Performance of Inlet Filtration System in Relation to the Uncaptured Particles Causing Fouling in the Gas Turbine Compressor

2015 ◽  
Vol 138 (1) ◽  
Author(s):  
Uyioghosa Igie ◽  
Domenico Amoia ◽  
Georgios Michailidis ◽  
Orlando Minervino
Keyword(s):  
Gas Turbine ◽  
Pressure Loss ◽  
Simulation Software ◽  
Differential Pressure ◽  
Capture Efficiency ◽  
Lower Power ◽  
Pressure Losses ◽  
Power Setting ◽  
Low Efficiency ◽  
The Impact

Accounting for the impact of uncaptured particles that cause compressor fouling and subsequently performance degradation when a filter system is in place is often ignored when evaluating the performance of filtration systems. Too often, the emphasis is on capture efficiency and the corresponding differential pressure loss, which are important aspects, however only constitutes a part of the overall impact on the engine performance. The main aim of this study is a first step to quantify the loss that is attributed to compressor fouling by the uncaptured particles, identify a threshold point for which further increase in pressure losses (increasing capture efficiency) no longer yields further increases in fouling levels, and subsequently investigate these respective losses and total losses in a reference high efficiency system (HES) and a hypothetical low efficiency system. Corrected operational data from a 268 MW gas turbine engine were used to evaluate the levels of degradation in the engine at different power settings. With the measured filter media pressure loss during operation and turbomatch (an in-house gas turbine performance simulation software), the impact of power reduction due to pressure loss of the filter was accounted for in the total estimated losses due to engine degradation. That of fouling was calculated based on applicable assumptions, while deducting the loss due to filtration systems from the total loss due to degradation. The study shows the inverse relationship between fouling effects and filter pressure losses as expected. More importantly, it indicates that the higher efficiency system performs better than the low efficiency system, notwithstanding the more dominant impact of higher differential pressure losses. It was also observed that the threshold where fouling effects are zero or negligible is around 800 Pa at high power setting and 600 Pa at lower power setting. In general, for all forms of the degradation using the engine data and simulation software, it is observed that at lower power settings, the impact on the engine is a lot more severe in a single-shaft constant speed operation.

Advanced Modeling of Fluid Thermodynamic Properties for Gas Turbine Performance Simulation

2008 ◽  
Author(s):  
Vishal Sethi ◽  
Fulvio Diara ◽  
Sina Atabak ◽  
Anthony Jackson ◽  
Arjun Bala ◽  
...  
Keyword(s):  
Thermodynamic Properties ◽  
Gas Turbine ◽  
Fluid Model ◽  
Simulation Software ◽  
Working Fluid ◽  
Performance Simulation ◽  
Turbine Performance ◽  
Fluid Properties ◽  
Convergence Problems ◽  
The Impact

This paper describes the structure of an advanced fluid thermodynamic model which has been developed for a novel advanced gas turbine simulation environment called PROOSIS. PROOSIS (PRopulsion Object Oriented SImulation Software) is part of the VIVACE-ECP (Value Improvement through a Virtual Aeronautical Collaborative Enterprise - European Cycle Programme) project. The main objective of the paper is to determine a way to achieve an accurate, robust and reliable fluid model. The results obtained demonstrate that accurate modeling of the working fluid is essential to avoid convergence problems of the thermodynamic functions thereby increasing the accuracy of calculated fluid properties. Additionally, the impact of accurately modeling fuel thermodynamic properties, at the point of the injection, is discussed.

Perforated Plate Pressure Losses With Improved Inlet and Outlet Flow Hole Features

2003 ◽  
Author(s):  
Kirkland D. Broach ◽  
Michael E. Conner ◽  
Jeffery L. Norrell ◽  
Carter E. Lunde
Keyword(s):  
Pressure Drop ◽  
Pressure Loss ◽  
Perforated Plate ◽  
Small Scale ◽  
Factors Affecting ◽  
Pressure Losses ◽  
Outlet Hole ◽  
Outlet Flow ◽  
Hole Geometry ◽  
The Impact

