Validation of Next Generation Catalyst Design Incorporating Advanced Materials and Processing Technology

2005 ◽  
Author(s):  
Sarento G. Nickolas ◽  
Philip B. Tuet ◽  
Jon G. McCarty ◽  
Suresh R. Vilayanur ◽  
Alberto E. Boleda ◽  
...  
Keyword(s):  
Performance Test ◽  
Technology Development ◽  
Catalyst Design ◽  
Operating Conditions ◽  
Advanced Materials ◽  
Next Generation ◽  
Load Range ◽  
Turbine Engine ◽  
Electrical Grid ◽  
Module Design

A Kawasaki Heavy Industries M1A-13X gas turbine engine equipped with a Xonon Cool Combustion® System was used to validate performance of a next generation catalyst module design incorporating advanced catalyst materials over 8000 hours of continuous operation. The unit ran unattended, 24 hours a day, 7 days a week connected to the electrical grid. NOx emissions were measured to be less than 2.5 ppm throughout the guaranteed operating load range (70–100%). CO emissions were measured to be less than 10 ppm; typically less than 1ppm across the same load range. The new catalyst module design incorporates features and technology developed during the past several years where durability was a primary focus. Performance test results from previous durability tests were used to develop theoretical predictive models. These models proved invaluable in determining the optimal catalyst formulation as well as the required operating conditions throughout the life of the combustion system. Successful validation of the new catalyst module design has led to incorporation of these advanced materials and design techniques in commercial products and prototype units. It is believed that continued technology development, as well as performance data gathered from field units, will support extending product life beyond the current guarantee of 8000 hours.

Technology Development Programs for the Advanced Turbine Systems Engine

1996 ◽  
Author(s):  
Ihor S. Diakunchak ◽  
Ronald L. Bannister ◽  
David J. Huber ◽  
D. Frank Roan
Keyword(s):  
Closed Loop ◽  
Technology Development ◽  
Combined Cycle ◽  
Advanced Materials ◽  
Development Programs ◽  
Turbine Engine ◽  
Design Concepts ◽  
Current State ◽  
Low Nox Combustion ◽  
Steam Cooling

This paper describes the technologies that are being developed or extended beyond the current state-of-the-art to achieve Advanced Turbine Systems (ATS) Program goals. The Westinghouse ATS plant is an advanced closed-loop enoled combined cycle, based on an advanced gas turbine engine incorporating novel design concepts and enhancements of existing technologies. The ATS engine is a fuel-flexible design operating nn natural gas with provisions fnr future conversion to coal or biomass fuels. It is based nn proven concepts employed in 501F and 501G engines. To achieve the required performance and reliability the engine will include closed-loop steam cooling, advanced materials and coatings, and enhanced component performance. To minimize NOx emissions, an ultra-low NOx combustion system will be incorporated. To ensure technical success, development programs are being conducted on the following: closed-loop steam cooling, advanced materials and coatings, component aerodynamic performance, flow visualization, optical diagnostics, combustion generated noise, and catalytic combustion.

IHX Design and Development for the Next Generation Nuclear Plant

2008 ◽  
Author(s):  
Scott R. Penfield ◽  
Renee Greyvenstein ◽  
Phillip L. Rittenhouse ◽  
James Nash
Keyword(s):  
Technology Development ◽  
Nuclear Plant ◽  
Operating Conditions ◽  
Design And Technology ◽  
Next Generation ◽  
Thin Sections ◽  
Compact Heat Exchangers ◽  
Corrosion Rates ◽  
Intermediate Heat Exchanger

This paper summarizes the results of a conceptual design study addressing the design and technology development requirements for a high-temperature intermediate heat exchanger (IHX) for the Next Generation Nuclear Plant (NGNP). Results of the study confirmed the incentives for compact heat exchangers and suggested new IHX configurations that provide for maintainability at the heat transfer module level. Scoping analyses provided encouragement that IHX life would not be limited by creep or fatigue effects, given the PBMR NGNP Heat Transport System architecture and operating conditions. However, corrosion rates implied by existing data are troubling for thin sections, and improved characterization of environmental effects was identified as a high priority for technology development.

