Fuel Flexible Distributed Combustion for Gas Turbine Engines

2012 ◽  
Author(s):  
Ahmed E. E. Khalil ◽  
Ashwani K. Gupta
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Low Noise ◽  
Liquid Fuels ◽  
Low Emission ◽  
Wide Range ◽  
Efficient Combustion ◽  
Pollutants Emission ◽  
Significant Performance ◽  
Reduction Of Nox

Distributed Combustion provides significant performance improvement of gas turbine combustors including uniform thermal field in the entire combustion chamber (improved pattern factor), ultra low emission of NOx and CO, low noise, enhanced stability and higher efficiency. Distributed combustion with swirl have been investigated to determine the beneficial aspects of such flows on clean and efficient combustion under simulated gas turbine combustion conditions with close focus on NOx emission. Near Zero emissions of NO and CO have been demonstrated using methane under distributed combustion conditions with heat release intensities commensurable to gas turbine applications. In this paper, distributed combustion is further investigated using both gaseous and liquid fuels with emphasis on pollutants emission and combustor performance with each fuel. Performance evaluation with the different fuels is established to outline the flexibility of the combustor in handling a wide range of fuels with different calorific values and phases with focus on ultra-low pollutants emission. Results obtained on pollutants emission and OH* chemiluminescence for the specific fuels examined at various equivalence ratios are presented. Near distributed combustion conditions with less than 5 PPM of NO emission were demonstrated under novel premixed conditions for the various fuels tested thus outlining the combustor ability to handle different fuels with high performance. Further reduction of NOx can be made with true distributed combustion condition.

Dual Injection Distributed Combustion for Gas Turbine Application

2013 ◽  
Vol 136 (1) ◽  
Author(s):  
Ahmed E. E. Khalil ◽  
Ashwani K. Gupta
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Fuel Injection ◽  
Scale Up ◽  
Low Noise ◽  
Dual Injection ◽  
Efficient Combustion ◽  
Pollutants Emission ◽  
Improved Performance ◽  
The Impact

Distributed combustion has been shown to provide significantly improved performance with near zero emissions for stationary gas turbine applications. Characteristics of distributed combustion include uniform thermal field in the entire combustion chamber (improved pattern factor), ultra-low emissions of NOx and CO, low noise, enhanced stability, and higher efficiency. Distributed combustion with swirl have been investigated to determine the beneficial aspects of such flows on clean and efficient combustion under simulated gas turbine combustion conditions with ultra-low NOx emissions. Results are presented here on the impact of employing dual injection of air and fuel in contrast to single injection. Dual and multi-injection is of great importance for combustor design scale up as to maintain flow similarities. Results showed that careful implementation of dual injection can result in emissions as low as single air/fuel injection method. With adequate fuel injection strategy, further reduction in emissions has been demonstrated. Results obtained on pollutants emission with dual injection and different fuel injection strategies at various equivalence ratios showed ultra-low emission (<5 PPM NO and <15 PPM CO) and high performance. OH* chemiluminescence revealed relative position of the flame within the combustor under various conditions for further improvements in distributed combustion conditions and to further reduce NOx emission.

Dual Injection Distributed Combustion for Gas Turbine Application

2013 ◽  
Author(s):  
Ahmed E. E. Khalil ◽  
Ashwani K. Gupta
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Fuel Injection ◽  
Scale Up ◽  
Low Noise ◽  
Dual Injection ◽  
Efficient Combustion ◽  
Pollutants Emission ◽  
Improved Performance ◽  
The Impact

