Relevant bibliographies by topics / Swirl expansion turbomachine

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Conference papers

Academic literature on the topic 'Swirl expansion turbomachine'

Author: Grafiati
Published: 28 May 2022
Last updated: 31 July 2025

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Journal articles on the topic "Swirl expansion turbomachine"

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Seng Wong, Choon, and Susan Krumdieck. "Scaling of Gas Turbine From Air to Refrigerants for Organic Rankine Cycle Using Similarity Concept." Journal of Engineering for Gas Turbines and Power 138, no. 6 (2015). http://dx.doi.org/10.1115/1.4031641.

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Similitude, or similarity concept, is an essential concept in turbomachinery to allow the designer to scale a turbine design to different sizes or different working fluids without repeating the whole design and development process. Similarity concept allows the testing of a turbomachine in a simple air test bench instead of a full-scale organic Rankine cycle (ORC) test bench. The concept can be further applied to adapt an existing gas turbine as an ORC turbine using different working fluids. This paper aims to scale an industrial gas turbine to different working fluids, other than the fluid th
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Dissertations / Theses on the topic "Swirl expansion turbomachine"

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Смоленко, Д. В. "Розробка та дослідження турбогенератора для власних потреб газорозподільних станцій на базі вихрової розширювальної турбомашини". Master's thesis, Сумський державний університет, 2018. http://essuir.sumdu.edu.ua/handle/123456789/72123.

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У роботі розроблено та досліджено турбогенератор для власних потреб газорозподільних станцій на базі вихрової розширювальної турбомашини.<br>В работе разработаны и исследованы турбогенератор для собственных нужд газораспределительных станций на базе вихревой расширительной турбомашины.<br>Turbogenerator for own needs of gas distribution stations on the basis of a vortex expansion turbomachine was developed and investigated.
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Conference papers on the topic "Swirl expansion turbomachine"

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Zhang, Liang, Xin Xue, Qian Yang, Huiru Wang, and Jibao Li. "Experiment Study of Pilot Stage Swirler Outlet Angles and Swirl Number on Flame Structures and Flow Field in a Stratified Swirl Combustor." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-83221.

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Abstract The stratified swirl combustor is generally used in an advanced aero-engine, in order to achieve a low emission and wide stabilization at the same time. The complex interactions between the pilot stage and main stage can determine the flame structure, flow field, further affecting the emission formation and stabilization. The present study investigates the interaction between pilot flame and flow field of a stratified swirl combustor, by varying the outlet angles and swirl numbers of the pilot stage swirler. Flame structures and flow fields are obtained while only the pilot stage work
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Kong, Xiaozhi, Gaowen Liu, Yuxin Liu, and Qing Feng. "Investigation on the Leakage Flow, Windage Heating and Swirl Development of Rotating Labyrinth Seal in a Compressor Stator Well." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56740.

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What make the labyrinth seal in a compressor stator well different from the normal labyrinth seal are the inlet and outlet rotor-stator disc cavities. Due to the presence of rotating disc cavities, the windage heating and the swirl development are remarkable, which can have a great influence on the leakage characteristic. Besides, when compressor operates at different speeds, the rotor and stator grow differently owing to centrifugal expansion and thermal expansion. Hence the tip clearance which determines the leakage mass flow changes with the varying of rotational speed and temperature in th
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Andreini, Antonio, Riccardo Becchi, Bruno Facchini, et al. "Experimental and Numerical Investigation of the Mutual Interaction Between Liner Film Cooling and Combustor Swirl Flow." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63460.

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In the continuous demand of increasing cooling efficiency for novel combustor liners, it is necessary to have a comprehensive understanding of the interaction of hot gases with coolant flows. The aim of the present study is the experimental characterization of the flow field and the measurement of liner heat transfer coefficient in a combustion chamber model equipped with an axial swirler and a liner slot cooling scheme. The test rig geometry consists in a linear three sector chamber fed by an open loop blower. The system is operated at isothermal conditions. A highly swirled main stream flow
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Notaristefano, Andrea, and Paolo Gaetani. "The Role of Turbine Operating Conditions on Combustor-Turbine Interaction – Part 1: Change in Expansion Ratio." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-81707.

