scholarly journals ПАРАМЕТРИЧЕСКАЯ ИДЕНТИФИКАЦИЯ И ОПТИМИЗАЦИЯ ВЫСОКОТЕМПЕРАТУРНЫХ ТЕНЗОРЕЗИСТОРОВ

2020 ◽  
pp. 91-99
Author(s):  
Юрий Алексеевич Гусев
Keyword(s):  
Gas Turbines ◽  
Gas Flow ◽  
Parametric Identification ◽  
Fine Tuning ◽  
Measuring System ◽  
Working Fluid ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Level Lines ◽  
Single Sensor

The development of gas turbine engines (GTE) is inextricably linked with an increase in their main characteristics. In this case, the parameters of the working fluid (in particular, the temperature of the gas flow) and the intensity of loads on the structural elements increase. The strength reliability of highly heated GTE elements is a factor that determines the life of the engine as a whole. The most common cases of damage to GTE elements are caused by static and vibration stresses and mainly relate to the blades of gas turbines operating at temperatures up to 1200оС. Vibration stresses of individual GTE parts can be determined only experimentally during GTE testing and fine-tuning. Their values are determined at individual points of the surfaces of parts by the values of directly measured deformations. At present, the main means for determining the vibration deformations of GTE elements are resistance strain gauges. In the process of testing, the information generated by the strain gages makes it possible to determine not only the dynamic deformation but also the static and dynamic temperature of the blade at the place where the strain gauge is installed. A technique is proposed for the parametric identification of a high-temperature tensoresistor (HTTR), based on the representation of the analyzed HTTR and affecting its state, as some, in the general case, non-linear measuring system. The structural and mathematical models of HTTR are considered, in which both temperature and strain are simultaneously measured using a single sensor element. An original technique is proposed for studying the reliability of the results of HTTR parametric identification. It is proved that the ellipsoidal character of the level lines of residual function, as well as the absence of an extremum region together with the point nature of the minimum, indicate the practical identifiability of the tensometric system. The proposed technique allows a quantitative and qualitative analysis of the effect of shunting on the accuracy of HTTR readings. This technique can also be used to create new types of insulating materials intended for HTTR insulator substrates. This method presents a possibility of the measurement deformation and temperature of element thermal using single platinum-based tensometer sensor.

Development of Ceramic Heat Exchangers for Indirect Fired Gas Turbines

1982 ◽  
Author(s):  
W. T. Bakker ◽  
D. Kotchick
Keyword(s):  
Heat Exchanger ◽  
Heat Exchangers ◽  
Gas Turbines ◽  
Large Scale ◽  
Working Fluid ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Short Term ◽  
The Status

Utilizing dirty fuels such as coal in gas turbine engines requires that heat input to the cycle working fluid occur through a heat exchanger. For high cycle efficiencies such a heat exchanger must operate in the 700–1400 KPA, 1100–1200°C (100–200 psi, 2000–2200°F) range. In this temperature range, ceramic heat exchangers are required. Ceramic heat exchangers that can operate in this regime have been under development for several years on a very modest scale. These programs are briefly reviewed. Major material issues are reviewed and the status of each is presented. Mechanical reliability and joining technology have been successfully demonstrated in short term tests. Long-term durability and the manufacturing technology to produce large scale components reproducibly remains to be demonstrated in the future.

scholarly journals Progress in Novel Electrodeposited Bond Coats for Thermal Barrier Coating Systems

Materials ◽  
2021 ◽  
Vol 14 (15) ◽  
pp. 4214
Author(s):  
Kranthi Kumar Maniam ◽  
Shiladitya Paul
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Gas Turbines ◽  
High Performance ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Potential Cost ◽  
Bond Coats ◽  
Barrier Coating