Evaluation of Fuel Preparation Systems for Lean Premixing-Prevaporizing Combustors

1986 ◽  
Vol 108 (2) ◽  
pp. 391-395
Author(s):  
W. J. Dodds ◽  
E. E. Ekstedt
Keyword(s):  
System Design ◽  
Large Scale ◽  
Fuel Injection ◽  
Operating Conditions ◽  
Turbine Engine ◽  
Fuel Injectors ◽  
Design Concepts ◽  
Mixture Preparation ◽  
Design Variables ◽  
System Length

A series of tests was conducted to provide data for the design of premixing-prevaporizing fuel-air mixture preparation systems for aircraft gas turbine engine combustors. Fifteen configurations of four different fuel-air mixture preparation system design concepts were evaluated to determine fuel-air mixture uniformity at the system exit over a range of conditions representative of cruise operation for a modern commercial turbofan engine. Operating conditions, including pressure, temperature, fuel-air ratio, and velocity had no clear effect on mixture uniformity in systems which used low-pressure fuel injectors. However, performance of systems using pressure atomizing fuel nozzles and large-scale mixing devices was shown to be sensitive to operating conditions. Variations in system design variables were also evaluated and correlated. Mixture uniformity improved with increased system length, pressure drop, and number of fuel injection points per unit area. A premixing system compatible with the combustor envelope of a typical combustion system and capable of providing mixture nonuniformity (standard deviation/mean) below 15% over a typical range of cruise operating conditions was demonstrated.

Optimal State-Space Control of a Gas Turbine Engine

1992 ◽  
Vol 114 (4) ◽  
pp. 763-767 ◽  
Author(s):  
J. W. Watts ◽  
T. E. Dwan ◽  
C. G. Brockus
Keyword(s):  
State Space ◽  
Gas Turbine ◽  
State Space Model ◽  
Gas Turbine Engine ◽  
The State ◽  
Operating Conditions ◽  
Turbine Engine ◽  
Analog Control ◽  
Linear State ◽  
High Level

An analog fuel control for a gas turbine engine was compared with several state-space derived fuel controls. A single-spool, simple cycle gas turbine engine was modeled using ACSL (high level simulation language based on FORTRAN). The model included an analog fuel control representative of existing commercial fuel controls. The ACSL model was stripped of nonessential states to produce an eight-state linear state-space model of the engine. The A, B, and C matrices, derived from rated operating conditions, were used to obtain feedback control gains by the following methods: (1) state feedback; (2) LQR theory; (3) Bellman method; and (4) polygonal search. An off-load transient followed by an on-load transient was run for each of these fuel controls. The transient curves obtained were used to compare the state-space fuel controls with the analog fuel control. The state-space fuel controls did better than the analog control.

The Effect of Heat Transfer Coefficient Increase on Tip Clearance Control in H.P. Compressors in Gas Turbine Engine

2013 ◽  
Author(s):  
Godwin Ita Ekong ◽  
Christopher A. Long ◽  
Peter R. N. Childs
Keyword(s):  
Heat Transfer ◽  
Heat Transfer Coefficient ◽  
Transfer Coefficient ◽  
Gas Turbine ◽  
Time Constant ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Tip Clearance ◽  
Test Facility ◽  
Turbine Engine

Compressor tip clearance for a gas turbine engine application is the radial gap between the stationary compressor casing and the rotating blades. The gap varies significantly during different operating conditions of the engine due to centrifugal forces on the rotor and differential thermal expansions in the discs and casing. The tip clearance in the axial flow compressor of modern commercial civil aero-engines is of significance in terms of both mechanical integrity and performance. In general, the clearance is of critical importance to civil airline operators and their customers alike because as the clearance between the compressor blade tips and the casing increases, the aerodynamic efficiency will decrease and therefore the specific fuel consumption and operating costs will increase. This paper reports on the development of a range of concepts and their evaluation for the reduction and control of tip clearance in H.P. compressors using an enhanced heat transfer coefficient approach. This would lead to improvement in cruise tip clearances. A test facility has been developed for the study at the University of Sussex, incorporating a rotor and an inner shaft scaled down from a Rolls-Royce Trent aero-engine to a ratio of 0.7:1 with a rotational speed of up to 10000 rpm. The idle and maximum take-off conditions in the square cycle correspond to in-cavity rotational Reynolds numbers of 3.1×106 ≤ Reφ ≤ 1.0×107. The project involved modelling of the experimental facilities, to demonstrate proof of concept. The analysis shows that increasing the thermal response of the high pressure compressor (HPC) drum of a gas turbine engine assembly will reduce the drum time constant, thereby reducing the re-slam characteristics of the drum causing a reduction in the cold build clearance (CBC), and hence the reduction in cruise clearance. A further reduction can be achieved by introducing radial inflow into the drum cavity to further increase the disc heat transfer coefficient in the cavity; hence a further reduction in disc drum time constant.

scholarly journals Performance of novel dielectric barrier discharge reactor for biodiesel production from palm oil and ethanol

