bluuebunny/crossref_metadata_2025_split huggingface dataset:
Platform Film Cooling Investigation on an HP Nozzle Vane Cascade With Discrete Shaped Holes and Slot Film Cooling
Authors: Barigozzi G. , Perdichizzi A. , Abba L. , Pestelli L. 
Published: January 2021

Abstract
The present paper reports on an experimental investigation on the aerodynamic and heat transfer performance of different platform cooling schemes: two based on cylindrical and shaped holes and one featuring a slot located upstream of the leading edge plane simulating the combustor to stator interface gap. Tests were run on a 6-vane cascade operated at an isentropic cascade exit Mach number of 0.4 and a significant inlet turbulence intensity level of about 9%. The cooling schemes were first tested to quantify their impact on secondary flows and related losses for variable injection conditions. Heat transfer performance was then assessed through adiabatic film cooling effectiveness and heat transfer coefficient measurements. The Net Heat Flux Reduction parameter was then computed to critically assess the cooling schemes. When compared with the cylindrical hole scheme, shaped holes outperform for all tested injection rates, while the slot alone is able to thermally protect only the front of the passage. Discrete holes are required to cool the platform region along the whole pressure side and the suction side leading edge region.
A Marine Turbocharger Retrofitting Platform
Authors: Ntonas Konstantinos , Aretakis Nikolaos , Roumeliotis Ioannis , Mathioudakis Konstantinos 
Published: January 2021

Abstract
A turbocharger retrofitting platform utilizing 1D models for calculating turbomachinery components maps and a fully coupled process for integration with the turbomachinery components and the diesel engine, is presented. The platform has been developed with two modes of operation, allowing the retrofitting process to become fully automatic. In the first mode, available turbo-components are examined, in order to select the one that best matches the entire engine system, aiming to retain or improve the diesel engine efficiency. In the second mode, an optimization procedure is employed, in order to redesign the compressor to match the entire system in an optimum way. Dimensionless parameters are used as optimization variables, for a given compressor mass flow and power.
A retrofitting case study is presented, where three retrofitting options are analyzed (compressor retrofit, turbocharger retrofit and compressor redesign). In the first and second option, turbocharger retrofitting is carried out, using available turbo-components. It is shown that initial performance cannot be reconstituted using off-the-self solutions. In the third option, compressor designing is performed, using the optimization mode, in order to provide an improved retrofitting solution, aiming to at least reconstituting the original diesel engine performance. Finally, a CFD analysis is carried out, in order to validate the compressor optimization tool capability to capture the performance trends, based on geometry variation.
Study of Heat Transfer Characteristics of a Single Jet Impinging on a Conical Surface
Authors: Su Bo , Xu Wei-jiang , Li Zhi-ping , Zhou Tian-liang , Lu Fei 
Published: January 2021

Abstract
In this paper, the heat transfer performance of single jet impinging conical surface is investigated based on transient liquid crystal experiments. Because of different target surface structures, impingement heat transfer will have different heat transfer characteristics. In order to better understand the heat transfer mechanism of the impinging conical target surface, this paper studies the three jet Reynolds number (Re) ranged from 25000 to 70000, three the dimensionless nozzle-to-surface distance (H/D) from 0.75 to 6 on heat transfer characteristics. The liquid crystal thermal imaging technology is used in the experiment to obtain the heat transfer efficiency of jet heat transfer on the conical target surface. The research in this paper shows that the larger the jet Reynolds number, the larger the Nusselt number at the stagnation point. It is worth noting that the maximum Nusselt number is not necessarily obtained at the stagnation point. When Re = 70000 and H/D = 0.75, the maximum value of the Nusselt number is 1.24 times the stagnation point. The larger the Reynolds number, the smaller the impingement distance, and the more obvious the secondary maxima. At the same impingement distance, when the Reynolds number is larger, the position of the secondary maxima appears earlier. When Re = 25000, H/D = 3.5, 6 and Re = 45000, H/D = 6, the local Nusselt number monotonously decreases from the maximum value at the stagnation point along the flow, and it appears secondary maxima in other experimental conditions. Within the scope of this study, the overall heat transfer performance is better when the dimensionless distance between the jet hole and the target surface is 3.5.
High-Fidelity Simulations of Multi-Jet Impingement Cooling Flows
Authors: Otero-Pérez J. Javier , Sandberg Richard D. , Mizukami Satoshi , Tanimoto Koichi 
Published: January 2021

