Impact of pressure drop in combustion chamber on gas turbine performance

2020 ◽  
Vol 2 (3) ◽  
pp. 131-138
Author(s):  
Jerzy Herdzik
Keyword(s):  
Pressure Drop ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Thermodynamic Cycle ◽  
Turbine Performance ◽  
Lack Of Information ◽  
Working Medium ◽  
Before And After ◽  
Characteristic Points ◽  
Flow Through

Paper discusses the problem of pressure drop in the process of working medium flow through combustion chamber of gas turbine. The pressure loss is an internal disadvantage of combustion chamber depends on many parameters, especially the chamber design and working gas flowrate. There is a problem to calculate the parameters of working medium in characteristic points of gas turbine thermodynamic cycle because the total pressure before and after combustion chamber is not known. There is a lack of information from manufacturer about it and in publications as well (mainly no experimental data, only theoretical considerations). It will be important information because the pressure drop has an meaningful influence on gas turbine performance. The paper presents an estimation of decreasing the performance of gas turbine from discussed reason. Author of that manuscript recognized the necessity of showing the importance of that parameter and turning the attention to not fully recognized problem.

Effect of Divergence Angle on Flow Through Inlet Section of Diffuser of a Gas Turbine Combustion Chamber: The CFD Approach

2006 ◽  
Author(s):  
Digvijay B. Kulshreshtha ◽  
S. A. Channiwala ◽  
Jitendra Chaudhary ◽  
Zoeb Lakdawala ◽  
Hitesh Solanki ◽  
...  
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Total Pressure ◽  
Divergence Angle ◽  
Velocity Head ◽  
Turbine Engine ◽  
Inlet Velocity ◽  
Pressure Losses ◽  
Flow Through ◽  
Mach Numbers

In the combustor inlet diffuser section of gas turbine engine, high-velocity air from compressor flows into the diffuser, where a considerable portion of the inlet velocity head PT3 − PS3 is converted to static pressure (PS) before the airflow enters the combustor. Modern high through-flow turbine engine compressors are highly loaded and usually have high inlet Mach numbers. With high compressor exit Mach numbers, the velocity head at the compressor exit station may be as high as 10% of the total pressure. The function of the diffuser is to recover a large proportion of this energy. Otherwise, the resulting higher total pressure loss would result in a significantly higher level of engine specific fuel consumption. The diffuser performance must also be sensitive to inlet velocity profiles and geometrical variations of the combustor relative to the location of the pre-diffuser exit flow path. Low diffuser pressure losses with high Mach numbers are more rapidly achieved with increasing length. However, diffuser length must be short to minimize engine length and weight. A good diffuser design should have a well considered balance between the confliction requirements for low pressure losses and short engine lengths. The present paper describes the effect of divergence angle on diffuser performance for gas turbine combustion chamber using Computational Fluid Dynamic Approach. The flow through the diffuser is numerically solved for divergence angles ranging from 5 to 25°. The flow separation and formation of wake regions are studied.

Experimental Investigations of Pressure Drop in the Combustion Chamber of Gas Turbine

1989 ◽  
Author(s):  
Marek Dzida ◽  
Krzysztof Kosowski
Keyword(s):  
Pressure Drop ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Conditions ◽  
Experimental Results ◽  
Experimental Investigations ◽  
Relative Pressure ◽  
Wide Range ◽  
Few Data

In bibliography we can find many methods of determining pressure drop in the combustion chambers of gas turbines, but there is only very few data of experimental results. This article presents the experimental investigations of pressure drop in the combustion chamber over a wide range of part-load performances (from minimal power up to take-off power). Our research was carried out on an aircraft gas turbine of small output. The experimental results have proved that relative pressure drop changes with respect to fuel flow over the whole range of operating conditions. The results were then compared with theoretical methods.

