Effects of Major Design and Operating Parameters on Achieving Low Emissions From Gas Turbine Combustors

1975 ◽  
Vol 97 (3) ◽  
pp. 303-309 ◽  
Author(s):  
E. P. Demetri
Keyword(s):  
Gas Turbine ◽  
Performance Testing ◽  
Air Distribution ◽  
Inlet Temperature ◽  
The Novel ◽  
Future Design ◽  
Primary Zone ◽  
Low Emission ◽  
Temperature And Pressure ◽  
And Performance

The results of a research program involving the design and performance testing of two low-emission combustors for vehicular gas turbine applications are described. The novel features of the combustor designs tested include the use of airblast fuel nozzles, a relatively high value of pressure-loss factor to promote vigorous mixing, and variable geometry to control the liner air flow distributions. Particular emphasis is placed on describing the relative effects of primary-zone equivalence ratio, combustor inlet temperature and pressure, residence time, and the uniformity of the fuel/air distribution in the primary zone. Guidelines for the future design of low-emission combustors based on the observed effects are also presented. The major conclusion reached is that essentially conventional combustor configurations have the capability of achieving the specified emission goals.

Residual Reactivity of Burned Gases in the Early Expansion Process of Future Gas Turbines

1996 ◽  
Vol 118 (1) ◽  
pp. 54-60 ◽  
Author(s):  
B. Leide ◽  
P. Stouffs
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
High Efficiency ◽  
Extreme Case ◽  
Inlet Temperature ◽  
Environmental Aspects ◽  
Expansion Process ◽  
Future Design ◽  
Expansion Path ◽  
Temperature And Pressure

The present study investigates the chemical evolution of the burned gases in a first-stage nozzle operated under high inlet temperature and pressure conditions as they are foreseen for next-generation high-efficiency gas turbine machinery. Coupled aerothermochemical simulations are performed up to the extreme case of stoichiometric combustion without ulterior dilution. The intent is to provide an estimation of possible consequences arising from the residual reactivity of gases downstream from the combustor. These consequences might affect the future design of the expansion path in order to render nonstationary chemistry compatible with aerodynamics, energetics, and environmental aspects.

Development of a Low-Emission Combustor for a 100-kW Automotive Ceramic Gas Turbine (II)

1996 ◽  
Vol 118 (1) ◽  
pp. 167-172 ◽  
Author(s):  
H. Kumakura ◽  
M. Sasaki ◽  
D. Suzuki ◽  
H. Ichikawa
Keyword(s):  
Gas Turbine ◽  
Gasoline Engine ◽  
Standard Test ◽  
Inlet Temperature ◽  
Performance Tests ◽  
Passenger Cars ◽  
Lean Combustion ◽  
Low Emission ◽  
Strength Tests ◽  
Combustion Tests

Performance tests were conducted on a low-emission combustor, which has a pre-vaporization–premixing lean combustion system and is designed for a 100 kW automotive ceramic gas turbine. The results of steady-state combustion tests performed at an inlet temperature of 1000–1200 K and pressure of 0.1–0.34 MPa indicate that the combustor would meet Japan’s emission standards for gasoline engine passenger cars without using an aftertreatment system. Flashback was suppressed by controlling the mixture velocity and air ratios. Strength tests conducted on rings and bars cut from the actual ceramic parts indicate that the combustor has nearly the same level of strength as standard test specimens.

Development of a Low-Emission Combustor for a 100-kW Automotive Ceramic Gas Turbine (III)

1996 ◽  
Author(s):  
Masafumi Sasaki ◽  
Hirotaka Kumakura ◽  
Daishi Suzuki ◽  
Hiroyuki Ichikawa ◽  
Youichiro Ohkubo ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Gas Turbine ◽  
Air Distribution ◽  
Performance Tests ◽  
Test Results ◽  
Combustion System ◽  
Stable Combustion ◽  
Lean Combustion ◽  
Low Emission ◽  
Combustion Region

A low emission combustor, which uses a prevaporization-premixing lean combustion system for the 100 kW automotive ceramic gas turbine (CGT), has been subjected to performance tests. Now a second combustor prototype (PPL-2), which incorporates improvements intended to overcome a flashback problem observed in an initial combustor prototype (PPL-1), is tested. The PPL-2 has been designed and built, so that it will substantially expand the stable combustion range. The improvement is accomplished by increasing the air distribution ratio in the lean combustion region to avoid flashback, providing a uniform flow velocity through the throat area and also by diluting the boundary layer so as to suppress flashback. Test results of the PPL-2 combustor show that it expands the flashback limit without affecting the blow out limit and is able to cover the stable combustion range need for the 100kW CGT.