Abstract
This article shows the first parametric study on turbulent multi-jet impingement cooling flows using large-eddy simulations (LES). We focus on assessing the influence of the inter-jet distance and the cross-flow conditions on the heat transfer at the impingement wall. The LES setup is thoroughly validated with both experimental and direct numerical simulation data, showing an excellent agreement. The inter-jet distance effect on the heat transfer is studied comparing three different distances, where the full Nusselt number profile decreases in amplitude when the jet distance is increased. To evaluate the cross-flow effects, we prescribe both laminar and turbulent inflow conditions at different cross-flow magnitudes ranging between 20% and 40% of the impinging jet speed. Large cross-flow intensities cause a jet deflection which reduces the maxima in the Nusselt number distribution, and it increases the heat transfer in the areas of the wall less affected by the jet impingement. Adding realistic turbulent fluctuations to the inflow enhances the cross-flow effects on the heat transfer at the impingement wall.
Development of the Functional-Gradient Turbine Wheel With Cooled Blades Without Lock Connection
Authors: Magerramova Liubov , Volkov Michael , Salnikov Anton , Kratt Eugene 
Published: January 2021

Abstract
Wheels of high-temperature turbines are traditionally produced in the form of detachable joints of the disk and blades made from different materials.
The blades, which are under the influence of high gas temperatures, are made with internal channels by air cooling. The disk is subject to significant centrifugal loads, but lower temperatures. The locking connection of the blades to the disk is a stress concentrator, which leads to resource limitation.
One of the solutions is the wheel of the turbine type blisk consisting of cast-cooled blades of heat-resistant alloys and a disk of granulated nickel alloys, interconnected by hot isostatic pressing.
The disk can be made of granules of different sizes in different parts. This approach is based on the fact that during operation, the disk is also subject to uneven heating and loading along the radius.
The blisk design of the wheel with cooled blades is developed on the basis of the turbine wheel with a detachable connection of the blades with the disk. The blades of the blisk are produced from casting heat-resistant nickel alloy. The disk portion is created from granulated alloy with different grain sizes along the disk radius. The system of supplying cooling air in the blades of the wheel is developed. The technology of manufacturing a disk consisting of granules of various sizes and technology of connection of a disk with cooled cast blades is developed.
To determine the mechanical characteristics of the zones of connection of dissimilar materials samples were tested. The combined samples were made of a granulated alloy with different sizes of granules. The bimetallic samples were made of a casting blade alloy and a granulated disk alloy.
Multi-parameter optimization of the blisk was carried out. The mass of the designed wheel was reduced by more than 40% compared to the original wheel with lock connection when the strength and service life conditions were satisfied.
Recuperator Transient Simulation for Supercritical Carbon Dioxide Cycle in CSP Applications
Authors: Thanganadar Dhinesh , Fornarelli Francesco , Camporeale Sergio , Asfand Faisal , Patchigolla Kumar 
Published: January 2021

Abstract
Supercritical carbon dioxide (sCO2) cycles are considered to provide a faster response to load change owing to their compact footprint. sCO2 cycles are generally highly recuperative, therefore the response time is mainly dictated by the heat exchanger characteristics. This study model the transient behaviour of a recuperator in 10 MWe simple recuperative Brayton cycle. The response for the variation of inlet temperature and mass flow boundary conditions were investigated using two approaches based on temperature and enthalpy. The performance of these two approaches are compared and the numerical schemes were discussed along with the challenges encountered. The simulation results were validated against the experimental data available in the literature with a fair agreement. The characteristic time of the heat exchanger for a step change of the boundary conditions is reported that supports the recuperator design process. Compact recuperator responded in less than 20 seconds for the changes in the temperature boundary condition whilst it can take upto 1.5 minutes for mass flow change. In order to reduce the computational effort, a logarithmic indexed lookup table approach is presented, reducing the simulation time by a factor of 20.
Experimental Study of the Endwall Heat Transfer of a Transonic Nozzle Guide Vane With Upstream Jet Purge Cooling: Part 2 — Effect of Combustor-NGV Misalignment
Authors: Sibold Ridge A. , Mao Shuo , Ng Wing F. , Xu Hongzhou , Fox Michael 
Published: January 2021