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Abstract Aeroengine lean-burn combustors release vorticity and temperature perturbations that, interacting with the first turbine stage, impact the stage aerodynamics, the blade cooling and noise production. The first of these issues is addressed in this paper that is part 1 of a two-fold contribution. A detailed experimental analysis is carried out to study the impact on the combustor-turbine interaction of the off-design conditions experienced by aero-engines in their duty. Engine-representative disturbances are generated by a combustor simulator able to produce swirling entropy waves. Two i
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Jella, Sandeep, Gilles Bourque, Jeffrey Bergthorson, Wing Yin Kwong, and Adam Steinberg. "RANS and LES Modeling of a Linear-Array Swirl Burner Using a Flamelet-Progress Variable Approach." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-75896.

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Multiple, interacting flames in DLE systems can increase flame surface area and promote mixing of hot-products into the reactants — leading to an efficient usage of combustion volume and improved injector performance. An optically-accessible, confined, linear array of five swirl nozzles was recently built [1] to investigate flame dynamics and validate computational strategies. The present work focuses on modeling a dataset representative of lean gas turbine conditions, using a flamelet approach. A preheated (500K), premixed fuel-air mixture (ϕ = 0.55, Tflame = 1732K) at atmospheric pressure wa
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Prieur, Kevin, Daniel Durox, Guillaume Vignat, Thierry Schuller, and Sébastien Candel. "Flame and Spray Dynamics During the Light-Round Process in an Annular System Equipped With Multiple Swirl Spray Injectors." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76840.

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The ignition process of an annular combustor can be divided in several steps that end with the light-round. This corresponds to the sequence from the ignition of the first injector to the merging of the two flame fronts spreading in the annular system. The present article focuses on this important step, where two arch-like flame branches propagate in the chamber. These two turbulent travelling flames, nearly perpendicular to the combustor backplane, successively ignite the injection units and finally collide head-on and merge. In the present study, light-round of spray flames fed by liquid n-h
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Wilkes, Jason, Abhay Patil, and Jon Bygrave. "Pulsations and Vibrations in the Discharge Piping of a Throttled Supercritical CO2 Turbine." In ASME Turbo Expo 2024: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2024. http://dx.doi.org/10.1115/gt2024-128951.

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Abstract Choke nozzles present an economical option to control the expander downstream conditions in high-pressure, high-temperature supercritical CO2 loops; however, the expansion and high fluid momentum exiting the choke may induce instability, causing pulsating behavior and vibration of the loop due to fluid-structure interaction. The current study investigates the performance of a conventional choke design utilizing CFD simulations to provide detailed insight into jet behavior and interaction with the wall. The analysis uses constant boundary conditions and doesn’t account for any flow ins
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Notaristefano, Andrea, and Paolo Gaetani. "The Role of Turbine Operating Conditions on Combustor-Turbine Interaction – Part 2: Loading Effects." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-82256.

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Abstract Aeroengine combustors burn a lean and premixed blend releasing vorticity and temperature perturbations. Interacting with the first turbine stage, these disturbances impact the cascade aerodynamics, add criticality to the blade cooling and are sources of noise. The first of these issues is addressed in this paper, focusing on off-design turbine conditions, as experienced by aero-engines in their duty. This paper, part II of a two-fold contribution, analyses the effect of the stage loading obtained by changing the RPM (three different values) at the same expansion ratio of 1.4, represen
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Wein, Lars, Tim Kluge, Joerg R. Seume, et al. "Validation of RANS Turbulence Models for Labyrinth Seal Flows by Means of Particle Image Velocimetry." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14885.

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Abstract Accurate prediction of labyrinth seal flows is important for the design and optimisation of turbomachinery. However, the prediction of such flows with RANS turbulence models is still lacking. The identification of modelling deficits and the development of improved turbulence models requires detailed experimental data. Consequently, a new test rig for straight labyrinth seals was built at the Institute for Turbomachinery and Fluid Dynamics which allows for non-intrusive measurements of the three dimensional velocity field in the cavities. Two linear eddy viscosity models and one algebr
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Moëll, Daniel, Daniel Lörstad, and Xue-Song Bai. "LES of Hydrogen Enriched Methane/Air Combustion in the SGT-800 Burner at Real Engine Conditions." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76434.

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DLE (Dry Low Emission) techniques are widely used today to reduce the harmful NOx emissions associated with high combustion temperatures. In many DLE systems the fuel and air are pre-mixed which effectively keep the flame temperature as low as possible, ideally equal to the turbine inlet temperature. By using pre-mixing stability issues such as flash back and combustion driven dynamics may occur. Operating the engine with hydrogen diluted natural gas will decrease the flash back limits of the system due to the high diffusivity and highly reactive nature of hydrogen. In this study the stability
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