although leaned blades are widely employed in turbomachinery design to mitigate secondary flow losses and improve aerodynamic efficiency, the combined influence of straight and compound lean configurations under residual swirl conditions remains comparatively less investigated. The objective of this study is therefore to numerically investigate the effect of blade lean on secondary flows and aerodynamic losses in axial turbine NGVs operating under simplified combustor-exit swirl conditions. The investigations are conducted on the NGV annular cascade developed at the NASA Lewis Research Center. Steady compressible flow simulations are performed by solving the Reynolds-Averaged Navier–Stokes equations using the Shear Stress Transport turbulence model. Three-dimensional vane geometries are generated by stacking the 2D blade profile along linear positive and negative lean axes with respect to the radial direction, with lean angles ranging from α = −8° to +8°. A total of sixteen configurations are first analyzed under axial inflow conditions to evaluate the influence of blade lean on aerodynamic performance. Based on the obtained performance trends, the baseline configuration together with the optimum straight-lean and compound-lean cases are subsequently investigated under two inlet swirl orientations (positive and negative) applied at the leading edge, with a swirl intensity of |Sn| = 0.4. The results show that the negative straight lean configuration NSL02 reduces the total pressure loss coefficient by approximately 3% under axial inflow conditions and by about 14% under negative swirl compared with the baseline case. Under positive swirl conditions, the negative compound lean configuration NCL08 achieves the best performance, reducing the loss coefficient from 2.274 to 1.914, corresponding to an improvement of approximately 16%.

Keywords

Supporting Institution

ICube Laboratory, UMR 7357, CNRS, University of Strasbourg, France.

Ethical Statement

The authors declare that the research work presented in this paper was conducted in accordance with the ethical standards of scientific integrity. All data were obtained and processed following accepted academic and professional ethical guidelines. The authors affirm that this manuscript is original, has not been published elsewhere, and is not under consideration by any other journal.

Thanks

The authors express their deep gratitude to the Laboratory of Energy Systems Technologies (LTSE), 23005 Annaba, Algeria for providing the ANSYS CFX Multiphysics software license, which significantly facilitated this work. Partial support for this research was provided by the ICube Laboratory, Laboratory of Engineering Science, Computer Science and Imaging (UMR 7357), CNRS, University of Strasbourg, Strasbourg, France.

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Details

Primary Language

English

Subjects

Aerodynamics (Excl. Hypersonic Aerodynamics)

Journal Section

Research Article

Authors

Aissaoui Mohammed Islem ^*
0009-0009-4565-1388
Algeria

Salaheddine Azzouz
0009-0006-0864-8671
Algeria

Zakaria Mansouri
0009-0003-8961-9714
United Kingdom

Publication Date

July 6, 2026

Submission Date

October 12, 2025

Acceptance Date

June 2, 2026

Published in Issue

Year 2026 Volume: 10 Number: 3

DOI

https://doi.org/10.31127/tuje.1802232

IZ

https://izlik.org/JA94JB76LW

Cite

RIS / Bibtex

APA

Mohammed Islem, A., Azzouz, S., & Mansouri, Z. (2026). Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl. Turkish Journal of Engineering, 10(3), 1138-1154. https://doi.org/10.31127/tuje.1802232

AMA

1.Mohammed Islem A, Azzouz S, Mansouri Z. Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl. TUJE. 2026;10(3):1138-1154. doi:10.31127/tuje.1802232

Chicago

Mohammed Islem, Aissaoui, Salaheddine Azzouz, and Zakaria Mansouri. 2026. “Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl”. Turkish Journal of Engineering 10 (3): 1138-54. https://doi.org/10.31127/tuje.1802232.

EndNote

Mohammed Islem A, Azzouz S, Mansouri Z (July 1, 2026) Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl. Turkish Journal of Engineering 10 3 1138–1154.

IEEE

[1]A. Mohammed Islem, S. Azzouz, and Z. Mansouri, “Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl”, TUJE, vol. 10, no. 3, pp. 1138–1154, July 2026, doi: 10.31127/tuje.1802232.

ISNAD

Mohammed Islem, Aissaoui - Azzouz, Salaheddine - Mansouri, Zakaria. “Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl”. Turkish Journal of Engineering 10/3 (July 1, 2026): 1138-1154. https://doi.org/10.31127/tuje.1802232.

JAMA

1.Mohammed Islem A, Azzouz S, Mansouri Z. Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl. TUJE. 2026;10:1138–1154.

MLA

Mohammed Islem, Aissaoui, et al. “Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl”. Turkish Journal of Engineering, vol. 10, no. 3, July 2026, pp. 1138-54, doi:10.31127/tuje.1802232.

Vancouver

1.Aissaoui Mohammed Islem, Salaheddine Azzouz, Zakaria Mansouri. Effect of Straight and Compound Blade Lean on the Aerodynamic Performance of a High-Pressure Turbine Nozzle Guide Vane under Residual Swirl. TUJE. 2026 Jul. 1;10(3):1138-54. doi:10.31127/tuje.1802232