Abstract
A misalignment between the combustor exit and the nozzle guide vane (NGV) platform commonly exists due to manufacturing tolerances and thermal transience. This study experimentally investigated the effect of the combustor-turbine misalignment on the heat transfer for an axisymmetric converging endwall with a jet purge cooling scheme at transonic conditions. Tests were conducted at engine-representative freestream exit Mach number of 0.85, inlet turbulence intensity of 16%, film cooling blowing ratio of 2.5 (design condition) and 3.5, and density ratio of 1.95. Three different step misalignments, combustor exit 4.9% span higher than turbine inlet (backward-facing), no step (baseline), and combustor exit 4.9% span lower than turbine inlet (forward-facing), were tested to demonstrate the misalignment effect on endwall Nusselt number, adiabatic film cooling effectiveness, and net heat flux reduction. A supportive numerical simulation was conducted to provide insight into the flow field.
Experimental and numerical results indicated a blowing ratio of 2.5 amid a backward-facing step leads to more turbulent mixing between the coolant and mainstream due to the horseshoe vortex and step-induced cavity vortex, reducing coolant coverage and adversely affecting coolant performance. For the same blowing ratio, a forward-facing step induced more lift-off and shifted the coverage downstream and toward the pressure side, ultimately slightly enhancing the cooling performance. Nevertheless, the forward-facing step leads to a large cooling effectiveness gradient in the pitch-wise direction. At a blowing ratio of 3.5, the baseline no-step case provided superior coolant performance, however, the effect of the step was much less significant as compared to the lower blowing case. The forward-facing step amid a blowing ratio of 3.5 results in severe jet lift-off, diminishing the returns traditionally associated with increasing coolant mass flow. Based on this study, a backward-facing step should be avoided to prevent endwall burnout in the nozzle guide. Additionally, a forward-facing step should be avoided, especially amid high blowing ratios.
Detailed Study of Front Module for Low-Emission Combustor
Authors: Vasilyev A. , Zakharov V. , Chelebyan O. , Zubkova O. 
Published: January 2021

Abstract
At the ASME Turbo Expo 2018 conference held in Oslo (Norway) on the 11th-15th of June 2018, the paper GT2018-75419 «Experience of Low-Emission Combustion of Aviation and Bio Fuels in Individual Flames after Front Mini-Modules of a Combustion Chamber» was published. This paper continues the studies devoted to the low-emission combustion of liquid fuels in GTE combustors. The paper presents a description of more detailed studies of the front module with a staged pneumatic fuel spray. The aerodynamic computations of the front module were conducted, and the disperse characteristics of the fuel-air spray were measured. The experimental research was carried out in two directions: 1) probing of the 3-burner sector flame tube at the distance of one third of its length (temperature field and gas sampling); 2) numerical study of the model combustor with actual arrangement of the modules in the dome within a wide range of fuel-air ratio. The calculated and experimental data of velocity field behind the front module were compared. And new data about the flame structure inside the test sector were obtained. Experimental data confirm the results of preliminary studies of the 3-burner sector: combustion efficiency is higher than 99.8%, EiNOx is at the level of 2–3 g/fuel kg at the combustor inlet air temperature of 680K and fuel-air ratio of 0.0225.
The conducted research allowed to receive additional information on the influence of some design units on the pollutant emission and to estimate the different elements of computational methods for simulation of a low-emission combustor with a multi-atomizer dome.
Investigation of Rotordynamic Coefficients of Gas Labyrinth Seals Using a Steady State CFD Approach
Authors: Palanca Casey , Engeda Abraham , Cave Mike 
Published: January 2021

Abstract
Labyrinth seals were one of the first seal configurations used in modern turbomachinery and continue to be one of the most frequently used clearance seal configurations today. Their primary purpose is to control internal leakage between the rotating and stationary components of centrifugal compressors. However, when fulfilling this objective, labyrinth seals have been shown to be a potential source of instability within the rotor-stator system. Driving forces inside the leakage flow path of the cavities often induce destabilizing vibrations on the rotor. The forces are characterized by stiffness and damping coefficients which describe the stability behavior of the seal. Therefore, accurately predicting these rotordynamic coefficients remains an important area of interest in gas compressor design. This paper reviews the status of current methods of obtaining rotordynamic coefficients. The objective of this work is to verify the accuracy of current steady state CFD models used to predict rotordynamic coefficients in dry gas labyrinth seals. For this purpose, a full 3D eccentric CFD model is conducted for three different labyrinth seal geometries. In this approach, the rotordynamic coefficients are predicted from the regression of the radial and tangential impedances as a function of whirl frequencies. For comparison, two seals are compared with experimental data available in literature, and a third seal is compared to bulk flow and numerical CFD results also found in the literature. Furthermore, the influence of pre-swirl entering the labyrinth seal and turbulence modeling are also considered in this work.
Research on the Periodicity of Flow Field in a Compressor Sector Cascade
Authors: Xu Wenfeng , Sun Peng , Yang Guogang 
Published: January 2021

