Experimental Analysis of Combustion in Gas Turbine

2019 ◽  
Author(s):  
M. S. N. Murthy ◽  
Subhash Kumar ◽  
Sheshadri Sreedhara
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Experimental Analysis ◽  
Air Flow ◽  
Measuring System ◽  
Maximum Pressure ◽  
Gear Pump ◽  
Air Flow Rate ◽  
Gas Turbine Combustor ◽  
Turbine Engine

Abstract This paper presents the methodology and results of an experimental analysis of combustion in a gas turbine combustor. The experimental setup is designed to imitate the conditions of a working gas turbine engine (GT), using an actual gas turbine combustor. Air is supplied by a heavy-duty air compressor at a maximum pressure of 7 bar to the combustor through an air pipe catering to the developing length. The air flow rate is measured using an ASME standard Venturimeter along with a manometer. The air flow rate and pressure are controlled by a combination of air outlet valve placed before developing length and by a throttle orifice in the exhaust duct at combustor outlet. Diesel fuel used in the experiments is provided at required atomizing pressure by a gear pump. Mass flow rate and pressure of fuel is controlled by combination of valves and varying the speed of gear pump using a variable speed electric motor. Combustion is initiated in a conventional pilot ignition unit using a spark plug and fuel burner. Fuel flow rate is measured accurately using a unique catch and time measuring system at the inlet of the gear pump.

scholarly journals AUTOMATION CONTROL SYSTEM OF TECHNICAL CONDITION OF GAS TURBINE ENGINE COMPRESSOR

2019 ◽  
pp. 121-128
Author(s):  
Микола Сергійович Кулик ◽  
Володимир Вікторович Козлов ◽  
Лариса Георгіївна Волянська
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Static Pressure ◽  
Air Flow ◽  
Gas Turbine Engine ◽  
Technical Condition ◽  
Operating Conditions ◽  
Air Flow Rate ◽  
Turbine Engine ◽  
Flow Duct

The article is devoted to one of the approaches to the construction of an automated system for solving the problems of diagnostics and monitoring of the flow duct of aircraft gas turbine engines and gas turbine plants. Timely detection of faults and subsequent monitoring of their development in operation are possible thanks to automated systems for assessing the technical condition of engines. This is particularly relevant in operating conditions as the knowledge of the technical condition of the engine is necessary in any engine maintenance system allows  to choose the content and timing of maintenance, repair of the flow duct of gas turbine engines and gas turbine plants, as well as commissioning. The engineering technique, which can be applied at performance of maintenance and at stages of tests and debugging of aircraft engines, is considered. The automated system implements a method of measuring the air flow through the compressor and a technique for assessing the technical condition of the compressor by the relative change in air flow. To determine the air flow rate through the gas turbine engine, it is sufficient to measure only static pressure values in the flow part. The static pressure receivers are not located in the flow part and do not obscure it, and thus do not affect the compressor gas dynamic stability margin. The inspection area is selected for measuring in the flow duct of the air intake. Static pressure in the maximum and minimum cross sections of the chosen area is measured; the maximum cross-section area of the flow duct, the total temperature of the air flow is measured outside the air intake.  To determine the air flow rate, the functional dependence of the air flow rate on the static pressure is used. The algorithm for monitoring and diagnosing the operating condition of the engine is based on a comparison of the actual values of air flow rate with the air flow rate determined during the control tests or when using a mathematical model adapted for this gas turbine engine. The positive effect of the using of the proposed automated control system of technical condition is that the air flow rate measured under operating conditions will significantly increase the objectivity of the control of the operation and technical condition of the gas turbine engine.

