Lean Operation of a Pulse Detonation Combustor by Fuel Stratification

2020 ◽  
Author(s):  
Fabian Habicht ◽  
Fatma C. Yücel ◽  
Niclas Hanraths ◽  
Neda Djordjevic ◽  
Christian Oliver Paschereit
Keyword(s):  
Gas Turbines ◽  
Equivalence Ratio ◽  
Pressure Ratio ◽  
Initial Pressure ◽  
Detonation Initiation ◽  
Nox Emissions ◽  
Shock Focusing ◽  
Successful Operation ◽  
Pulse Detonation ◽  
Fuel Stratification

Abstract Pressure gain combustion is a promising concept to substantially increase the thermal efficiency of gas turbines. One possible implementation are pulse detonation combustors (PDCs), as they permit stable and reliable operation. Besides, the need for part-load operation and low NOx emissions requires combustion concepts in the lean regime. The present work investigates an approach to realize lean combustion in a PDC by applying fuel stratification experimentally. The necessary increase of fuel concentration inside the pre-detonation chamber to provide reliable DDT with respect to the overall equivalence ratio is identified. Emission measurements in the exhaust allow for a quantification of the NOx emissions as a function of the injected fuel profile. A valveless PDC test rig is used, which contains a shock-focusing geometry for detonation initiation and is ignited by a spark plug close to the upstream end wall. The subsequent expansion of the burned gas and interaction of the flame front with turbulence leads to the formation of a leading shock inside the pre-detonation chamber, which is then focused inside a converging-diverging geometry. The successful initiation of a detonation wave by shock focusing is very sensitive to the pressure ratio across the leading shock, which can be influenced by initial pressure, reactant composition and flow velocity. Results reveal that fuel stratification allows for reliable detonation initiation at a global equivalence ratio of 0.65, whereas repeatable successful operation with non-stratified fuel injection is limited to a global equivalence ratio greater than 0.85.

Lean Operation of a Pulse Detonation Combustor by Fuel Stratification

2020 ◽  
Author(s):  
Fabian E. Habicht ◽  
Fatma C. Yücel ◽  
Niclas Hanraths ◽  
Neda Djordjevic ◽  
Christian Oliver Paschereit
Keyword(s):  
Gas Turbines ◽  
Equivalence Ratio ◽  
Pressure Ratio ◽  
Initial Pressure ◽  
Detonation Initiation ◽  
Nox Emissions ◽  
Shock Focusing ◽  
Pulse Detonation ◽  
Lean Combustion ◽  
Fuel Stratification

Abstract Pressure gain combustion is a promising concept to substantially increase the thermal efficiency of gas turbines. One possible implementation that has been frequently investigated are pulse detonation combustors (PDCs), as they permit stable and reliable operation. At the same time, the need for part-load operation and low NOx emissions requires combustion concepts in the lean regime. However, realizing lean combustion is still very challenging in PDCs since the deflagration to detonation transition (DDT) is very sensitive to the reactant composition. The present work investigates an approach to realize lean combustion in PDC by applying fuel stratification experimentally. The scope is to find the necessary increase of fuel concentration inside the pre-detonation chamber to provide reliable DDT with respect to the overall equivalence ratio. Emission measurements in the exhaust of the PDC allow for a quantification of the NOx emissions as a function of the injected fuel profile. A valveless PDC test rig is used, which contains a shock focusing geometry for detonation initiation and is ignited by a spark plug close to the upstream end wall. The subsequent expansion of the burned gas and interaction of the flame front with turbulence leads to the formation of a leading shock inside the pre-detonation chamber, which is then focused inside a converging-diverging geometry. The successful initiation of a detonation wave by shock focusing is very sensitive to the pressure ratio across the leading shock, which can be influenced by initial pressure, reactant composition and flow velocity. Results reveal that fuel stratification allows for reliable detonation initiation at a global equivalence ratio of ϕglob = 0.65, whereas repeatable successful operation with non-stratified fuel injection is limited to ϕglob ≥ 0.85.

scholarly journals Detonation initiation by shock focusing at elevated pressure conditions in a pulse detonation combustor

2020 ◽  
Vol 12 ◽  
pp. 175682772092171
Author(s):  
Fabian E Habicht ◽  
Fatma C Yücel ◽  
Joshua AT Gray ◽  
Christian O Paschereit
Keyword(s):  
Success Rate ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Initial Pressure ◽  
Detonation Initiation ◽  
Major Influence ◽  
Mean Flow ◽  
Shock Focusing ◽  
Pulse Detonation

