scholarly journals Analysis of NOx Formation in a Hydrogen-Fueled Gas Turbine Engine

2009 ◽  
Vol 131 (3) ◽  
Author(s):  
Peter Therkelsen ◽  
Tavis Werts ◽  
Vincent McDonell ◽  
Scott Samuelsen
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Full Range ◽  
Gas Turbine Engine ◽  
System Level ◽  
Stable Operation ◽  
No Production ◽  
No Emission ◽  
Nox Formation ◽  
Turbine Engine

A commercially available natural gas fueled gas turbine engine was operated on hydrogen. Three sets of fuel injectors were developed to facilitate stable operation while generating differing levels of fuel∕air premixing. One set was designed to produce near uniform mixing while the others have differing degrees of nonuniformity. The emission performance of the engine over its full range of loads is characterized for each of the injector sets. In addition, the performance is also assessed for the set with near uniform mixing as operated on natural gas. The results show that improved mixing and lower equivalence ratio decrease NO emission levels as expected. However, even with nearly perfect premixing, it is found that the engine, when operated on hydrogen, produces a higher amount of NO than when operated with natural gas. Much of this attributed to the higher equivalence ratios that the engine operates on when firing hydrogen. However, even the lowest equivalence ratios run at low power conditions, higher NO was observed. Analysis of the potential NO formation effects of residence time, kinetic pathways of NO production via NNH, and the kinetics of the dilute combustion strategy used are evaluated. While no one mechanism appears to explain the reasons for the higher NO, it is concluded that each may be contributing to the higher NO emissions observed with hydrogen. In the present configuration with the commercial control system operating normally, it is evident that system level effects are also contributing to the observed NO emission differences between hydrogen and natural gas.

scholarly journals Analysis of NOx Formation in a Hydrogen Fueled Gas Turbine Engine

2008 ◽  
Author(s):  
Peter Therkelsen ◽  
Tavis Werts ◽  
Vincent McDonell ◽  
Scott Samuelsen
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Full Range ◽  
Gas Turbine Engine ◽  
System Level ◽  
Stable Operation ◽  
No Production ◽  
No Emission ◽  
Nox Formation ◽  
Turbine Engine

A commercially available natural gas fueled gas turbine engine was operated on hydrogen. Three sets of fuel injectors were developed to facilitate stable operation while generating differing levels of fuel/air premixing. One set was designed to produce near uniform mixing while the others have differing degrees of non-uniformity. The emissions performance of the engine over its full range of loads is characterized for each of the injector sets. In addition, the performance is also assessed for the set with near uniform mixing as operated on natural gas. The results show that improved mixing and lower equivalence ratio decreases NO emission levels as expected. However, even with nearly perfect premixing, it is found that the engine, when operated on hydrogen, produces a higher amount of NO than when operated with natural gas. Much of this attributed to the higher equivalence ratios that the engine operates on when firing hydrogen. However, even at the lowest equivalence ratios run at low power conditions, higher NO was observed. Analysis of the potential NO formation effects of residence time, kinetic pathways of NO production via NNH, and the kinetics of the dilute combustion strategy used are evaluated. While no one mechanism appears to explain the reasons for the higher NO, it is concluded that each may be contributing to the higher NO emissions observed with hydrogen. In the present configuration with the commercial control system operating normally, it is evident that system level effects are also contributing to the observed NO emission differences between hydrogen and natural gas.

A Simple Thermal Model of Bearings With Transient Effects

2010 ◽  
Author(s):  
Karleine M. Justice ◽  
Ian Halliwell ◽  
Jeffrey S. Dalton
Keyword(s):  
Steady State ◽  
Gas Turbine ◽  
Thermal Management ◽  
Heat Load ◽  
Transient Behavior ◽  
Gas Turbine Engine ◽  
System Level ◽  
Lubrication System ◽  
Transient Effects ◽  
Turbine Engine