Distributed Combustion has been shown to provide significantly improved performance with near zero emissions for stationary gas turbine applications. Characteristics of distributed combustion include uniform thermal field in the entire combustion chamber (improved pattern factor), ultra low emissions of NOx and CO, low noise, enhanced stability and higher efficiency. Distributed combustion with swirl have been investigated to determine the beneficial aspects of such flows on clean and efficient combustion under simulated gas turbine combustion conditions with ultra-low NOx emissions. Results are presented here on the impact of employing dual injection of air and fuel in contrast to single injection. Dual and multi injection is of great importance for combustor design scale up as to maintain flow similarities. Results showed that careful implementation of dual injection can result in emissions as low as single air/fuel injection method. With adequate fuel injection strategy, further reduction in emissions has been demonstrated. Results obtained on pollutants emission with dual injection and different fuel injection strategies at various equivalence ratios showed ultra-low emission (<5PPM NO and <15PPM CO) and high performance. OH* chemiluminescence revealed relative position of the flame within the combustor under various conditions for further improvements in distributed combustion conditions and to further reduce NOx emission.

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

2021 ◽  
pp. 095441002110253
Author(s):  
Babak Aryana
Keyword(s):  
High Performance ◽  
Static Condition ◽  
Propulsion System ◽  
Hybrid Propulsion ◽  
Pulse Detonation ◽  
Low Emission ◽  
Wide Range ◽  
Exit Nozzle ◽  
Distributed Propulsion ◽  
Detonation Process

This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

Detailed Study of Front Module for Low-Emission Combustor

2020 ◽  
Author(s):  
A. Vasilyev ◽  
V. Zakharov ◽  
O. Chelebyan ◽  
O. Zubkova
Keyword(s):  
Experimental Data ◽  
Numerical Study ◽  
Flame Structure ◽  
Combustion Efficiency ◽  
Liquid Fuels ◽  
Pollutant Emission ◽  
Additional Information ◽  
Low Emission ◽  
Wide Range ◽  
To Receive

Abstract At the ASME Turbo Expo 2018 conference held in Oslo (Norway) on the 11th-15th of June 2018, the paper GT2018-75419 «Experience of Low-Emission Combustion of Aviation and Bio Fuels in Individual Flames after Front Mini-Modules of a Combustion Chamber» was published. This paper continues the studies devoted to the low-emission combustion of liquid fuels in GTE combustors. The paper presents a description of more detailed studies of the front module with a staged pneumatic fuel spray. The aerodynamic computations of the front module were conducted, and the disperse characteristics of the fuel-air spray were measured. The experimental research was carried out in two directions: 1) probing of the 3-burner sector flame tube at the distance of one third of its length (temperature field and gas sampling); 2) numerical study of the model combustor with actual arrangement of the modules in the dome within a wide range of fuel-air ratio. The calculated and experimental data of velocity field behind the front module were compared. And new data about the flame structure inside the test sector were obtained. Experimental data confirm the results of preliminary studies of the 3-burner sector: combustion efficiency is higher than 99.8%, EiNOx is at the level of 2–3 g/fuel kg at the combustor inlet air temperature of 680K and fuel-air ratio of 0.0225. The conducted research allowed to receive additional information on the influence of some design units on the pollutant emission and to estimate the different elements of computational methods for simulation of a low-emission combustor with a multi-atomizer dome.

Passive Control of Combustion Instability in a Low Emissions Aeroderivative Gas Turbine

2004 ◽  
Author(s):  
Tomas Scarinci ◽  
Christopher Freeman ◽  
Ivor Day
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Laboratory Testing ◽  
Passive Control ◽  
Pressure Ratio ◽  
Combustion Process ◽  
Field Trials ◽  
Low Noise ◽  
Wide Range ◽  
Air Mixing

This paper describes the conceptual ideas, the theoretical validation, the laboratory testing and the field trials of a recently patented fuel-air mixing device for use in high-pressure ratio, low emissions, gaseous-fueled gas turbines. By making the fuel-air mixing process insensitive to pressure fluctuations in the combustion chamber, it is possible to avoid the common problem of positive feedback between mixture strength and the unsteady combustion process. More specifically, a mixing duct has been designed such that fuel-air ratio fluctuations over a wide range of frequencies can be damped out by passive design means. By scaling the design in such a way that the range of damped frequencies covers the frequency spectrum of the acoustic modes in the combustor, the instability mechanism can be removed. After systematic development, this design philosophy was successfully applied to a 35:1 pressure ratio aeroderivative gas turbine yielding very low noise levels and very competitive NOx and CO measurements. The development of the new premixer is described from conceptual origins through analytic and CFD evaluation to laboratory testing and final field trials. Also included in this paper are comments about the practical issues of mixing, flashback resistance and autoignition.