The Influence of Film Cooling on Emissions for a Low NOx Radial Swirler Gas Turbine Combustor

2001 ◽  
Author(s):  
G. E. Andrews ◽  
M. N. Kim
Keyword(s):  
Mach Number ◽  
Gas Turbine ◽  
Flow Rate ◽  
Film Cooling ◽  
Equivalence Ratio ◽  
Air Flow ◽  
Gas Turbine Combustor ◽  
Cooling Flow ◽  
Full Coverage ◽  
Primary Zone

An experimental investigation was undertaken of the influence on emissions of full coverage discrete hole film cooling of a lean low NOx radial swirler natural gas combustor. The combustor used radial swirler vane passage fuel injection on the centre of the vane passage inlet. The test configuration was similar to that used in the Alstom Power Tornado and related family of low NOx gas turbines. The test conditions were simulated at atmospheric pressure at the flow condition of lean low NOx gas turbine primary zones. The tests were carried out at an isothermal flow Mach number of 0.03, which represents 60% of industrial gas turbine combustor airflow through the swirl primary zone. The effusion film cooling used was Rolls-Royce Transply, which has efficient internal cooling of the wall as well as full coverage discrete hole film cooling. Film cooling levels of 0, 16 and 40% of the primary zone airflow were investigated for a fixed total primary zone air flow and reference Mach number of 0.03. The results showed that there was a major increase in the NOx emissions for 740K inlet temperature and 0.45 overall equivalence ratio from 6ppm at zero film cooling air flow to 32ppm at 40% coolant flow rate. CO emissions increased from 25ppm to 75ppm for the same increase in film cooling flow rate. It was shown that the main effect was the creation of a richer inner swirler combustion with a surrounding film cooling flow that did not mix well with the central swirling combustion. The increase in NOx and CO could be predicted on the basis of the central swirl flow equivalence ratio.

Modeling of Variable Inlet Guide Vanes Affects on a One Shaft Industrial Gas Turbine Used in a Combined Cycle Application

2008 ◽  
Author(s):  
Cesar Celis ◽  
Paula de M. Ribeiro Pinto ◽  
Rafael S. Barbosa ◽  
Sandro B. Ferreira
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Air Flow ◽  
Combined Cycle ◽  
Variable Geometry ◽  
Correction Factors ◽  
Air Flow Rate ◽  
Design Point ◽  
Inlet Guide Vanes ◽  
Industrial Gas Turbine

It is well known that gas turbine simulation involves satisfying the conditions of compatibility between its components. At design point, the components are all well matched and working at high efficiency regions. However, at steady state off-design, due to the compatibility issues and changes in operating parameters, basically turbine entry temperature and pressure ratio to attain a certain load, it is possible that the components may be working within regions of low efficiency. A reason for this phenomenon is that the flow areas at the various sections of the engine correspond to that at design point, such that operation at off-design is restricted. One way to widen the operational envelope of an engine is varying these flow areas, providing a good match between the gas turbine components. A widely used type of variable geometry which has attracted a great amount of interest is the use of compressor variable geometry, the so called variable inlet guide vanes (VIGVs), as a power control strategy, which involves the control of the air flow rate entering the compressor and the power output modulation at constant rotational speed. The purpose of the air flow rate modulation is to enhance the heat recovery performance and thus increase the combined cycle efficiency by maintaining high turbine exhaust temperature. One methodology used to model a variable geometry compressor, in the absence of its geometric data involves the use of correction factors, as functions of the VIGV change. Fundamentally, this methodology assumes that each new position of the VIGVs represents a new machine, i.e., a new design point, such that its original map of characteristics is displaced in order to describe this “new” compressor. The purpose of this work is to analyze the influence of the use of different functions for these correction factors on a W501F (one shaft, industrial) gas turbine simulation. An in-house computer program developed for performance modeling of gas turbines was utilized to carry out the simulations. The results provided by this computer code show good agreement with operational data, indicating that, although more tests must be conducted, the methodology seems to be reliable enough for the aims of the project for which it has been developed.

Design of a Gas Turbine Based Air Start Unit for Larger Aircraft Engine

2004 ◽  
Author(s):  
Li-Chieh Hsu ◽  
Wu-Chi Ho ◽  
Chien-Ching Hsueh
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Flow Rate ◽  
Centrifugal Compressor ◽  
Aircraft Engine ◽  
Aircraft Engines ◽  
Air Flow Rate ◽  
Turbine Engine ◽  
Engine Control System ◽  
Compact Design