Hydrogen Combustion Within a Gas Turbine Reheat Combustor

2012 ◽  
Author(s):  
Madhavan Poyyapakkam ◽  
John Wood ◽  
Steven Mayers ◽  
Andrea Ciani ◽  
Felix Guethe ◽  
...  
Keyword(s):  
Pressure Drop ◽  
Natural Gas ◽  
Gas Turbine ◽  
Dynamic Properties ◽  
Fluid Dynamic ◽  
Fold Increase ◽  
Inlet Temperature ◽  
Turbine Performance ◽  
Auto Ignition ◽  
Operating Window

This paper describes a novel lean premixed reheat burner technology suitable for Hydrogen-rich fuels. The inlet temperature for such a combustor is very high and reaction of the fuel/oxidant mixture is initiated through auto-ignition, the delay time for which reduces significantly for Hydrogen-rich fuels in comparison to natural gases. Therefore the residence time available for premixing within the burner is reduced. The new reheat burner concept has been optimized to allow rapid fuel/oxidant mixing, to have a high flashback margin and to limit the pressure drop penalty. The performance of the burner is described, initially in terms of its fluid dynamic properties and then its combustion characteristics. The latter are based upon full-scale high-pressure tests, where results are shown for two variants of the concept, one with a pressure drop comparable to today’s natural gas burners, and the other with a two-fold increase in pressure drop. Both burners indicated that Low NOx emissions, comparable to today’s natural gas burners, were feasible at reheat engine conditions (ca. 20 Bars and ca. 1000C inlet temperature). The higher pressure drop variant allowed a wider operating window. However the achievement of the lower pressure drop burner shows that the targeted Hydrogen-rich fuel (70/30 H2/N2 by volume) can be used within a reheat combustor without any penalty on gas turbine performance.

scholarly journals Effect of a regenerator on hybrid solar gas turbine performance in Barranquilla, Colombia

2021 ◽  
Vol 2139 (1) ◽  
pp. 012012
Author(s):  
F Moreno-Gamboa ◽  
J C Acevedo-Paéz ◽  
D Sanin-Villa
Keyword(s):  
Solar Radiation ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Plant Performance ◽  
Maximum Temperature ◽  
Experimental Plant ◽  
Power Cycle ◽  
Turbine Performance ◽  
Central Receiver ◽  
Solar Plant

Abstract A thermodynamic analysis of a hybrid gas turbine solar plant, represented in three basic subsystems related to the power cycle, the combustion chamber subsystem, and the solar concentrator subsystem, allows evaluating the performance of a hybrid cycle from a reduced number of parameters, which include energy losses in each of its components. The solar radiation values are estimated with an evaluated and validated theoretical model, the combustion chamber uses natural gas as fuel and the numerical values of the system are taken from the Solugas experimental plant in Spain. This work presents an integrated model that allows to estimate the operation of a hybrid solar Brayton power plant in any place and day of the year. The evaluation of the plant in Barranquilla, Colombia is shown from the influence of the regenerator has on the plant performance and solar concentrating system. The results show that the regenerator can increase the overall efficiency of the plant by 29% and allows reaching a maximum temperature of the central receiver of the concentrator of 1044 K at noon, when solar radiation is maximum.

A Simple Sub-Idle Component Map Extrapolation Method

2007 ◽  
Author(s):  
Shaun R. Gaudet ◽  
J. E. Donald Gauthier
Keyword(s):  
Gas Turbine ◽  
Extrapolation Method ◽  
Test Case ◽  
Performance Models ◽  
Idle Speed ◽  
Turbine Performance ◽  
Lack Of Information ◽  
Start Up ◽  
Map Data ◽  
Component Map

This paper describes a simple sub-idle component map extrapolation method. Used in conjunction with gas turbine performance models, it enables designers to estimate sub-idle gas turbine performance during engine start-up. The lack of information available regarding component maps in the sub-idle regime creates major challenges for starting system designers or control system designers as the numerical convergence of performance models decreases rapidly below idle speed. The proposed component map extrapolation method alleviates this problem by extrapolating given component map data well below idle speed. The underlying equations of the method are based on the principles of incompressible similarity laws. Also known as pump laws, these equations are modified to account for compressibility effects by varying the similarity law exponents. To estimate the integrity of the extrapolated component maps and to build confidence in the sub-idle extrapolation method, extrapolate speed lines were compared to speed lines found in the original component map. Even though the extrapolation method is yet to be experimentally validated, preliminary estimates showed that the extrapolation method did produce adequate component maps. To demonstrate the potential of the component extrapolation method when used in conjunction with gas turbine performance models, a virtual test case engine was modeled and used to produce start-up performance data.

scholarly journals Heat Transfer Effect on Micro Gas Turbine Performance for Solar Power Applications