Design and Study on Power Supply for Giant Magnetostrictive Accurate-Motion Actuator

2008 ◽  
Vol 392-394 ◽  
pp. 787-792
Author(s):  
M. Wu ◽  
Xi Lin Zhu
Keyword(s):  
High Speed ◽  
High Performance ◽  
Design Method ◽  
Current Source ◽  
Fast Response ◽  
Low Noise ◽  
Constant Current ◽  
Loop Current ◽  
Constant Current Source ◽  
Wide Range

The architecture and operation theory of Giant Magnetostrictive Accurate-motion Actuator have been introduced. After analysing the driving characteristic of giant magnetostrictive material and requirement of driving power, a design method of wide range and high precision NC constant-current source has been put out. The output circuit is composed of serial 12-bit DACs Max531, low-noise high-speed precision operational amplifiers OP27 and driving circuit. It provides current from 0 to 2.048A with 0.5mA step value. Two fully differential input channels 16-bit, sigma-delta ADCs AD7705 collects output current in feedback loop. Current ripple is controlled under 0.25mA through using homemade high-performance linear power. The result shows that the driving power with characteristic of high stability and fast response meets the needs of driving of Giant Magnetostrictive Accurate-motion.

A hybrid propulsion system for a high-endurance UAV: configuration selection, aerodynamic study, and gas turbine bench tests

2014 ◽  
Vol 02 (01) ◽  
pp. 16-35 ◽  
Author(s):  
R. Capata ◽  
L. Marino ◽  
E. Sciubba
Keyword(s):  
Gas Turbine ◽  
Electric Propulsion ◽  
High Performance ◽  
Limited Range ◽  
Propulsion System ◽  
Major Drawback ◽  
Hybrid Propulsion ◽  
Electric Generator ◽  
Wide Range ◽  
Configuration Selection

In recent years, renewed interest in the development of unmanned aerial vehicles (UAVs) has led to a wide range of interesting applications in reconnaissance and surveillance. In these missions, the noise produced by propeller-driven UAVs is a major drawback, which can be partially solved by installing an electric motor to drive the propeller. While the evolution of high performance brushless motors makes electric propulsion particularly appealing, at least for small and medium UAVs, all electric propulsion systems developed to date are penalized by the limited range and endurance that can be provided by a reasonably sized battery pack. In this paper we propose a hybrid propulsion system based on a recently developed ultramicro gas–turbine (UMGT), which can be used to power an electric generator, providing a significant range and (or) mission time extension. The UMGT is undergoing operational testing in our laboratory, to identify the most suitable configuration and to improve performance: a new compact regenerative combustion chamber was developed and several tests are being carried out to reduce its weight and size so as to increase, all other things being equal, the vehicle payload. This paper aims to propose a high endurance UAV, by a preliminary configuration selection and aerodynamic study of its performance.

scholarly journals Gas Turbine Tubular Combustor Main Injector Optimization for Low Emission Combustion

2018 ◽  
Vol 26 (10) ◽  
pp. 1-12
Author(s):  
Arkan Khikhal Husain ◽  
Mahmood Attallah Mashkoor ◽  
Fuad Abdul Ameer Khalaf
Keyword(s):  
Gas Turbine ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
High Performance ◽  
Atmospheric Conditions ◽  
Air Mass ◽  
Fuel Flow ◽  
Low Emission ◽  
Gas Fuel