The increased demand for high performance gas turbine engines has resulted in a continuous search for new base materials and coatings. With the significant developments in nickel-based superalloys, the quest for developments related to thermal barrier coating (TBC) systems is increasing rapidly and is considered a key area of research. Of key importance are the processing routes that can provide the required coating properties when applied on engine components with complex shapes, such as turbine vanes, blades, etc. Despite significant research and development in the coating systems, the scope of electrodeposition as a potential alternative to the conventional methods of producing bond coats has only been realised to a limited extent. Additionally, their effectiveness in prolonging the alloys’ lifetime is not well understood. This review summarises the work on electrodeposition as a coating development method for application in high temperature alloys for gas turbine engines and discusses the progress in the coatings that combine electrodeposition and other processes to achieve desired bond coats. The overall aim of this review is to emphasise the role of electrodeposition as a potential cost-effective alternative to produce bond coats. Besides, the developments in the electrodeposition of aluminium from ionic liquids for potential applications in gas turbines and the nuclear sector, as well as cost considerations and future challenges, are reviewed with the crucial raw materials’ current and future savings scenarios in mind.

Design, Development and Application of Vehicle Gas Turbine Engines

1966 ◽  
Vol 181 (1) ◽  
pp. 149-172
Author(s):  
P. A. Phillips ◽  
Peter Spear
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Low Cost ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Development ◽  
Turbine Engine ◽  
Wide Range ◽  
Cycle Temperature

After briefly summarizing worldwide automotive gas turbine activity, the paper analyses the power plant requirements of a wide range of vehicle applications in order to formulate the design criteria for acceptable vehicle gas turbines. Ample data are available on the thermodynamic merits of various gas turbine cycles; however, the low cost of its piston engine competitor tends to eliminate all but the simplest cycles from vehicle gas turbine considerations. In order to improve the part load fuel economy, some complexity is inevitable, but this is limited to the addition of a glass ceramic regenerator in the 150 b.h.p. engine which is described in some detail. The alternative further complications necessary to achieve satisfactory vehicle response at various power/weight ratios are examined. Further improvement in engine performance will come by increasing the maximum cycle temperature. This can be achieved at lower cost by the extension of the use of ceramics. The paper is intended to stimulate the design application of the gas turbine engine.

Determination of Cycle Configuration of Gas Turbines and Aircraft Engines by Optimization Procedure

1990 ◽  
Author(s):  
Yoshiharu Tsujikawa ◽  
Makoto Nagaoka
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Specific Impulse ◽  
Optimization Procedure ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Aircraft Engines ◽  
Scramjet Engine ◽  
Aero Engines

This paper is devoted to the analyses and optimization of simple and sophisticated cycles, particularly for various gas turbine engines and aero-engines (including scramjet engine) to achive the maximum performance. The optimization of such criteria as thermal efficiency, specific output and total performance for gas turbine engines, and overall efficiency, non-dimensional thrust and specific impulse for aero-engines have been performed by the optimization procedure with multiplier method. The comparisons of results with analytical solutions establishes the validity of the optimization procedure.

scholarly journals Inlet Air Fogging of Marine Gas Turbine in Power Output Loss Compensation

2015 ◽  
Vol 22 (4) ◽  
pp. 53-58 ◽  
Author(s):  
Zygfryd Domachowski ◽  
Marek Dzida
Keyword(s):  
Gas Turbine ◽  
Power Output ◽  
Gas Turbines ◽  
Evaporative Cooling ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Output Loss ◽  
Direct Evaporative Cooling ◽  
Loss Compensation ◽  
The World

Abstract The use of inlet air fogging installation to boost the power for gas turbine engines is widely applied in the power generation sector. The application of fogging to mechanical drive is rarely considered in literature [1]. This paper will cover some considerations relating to its application for gas turbines in ship drive. There is an important evaporative cooling potential throughout the world, when the dynamic data is evaluated, based on an analysis of coincident wet and dry bulb information. This data will allow ships’ gas turbine operators to make an assessment of the economics of evaporative fogging. The paper represents an introduction to the methodology and data analysis to derive the direct evaporative cooling potential to be used in marine gas turbine power output loss compensation.

