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Engineering for Turbomachinery

A special issue of Energies (ISSN 1996-1073). This special issue belongs to the section "A: Sustainable Energy".

Deadline for manuscript submissions: 20 June 2025 | Viewed by 554

Special Issue Editor

School of Energy and Power Engineering, Beihang University, Beijing 102206, China
Interests: computational fluid dynamics; unsteady flow in turbomachinery numerical simulation of turbomachinery; solid heat transfer

Special Issue Information

Dear Colleagues,

The special issue of Engineering for Turbomachinery for Journal of Energies publishes archival-quality, peer-reviewed original technical papers that advance the state-of-the-art of engineering for turbomachinery. Contributions to the journal emphasize advances with investigative techniques, including new developments in analytical, computational, and experimental methods, and physical interpretation of results to enhance knowledge and understanding of power generation and propulsion systems. The broad scope of the subject matter includes the aerodynamics, heat transfer, combustion and structure dynamics associated with the gas and steam turbines, aircraft engines, internal combustion engines, and power generation.

Dr. Yun Zheng
Guest Editor

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Keywords

  • computational fluid dynamics (CFD) analysis
  • aerodynamics
  • structure dynamics
  • aeromechanics
  • energy conversion, thermodynamic cycles and power plants
  • cycle innovations
  • heat transfer and thermal management
  • combustion fuels and emissions
  • biomass and alternative fuels
  • compressor
  • turbines
  • turbulence
  • wakes
  • compressor stall and surge
  • compressible flow
  • multiphase flows
  • aircraft engines
  • fluid-structure interaction
  • stability and transition

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Published Papers (1 paper)

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Research

26 pages, 7030 KiB  
Article
Winglet Geometries Applied to Rotor Blades of a Hydraulic Axial Turbine Used as a Turbopump: A Parametric Analysis
by Daniel da Silva Tonon, Jesuino Takachi Tomita, Ezio Castejon Garcia, Cleverson Bringhenti, Luiz Eduardo Nunes de Almeida, Jayanta Kapat and Ladislav Vesely
Energies 2025, 18(8), 2099; https://doi.org/10.3390/en18082099 - 18 Apr 2025
Viewed by 309
Abstract
Turbines are rotating machines that generate power by the expansion of a fluid; due to their characteristics, these turbomachines are widely applied in aerospace propulsion systems. Due to the clearance between the rotor blade tip and casing, there is a leakage flow from [...] Read more.
Turbines are rotating machines that generate power by the expansion of a fluid; due to their characteristics, these turbomachines are widely applied in aerospace propulsion systems. Due to the clearance between the rotor blade tip and casing, there is a leakage flow from the blade pressure to the suction sides, which generates energy loss. There are different strategies that can be applied to avoid part of this loss; one of them is the application of so-called desensitization techniques. The application of these techniques on gas turbines has been widely evaluated; however, there is a lack of analyses of hydraulic turbines. This study is a continuation of earlier analyses conducted during the first stage of the hydraulic axial turbine used in the low-pressure oxidizer turbopump (LPOTP) of the space shuttle main engine (SSME). The previous work analyzed the application of squealer geometries at the rotor tip. In the present paper, winglet geometry techniques are investigated based on three-dimensional flowfield calculations. The commercial CFX v.19.2 and ICEM v.19.2 software were used, respectively, on the numerical simulations and computational mesh generation. Experimental results published by the National Aeronautics and Space Administration (NASA) and data from previous works were used on the computational model validation. The parametric analysis was conducted by varying the thickness and width of the winglet. The results obtained show that by increasing the winglet thickness, the stage efficiency is also increased. However, the geometric dimension of its width has minimal impact on this result. An average efficiency increase of 2.0% was observed across the entire turbine operational range. In the case of the squealer, for the design point, the maximum efficiency improvement was 1.62%, compared to the current improvement of 2.23% using the winglet desensitization technique. It was found that the proposed geometries application also changes the cavitation occurrence along the stage, which is a relevant result, since it can impact the turbine life cycle. Full article
(This article belongs to the Special Issue Engineering for Turbomachinery)
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