Energies ◽  
2021 ◽  
Vol 14 (20) ◽  
pp. 6745
Author(s):  
Mahmoud A. Khader ◽  
Mohsen Ghavami ◽  
Jafar Al-Zaili ◽  
Abdulnaser I. Sayma
Keyword(s):  
Heat Transfer ◽  
Power Systems ◽  
Gas Turbine ◽  
Computational Study ◽  
Thermodynamic Cycle ◽  
Operating Conditions ◽  
Micro Gas Turbine ◽  
Turbine Performance ◽  
Wide Range ◽  
The Cost

This paper presents an experimentally validated computational study of heat transfer within a compact recuperated Brayton cycle microturbine. Compact microturbine designs are necessary for certain applications, such as solar dish concentrated power systems, to ensure a robust rotodynamic behaviour over the wide operating envelope. This study aims at studying the heat transfer within a 6 kWe micro gas turbine to provide a better understanding of the effect of heat transfer on its components’ performance. This paper also investigates the effect of thermal losses on the gas turbine performance as a part of a solar dish micro gas turbine system and its implications on increasing the size and the cost of such system. Steady-state conjugate heat transfer analyses were performed at different speeds and expansion ratios to include a wide range of operating conditions. The analyses were extended to examine the effects of insulating the microturbine on its thermodynamic cycle efficiency and rated power output. The results show that insulating the microturbine reduces the thermal losses from the turbine side by approximately 11% without affecting the compressor’s performance. Nonetheless, the heat losses still impose a significant impact on the microturbine performance, where these losses lead to an efficiency drop of 7.1% and a net output power drop of 6.6% at the design point conditions.

Introduction and Performance Prediction of a Nutating-Disk Engine

2004 ◽  
Vol 126 (2) ◽  
pp. 294-299 ◽  
Author(s):  
T. Korakianitis ◽  
L. Meyer ◽  
M. Boruta ◽  
H. E. McCormick
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Combustion Engine ◽  
Thermodynamic Cycle ◽  
Simple Cycle ◽  
Specific Power ◽  
Engine Operation ◽  
And Performance ◽  
Stroke Engine

A new type of internal combustion engine and its thermodynamic cycle are introduced. The core of the engine is a nutating nonrotating disk, with the center of its hub mounted in the middle of a Z-shaped shaft. The two ends of the shaft rotate, while the disk nutates. The motion of the disk circumference prescribes a portion of a sphere. A portion of the area of the disk is used for intake and compression, a portion is used to seal against a center casing, and the remaining portion is used for expansion and exhaust. The compressed air is admitted to an external accumulator, and then into an external combustion chamber before it is admitted to the power side of the disk. The accumulator and combustion chamber are kept at constant pressures. The engine has a few analogies with piston-engine operation, but like a gas turbine it has dedicated spaces and devices for compression, burning, and expansion. The thermal efficiency is similar to that of comparably sized simple-cycle gas turbines and piston engines. For the same engine volume and weight, this engine produces less specific power than a simple-cycle gas turbine, but approximately twice the power of a two-stroke engine and four times the power of a four-stroke engine. The engine has advantages in the 10 kW to 200 kW power range. This paper introduces the geometry and thermodynamic model for the engine, presents typical performance curves, and discusses the relative advantages of this engine over its competitors.

Introduction and Performance Prediction of a Nutating-Disk Engine

1999 ◽  
Author(s):  
T. Korakianitis ◽  
L. Meyer ◽  
M. Boruta ◽  
H. E. McCormick
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Combustion Engine ◽  
Thermodynamic Cycle ◽  
Rotating Disk ◽  
Simple Cycle ◽  
Specific Power ◽  
Engine Operation ◽  
Stroke Engine

A new type of internal combustion engine and its thermodynamic cycle are introduced. The core of the engine is a nutating non-rotating disk, with the center of its hub mounted in the middle of a Z-shaped shaft. The two ends of the shaft rotate, while the disk nutates. The motion of the disk circumference prescribes a portion of a sphere. A portion of the area of the disk is used for intake and compression, a portion is used to seal against a center casing, and the remaining portion is used for expansion and exhaust. The compressed air is admitted to an external accumulator, and then into an external combustion chamber before it is admitted to the power side of the disk. The accumulator and combustion chamber are kept at constant pressures. The engine has a few analogies with piston-engine operation, but like a gas turbine it has dedicated spaces and devices for compression, burning and expansion. The thermal efficiency is similar to that of comparably-sized simple-cycle gas turbines and piston engines. For the same engine volume and weight, this engine produces less specific power than a simple-cycle gas turbine, but approximately twice the power of a two-stroke engine and four times the power of a four-stroke engine. The engine has advantages in the 10 kW to 200 kW power range. This paper introduces the geometry and thermodynamic model for the engine, presents typical performance curves, and discusses the relative advantages of this engine over its competitors.