This work presents the experimental investigation results of high performance and low emission colorless combustion in a gas turbine tubular combustor at atmospheric conditions. Low emission and colorless oxidation reaction is characterized by dispersed flame and temperature under the conditions of preheated air. System performance, emissions of CO and UHC are recorded up to achieve low emission colorless combustion, the flame capturing, Measurements of temperature, inlet air mass flow rate and gas fuel LPG flow rate for variable of fuel main injector holes diameter. concluded that maximal air mass flow rate, with choked fuel flow in the main injector for each cases promotes the formation of colorless pal blue flame combustion, for 3.2 g/s of fuel flow rate with 6 holes and 1mm main injector holes diameter and lower CO emissions and decreasing in UHC emissions (70 → 10) ppmv with increasing in power generation (0.5 → 3.42) kW and decreasing in S.F.C. (21.5 → 3.49) kg/kwh.

Low-Emission Operation of Aeroderivative Gas-Turbine Combustor over a Wide Range of Ambient Conditions

2020 ◽  
Vol 54 (1) ◽  
pp. 93-95 ◽  
Author(s):  
L. A. Bulysova ◽  
A. G. Tumanovskii ◽  
M. N. Gutnik ◽  
V. D. Vasil’ev ◽  
A. M. Sipatov ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Ambient Conditions ◽  
Gas Turbine Combustor ◽  
Low Emission ◽  
Wide Range

scholarly journals A high-performance 8 nV/√Hz 8-channel wearable and wireless system for real-time monitoring of bioelectrical signals

2019 ◽  
Vol 16 (1) ◽  
Author(s):  
Konstantinos Petkos ◽  
Simos Koutsoftidis ◽  
Thomas Guiho ◽  
Patrick Degenaar ◽  
Andrew Jackson ◽  
...  
Keyword(s):  
Real Time ◽  
High Performance ◽  
Ex Vivo ◽  
Low Noise ◽  
Patient Treatment ◽  
Pathological State ◽  
Clinical Environment ◽  
High Dependency ◽  
Wide Range

Abstract Background It is widely accepted by the scientific community that bioelectrical signals, which can be used for the identification of neurophysiological biomarkers indicative of a diseased or pathological state, could direct patient treatment towards more effective therapeutic strategies. However, the design and realisation of an instrument that can precisely record weak bioelectrical signals in the presence of strong interference stemming from a noisy clinical environment is one of the most difficult challenges associated with the strategy of monitoring bioelectrical signals for diagnostic purposes. Moreover, since patients often have to cope with the problem of limited mobility being connected to bulky and mains-powered instruments, there is a growing demand for small-sized, high-performance and ambulatory biopotential acquisition systems in the Intensive Care Unit (ICU) and in High-dependency wards. Finally, to the best of our knowledge, there are no commercial, small, battery-powered, wearable and wireless recording-only instruments that claim the capability of recording electrocorticographic (ECoG) signals. Methods To address this problem, we designed and developed a low-noise (8 nV/√Hz), eight-channel, battery-powered, wearable and wireless instrument (55 × 80 mm2). The performance of the realised instrument was assessed by conducting both ex vivo and in vivo experiments. Results To provide ex vivo proof-of-function, a wide variety of high-quality bioelectrical signal recordings are reported, including electroencephalographic (EEG), electromyographic (EMG), electrocardiographic (ECG), acceleration signals, and muscle fasciculations. Low-noise in vivo recordings of weak local field potentials (LFPs), which were wirelessly acquired in real time using segmented deep brain stimulation (DBS) electrodes implanted in the thalamus of a non-human primate, are also presented. Conclusions The combination of desirable features and capabilities of this instrument, namely its small size (~one business card), its enhanced recording capabilities, its increased processing capabilities, its manufacturability (since it was designed using discrete off-the-shelf components), the wide bandwidth it offers (0.5–500 Hz) and the plurality of bioelectrical signals it can precisely record, render it a versatile and reliable tool to be utilized in a wide range of applications and environments.

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