scholarly journals Study on the Improvement of Turning Technology for Ring Groove of Flame Tube of Heavy Gas Turbine

2018 ◽  
Author(s):  
LI-LI ZHAO ◽  
NING-JIA YANG
Keyword(s):  
Gas Turbine ◽  
Ring Groove ◽  
Flame Tube ◽  
Heavy Gas

scholarly journals Hybrid Data-Driven and Physics-Based Modeling for Gas Turbine Prescriptive Analytics

2020 ◽  
Vol 5 (4) ◽  
pp. 29
Author(s):  
Sergei Belov ◽  
Sergei Nikolaev ◽  
Ighor Uzhinsky
Keyword(s):  
Gas Turbine ◽  
Data Driven ◽  
Machine Learning Techniques ◽  
Flame Tube ◽  
Learning Techniques ◽  
Prescriptive Analytics ◽  
Hybrid Data ◽  
Data Driven Modeling ◽  
Engine Power

This paper presents a methodology for predictive and prescriptive analytics of a gas turbine. The methodology is based on a combination of physics-based and data-driven modeling using machine learning techniques. Combining these approaches results in a set of reliable, fast, and continuously updating models for prescriptive analytics. The methodology is demonstrated with a case study of a jet-engine power plant preventive maintenance and diagnosis of its flame tube. The developed approach allows not just to analyze and predict some problems in the combustion chamber, but also to identify a particular flame tube to be repaired or replaced and plan maintenance actions in advance.

scholarly journals Erratum to: Investigation of the Flow Mixing behind the Flame Tube Head of a Combustion Chamber in a Gas Turbine Engine

2019 ◽  
Vol 62 (3) ◽  
pp. 528-528
Author(s):  
A. I. Sulaiman ◽  
B. G. Mingazov ◽  
Yu. B. Aleksandrov ◽  
T. D. Nguyen
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Flame Tube ◽  
Flow Mixing ◽  
Flame Tube Head

Analytical Comparison of Structures of Heavy Gas Turbine Rotor’s Support

2010 ◽  
Vol 139-141 ◽  
pp. 1032-1035
Author(s):  
Wen Lei Sun ◽  
Yan Biao Zhang ◽  
Jian Guo
Keyword(s):  
Gas Turbine ◽  
Ultimate Load ◽  
Dynamic Characterization ◽  
Working Mechanism ◽  
Sliding Bearing ◽  
Analytical Comparison ◽  
Ansys Cfx ◽  
Shaft Power ◽  
Heavy Gas ◽  
The Stability

This paper aims at the structures of heavy gas turbine rotor’s support, the analyze method of fluid-solid couple and that of thermal-solid couple is adopted to simulate by ANSYS CFX, by compared with the deformation of the different structures of their support, it sums up that the tangential support is the best structure. Furthermore, the deformation of the tangential support under different conditions is analyzed, such as the different temperature of gas and the ultimate load of shaft, that supports the research of the working mechanism of the sliding bearing and the dynamic characterization, and finally the research achievements are expanded to apply the study of the stability of shaft power, providing a basis for the study and development of the future’s gas turbine technology.

scholarly journals Optical Characterization of a Multipoint Lean Direct Injector for Gas Turbine Combustors: Velocity and Fuel Drop Size Measurements

2010 ◽  
Author(s):  
Christopher M. Heath ◽  
Yolanda R. Hicks ◽  
Robert C. Anderson ◽  
Randy J. Locke
Keyword(s):  
Gas Turbine ◽  
Drop Size ◽  
Fuel Injection ◽  
Direct Injection ◽  
Operating Conditions ◽  
Diagnostic Methods ◽  
Spray Angle ◽  
Fuel Injector ◽  
Flame Tube ◽  
Component Velocity