This paper describes the tests and studies performed to better understand the geometric factors affecting pressure loss in a perforated plate. In this study, the impact of a specific perforated plate flow hole geometry on pressure drop was investigated. The methodology established in this paper to investigate this hole geometry can be extended to other components with orifice type perforated plates. To reduce the pressure drop of the perforated plate, various fundamental hole geometries, including edge chamfers and edge radii, were considered. Results from various edge treatments are provided in this study, including separate effects for inlet and outlet hole geometries. Specific trends, such as the effect of increasing edge geometries on the hydraulic losses, are presented. Additionally, a correlation between small-scale and full-scale pressure loss coefficients was found and is defined.

scholarly journals Gas turbine outlets: test results

2020 ◽  
Vol 4 (394) ◽  
pp. 121-128
Author(s):  
Nikolay N. Ponomarev
Keyword(s):  
Experimental Study ◽  
Gas Turbine ◽  
Pressure Loss ◽  
Total Pressure ◽  
Mutual Influence ◽  
Engineering Calculation ◽  
Total Pressure Loss ◽  
Flow Section ◽  
Pressure Losses ◽  
Flow Parameters

Object and purpose of research. The object of this work is gas turbine outlet consisting of axial-radial diffuser with the struts and the volute. The purpose is to create a methodology for engineering calculations, taking into account the mutual influence of the diffuser and the volute. Materials and methods. Experimental study of the flow in the models of outlets by measuring total and static pressure in characteristic sections. Calculation of integral and averaged flow parameters in measurement sections. Visualization of boundary flows. Based on the experimental results, development of regression models for the correction factors to be applied in the theoretical model, with selection of relevant factors. Main results. An experimental study of 23 variants of models with a total volume of 112 experimental points (modes) was carried out. On the basis of the experiment, methodology and program for engineering calculation of total pressure losses in the outlets were developed. It was found that the installation of guide blades and radial ribs in the diffuser in order to reduce local expansion angles with the ultimate purpose of mitigating total pressure losses actually does not lead to this result due to the because the flow in the diffuser becomes asymmetric due to its interaction with the volute. Visualization of boundary flows in the diffusers and the volutes has been performed, which makes it possible to identify the locations of separations causing increased pressure losses. Conclusion. An engineering method for calculating the total pressure loss in gas turbine outlet has been developed. The technique makes it possible, taking size restrictions into account, to select the geometry of the flow section that ensures minimum total pressure loss.

Effects of Air Induct Structure to Flow Uniformity and Resistance for Primary Surface Recuperator of a Micro Gas Turbine

2010 ◽  
Author(s):  
Wei Qu ◽  
Shan Gao
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Loss ◽  
Air Flow ◽  
Flow Distribution ◽  
Structure Design ◽  
Flow Uniformity ◽  
Local Pressure ◽  
Pressure Losses ◽  
Micro Gas Turbine

Primary surface recuperator is important for micro gas turbines, the flow distribution and pressure loss are sensitive to the induct structure design significantly. The air induct structure for one recuperator is modelled and simulated. Several flow fields and pressure losses are obtained for different designs of air induct structure. The air induct structure can affect the flow uniformity, further influence the pressure loss a lot. For several changes of air induct structure, the non-distribution of air flow can be decreased from 67% to 13%, and the pressure loss can be decreased to 50% of the original. Considering the recuperator design and the gas turbine, one optimized structure is recommended, which has less local pressure loss and better flow distribution.

Thermo-Fluid Modelling for Gas Turbines—Part I: Theoretical Foundation and Uncertainty Analysis

2009 ◽  
Author(s):  
Konstantinos G. Kyprianidis ◽  
Vishal Sethi ◽  
Stephen O. T. Ogaji ◽  
Pericles Pilidis ◽  
Riti Singh ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Simulation Software ◽  
System Level ◽  
Fluid Models ◽  
Performance Simulation ◽  
Turbine Performance ◽  
Aircraft System ◽  
The Impact ◽  
Made In