This work contains experimental investigations on the correlation of the detonation initiation process via a shock-focusing device with various initial pressures and mass flow rates. A pulse detonation combustor is operated with stoichiometric hydrogen--air--oxygen mixtures in single cycle operation. A rotationally symmetric shock-focusing geometry evokes the onset of a detonation by the focusing of the reflected leading shock wave, while a blockage plate at the rear end of the test rig is applied to induce an elevated initial pressure. The results show that the reactivity has a major influence on the success rate of detonation initiation. However, measurements with different blockage plates suggest that the mass flow rate has to be considered as well when predicting the success rate. Three main statements can be drawn from the results. (1) An increase in the mean flow velocity induces higher velocity fluctuations which result in a stronger leading shock ahead of the accelerating deflagration front. (2) An increase in the initial static pressure reduces the critical shock strength that must be exceeded to ensure successful detonation initiation by shock focusing. (3) Since the initial pressure is directly linked to the mass flow rate, these contrary trends can cancel each other out, which could be observed for 40% vol. of oxygen in the oxidizer. High-speed images were taken, which confirm that the detonation is initiated in the center of the converging--diverging nozzle due to focusing of the leading shock.

Design Study of an Advanced Concept Simple Gas Turbine for Possible Use in Low Emission Automobiles

1972 ◽  
Author(s):  
H. C. Eatock ◽  
M. D. Stoten
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Simple Cycle ◽  
Turbine Engines ◽  
Nox Emissions ◽  
Preliminary Design ◽  
Gas Turbine Engines ◽  
High Pressure Ratio

United Aircraft Corporation studied the potential costs of various possible gas turbine engines which might be used to reduce automobile exhaust emissions. As part of that study, United Aircraft of Canada undertook the preliminary design and performance analysis of high-pressure-ratio nonregenerated (simple cycle) gas turbine engines. For the first time, high levels of single-stage component efficiency are available extending from a pressure ratio less than 4 up to 10 or 12 to 1. As a result, the study showed that the simple-cycle engine may provide satisfactory running costs with significantly lower manufacturing costs and NOx emissions than a regenerated engine. In this paper some features of the preliminary design of both single-shaft and a free power turbine version of this engine are examined. The major component technology assumptions, in particular the high pressure ratio centrifugal compressor, employed for performance extrapolation are explained and compared with current technology. The potential low NOx emissions of the simple-cycle gas turbine compared to regenerative or recuperative gas turbines is discussed. Finally, some of the problems which might be encountered in using this totally different power plant for the conventional automobile are identified.

Numerical Study on the Reduction of NOx Emissions From Pulse Detonation Combustion

2017 ◽  
Vol 140 (4) ◽  
Author(s):  
Neda Djordjevic ◽  
Niclas Hanraths ◽  
Joshua Gray ◽  
Phillip Berndt ◽  
Jonas Moeck
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Conditions ◽  
Pollutant Emissions ◽  
Emissions Reduction ◽  
Nox Emissions ◽  
Primary Methods ◽  
Detonation Cell ◽  
Pulse Detonation ◽  
Detonation Combustion

A change in the combustion concept of gas turbines from conventional isobaric to constant volume combustion, such as in pulse detonation combustion (PDC), promises a significant increase in gas turbine efficiency. Current research focuses on the realization of reliable PDC operation and its challenging integration into a gas turbine. The topic of pollutant emissions from such systems has so far received very little attention. Few rare studies indicate that the extreme combustion conditions in PDC systems can lead to high emissions of nitrogen oxides (NOx). Therefore, it is essential already at this stage of development to begin working on primary measures for NOx emissions reduction if commercialization is to be feasible. The present study evaluates the potential of different primary methods for reducing NOx emissions produced during PDC of hydrogen. The considered primary methods involve utilization of lean combustion mixtures or its dilution by steam injection or exhaust gas recirculation. The influence of such measures on the detonability of the combustion mixture has been evaluated based on detonation cell sizes modeled with detailed chemistry. For the mixtures and operating conditions featuring promising detonability, NOx formation in the detonation wave has been simulated by solving the one-dimensional (1D) reacting Euler equations. The study enables an insight into the potential and limitations of considered measures for NOx emissions reduction and lays the groundwork for optimized operation of PDC systems.

