USE OF VACUUM MICROGAS TURBINE PLANTS FOR HEATPOWER SUPPLY OF LOCAL OBJECTS

2020 ◽  
Vol 4 (1) ◽  
pp. 42-48
Author(s):  
A.V. DOLOGLONYAN ◽  
D.S. STREBKOV ◽  
V.T. MATVIIENKO ◽  
I.N. STACENKO
Keyword(s):  
Pressure Ratio ◽  
Simple Cycle ◽  
Specific Power ◽  
Ratio Increase ◽  
Turbine Expansion ◽  
Optimum Parameters ◽  
Compressor Pressure Ratio

Consideration subject in article are vacuum cycles of microgas turbine plants (MGTP) for the purpose of studying of their profitability and perspectives of use for heatpower supply of local objects. Vacuum MGTP of a simple cycle and with warmth regeneration is investigated. Optimum parameters of cycles – ratio of turbine expansion and regeneration ratio are found. It is established that profitability of MGTP with regeneration of warmth is higher in comparison with MGTP of a simple cycle almost twice, specific power decreases approximately by 1,35 times. By virtue of profitability and smaller values of compressor pressure ratio increase of the microturbine it is reasonable to apply in MGTP of a vacuum cycle with warmth regeneration.

Heat-Exchanged Propulsion Gas Turbines: A Candidate for Future Lower SFC and Reduced-Emission Military and Civil Aeroengines

2009 ◽  
Author(s):  
Colin F. McDonald ◽  
Colin Rodgers
Keyword(s):  
Gas Turbines ◽  
High Efficiency ◽  
Pressure Ratio ◽  
Thermodynamic Cycle ◽  
Simple Cycle ◽  
Specific Power ◽  
Operational Experience ◽  
Fuel Cost ◽  
Turbofan Engines ◽  
Fuel Burn

After seven decades of service the evolution of simple cycle propulsion gas turbines continues with emphasis now being placed on reduced fuel burn, lower emissions, and less noise. With compressor and turbine efficiencies near plateauing, and turbine inlet temperatures paced by materials and blade cooling technologies, improvements in SFC, specific power and weight for conventional engines (including small turboprop, and turboshaft engines and larger turbofans) will likely be incremental compared with the past. With retention of the simple cycle both evolutionary and revolutionary approaches are being taken by the aeroengine industry to improve performance, particularly reduced fuel burn in an era of high fuel cost. In this paper a further step is suggested, that is in concert with meeting performance, economic, and environmental goals of future aeroengines, namely the use of a more complex thermodynamic cycle involving recuperation for turboprop and turboshaft engines, and intercooling together with recuperation for higher pressure ratio turbofan engines. The idea of heat exchanged propulsion gas turbines is not new, but the many concepts identified from studies done periodically over the last 65 years, including the few engines that were static tested and one test flown, didn’t find acceptance in an era of low fuel cost and concerns about recuperator integrity and reliability. With today’s very high fuel cost there is current interest in this type of engine because of its potential for low SFC and reduced emissions. In this paper potential applications are summarized and the features of various heat exchanged aeroengine design concepts together with projected performance are presented. Included is a discussion on the various issues that must be resolved before they enter service. A postulated deployment scenario is suggested with engines initially developed to meet military aviation needs, such as recuperated turboprop and turbofan engines for extended range UAV’s, followed by a recuperated turboshaft engine for a helicopter. Operational experience and demonstrated reliability from these would pave the way for high efficiency ICR turbofan engines for military and civil aircraft service sometime after the year 2020.

scholarly journals The Constant Volume Gas Turbine: A Thermodynamic Assessment

1974 ◽  
Author(s):  
M. Zockel
Keyword(s):  
Heat Exchanger ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Constant Pressure ◽  
Pressure Ratio ◽  
Constant Volume ◽  
Specific Power ◽  
Inlet Temperature ◽  
Turbine Efficiency ◽  
Compressor Pressure Ratio