In this two-part publication, various aspects of thermo-fluid modelling for gas turbines are described and their impact on performance calculations and emissions predictions at aircraft system level is assessed. Accurate and reliable fluid modelling is essential for any gas turbine performance simulation software as it provides a robust foundation for building advanced multi-disciplinary modelling capabilities. Caloric properties for generic and semi-generic gas turbine performance simulation codes can be calculated at various levels of fidelity; selection of the fidelity level is dependent upon the objectives of the simulation and execution time constraints. However, rigorous fluid modelling may not necessarily improve performance simulation accuracy unless all modelling assumptions and sources of uncertainty are aligned to the same level. Certain modelling aspects such as the introduction of chemical kinetics, and dissociation effects, may reduce computational speed and this is of significant importance for radical space exploration and novel propulsion cycle assessment. This paper describes and compares fluid models, based on different levels of fidelity, which have been developed for an industry standard gas turbine performance simulation code and an environmental assessment tool for novel propulsion cycles. The latter comprises the following modules: engine performance, aircraft performance, emissions prediction, and environmental impact. The work presented aims to fill the current literature gap by: (i) investigating the common assumptions made in thermo-fluid modelling for gas turbines and their effect on caloric properties and (ii) assessing the impact of uncertainties on performance calculations and emissions predictions at aircraft system level. In Part I of this two-part publication, a comprehensive analysis of thermo-fluid modelling for gas turbines is presented and the fluid models developed are discussed in detail. Common technical models, used for calculating caloric properties, are compared while typical assumptions made in fluid modelling, and the uncertainties induced, are examined. Several analyses, which demonstrate the effects of composition, temperature and pressure on caloric properties of working mediums for gas turbines, are presented. The working mediums examined include dry air and combustion products for various fuels and H/C ratios. The errors induced by ignoring dissociation effects are also discussed.

Evaluating Gas Turbine Performance Using Machine-Generated Data: Quantifying Degradation and Impacts of Compressor Washing

2016 ◽  
Vol 138 (12) ◽  
Author(s):  
Uyioghosa Igie ◽  
Pablo Diez-Gonzalez ◽  
Antoine Giraud ◽  
Orlando Minervino
Keyword(s):  
Gas Turbine ◽  
Measurement Data ◽  
Engine Performance ◽  
Large Data ◽  
Simulation Software ◽  
Engine Operation ◽  
Compressor Inlet ◽  
Data Points ◽  
Global And Local ◽  
The Impact

Gas turbine (GT) operators are often met with the challenge of utilizing and making meaning of the vast measurement data collected from machine sensors during operation. This can easily be about 576 × 106 data points of gas path measurements for one machine in a base load operation in a year, if the width of the data is 20 columns of measured and calculated parameters. This study focuses on the utilization of large data in the context of quantifying the degradation that is mostly related to compressor fouling, in addition to investigations on the impact of offline and online compressor washing. To achieve this, four GT engines operating for about 3.5 years with 51 offline washes and 1184 occasions of online washes were examined. This investigation includes different wash frequencies, liquid concentrations, and one engine operation without online washing (only offline). This study has involved correcting measurement data not only just with compressor inlet temperatures (CITs) and pressures but also with relative humidity (RH). turbomatch, an in-house GT performance simulation software has been implemented to obtain nondimensional factors for the corrections. All of the data visualization and analysis have been conducted using tableau analytics software, which facilitates the investigation of global and local events within an operation. The concept of using of handles and filters is proposed in this study, and it demonstrates the level of insight to the data and forms the basis of the outcomes obtained. This work shows that during operation, the engine performance is mostly deteriorating, though to varying degrees. Online washing also showed an influence on this, reducing the average degradation rate each hour by half, when compared to the engine operating only with offline washing. Hourly marginal improvements were also observed with an increased average wash frequency of nine hours and a similar outcome obtained when the washing solution is 2.3 times more concentrated. Clear benefits of offline washes are also presented, alongside the typically obtainable values of increased power output after a wash, also in relation to the number of operating hours before a wash.

Research of Single Cavity Exhaust Muffler Based on AML and CFD Method

2014 ◽  
Vol 926-930 ◽  
pp. 3179-3182
Author(s):  
Huai Hui Du ◽  
Yu Hong Long ◽  
Jun Liang Liu ◽  
Wen Shang Li ◽  
Jie Cai
Keyword(s):  
Pressure Loss ◽  
Transmission Loss ◽  
Simulation Software ◽  
Fluid Simulation ◽  
Local Pressure ◽  
Acoustic Simulation ◽  
Virtual Lab ◽  
Cfd Method ◽  
The Impact ◽  
Single Cavity