Experimental and Numerical Investigations of Low-Swirl Multi-Nozzle Combustion in a Lean Premixed Combustor

2014 ◽  
Author(s):  
Weijie Liu ◽  
Bing Ge ◽  
Yinshen Tian ◽  
Yongwen Yuan ◽  
Shusheng Zang ◽  
...  
Keyword(s):  
Gas Turbines ◽  
Equivalence Ratio ◽  
Flame Temperature ◽  
Main Reaction ◽  
Nox Emissions ◽  
Lean Premixed ◽  
Planar Laser ◽  
Reaction Zones ◽  
Promising Solution ◽  
Log Linear

This paper presents large-eddy simulations (LES) and laser diagnostic experiments of low-swirl lean premixed methane/air flames in a multi-nozzle combustor including five nozzles with the same structure. OH Planar Laser Induced Fluorescence (PLIF) is used to observe flame shapes and identify main reaction zones. NOx and CO emissions are also recorded during the experiment. The flows and flames are studied at different equivalence ratios ranging from 0.5 to 0.8, while the inlet velocity is fixed at 6.2 m/s. Results show that the neighboring swirling flows interact with each other, generating a highly turbulent mixing zone where intensive reactions take place. The flame is stabilized above the nozzle rim and its liftoff height decreases with increasing equivalence ratio. The center flow is confined and distorted by the neighboring flows, resulting in instabilities of the center flame. Mean OH radical images reveals that the center nozzle flame is extinguished when equivalence ratio is equals to 0.5, which is successfully predicted by LES. In addition, NOx emissions show log-linear dependency on the adiabatic flame temperature, while the CO emissions remain lower than 10 ppm. NOx emissions for multi-nozzle flame are less sensitive to the flame temperature than that for single nozzle. These results demonstrate that the low-swirl multi-nozzle concept is a promising solution to achieve stable combustion with ultra-low emissions in gas turbines.

Rotor Design for Large Industrial Gas Turbines

1992 ◽  
Author(s):  
W. Endres
Keyword(s):  
Gas Turbines ◽  
Low Cycle Fatigue ◽  
Pressure Ratio ◽  
High Strength ◽  
Moderate Pressure ◽  
Cycle Fatigue ◽  
Successful Operation ◽  
Air Temperatures ◽  
Proof Testing ◽  
Industrial Gas Turbines

The overall designs of rotors for modern large industrial gas turbines are all very similar; however, the manufacturers have widely different internal designs. Building up the discs and drums to form the rotor is achieved either by a number of different mechanical joining techniques or by welding. In addition the rotor materials, the mechanical integrity, proof testing and critical rotor areas are also discussed. The conflicting design requirements, i.e. for supporting the centrifugal loads, protecting the rotor against the hot gases and warming the rotor during a start-up without excessive thermal stress, lead to very different design solutions. Thus in this paper the stresses, low cycle fatigue and the operational behavior of some typical designs are compared. The investigation was limited to turbines with moderate pressure ratio (<16) and low cooling air temperatures allowing the rotors to be made of high strength ferritic steels. The result shows a preference for welded designs with discs of constant stress which are free of holes in the center. Strength, low cycle fatigue and safety aspects, as well as operational advantages like avoidance of vibrations and ease of inspection speak for this solution. However, all three considered designs are presently being used by different manufacturers and meet all requirements for successful operation.

Numerical Study on the Reduction of NOx Emissions From Pulse Detonation Combustion

2017 ◽  
Author(s):  
Neda Djordjevic ◽  
Niclas Hanraths ◽  
Joshua Gray ◽  
Phillip Berndt ◽  
Jonas Moeck
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Operating Conditions ◽  
Pollutant Emissions ◽  
Emissions Reduction ◽  
Nox Emissions ◽  
Primary Methods ◽  
Detonation Cell ◽  
Pulse Detonation ◽  
Detonation Combustion

A change in the combustion concept of gas turbines from conventional isobaric to constant volume combustion (CVC), such as in pulse detonation combustion (PDC), promises a significant increase in gas turbine efficiency. Current research focuses on the realization of reliable PDC operation and its challenging integration into a gas turbine. The topic of pollutant emissions from such systems has so far received very little attention. Few rare studies indicate that the extreme combustion conditions in PDC systems can lead to high emissions of nitrogen oxides (NOx). Therefore, it is essential already at this stage of development to begin working on primary measures for NOx emissions reduction, if commercialization is to be feasible. The present study evaluates the potential of different primary methods for reducing NOx emissions produced during pulsed detonation combustion of hydrogen. The considered primary methods involve utilization of lean combustion mixtures or its dilution by steam injection or exhaust gas recirculation. The influence of such measures on the detonability of the combustion mixture has been evaluated based on detonation cell sizes modelled with detailed chemistry. For the mixtures and operating conditions featuring promising detonability, NOx formation in the detonation wave has been simulated by solving the one-dimensional reacting Euler equations. The study enables an insight into the potential and limitations of considered measures for NOx emissions reduction and lays the groundwork for optimized operation of pulse detonation combustion systems.