Performance of a multipoint, lean direct injection (MP-LDI) strategy for low emission aero-propulsion systems has been tested in a Jet-A fueled, lean flame tube combustion rig. Operating conditions for the series of tests included inlet air temperatures between 672 K and 828 K, pressures between 1034 kPa and 1379 kPa and total equivalence ratios between 0.41 and 0.45, resulting in equilibrium flame temperatures approaching 1800 K. Ranges of operation were selected to represent the spectrum of subsonic and supersonic flight conditions projected for the next-generation of commercial aircraft. This document reports laser-based measurements of in situ fuel velocities and fuel drop sizes for the NASA 9-point LDI hardware arranged in a 3 × 3 square grid configuration. Data obtained represent a region of the flame tube combustor with optical access that extends 38.1-mm downstream of the fuel injection site. All data were obtained within reacting flows, without particle seeding. Two diagnostic methods were employed to evaluate the resulting flow path. Three-component velocity fields have been captured using phase Doppler interferometry (PDI), and two-component velocity distributions using planar particle image velocimetry (PIV). Data from these techniques have also offered insight into fuel drop size and distribution, fuel injector spray angle and pattern, turbulence intensity, degree of vaporization and extent of reaction. This research serves to characterize operation of the baseline NASA 9-point LDI strategy for potential use in future gas-turbine combustor applications. An additional motive is the compilation of a comprehensive database to facilitate understanding of combustor fuel injector aerodynamics and fuel vaporization processes, which in turn may be used to validate computational fluid dynamics codes, such as the National Combustor Code (NCC), among others.

Evaluation of a New Design Concept for a Ceramic Flame Tube Under Engine Conditions

1996 ◽  
Author(s):  
S. Münz ◽  
A. Schulz ◽  
S. Wittig
Keyword(s):  
Gas Turbine ◽  
Thermal Load ◽  
Operating Conditions ◽  
Design Concept ◽  
Experimental Investigations ◽  
Test Bed ◽  
Test Rig ◽  
Ceramic Structure ◽  
Flame Tube ◽  
Design Concepts

At the Institut für Thermische Strömungsmaschinen in Karlsruhe new design concepts for thermally high-loaded ceramic gas turbine components were developed. The present concept is based on a load-oriented segmentation in combination with a flexible suspension and thermal insulation of the ceramic structure. The concept was applied to a flame tube for a small gas turbine. In order to ensure real operating conditions, a Klöckner Humboldt Deutz T216 type gas turbine was used as test bed for the ceramic combustor. The paper gives a description of the combustor and the test rig. Furthermore, experimental results of the engine tests with special emphasis on the liner wall temperature distribution for various steady and transient operating conditions are presented. A major result of the tests is that the design concept proved to be reliable under real engine conditions. After more than 100 hours no failure of the ceramic parts occured. In order to determine the thermal load of the ceramic flame tube under real conditions, the experimental investigations are supported by numerical calculations.

Optimization of Flow Matching Schemes for a Heavy Gas Turbine Burning Syngas

2020 ◽  
Vol 29 (5) ◽  
pp. 1292-1299
Author(s):  
Lei Guo ◽  
Guoqing Li ◽  
Chunyan Hu ◽  
Zhijun Lei ◽  
Enliang Huang ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Heavy Gas ◽  
Matching Schemes

Preliminary Gas Turbine Combustor Design Using a Network Approach

1997 ◽  
Vol 119 (3) ◽  
pp. 546-552 ◽  
Author(s):  
P. J. Stuttaford ◽  
P. A. Rubini
Keyword(s):  
Gas Turbine ◽  
Reverse Flow ◽  
Design Tool ◽  
Transfer Model ◽  
Network Approach ◽  
Gas Turbine Combustor ◽  
Flame Tube ◽  
Drop Flow ◽  
Combustion Processes ◽  
Semi Empirical

The preliminary design process of a gas turbine combustor often involves the use of cumbersome, geometry restrictive semi-empirical models. The objective of this analysis is the development of a versatile design tool for gas turbine combustors, able to model all conceivable combustor types. A network approach is developed that divides the flow into a number of independent semi-empirical subflows. A pressure-correction methodology solves the continuity equation and a pressure-drop/flow rate relationship. The development of a full conjugate heat transfer model allows the calculation of flame tube heat loss in the presence of cooling films, annulus heat addition, and flame tube feature heat pick-up. A constrained equilibrium calculation, incorporating mixing and recirculation models, simulates combustion processes. Comparison of airflow results to a well-validated combustor design code showed close agreement. The versatility of the network solver is illustrated with comparisons to experimental data from a reverse flow combustor.