Experimental study of the Effect of the Blades of Number on Characteristics Pico Bulb Turbine on Horizontal Flow

Teknik ◽  
2021 ◽  
Vol 42 (2) ◽  
pp. 236-240
Author(s):  
Dwi Aries Himawanto ◽  
Akhmad Nurdin ◽  
Hasan Bisri
Keyword(s):  
Pressure Drop ◽  
Horizontal Flow ◽  
Small Scale ◽  
Blade Angle ◽  
Turbine Performance ◽  
Dynamic Head ◽  
Piping Systems ◽  
Before And After ◽  
Water Turbines ◽  
Bulb Turbine

This study discusses the effect of the number of blades on a horizontal flow propeller turbine performance on a small scale experimentally. The development of small-scale water turbines has made many advances, including water turbines with the horizontal flow. Water turbines in horizontal flow can be applied to irrigation systems, piping systems, the wastewater treatment channel, and other closed channels. Pengukuran dynamic head pada aliran horisontal berdasarkan nilai pressure drop atau perbedaan tekanan sebelum dan sesudah turbin. Dynamic head measurement on the horizontal flow is based on pressure drop values or pressure before and after the turbine. Static bulbs placed before the turbine aim to increase the speed of water flow and potentially improve turbine performance. This study aims to determine the effect of the number of blades on the performance and efficiency of propeller turbines. The blade angle used is 200 with a bulb ratio of 0.6 to the pipe diameter. The variations in the number of blades used were 4, 5, 6, and 7, with each tested at 7 L / s, 9 L / s, 11 L / s, and 13 L / s. The results of this study indicate the number of blades 5 with a discharge of 13 L / s shows the best turbine performance compared to the number of other blades, besides that the number of blades 5 with a flow rate of 13 L / s shows the best efficiency value of around 40%.

scholarly journals ОПТИМІЗАЦІЯ КОНСТРУКЦІЇ ФАКЕЛЬНОГО ЗАПАЛЬНИКА ГТД ЧИСЕЛЬНИМ МЕТОДОМ

2020 ◽  
pp. 83-95
Author(s):  
Юрий Иванович Торба ◽  
Дмитрий Викторович Павленко ◽  
Ярослав Викторович Двирник
Keyword(s):  
Pressure Drop ◽  
Combustion Chamber ◽  
Gas Turbine ◽  
Flame Temperature ◽  
Gas Turbine Engine ◽  
Geometric Parameters ◽  
Air Pressure ◽  
Turbine Engine ◽  
Stationary Combustion ◽  
Engine Combustion

Solved the problem of gas-turbine engine combustion chamber flame igniter efficiency increasing by increasing the flame temperature via optimizing the body design. To determine the influence of the igniter body various geometric parameters, affecting the formation and combustion of the fuel-air mixture, a parametric model was developed. This model together with the developed project in the ANSYS Workbench software package made it possible to automate the modeling process. The influence of the geometric parameters of the igniter body and external factors on the average flame temperature has been studied via a numerical model of the stationary combustion process of the air-fuel mixture formed inside the igniter of the combustion chamber of a gas turbine engine by evaporation and spraying particles of aviation kerosene in the air stream. The adequacy of the numerical simulation results was confirmed by the implementation of a series of full-scale experiments using the Fisher criterion.The uniformity of temperature and adequacy of the average temperature estimation algorithm was established using the correlation analysis of the results of measured temperature at various points of the flame. To determine the degree and nature of their influence, sequentially screening (fractional), as well as full-factor experiments with varying factors at two and three levels were implemented. Based on the results of the analysis of variance, the most statistically significant factors were selected. A regression dependence was established that relates the diameter of the air inlet orifice and the air pressure drop to the flame temperature. A qualitative and quantitative assessment of the influence of the considered factors on the process of formation of a hot air mixture and its combustion has been performed. The optimal values of the geometric parameters of the igniter body and its operating conditions are determined under which the maximum flame temperature at the stationary combustion stage is ensured. Relationships between design features, igniter operation mode, and the temperature of the flame are established. This allows expanding the range of stable ignition of gas turbine engine combustion chambers in accordance with the design of the igniter, the starting fuel supply mode, and the air pressure drop.

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