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  • 2.1
    Impact Factor
  • 3.7
    CiteScore
  • 40 days
    Submission to First Decision
  • 29 days
    Acceptance to Publication

International Journal of Turbomachinery, Propulsion and Power

International Journal of Turbomachinery, Propulsion and Power (IJTPP) is an international, peer-reviewed, open access journal on turbomachinery, propulsion and power, published quarterly online. It is the official journal of the EUROTURBO European Turbomachinery Society. Society members receive discounts on the article processing charges.
  • Open Access— free for readers, with article processing charges (APC) paid by authors or their institutions.
  • High Visibility: indexed within Scopus, ESCI (Web of Science), Inspec, Ei Compendex, and other databases.
  • Journal Rank: JCR - Q2 (Engineering, Aerospace) / CiteScore - Q2 (Aerospace Engineering)
  • Rapid Publication: manuscripts are peer-reviewed and a first decision is provided to authors approximately 39.5 days after submission; acceptance to publication is undertaken in 28.9 days (median values for papers published in this journal in the first half of 2026).
  • Recognition of Reviewers: Reviewers whose reports are timely and of high quality receive an APC discount voucher for a future publication in an MDPI journal. Become a reviewer.

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All Articles (390)

  • Article
  • Open Access

In current low-pressure turbine cascades, around a third of the losses are determined by the complex interaction between endwall boundary layers and blade profiles. Research has focused on the origin of secondary flow structures through numerical and experimental approaches, which shed light on vorticity transport throughout the cascades. This paper details the study of the endwall flow characteristics in the newly published open-access high-speed low-pressure turbine cascade SPLEEN. This study focuses on the effect of inlet turbulence profile specification, which is studied by computational fluid dynamics in design and off-design conditions. Numerical simulations are performed using transition-sensitive Reynolds-Averaged Navier–Stokes closures, which have proved to be a reliable tool for identifying secondary flow structures in similar configurations. In this activity, RANS-based transition models capture the secondary flow structure, but underestimate mixing and over-predict losses near the hub. Inlet turbulence profiles have little effect on endwall pressure, while higher turbulence intensity and integral length scales enhance secondary flow mixing, reduce vortex penetration, and increase hub losses. In off-design conditions, a low Mach number increases secondary flow penetration and endwall losses, whereas a high Reynolds number reduces both profile and endwall losses. Finally, selected correlations from the literature agree at the nominal Reynolds number but do not capture the variations across the various conditions explored.

Experimental setup. (a) Linear cascade and constituents. (b) Meridional cut with location of measurement planes and instrumentation.
  • Article
  • Open Access

High-Fidelity Sliding Mesh Method for Moving Geometries in Turbomachinery Applications

  • Junjie Ye,
  • Guglielmo Vivarelli and
  • Chris Cantwell
  • + 3 authors

The accurate, high-fidelity modeling of moving geometries involving translation and rotation is important in fluid mechanics applications, particularly turbomachinery. These simulations facilitate the analysis of various turbomachinery stages, where complex movements are integral to their functionality. We integrated a sliding mesh capability into the iLES/DNS compressible Navier–Stokes solver within Nektar++, which is a spectral/hp element open-source framework. Static and moving regions of the finite element mesh are coupled across a non-conformal interface using a point-to-point interpolation method (PTPM). The solver is verified on two canonical benchmarks, the isentropic vortex and Couette flow, and validated on the T106A low-pressure turbine cascade with an upstream translating bar that generates inflow wakes, emulating rotor–stator interaction. This paper aims to provide robust validation of the new solver developments and supply a tool to understand how the upstream bar motion influences the downstream blade efficiency, which is crucial for enhancing turbomachinery design and performance.

Schematic of the non-conformal translating mesh. The arrow indicates the direction of motion of the translating (blue) region.
  • Article
  • Open Access

Safety, profitability, as well as energy and resource efficiency of hydropower plants require, among others, appropriate operation of hydraulic turbines, which involves reliable estimation and monitoring of water flow rate. In this work, computer simulation is used for investigation of water flow through the spiral casing of a hydraulic turbine under real operating conditions. The wall pressure at the pre-defined monitoring points in a radial plane, such as used in the Winter–Kennedy measurement method, is calculated for a range of water flow rates. The choice of the boundary-condition type downstream of the stay vanes and sensitivity to adopted turbulent-flow approach are also investigated. The numerical results agree well with the reference measurements. A relation is established between the computed monitoring pressure difference and the corresponding incoming flow rate. Having measured the static pressure at the given points, it can be used for continuous estimation of the water flow rate in the turbine under actual operating conditions.

Geometric domain: the initial point cloud obtained by 3D scanning (left) and the resulting triangulated surface, shown from above (right top), and with the view in horizontal direction (right bottom).
  • Article
  • Open Access

CFD Study of the Leakage Flow in a Low-Speed Axial Fan with Rotating Shroud

  • Mohammad Amir Neshat,
  • Edward Canepa and
  • Andrea Cattanei

This paper presents a numerical investigation of the effect of rotational speed on the development of leakage flow in a low-speed axial fan equipped with a rotating shroud. Rotor deformation induced by centrifugal forces and aerodynamic loading is taken into account through a one-way coupling between steady CFD simulations and static FEM analyses. Aerodynamic and structural results obtained at four rotational speeds are validated against available experimental data collected by the same research group, and the different leakage flow patterns associated with rotor deformation are correctly reproduced. Subsequently, the deformed geometries corresponding to two rotational speeds and operating at the same non-dimensional flow coefficient are used to perform URANS simulations. The numerical results provide insight into the leakage flow behavior within the gap between the rotating shroud and the stationary casing, a region that cannot be experimentally investigated due to optical access limitations. It is shown that the leakage flow rate through the gap shows limited sensitivity to rotor deformation, as it scales with rotational speed, and it is fed by two main contributions: a flow directly extracted from the rotor outlet and a recirculating flow developing along the mounting panel. Conversely, the non-dimensional angular momentum flow rate is larger at the lower rotational speed, corresponding to the case in which the leakage flow is rapidly re-ingested by the rotor. This indicates that the centrifugal effects associated with the leakage flow swirl are not responsible for the observed change in leakage flow pattern. Finally, significant periodic and non-periodic components are identified within the leakage flow. These components are expected to contribute to the formation of the large-scale structures impinging on the rotor blades and thus generating significant noise.

Rotor prototype and gap geometry (the white arrow indicates the direction of fan rotation).

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Int. J. Turbomach. Propuls. Power - ISSN 2504-186X