Inlet Fogging of Gas Turbine Engines: Part B — Fog Droplet Sizing Analysis, Nozzle Types, Measurement and Testing

2002 ◽  
Author(s):  
Mustapha Chaker ◽  
Cyrus B. Meher-Homji ◽  
Thomas Mee
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Measurement Techniques ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Size Measurement ◽  
The Past ◽  
Testing Method ◽  
Measurement And Testing ◽  
Experimental And Theoretical Studies

The inlet fogging of gas turbine engines for power augmentation has seen increasing application over the past decade yet not a single technical paper treating the physics and engineering of the fogging process, droplet size measurement, droplet kinetics, or the duct behavior of droplets, from a gas turbine perspective, is available. This paper provides the results of extensive experimental and theoretical studies conducted over several years, coupled with practical aspects learned in the implementation of nearly 500 inlet fogging systems on gas turbines ranging in power from 5 to 250 MW. Part B of the paper treats the practical aspects of fog nozzle droplet sizing, measurement and testing presenting the information from a gas turbine fogging perspective. This paper describes the different measurement techniques available, covers design aspects of nozzles, provides experimental data on different nozzles and provides recommendations for a standardized nozzle testing method for gas turbine inlet air fogging.

Inlet Fogging of Gas Turbine Engines: Part A — Theory, Psychrometrics and Fog Generation

2000 ◽  
Author(s):  
Cyrus B. Meher-Homji ◽  
Thomas R. Mee
Keyword(s):  
Gas Turbine ◽  
Air Temperature ◽  
Gas Turbines ◽  
State Of The Art ◽  
Ambient Air ◽  
Process Industry ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Strong Function ◽  
Turbine Output

Gas Turbine output is a strong function of the ambient air temperature with power output dropping by 0.3–0.5 % for every 1°F rise in ambient temperature. This loss in output presents a significant problem to utilities, cogenerators and IPPs when electric demands are high during the hot months. In the petrochemical and process industry, the reduction in output of mechanical drive gas turbines curtails plant output. One way to counter this drop in output is to cool the inlet air. The paper contrasts the traditional evaporative cooling technique with direct inlet fogging. The state of the art relating to fog generation and psychrometrics of inlet fogging are described.

Fuel Flexible Rich Catalytic Lean Burn System for Low BTU Fuels

2013 ◽  
Author(s):  
Sandeep K. Alavandi ◽  
Shahrokh Etemad ◽  
Benjamin D. Baird
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Energy Content ◽  
Methane Content ◽  
Combustion Stability ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Waste Streams ◽  
Lean Burn ◽  
Process Waste

Limited fuel resources, increasing energy demand, and stringent emission regulations are drivers to evaluate process off-gases or process waste streams as fuels for power generation. Often these process waste streams have low energy content and their operability in gas turbines leads to issues such as unstable or incomplete combustion and changes in acoustic response. Due to above reasons, these fuels cannot be used directly without modifications or efficiency penalties in gas turbine engines. To enable the use of the wide variety of ultra-low and low Btu fuels in gas turbine engines, a rich catalytic lean burn (RCL®) combustion system was developed and tested in a subscale high pressure (10 atm.) rig. Previous work has shown promise with fuels such as blast furnace gas (BFG) with Lower Heating Value (LHV) of 3.1 MJ/Nm3 (85 Btu/scf). The current testing extends the limits of RCL® operability to other weak fuels by further modifying and improving the injector to achieve enhanced flame stability. Fuels containing low methane content such as weak natural gas with an LHV of 6.5 MJ/Nm3 (180 Btu/scf) to fuels containing higher methane content such as landfill gas with an LHV of 21.1 MJ/Nm3 (580 Btu/scf) were tested. These fuels demonstrated improved combustion stability with an extended turndown (defined as the difference between catalytic and non-catalytic lean blow out) of 140°C–170°C (280°F–340°F) with CO and NOx emissions lower than 5 ppm corrected to 15% O2.

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