Development of a Low Emission Combustor for a 100kW Automotive Ceramic Gas Turbine: I

1993 ◽  
Author(s):  
Masafumi Sasaki ◽  
Hirotaka Kumakura ◽  
Daishi Suzuki ◽  
Katsuhiko Sugiyama ◽  
Youichirou Ohkubo
Keyword(s):  
Gas Turbine ◽  
Inlet Temperature ◽  
Performance Tests ◽  
Combustion System ◽  
Passenger Cars ◽  
Temperature Level ◽  
Fuel Injectors ◽  
Low Emission ◽  
Ceramic Components ◽  
Suitable System

A low emission combustor for a 100kW ceramic gas turbine, which is intended to meet Japanese emission standards for gasoline passenger cars, has been designed and subjected to initial performance tests. A prevaporization-premixing combustion system was chosen as the most suitable system for the combustor. The detailed combustor design, including the use of ceramic components and fuel injectors, was pursued taking into account the allowable engine dimensions for vehicle installation. In the initial performance tests conducted at a combustor inlet temperature of 773K, a low NOx level was obtained that satisfied the steady state target at this temperature level.

Status of the Automotive Ceramic Gas Turbine Development Program: Year Five Progress

1996 ◽  
Author(s):  
Tsubura Nisiyama ◽  
Norio Nakazawa ◽  
Masafumi Sasaki ◽  
Masumi Iwai ◽  
Haruo Katagiri ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Ceramic Materials ◽  
Inlet Temperature ◽  
Test Rig ◽  
Target Values ◽  
Ceramic Components ◽  
Combined Test ◽  
And Performance ◽  
The Individual

Petroleum Energy Center of Japan has been carrying out a 7-year development program to prove the potential of an automotive ceramic gas turbine for five years with the support of the Ministry of International Trade and Industry. The ceramic gas turbine now under development is a regenerative single shaft engine. The output is 100kW, and the turbine inlet temperature (TIT) is 1350°C. All the ceramic components are now entering the 1350°C TIT test phase after completing 1200°C TIT evaluation tests, including durability tests, in various types of test rigs. The compressor-turbine combined test rig and the full assembly test rig which is the same as an actual engine and incorporates all the components are now going through 1200°C TIT function and performance evaluation tests. In the near future, we are planning to increase the TIT to 1350°C. In consideration of the current level of high-temperature, long-term strength available from the ceramic materials, we decided to change the rated speed to 100,000 rpm because the initial rated speed of 110,000 rpm, if unchanged, involves considerable risks. Then we reviewed mainly the designs of the compressor and turbine and revised the target values of the individual components to match the specifications that satisfy the target performance of the engine.

Preliminary design and performance analysis of a low emission aero-derived gas turbine combustor

2013 ◽  
Vol 117 (1198) ◽  
pp. 1249-1271 ◽  
Author(s):  
B. Khandelwal ◽  
A. Karakurt ◽  
V. Sethi ◽  
R. Singh ◽  
Z. Quan
Keyword(s):  
Gas Turbine ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Gas Turbine Combustor ◽  
Detailed Method ◽  
Low Emission ◽  
Heat Shields ◽  
Lean Fuel ◽  
Reduce Emissions ◽  
And Performance

Abstract Modern gas turbine combustor design is a complex task which includes both experimental and empirical knowledge. Numerous parameters have to be considered for combustor designs which include combustor size, combustion efficiency, emissions and so on. Several empirical correlations and experienced approaches have been developed and summarised in literature for designing conventional combustors. A large number of advanced technologies have been successfully employed to reduce emissions significantly in the last few decades. There is no literature in the public domain for providing detailed design methodologies of triple annular combustors. The objective of this study is to provide a detailed method designing a triple annular dry low emission industrial combustor and evaluate its performance, based on the operating conditions of an industrial engine. The design methodology employs semi-empirical and empirical models for designing different components of gas turbine combustors. Meanwhile, advanced DLE methods such as lean fuel combustion, premixed methods, staged combustion, triple annular, multi-passage diffusers, machined cooling rings, DACRS and heat shields are employed to cut down emissions. The design process is shown step by step for design and performance evaluation of the combustor. The performance of this combustor is predicted, it shows that NO x emissions could be reduced by 60%-90% as compared with conventional single annular combustors.

Design, Evaluation and Performance Analysis of Staged Low Emission Combustors

2012 ◽  
Author(s):  
Gajanana B. Hegde ◽  
Bhupendra Khandelwal ◽  
Vishal Sethi ◽  
Riti Singh
Keyword(s):  
Combustion Chamber ◽  
Gas Turbine ◽  
Design Methodology ◽  
Reverse Flow ◽  
Axial Flow ◽  
Design Procedure ◽  
Extensive Study ◽  
Theoretical Design ◽  
Low Emission ◽  
And Performance