In thermal management, system-level models provide an understanding of interactions between components and integration constraints — issues which are exacerbated by tighter coupling in both real life and simulation. A simple model of the steady-state thermal characteristics of the bearings in a two-spool turbofan engine has been described in previous work [1], where it was compared with a more comprehensive tribology-based simulation. Since failure is more likely to occur during transient rather than steady-state operating conditions, it is important that transient behavior is also studied. Therefore, development of models capable of capturing transient system-level performance in air vehicles is critical. In the current paper, the former simple model is used for the generation of a method to replicate the transient effects of heat loads within the lubrication system of a gas turbine engine. The simple engine model that defined the lubrication system is representative of a twin-spool, mid-size, high bypass ratio turbofan used in commercial transport. In order to demonstrate the range and versatility of the parametric heat load model, the model is now applied to the transient operation of a low-thrust unmanned aerial vehicle (UAV) engine, similar to that found on the Global Hawk. There are five separate bearings in the oil loop model and four separate oil sump locations. Contributions to the heat load calculations are heat transfer through the bearing housings and friction caused by station temperatures and shaft speeds, respectively. The lubrication system has been simplified by applying general assumptions for a proof-of-concept of the new transient parametric model. The fuel flow rate for the fuel-cooled oil cooler (FCOC) is set via the full authority digital electronic control (FADEC) in the transient engine model which is coupled to the parametric heat load model. Initially, it is assumed that total heat transfer from the bearings to the oil correspond to oil temperature changes of 150–250°F (83–139°C). The results show that successful modeling of the transient behavior on the thermal effects in the bearings of a gas turbine engine using the MATLAB/Simulink environment have been achieved. This is a valuable addition to the previous steady-state simulation, and the combined tools may be used as part of a more sophisticated thermal management system. Because it is so simple and scalable, the tool enables thermal management issues to be addressed in the preliminary design phase of a gas turbine engine development program.

Lube Oil and Bearing Thermal Management System

2009 ◽  
Author(s):  
Karleine M. Justice ◽  
Jeffrey S. Dalton ◽  
Ian Halliwell ◽  
Stephen Williamson
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Thermal Management ◽  
Gas Turbine Engine ◽  
System Level ◽  
Engine Oil ◽  
Management Systems ◽  
Lubrication System ◽  
Turbine Engine ◽  
Heat Loads

Recent improvements in technology have enabled the development of models capable of capturing performance interactions in the thermal management of air vehicle systems. Such system level models are required for better understanding of integration constraints and interactions, and are becoming increasingly important because of the need for tighter coupling between the components of thermal management systems. The study described here integrates current engine modeling capabilities with an improved, more comprehensive thermal management simulation. More specifically, the current effort evaluates the heat loads associated with the lubrication system of a gas turbine engine. The underlying engine model represents a mid-size, two-spool, subsonic transport engine. The architecture of the model is adaptable to other two-spool turbine engines and missions. Mobil Avrex S Turbo 256 engine oil is used as the lubrication medium. The model consists of five bearing heat loads. Within the engine flowpath, local temperatures and the appropriate rotational speeds are the only parameters pertinent to the heat load calculations. General assumptions have been made to simplify the representation of the lubrication system. Fuel properties into the heat exchanger are assumed. A gear box attached to the high-speed shaft operates both supply pump and scavenge pump and sends compressed air to the oil reservoir. Once the oil is distributed to the bearings, the scavenge pump collects and sends it through a filter and a fuel/oil heat exchanger before it is remixed with the contents of the reservoir. A MATLAB/Simulink modeling environment provides a general approach that may be applied to the thermal management of any engine. As a result of this approach, the new model serves as a starting point for a flexible architecture that can be modified as more detailed specifications or data are made available. In this paper, results from the simple model are compared to a more comprehensive tribology-based analysis. The results demonstrate its successful application to a typical mission, based on very limited data. In general, these results will allow system designers to conduct preliminary analyses and trade studies of gas turbine engine thermal management systems.

