Journal of Turbomachinery: Recent submissions
Now showing items 101-120 of 4519
-
A Novel Approach to Dirt Mitigation for Combustor Walls
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Ingestion of particulate within a gas turbine engine leads to undesirable consequences such as erosion, hot spots, and cooling hole blockages. These concerns are prevalent in the combustor wall region that commonly ... -
Impact of Nozzle Guide Vane Trailing Edge Damage on High-Pressure Turbine Stage Performance
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. In this paper we consider the impact of nozzle guide vane trailing edge burn-back (damage) on cooled high-pressure turbine stage performance. We analyse four levels of simulated burn-back ranging from new parts ... -
Design Optimization of Complex Total Pressure Distortion Screens for Gas Turbine Engine Testing
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. In a gas turbine engine, inlet flow distortion occurs due to factors such as flow separation in the aircraft inlet due to aircraft maneuvers and flight conditions. The distorted inlet flow significantly impacts ... -
Enhancing Blade Durability to Foreign Object Damage Through Multidisciplinary Design Optimization
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Foreign object damage (FOD) poses a significant challenge to the durability of compressor blades in aero engines. Impacts from foreign objects can threaten structural integrity and increase maintenance costs. ... -
Experimental Investigation on the Effects of Inlet Circumferential Distortion and Optimized Casing Treatment in a Transonic Compressor
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Casing treatment has been widely adopted to enhance the operating range of compressors by extending the stall margin. In this article, a high-precision experimental investigation is conducted in a transonic ... -
Numerical Analysis of Sealing Flows in Gas Turbines Using RANS and Large Eddy Simulation Approaches
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. The flow field developing inside the stator–rotor disc cavities of gas turbines is characterized by highly complex and unsteady behavior driven by strong vortical structures and transient interactions. These ... -
Heat Transfer Analysis in a Turbine Bottom Platform Cavity With Hot Gas Ingestion: An Investigation on the Applicability of the Superposition Approach
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. This study focuses on the heat transfer mechanisms within the bottom platform cavity, which is located underneath the turbine endwall between two adjacent blades of gas turbines. A new test rig has been designed, ... -
Quantification of Combustion Inhomogeneity Based on Sparsely Arranged Thermocouples at the Outlet of Multistage Turbines
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. The localized temperature anomalies induced by combustion, manifested as circumferential or radial temperature inhomogeneity, are detrimental to the performance and reliability of the turbine cascades. Temperature ... -
Loss Characteristics of Cantilevered Cascade With Moving Endwall Under Upstream Wake Influence
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. In multistage small-core compressors, the inflow conditions of cantilevered cascades exhibit considerable complexity. It is characterized by a larger ratio of tip clearance size to chord length and a larger ratio ... -
Investigation on the Blade Leading-Edge Film Cooling With Normal and Staggered-Oblique Impinging Jets
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Film cooling is widely employed to protect the external wall of the turbine blade leading edge from hot gas exposure, while impingement cooling is a common internal cooling technique. This article experimentally ... -
Adiabatic Effectiveness Measurements of Film Cooling in Supersonic Flow
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. High-temperature, high supersonic Mach number flows can be encountered in different innovative propulsion system configurations such as rotating detonation combustors (RDCs) and scramjets, requiring the use of ... -
Effect of Purge–Mainstream Density Ratio on the Secondary Flow Field of a Turbine Blade Row
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Gas turbine secondary air systems enable elevated turbine entry temperatures for increased cycle efficiency and work output. To prevent the ingress of hot mainstream gas into the turbine cavity, purge flow is ... -
Heat Transfer Enhancement in Variable Aspect Ratio Serpentine Passages With Hemispherical Dimples
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. The current study focuses on the effect of acceleration and deceleration in a two-pass channel with hemispherical dimples. Acceleration is achieved by reducing the aspect ratio of the serpentine passages from 4:1 ... -
Comparisons of Measured Blade Temperatures With Predictions Using Available Correlations
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. As turbine inlet temperatures have steadily increased over several decades, turbine blade designs have transformed to accommodate higher gas path temperatures through the addition of internal convective cooling, ... -
A Novel Cooling Design and Improvement of a Radial-Inflow Turbine Rotor Blade
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. With the continuous increase in turbine inlet temperature, traditional uncooled radial-inflow turbines are becoming inadequate for operation in higher-temperature environments. This study investigates both the ... -
Predicting Endwall Corner Separation in Compressor Cascades Using RANS: Influence of Transition Treatment and Inflow Conditions
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Corner separations are a complex physical phenomenon that significantly affects the off-design operation of axial compressors, contributing to instability and limiting their operating range. At the same time, ... -
Numerical Design of Experiments for Repeating Low-Pressure Turbine Stages Part II: Effect of Reynolds Number on Different Blade Geometries
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. The complex transitional and turbulent nature of unsteady flows seen in low-pressure turbines (LPTs) often demands high-order methods such as large eddy simulations (LES) for accurate predictions of turbine ... -
Numerical Design of Experiments for Repeating Low-Pressure Turbine Stages Part I: Computational Opportunities and Methodology
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. The complex transitional and turbulent nature of unsteady flows seen in low-pressure turbines often demands high-order methods such as large eddy simulations (LES) for accurate predictions of turbine efficiency ... -
Consolidating Data for Boundary Layer Transition Onset Under the Influence of Freestream Turbulence and Pressure Gradients
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. Laminar-turbulent transition in boundary layers is important to turbomachinery flows. Accurate prediction of the boundary layer state is necessary when calculating entropy generation and heat transfer rates on ... -
On the Mechanism of Unsteady Tip Flow Occurrence in a Transonic Fan
(The American Society of Mechanical Engineers (ASME), 2026)Abstract. The tip clearance flow, closely related to stable margin and efficiency, influences the performance of the fan/compressor in aeroengines. The unsteady tip flow in a high-speed transonic fan rotor is studied by ...