The most uncertain and challenging part in the design of a gas turbine has long been the combustion chamber. There has been large number of experimentations in industries and universities alike to better understand the dynamic and complex processes that occur inside a combustion chamber. This study concentrates on gas turbine combustors as a whole, and formulates a theoretical design procedure for staged combustors in particular. Not much of literatures available currently in public domain provide intensive study on designing staged combustors. The work covers an extensive study of design methods applied in conventional combustor designs, which includes the reverse flow combustor and the axial flow annular combustors. The knowledge acquired from this study is then applied to develop a theoretical design methodology for double staged (radial and axial) low emission annular combustors. Additionally a model combustor is designed for each type; radial and axial staging using the developed methodology. A prediction of the performance for the model combustors is executed. The main conclusion is that the dimensions of model combustors obtained from the developed design methodology are within the feasibility limits. The comparison between the radially staged and the axially staged combustor has yielded the predicted results such as lower NOx prediction for the latter and shorter combustor length for the former. The NOx emission result of the new combustor models are found to be in the range of 50–60ppm. However the predicted NOx results are only very crude and need further detailed study.

scholarly journals 100s and 1000s Mw Open and Semi-Closed Cycle Gas Turbines for Base and Peak Operation

1974 ◽  
Author(s):  
V. V. Uvarov ◽  
V. S. Beknev ◽  
E. A. Manushin
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Simple Cycle ◽  
Inlet Temperature ◽  
Closed Cycle ◽  
Turbine Inlet Temperature ◽  
Unit Capacity ◽  
Temperature And Pressure ◽  
Different Levels

There are two different approaches to develop the gas turbines for power. One can get some megawatts by simple cycle or by more complex cycle units. Both units require very different levels of turbine inlet temperature and pressure ratio for the same unit capacity. Both approaches are discussed. These two approaches lead to different size and efficiencies of gas turbine units for power. Some features of the designing problems of such units are discussed.

Combustion System Development and Testing for MAN’s New Industrial Gas Turbines MGT 6100 and MGT 6200

2014 ◽  
Author(s):  
Frank Reiss ◽  
Sven-Hendrik Wiers ◽  
Ulrich Orth ◽  
Emil Aschenbruck ◽  
Martin Lauer ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Test Facility ◽  
Combustion System ◽  
Test Rig ◽  
Low Emission ◽  
Pressure Test ◽  
Industrial Gas Turbines ◽  
And Performance

This paper describes the development and test results of the low emission combustion system for the new industrial gas turbines in the 6–7 MW class from MAN Diesel & Turbo. The design of a robust combustion system and the achievement of very low emission targets were the most important design goals of the combustor development. During the design phase, the analysis of the combustor (i.e. burner design, air distribution, liner cooling design) was supported with different CFD tools. This advanced Dry Low Emission can combustion system (ACC) consists of 6 cans mounted externally on the gas turbine. The behavior and performance of a single can sector was tested over a wide load range and with different boundary conditions; first on an atmospheric test rig and later on a high pressure test rig with extensive instrumentation to ensure an efficient test campaign and accurate data. The atmospheric tests showed a very good performance for all combustor parts and promising results. The high pressure tests demonstrated very stable behavior at all operation modes and very low emissions to satisfy stringent environmental requirements. The whole operation concept of the combustion system was tested first on the single-can high pressure test bed and later on twin and single shaft gas turbines at MAN’s gas turbine test facility. During the engine tests, the can combustors demonstrated the expected combustion performance under real operation conditions. All emissions and performance targets were fully achieved. On the single shaft engine, the combustors were running with single digit ppm NOx levels between 50% and 100% load. The validation phase and further optimization of the gas turbines and the engine components are ongoing. The highlights of the development process and results of the combustor and engine tests will be presented and discussed within this paper.

scholarly journals Diurnal Temperature and Pressure Effects on Axial Turbomachinery Stability in Solid Oxide Fuel Cell-Gas Turbine Hybrid Systems

2011 ◽  
Vol 8 (3) ◽  
Author(s):  
James D. Maclay ◽  
Jacob Brouwer ◽  
G. Scott Samuelsen
Keyword(s):  
Fuel Cell ◽  
Ambient Temperature ◽  
Gas Turbine ◽  
Solid Oxide ◽  
Inlet Temperature ◽  
Electrolyte Temperature ◽  
Turbine Inlet Temperature ◽  
Compressor Surge ◽  
Turbine Shaft ◽  
Temperature And Pressure

A dynamic model of a 100 MW solid oxide fuel cell-gas turbine hybrid system has been developed and subjected to perturbations in diurnal ambient temperature and pressure as well as load sheds. The dynamic system responses monitored were the fuel cell electrolyte temperature, gas turbine shaft speed, turbine inlet temperature, and compressor surge. Using a control strategy that primarily focuses on holding fuel cell electrolyte temperature constant and secondarily on maintaining gas turbine shaft speed, safe operation was found to occur for expected ambient pressure variation ranges and for ambient temperature variations up to 28 K when tested nonsimultaneously. When ambient temperature and pressure were varied simultaneously, stable operation was found to occur when the two are in phase but not when the two are out of phase. The latter case leads to shaft overspeed. Compressor surge was found to be more likely when the system is subjected to a load shed initiated at minimum ambient temperature rather than at maximum ambient temperature. Fuel cell electrolyte temperature was found to be well-controlled except in the case of shaft overspeeds. Turbine inlet temperature remained in safe bounds for all cases.

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