A novel Air Start Unit powered by gas turbine engine is developed. The feature of this unit is that it can start various aircraft engines, including the hundred thousand pound thrust class engine like GE90, with different air flow rate in a compact design. This paper introduces the complete design and development of large centrifugal compressor, digital engine control system, testing of gas turbine system.

scholarly journals Aerodynamic improvement of an aircraft gas-turbine engine fan

2021 ◽  
Vol 2021 (3) ◽  
pp. 23-29
Author(s):  
Yu.A. Kvasha ◽  
◽  
N.A. Zinevych ◽  
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Turbine Engines ◽  
Gas Flows ◽  
Gas Turbine Engines ◽  
Air Flow Rate ◽  
Profile Angle ◽  
Turbine Engine ◽  
Blade Height ◽  
Second Stage

This work is concerned with the development of approaches to the aerodynamic improvement of axial-flow compressors for gas-turbine engines. The aim of this work is the aerodynamic improvement of an aircraft gas-turbine engine two-stage fan by numerical simulation of 3D turbulent gas flows. The approach used in this study features: varying the spatial shape of the fan blades for the first- and the second-stage impeller by varying the profile angle along the blade height; formulating quality criteria as the mean integral values of the power characteristics of each impeller of the fan over the operating range of the air flow rate through the impeller; and searching for advisable values of the impeller blade parameters by scanning the independent variable range at points that form a uniformly distributed sequence of small length. The basic tool is a numerical method developed at the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine, which simulates 3D turbulent gas flows using the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. It is shown that varying the profile angle along the blade height for the fan second-stage impeller allows one to increase the air compression ratio in the fan by about 2 percent throughout the operating range of the fan air flow rate without affecting the adiabatic efficiency of the fan. On the whole, by the example of the fan under study, the paper considers the assumption that the aerodynamic improvement of compressors at the initial stage can be made on an impeller by impeller basis. It is shown that in further analysis providing the gas-dynamic stability of the compressor should be accounted for. The results obtained are intended to be used in the aerodynamic improvement of multistage compressors for aircraft gas-turbine engines and various power plant.

Performance Analysis of a Reheat Cycle Gas Turbine Based on Measured Data

2007 ◽  
Author(s):  
Soo Hyoung Yoon ◽  
Dae Hwan Jeong ◽  
Jong Joon Lee ◽  
Tong Seop Kim
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Flow Rate ◽  
Air Flow ◽  
Combined Cycle ◽  
Inlet Guide Vane ◽  
Air Flow Rate ◽  
Operating Condition ◽  
Estimated Parameters ◽  
Condition Change

This study evaluated component characteristics of the reheat cycle gas turbine in a combined cycle power plant. High pressure ratio, sequential combustion, large amount of cooling flow and full utilization of the inlet guide vane distinguishes the engine from simple cycle engines. Considering the detailed engine configuration, performance analysis using an inverse calculation, based on measured performance data, has been carried out to estimate the component characteristic parameters that closely match the measured performance parameters. The measured parameters are power, fuel flow rates of two combustors, and temperatures and pressures at compressor discharge, exits of both high and low pressure turbines. The estimated parameters from the analysis include not only the compressor and turbine efficiencies but also the inlet air flow rate. The analysis has been performed for a wide operation range in terms of ambient temperature and load. Not only the absolute value of the inlet air flow rate but also its variation with the operating condition change correspond very well with the reference data from the manufacturer. The compressor and turbine efficiencies at each full load condition and their variations with the operating condition change were examined. The sensitivity of the estimated parameters to the uncertainties of the measured parameters has also been investigated.

scholarly journals Reduction of air flow rate for pulse-detonation-turbine-engine operation by water-droplet injection

2016 ◽  
Vol 11 (2) ◽  
pp. JTST0022-JTST0022 ◽  
Author(s):  
Takuma ENDO ◽  
Keiji MASUDA ◽  
Wataru WATANABE ◽  
Takuya MUKAI ◽  
Hiroki NAGAI ◽  
...  
Keyword(s):  
Flow Rate ◽  
Water Droplet ◽  
Air Flow ◽  
Air Flow Rate ◽  
Engine Operation ◽  
Turbine Engine ◽  
Pulse Detonation
Sign in / Sign up

Export Citation Format

Share Document