Evaluation of the Effects of Carbon to Hydrogen Ratio and Sulfur Level in Fuel on Particulate Matters From Micro Gas Turbine Engine

2013 ◽  
Vol 136 (2) ◽  
Author(s):  
Takeshi Akamatsu ◽  
Richard Hack ◽  
Vince McDonell ◽  
Scott Samuelsen
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Atomic Ratio ◽  
Gas Turbine Engine ◽  
Engine Exhaust ◽  
Turbine Engine ◽  
Micro Gas Turbine ◽  
Sulfur Level ◽  
Gaseous Sulfur ◽  
Test Fuel

The present work investigated the effects of fuel components on particulate matter (PM) from a natural gas-fueled micro gas turbine engine. A variety of fuel compositions were prepared considering atomic ratio of hydrogen to carbon (H/C ratio) and sulfur level. In the first test, controlled amounts of propane were injected into natural gas to establish H/C ratios between 3.23 and 3.99. In the second test, fuel-bound sulfur was scrubbed and controlled amounts of methyl mercaptan were injected into natural gas to establish sulfur levels between 0.0 ppm and 12.9 ppm. Sonic orifices were used for H/C ratio and fuel sulfur management. In each test, PM was collected from engine exhaust and analyzed. In the second test, total gaseous sulfur in the exhaust was also measured to establish the ratio of PM and gaseous sulfur formed from fuel sulfur. Test result showed no correlation between H/C ratio and PM, and strong correlation between fuel sulfur and PM. 82.4% of fuel sulfur contributed to form gaseous sulfur and 17.6% contributed to form PM in the exhaust. An increase of 1.0 ppm fuel sulfur produced an increase of approximately 4.7μg/m3 PM. By removing fuel-bound sulfur, PM levels from micro gas turbine engine exhaust are comparable to ambient levels of PM.

Design and Development of a Family of Natural Gas Compressors for a 3000-Hp Gas Turbine Engine

1972 ◽  
Author(s):  
J. G. Batman
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Aerodynamic Characteristics ◽  
Gas Turbine Engine ◽  
Flow Conditions ◽  
Turbine Engine ◽  
Wide Range ◽  
Selection Of ◽  
Mechanical Arrangement

A family of natural gas compressors is designed and developed for application with the Solar Centaur T-3000 gas turbine engine. These compressors are capable of matching the power and speed of the engine over a wide range of compressor suction pressure and flow conditions. Design of these compressors includes analysis of possible aerodynamic configurations, and selection of the mechanical arrangement to best meet the expected installation requirements. Aerodynamic characteristics, bearing and seal performance, impeller integrity, and housing rigidity are all developed in a test program prior to shipment of the first compressors. Follow-up of the first field operation further verifies that the design objectives had been met.

WR21 Intercooled Recuperated (ICR) Gas Turbine Engine System Level Development Test Program Summary

2000 ◽  
Author(s):  
Jay T. Janton ◽  
Chai Uawithya
Keyword(s):  
Gas Turbine ◽  
Cooling System ◽  
Gas Turbine Engine ◽  
System Level ◽  
Second Phase ◽  
Gas Generator ◽  
Endurance Test ◽  
Test Program ◽  
Engine Operation ◽  
Turbine Engine

The WR21 Intercooled Recuperated (ICR) Gas Turbine engine has undergone system level development testing from July of 1994 to December 1999. There have been a total of ten engine builds and 2126 hours of engine operation performed through December of 1999. A significant number of unique development tests (experiments) have been performed over the ten engine builds. The last development test just completed and that was a USN specified 500-hour endurance test from 4 October through 16 December of 1999. All the development testing to date has been performed at the Defense Evaluation and Research Agency (DERA), Pyestock, England which is part of the UK Ministry of Defense (MOD). The last 500-hour endurance test was performed at the Advanced Propulsion & Power Generation Test Site (APPGTS) located at the Naval Surface Warfare Center Carderock Division (NSWCCD), Philadelphia, PA. The system level testing performed has evaluated the gas generator, power turbine, enclosure systems, recuperator, intercooler, and engine electronic controller (EEC). The enclosure systems include two off-engine skids (lube oil module and Intercooler Heat Exchanger module), accessory gearbox, fire protection system, enclosure cooling system, water wash, structureborne and airborne noise, fuel system and air start system. A three-phase development test strategy was employed. The first phase was to demonstrate the ICR technology and identify the highest-risk areas. Due to the unique challenges introduced by the intercooler, recuperator, variable area nozzles, and new EEC the test program was continually reviewed and revised. The second phase focused on component and system improvements. The final phase is the verification of the ICR in a 500-hr endurance test. At the completion of development testing a final design review will be held (DR5), followed by qualification testing. The qualification tests will include a 3150-hr endurance test and shock test. This paper summarizes and discusses the major tests performed during the development phases. The plan for the final development 500-hr endurance test and 3150-hr qualification test will be presented.