2018 ◽  
Vol 67 ◽  
pp. 02010 ◽  
Author(s):  
Sari Dafinah Ramadhani ◽  
Saphira Nurina Fakhri ◽  
Setijo Bismo
Keyword(s):  
Palm Oil ◽  
Performance Test ◽  
Plasma Reactor ◽  
Operating Conditions ◽  
Biodiesel Production ◽  
Molar Ratio ◽  
Synthesis Methods ◽  
Dbd Plasma ◽  
Spiral Coil ◽  
Biodiesel Synthesis

The disadvantages of conventional biodiesel synthesis trigger the birth of new biodiesel synthesis methods using the DBD plasma reactor. The conventional methods with homogeneous and heterogeneous catalysts have significant constraints that the formation of glycerol compounds in large enough quantities that require considerable energy. The aim of present experiment is to design DBD non-thermal plasma reactor coaxial pipe type and to do its performance test in converting biodiesel The feed stock used are palm oil, ethanol, and argon gas as plasma carrier. Such a chemical reactor, this plasma reactor is also influenced by reaction kinetics and hydrodynamic factors. From this research, it can be seen that the optimum feed and gas flowrate being operated is 1.64 and 41.67 mL/s. The plasma reactor is used in the form of a quartz glass tube surrounded by a SS-314 spiral coil as an outer electrode. The applied operating conditions are 1 : 1 molar ratio of methanol/oil, ambient temperature of 28 - 30 °C, and pressure 1 bar. From this performance test, it is found that this plasma reactor can be used to synthesize biodiesel from palm oil and methanol without catalyst, no formation of soap, and minimal byproducts.

scholarly journals Comprehensive report on Materials for Gas Turbine Engine Components

2019 ◽  
Vol 9 (2S2) ◽  
pp. 155-158
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Thermal Stresses ◽  
Prolonged Exposure ◽  
Raw Materials ◽  
Turbine Blades ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Turbine Engine ◽  
Engine Component

In the past three decades, it is very challenging for the researchers to design and development a best gas turbine engine component. Engine component has to face different operating conditions at different working environments. Nickel based superalloys are the best material to design turbine components. Inconel 718, Inconel 617, Hastelloy, Monel and Udimet are the common material used for turbine components. Directional solidification is one of the conventional casting routes followed to develop turbine blades. It is also reported that the raw materials are heat treated / age hardened to enrich the desired properties of the material implementation. Accordingly they are highly susceptible to mechanical and thermal stresses while operating. The hot section of the turbine components will experience repeated thermal stress. The halides in the combination of sulfur, chlorides and vanadate are deposited as molten salt on the surface of the turbine blade. On prolonged exposure the surface of the turbine blade starts to peel as an oxide scale. Microscopic images are the supportive results to compare the surface morphology after complete oxidation / corrosion studies. The spectroscopic results are useful to identify the elemental analysis over oxides formed. The predominant oxides observed are NiO, Cr2O3, Fe2O3 and NiCr2O4. These oxides are vulnerable on prolonged exposure and according to PB ratio the passivation are very less. In recent research, the invention on nickel based superalloys turbine blades produced through other advanced manufacturing process is also compared. A summary was made through comparing the conventional material and advanced materials performance of turbine blade material for high temperature performance.

scholarly journals Development of Ceramic Gas Turbine Components for the CGT301 Engine

1996 ◽  
Author(s):  
Mitsuru Hattori ◽  
Tsutomu Yamamoto ◽  
Keiichiro Watanabe ◽  
Masaaki Masuda
Keyword(s):  
Gas Turbine ◽  
Technology Development ◽  
Turbine Blades ◽  
High Heat ◽  
Turbine Engine ◽  
Development Organization ◽  
All Ceramic ◽  
New Energy ◽  
Ceramic Components ◽  
Resistant Ceramic

NGK Insulators, Ltd. (NGK) has undertaken the research and development on the fabrication processes of high-heat-resistant ceramic components for the CGT301, which is a 300kW recuperative industrial ceramic gas turbine engine. This program is under the New Sunshine Project, funded by the Ministry of International Trade and Industry (MITI), and has been guided by the Agency of Industrial Science & Technology (AIST) since 1988. The New Energy and Industrial Technology Development Organization (NEDO) is the main contractor. The fabrication techniques for ceramic components, such as turbine blades, turbine nozzles, combustor liners, gas-path parts, and heat exchanger elements, for the 1,200°C engine were developed by 1993. Development for the 1,350°C engine has been underway since 1994. The baseline conditions for fabricating of all ceramic components have been established. This paper reports on the development of ceramic gas turbine components, and the improved accuracies of their shapes as well as improved reliability from the results of the interim appraisal conducted in 1994.

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