A quasi-steady-state analysis is made of the performance of a gas-turbine working with intermittent, constant volume combustion. Variables considered include inlet temperature, compressor pressure ratio, scavenge ratio, combustion time, heat exchanger thermal ratio. Characteristics are computed over a full loading range. Computations are based on turbines having the following behavior: (a) constant turbine efficiency, (b) characteristics of a multistage axial turbine, and (c) characteristics of a single-stage radial turbine. The analysis indicates that the constant volume gas turbine has advantages in thermal efficiency, specific power and part load performance over constant pressure gas turbines operating at the same compressor pressure ratio and turbine inlet temperature. However, the addition of a heat exchanger shows less advantage when applied to a constant volume than to a constant pressure engine.

scholarly journals Optimum Peak Cycle Pressure for the Intercooled-Supercharged Gas Turbine Engine

1995 ◽  
Author(s):  
Lin-Shu Wang ◽  
Lili Pan
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Pressure Ratio ◽  
Optimization Procedure ◽  
Simple Cycle ◽  
Specific Power ◽  
Turbine Engine ◽  
Performance Curves ◽  
Pressure Maximum ◽  
Cycle Temperature

Performance (thermal efficiency and mass specific power) of a simple-cycle gas turbine increases monotonically with peak cycle temperatures, for a given peak cycle temperature, the performance also depends on cycle pressure ratio or peak cycle pressure: maximum performance (both mass specific power and thermal efficiency near their maximum values) is achieved in a narrow range of optimum peak cycle pressures. A recently proposed intercooled-supercharged cycle gas turbine differs from the conventional intercooled cycle gas turbine in their intercooler placement. This paper studies the performance of the proposed cycle based on a reformulated intercooling-supercharging optimization procedure. The intercooler placement is defined by a new parameter, the intercooling supercharging parameter. In terms of the intercooling supercharging parameter and the peak cycle pressure, a map of performance curves (efficiency versus specific power) is constructed, which discloses a higher performance zone for the proposed cycle. This performance zone is defined by optimal intercooler placement and peak cycle pressures that are considerably higher than the simple-cycle’s optimum peak cycle pressures. At these higher pressures, the intercooled-supercharged-cycle gas turbine can achieve a new level of performance: a 20% to 30% improvement over the simple cycle in thermal efficiency and mass specific power.

Optimization of a Turboprop UAV for Maximum Loiter and Specific Power Using Genetic Algorithm

2016 ◽  
Vol 33 (3) ◽  
Author(s):  
Ali Dinc
Keyword(s):  
Genetic Algorithm ◽  
Pressure Ratio ◽  
Specific Power ◽  
Multi Objective Optimization ◽  
Multi Objective ◽  
Burner Exit ◽  
First Case ◽  
Turboprop Engine ◽  
Compressor Pressure Ratio ◽  
Aerial Vehicle

AbstractIn this study, a genuine code was developed for optimization of selected parameters of a turboprop engine for an unmanned aerial vehicle (UAV) by employing elitist genetic algorithm. First, preliminary sizing of a UAV and its turboprop engine was done, by the code in a given mission profile. Secondly, single and multi-objective optimization were done for selected engine parameters to maximize loiter duration of UAV or specific power of engine or both. In single objective optimization, as first case, UAV loiter time was improved with an increase of 17.5% from baseline in given boundaries or constraints of compressor pressure ratio and burner exit temperature. In second case, specific power was enhanced by 12.3% from baseline. In multi-objective optimization case, where previous two objectives are considered together, loiter time and specific power were increased by 14.2% and 9.7% from baseline respectively, for the same constraints.

scholarly journals Comprehensive Performance Analysis for the Rotating Detonation-Based Turboshaft Engine

2020 ◽  
Vol 2020 ◽  
pp. 1-11
Author(s):  
Zifei Ji ◽  
Ruize Duan ◽  
Renshuai Zhang ◽  
Huiqiang Zhang ◽  
Bing Wang
Keyword(s):  
Performance Analysis ◽  
Fuel Consumption ◽  
Thermal Efficiency ◽  
Pressure Ratio ◽  
Specific Fuel Consumption ◽  
Specific Power ◽  
Compressor Pressure Ratio ◽  
Comprehensive Performance ◽  
Turboshaft Engine ◽  
Rotating Detonation