Ceramic Gas-Turbine 2.5 MW Engine for Gas Industry Application in Russia

2000 ◽  
Author(s):  
A. V. Soudarev ◽  
A. A. Souryaninov ◽  
V. V. Grishaev ◽  
V. Ya. Podgorets ◽  
V. Yu. Tikhoplav ◽  
...  
Keyword(s):  
High Temperature ◽  
Natural Gas ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Gas Industry ◽  
Turbine Engine ◽  
Metal Ceramic

Some important aspects of attacking the problem of development of a low-NOx high-temperature metal-ceramic 2.5 MW gas-turbine engine (GTE) for stationary application, in particular, gas industry of Russia are discussed in the paper. At present, to drive the natural gas blower for gas industry in Russia gas-turbine units (GTU) are mainly used.

The Thermal Impact of Using Syngas as Fuel in the Regenerator of Regenerative Gas Turbine Engine

2009 ◽  
Author(s):  
Luciana M. Oliveira ◽  
Marco A. R. Nascimento ◽  
Gene´sio J. Menon
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Thermal Characteristics ◽  
Primary Energy ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Gasification Process ◽  
Survival And Development ◽  
Heat Value ◽  
The Cost

Environment and energy are driven force of human survival and development. Nowadays the use of primary energy comprises mostly mineral fuels, which have limited reserves and whose utilization may cause serious environmental impacts. Attention has been paid to discover clean and renewable resources such as syngas which is an important renewable source of energy and is environment friendly. The use of syngas from biomass gasification process as fuel in regenerative gas turbine causes an increase in turbine exhaust mass flow and a change in the gas composition due to a low heat value. As a result, the regenerator changes its size, thermal characteristics, weight and cost compared with the use of natural gas as fuel. The aim of this work is to assess the thermal performance, the size and the cost of the recuperator of 600 kW regenerative gas turbine engine when designed for syngas and natural gas. Two different types of surfaces, Cross-Corrugated and Undulated-Corrugated, are used for analysis. The results are shown, comparing heat transfer coefficient, effectiveness, pressure loss, size and cost for syngas and natural gas.

The Thermal Impact of Using Syngas as Fuel in the Regenerator of Regenerative Gas Turbine Engine

2010 ◽  
Vol 132 (6) ◽  
Author(s):  
Luciana M. Oliveira ◽  
Marco A. R. Nascimento ◽  
Genésio J. Menon
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Thermal Characteristics ◽  
Primary Energy ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Gasification Process ◽  
Survival And Development ◽  
Heat Value ◽  
The Cost

Environment and energy are driven forces of human survival and development. Nowadays the use of primary energy comprises mostly mineral fuels, which have limited reserves and whose utilization may cause serious environmental impacts. Attention has been paid to discover clean and renewable resources such as syngas, which is an important renewable source of energy and is environment friendly. The use of syngas from biomass gasification process as fuel in regenerative gas turbine causes an increase in turbine exhaust mass flow and a change in the gas composition due to a low heat value. As a result, the regenerator changes its size, thermal characteristics, weight, and cost compared with the use of natural gas as fuel. The aim of this work is to assess the thermal performance, the size, and the cost of the recuperator of a 600 kW regenerative gas turbine engine when designed for syngas and natural gas. Two different types of surfaces, cross-corrugated and undulated-corrugated, are used for analysis. The results are shown, comparing heat-transfer coefficient, effectiveness, pressure loss, size, and cost for syngas and natural gas.

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