CFD Investigation of the Effects of Different Diluents on the Emissions in a Swirl Stabilized Premixed Combustion System

2005 ◽  
Author(s):  
Ulf Engdar ◽  
Fredrik Hermann ◽  
Rolf Gabrielsson ◽  
Jens Klingmann
Keyword(s):  
Fluid Dynamics ◽  
Experimental Data ◽  
Flow Field ◽  
Gas Turbines ◽  
Equivalence Ratio ◽  
Premixed Combustion ◽  
Inlet Temperature ◽  
Nox Emissions ◽  
Combustion System ◽  
Laminar Flamelet

Recently, new cycles for power generation, such as wet cycles and cycles for CO2 capture, have gained increasing interest. These new cycles use some sort of dilution in the air/fuel mixture, e.g. steam or CO2. Gas turbine cycles using LCV gases can also be said to fit this description. Almost all modern gas turbines use a lean premixed combustion system, since it combines low NOx emissions with high combustion efficiency. The main objective of this paper is to study the influence of different diluents on the NOx and CO emissions at different inlet temperature, equivalence ratio, pressure and mass flow. The studied combustor was a premixed swirl stabilized combustor with optical access and emission sampling equipment. The combustor uses Danish natural gas as its main fuel. Computational fluid dynamics (CFD) has been employed to perform the investigations. It is common knowledge that turbulence models based on the Buissinesq assumption are not generally capable of handling a highly swirling flow in a correct way. Therefore, a differential Reynolds stress model (DRSM) has been employed for modeling of the turbulence. The turbulent combustion has been modeled with the level-set flamelet library approach (FLA). In this approach a laminar flamelet is linked to turbulent flow field via a non-reacting scalar G and its variance. The laminar flamelet is modeled with separate code. This code solves the combustion development with a detailed reaction mechanism for a laminar, non-stretched and premixed one-dimensional flame. This is of great importance when emissions are to be predicted. All fluid dynamics computations were performed with the commercial CFD code Star-CD, version 3.20, where the FLA combustion model was implemented through Fortran based user subroutines. The computed flow field was validated against experimental data during non-reaction flow conditions. The computations showed good agreement with the experimental data. The computed CO and NOx emissions showed the same trends as the experimental data for the reacting case with an undiluted flame, when the equivalence ratio was altered. The computed emissions were used to build up an emission map for different dilutions during different operation conditions.

scholarly journals Feasibility of a Helium Closed-Cycle Gas Turbine for UAV Propulsion

2020 ◽  
Vol 11 (1) ◽  
pp. 28
Author(s):  
Emmanuel O. Osigwe ◽  
Arnold Gad-Briggs ◽  
Theoklis Nikolaidis
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Low Noise ◽  
Closed Cycle ◽  
Propulsion Systems ◽  
Component Design ◽  
Readiness Level ◽  
Aerial Vehicle ◽  
Turbine Design

When selecting a design for an unmanned aerial vehicle, the choice of the propulsion system is vital in terms of mission requirements, sustainability, usability, noise, controllability, reliability and technology readiness level (TRL). This study analyses the various propulsion systems used in unmanned aerial vehicles (UAVs), paying particular focus on the closed-cycle propulsion systems. The study also investigates the feasibility of using helium closed-cycle gas turbines for UAV propulsion, highlighting the merits and demerits of helium closed-cycle gas turbines. Some of the advantages mentioned include high payload, low noise and high altitude mission ability; while the major drawbacks include a heat sink, nuclear hazard radiation and the shield weight. A preliminary assessment of the cycle showed that a pressure ratio of 4, turbine entry temperature (TET) of 800 °C and mass flow of 50 kg/s could be used to achieve a lightweight helium closed-cycle gas turbine design for UAV mission considering component design constraints.

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