Abstract
Sector cascade experiments can not only be convenient to measure various aerodynamic parameters but also reveal the real flow characteristics in turbomachinery. However, the sector cascade is only a part of the whole annular cascade. The circumferential angle, the structure of the side guide plate (SGP) and the suction mode on the SGP have a great effect on the periodicity of the flow field. Therefore, the effect of structure on periodicity must be taken into consideration in order to obtain accurate data of the sector cascade experiment. In this paper, a compressor sector cascade composed of a row of adjustable guide vanes (AGVs) and a row of stators is designed. The effect of the circumferential angle, SGP structure and suction position on the periodicity is studied by numerical simulation. An optimal cascade scheme is selected for experimental research. The results show that a larger circumferential angle can weaken the effect of low-energy fluid near the SGP on the middle passages. However, given the limited experimental conditions, the circumferential angle is set at 110° which consists of 15 AGVs and 14 stators. What’s more, the SGP with the same bowed angle of AGV on both sides of the cascade can reduce the influence of the SGP on the adjacent passages and obtain a regular periodicity. The low-energy fluids still accumulate near the SGP. The suction near the stator suction side of the SGP can alleviate the blockage in the flow passage and further improve the periodicity of the cascade. Serious analysis of the experiment results have further identified that the suction near the stator suction side of SGP can make the aerodynamic parameters of the flow field uniform and lead to a good periodicity. At the same time, the feasibility of this design method is verified.
Experimental and Numerical Rotordynamic Analysis of a 1500 KW Turbocharger
Authors: Zamanian Yazdi Behzad , Tran Dung L. , Deshpande Chinmay 
Published: January 2021

Abstract
Hydraulic turbochargers are used in sea water reverse osmosis or acid gas removal cycles to recover wasted pressure energy, decrease operating cost, and increase the overall process efficiency. This paper presents rotordynamic analysis of a large hydraulic turbocharger developed for the acid gas removal process (1500 KW output power, shaft diameter of 101 mm, and operating speed of 8,000 rpm). The hydraulic turbocharger has significant advantages when compared to a reverse running pump such as high speed, compact hydraulics, seal-less design and process lubricated bearings. Utilizing a hydraulic turbocharger in acid gas removal cycles results in a much smaller footprint and no external lubrication oil skid and support system for mechanical seals. The turbocharger rotor consists of a hydraulic turbine runner directly coupled to a pump impeller in a back-to-back arrangement. The shaft is supported in the middle by a set of rigid-walled process-lubricated journal bearings resulting in an overhung configuration (bearing span = 180 mm, rotor mass = 50 kg). For a large high-speed rotor-bearing system, the bearing load-carrying capacity and rotordynamic stability are crucial to ensure a stable performance and to avoid catastrophic failure.
In the presented study, rotordynamic performance of a rotor-bearing system is evaluated analytically and experimentally. An analytical model is developed to simulate the rotordynamic performance of a shaft supported by a set of journal bearings. The analytical model simulates the rotor’s orbit in the time domain by solving the rotor’s equation of motion, and solving the transient Reynold equation for each bearing simultaneously. In addition, the model considers the effect of turbulence. An in-house test loop is developed and used to evaluate the turbocharger’s hydraulic and mechanical performance. The test loop runs on a LabView-based control system. The rotor vibration is measured by a set of eddy-current probes, oriented perpendicular to each other. The simulation results from the analytical model are compared against measured experimental data. Comparison of the simulated waterfall and bode plots with experimental data shows that the simulation results agree with the measured data for the frequency and amplitude of vibration. Moreover, the effect of turbulence on the rotordynamic performance of the hydraulic turbocharger is investigated, and it is shown that the turbulence significantly changes the rotordynamic behavior of the system.
A Statistical Study on HCF Validation Data for Axial Gas Turbine Compressor Blades
Authors: Schuchard Lukas C. , Cerutti Stefano , Voigt Matthias , Mailach Ronald 
Published: January 2021

Abstract
An enhanced process to Ansaldo Energia Switzerland’s validation approach for vibrational behaviour of gas turbine compressor blading is investigated. The opportunity of relying on less and early-stage measurements is assessed as a driver for cost and time optimisation. Accordingly, an analysis of possible variations of measurement data available during all validation phases is performed in order to confirm observed and expected correlations on a large scale, facilitating measurement chain improvement and simplification.
Profile deviation and frequency distribution analysis finds the present coordinate-measuring machine (CMM) data and statically measured eigenfrequencies to be normally distributed. Correlation analysis exposes strong autocorrelations of CMM and static frequency data and distinct linear correlations between them. Consistent correlations with and within rotating machinery cannot be established with the limited data basis at hand as clamping conditions of blades with hammer foot roots introduce an additional degree of variation.
CMM data are employed for meta-models translating geometry deviations into static-test-alike frequency information. Average aerofoil thickness deviation is identified as the decisive parameter for eigenfrequency uncertainties founded in geometry deviations.
A stage statistics based approach for frequency forecasting in rotating machinery is proposed, allowing the calculation of expected eigenfrequency bands with corresponding confidence levels. Brought up to operational levels it would allow more efficient forecasting of in-engine conditions and constitute a valuable means for exploring compressor blading design space.