Two mufflers of single exhaust muffler and double exhaust muffler were researched based on the method of AML technology of acoustic simulation software LMS Virtual lab and got transmission loss graph of the two mufflers, indicating that the single exhaust muffler had better effect of noise reduction. Then the fluid simulation was carried out on two mufflers and velocity and pressure cloud maps were draw based on the method of computational fluid dynamics in FLUENT. It is pointed out that the double exhaust muffler is slightly greater than the single exhaust muffler on pressure loss, this is because the airflow in single exhaust muffler is mainly jet flow and the pressure loss is mainly local pressure loss, while the airflow of double exhaust muffler is mainly rotary flow and the pressure loss is mainly frictional pressure loss. The impact that the airflow has on the cavity of the double exhaust muffler is higher.

scholarly journals Development of a Regenerator for an Automotive Gas Turbine Engine

1992 ◽  
Author(s):  
Junichi Sayama ◽  
Teru Morishita
Keyword(s):  
Velocity Distribution ◽  
Gas Turbine ◽  
Pressure Loss ◽  
Prediction Method ◽  
Gas Turbine Engine ◽  
Core Size ◽  
Turbine Engine ◽  
Pressure Losses ◽  
The Core ◽  
Core Matrix

It is vital to accurately estimate the temperature effectiveness and pressure loss of the regenerator when designing a gas turbine engine because these characteristics basically determine the size, weight, and fuel consumption of the regenerative gas turbine engine. In operation of an actual engine, regenerators often fail to attain the characteristics predicted by conventional methods, because there are many performance-reducing irregularities such as the non-uniform velocity distribution of gases flowing into the core. In this paper, a prediction method that is based on data from actual engine tests is examined as a way to predict regenerator temperature effectiveness and pressure losses when there are causes for deterioration of these characteristics. This method resulted in a system, taking the deterioration of these characteristics into consideration as they occur in an actual engine, that represents temperature effectiveness and pressure loss as the function of core specifications such as the core size and the core matrix. This prediction method was then used to predict the regenerator characteristics of actual engines with more than satisfactory results (The accuracy is ±1.25% for temperature effectiveness and ±4% for pressure loss).

Detection and Localization of Fouling in a Gas Turbine Compressor From Aerothermodynamic Measurements

2004 ◽  
Author(s):  
Knox T. Millsaps ◽  
Jon Baker ◽  
Jeffrey S. Patterson
Keyword(s):  
Gas Turbine ◽  
Mass Flow ◽  
Total Pressure ◽  
Axial Flow ◽  
Pressure Losses ◽  
Sensitive Parameter ◽  
Influence Coefficients ◽  
Gas Turbine Compressor ◽  
Detection And Localization ◽  
The Impact

This paper presents a new method for condition assessment of axial flow compressors that provides a tool for specifying the magnitude and location of degradation due to fouling. A simple, meanline, stage-stacking analysis is developed, which includes the impact of blade roughness on the mass flow, work coefficient, and efficiency. The performance of a baseline, three-stage compressor with hydrodynamically smooth blades is calculated. Using the baseline geometry, the influence of roughness of the blade surfaces in the front, middle and rear stages are calculated. Empirical data for the increased total pressure losses and greater turning deviation that occurs due to rough blades are used. This analysis indicates that airfoil fouling in different stages, produce characteristic aerothermodynamic signatures, and hence the faults can be localized by the magnitudes of the various influence coefficients. This analysis also predicts that the most sensitive parameter for predicting fouling in the front stages is the percentage change in mass flow and the most sensitive parameter for predicting fouling in the rear stages is the adiabatic efficiency.

Gas Turbine Degradation in the Techno-Economic Environmental and Risk Analysis of Flare Gas Utilization in Nigeria

2013 ◽  
Author(s):  
Isaiah Allison ◽  
Kenneth Ramsden ◽  
Pericles Pilidis ◽  
Agbadede Roupa
Keyword(s):  
Gas Turbine ◽  
Energy Gap ◽  
Simulation Software ◽  
Offshore Platforms ◽  
Gas Utilization ◽  
Niger Delta Region ◽  
Wide Energy ◽  
Design Calculations ◽  
Installed Capacity ◽  
The Impact

There is a wide energy gap in Nigeria: electricity generation meets only about 30% of the required 10000MW; and only about 40% of the installed capacity has been achieved. The Niger Delta region of Nigeria is dominated by oil exploration activities with a conglomeration of flow stations and onshore/offshore platforms that flare gases. This work explores the utilization of flare gas in a gas turbine for electricity, and addresses the impact of flare gas on the turbine hot end components. TurboMatch simulation software is used for design and off-design calculations, while investigating optimistic, slow, medium and fast degradation scenarios.

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