The Use of Perforated Damping Liners in Aero Gas Turbine Combustion Systems

2011 ◽  
Author(s):  
Jochen Rupp ◽  
Jon Carrotte ◽  
Michael Macquisten
Keyword(s):  
Pressure Drop ◽  
Flow Field ◽  
Gas Turbine ◽  
Analytical Model ◽  
Operating Conditions ◽  
Acoustic Energy ◽  
Fuel Injector ◽  
Flame Tube ◽  
Gas Turbine Combustion ◽  
Combustion Systems

This paper considers the use of perforated porous liners for the absorption of acoustic energy within aero style gas turbine combustion systems. The overall combustion system pressure drop means that the porous liner (or ‘damping skin’) is typically combined with a metering skin. This enables most of the mean pressure drop, across the flame tube, to occur across the metering skin with the porous liner being exposed to a much smaller pressure drop. In this way porous liners can potentially be designed to provide significant levels of acoustic damping, but other requirements (e.g. cooling, available space envelope etc) must also be considered as part of this design process. A passive damper assembly was incorporated within an experimental isothermal facility that simulated an aero-engine style flame tube geometry. The damper was therefore exposed to the complex flow field present within an engine environment (e.g. swirling efflux from a fuel injector, coolant film passing across the damper surface etc.). In addition, plane acoustic waves were generated using loudspeakers so that the flow field was subjected to unsteady pressure fluctuations. This enabled the performance of the damper, in terms of its ability to absorb acoustic energy, to be evaluated. To complement the experimental investigation a simplified 1D analytical model was also developed and validated against the experimental results. In this way not only was the performance of the acoustic damper evaluated, but also the fundamental processes responsible for this measured performance could be identified. Furthermore the validated analytical model also enabled a wide range of damping geometry to be assessed for a range of operating conditions. In this way damper geometry can be optimized (e.g. for a given space envelope) whilst the onset of non-linear absorption (and hence the potential to ingest hot gas) can also be identified.

Influence of plasma-chemical products on process stability in a low-emission gas turbine combustion chamber

2021 ◽  
Vol 0 (0) ◽  
Author(s):  
Serhiy Serbin ◽  
Artem Kozlovskyi ◽  
Kateryna Burunsuz
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Fuel Combustion ◽  
Gaseous Fuel ◽  
Plasma Chemical ◽  
Flame Tube ◽  
Low Emission ◽  
Gas Turbine Combustion ◽  
The Stability ◽  
The Impact

Abstract The article describes the stability of gaseous fuel combustion in gas turbine low-emission combustion chambers with the plasma-chemical assistance. The mathematical model of unsteady processes in a low-emission combustion chamber with a plasma-chemical stabilizer that takes into consideration the impact of low-temperature plasma on aerodynamics flow in a combustion chamber and the characteristics of heat release is developed. A methodology of a numerical experiment concerning the stability of gaseous fuel combustion in a combustion chamber with plasma assistance using computational fluid dynamics, which enhances the efficiency of designing and adjustment, is proposed. Practical recommendations for improvement of stability of a gas turbine combustion chamber with partially premixed lean fuel–air mixtures, working on gaseous fuels, are developed. They allow to reduce pressure fluctuations inside the flame tube by 10–35%, to decrease spectral power of static pressure in the flame tube in 1.5–2.0 times, to reduce nitrogen oxide emission up to 33.6 ppm in the exit section while retaining a carbon monoxide emission level, that corresponds modern international ecological standards.

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