The potential advantages of rotating detonation combustion are gradually approved, and it is becoming a stable and controllable energy conversion way adopted to the propulsion devices or ground-engines. This study focuses on the rotating detonation-based turboshaft engine, and the architecture is presented for this form of engine with compatibility between the turbomachinery and rotating detonation combustor being realized. The parametric performance simulation model for the rotating detonation-based turboshaft engine are developed. Further, the potential performance benefits as well as their generation mechanism are revealed, based on the comprehensive performance analysis of the rotating detonation-based turboshaft engine. Comparisons between the rotating detonation turboshaft engine and the conventional one reveal that the former holds significant improvements in specific power, thermal efficiency, and specific fuel consumption at lower compressor pressure ratios, and these improvements decrease with the increase of compressor pressure ratio and increase as turbine inlet temperature increases. The critical compressor pressure ratio corresponding to the disappearance of specific power improvement is higher than that corresponding to the disappearance of thermal efficiency and specific fuel consumption. These critical compressor pressure ratios are positively correlated with flight altitude and negatively correlated with flight velocity. The conductive research conclusion is guidable for the design and engineering application of rotating detonation-based engines.

Design and Off-Design Characteristics of the Alternative Recuperated Gas Turbine Cycle With Divided Turbine Expansion

2006 ◽  
Vol 129 (2) ◽  
pp. 428-435 ◽  
Author(s):  
Sung Hoon Hwang ◽  
Soo Hyoung Yoon ◽  
Tong Seop Kim
Keyword(s):  
Mechanical Design ◽  
Pressure Ratio ◽  
Variable Speed ◽  
Part Load ◽  
Turbine Expansion ◽  
Compressor Pressure Ratio ◽  
Design Characteristics ◽  
Inlet Conditions ◽  
Design Analyses ◽  
Gas Turbine Cycle

In order to fully address the characteristics of the alternative recuperated cycle with divided turbine expansion, both design and off-design analyses have been performed. Two types of mechanical design are assumed: two shaft and single shaft. In particular, optimal pressure ratio division between the high- and low-pressure turbines is evaluated for the single-shaft configuration. It is predicted that the alternative recuperated cycle hardly exhibits sensible design efficiency advantage over the conventional recuperated cycle for moderate turbine inlet conditions and with usual component performances. An advantage of the alternative cycle with single-shaft design is that thermal efficiency is less sensitive to compressor pressure ratio compared to other configurations, and we can also have flexibility in the turbine division without much efficiency loss. The part load analyses have been carried out with the aid of realistic component maps and models for off-design operation. In addition to the general fuel only control, a variable speed control is assumed as the part load operating strategy of the single-shaft configuration. Obvious advantage with the alternative cycle is observed in the variable speed operation of the single-shaft design. With this strategy, the part load efficiency of the alternative cycle is far superior to the conventional cycle. Almost constant efficiency is predicted for a wide power range.

Performance Enhancement of a Gas Turbine With Humid Air and Utilization of LNG Cold Energy

1998 ◽  
Author(s):  
C. H. Song ◽  
S. T. Ro
Keyword(s):  
Natural Gas ◽  
Gas Turbine ◽  
Power Efficiency ◽  
Performance Enhancement ◽  
Pressure Ratio ◽  
Simple Cycle ◽  
Cycle Performance ◽  
Specific Power ◽  
Humid Air ◽  
Cold Energy

It is well known that a cycle performance can be improved considerably by adopting humid air to a simple gas turbine. Further improvement can be achieved by utilizing LNG (liquified natural gas) cold energy which is obtained during vaporization process of natural gas from liquid to gas state. Qualitatively well known fact of high specific power and improvement of efficiency are analyzed quantitatively for various cases. These include comparisons of power, efficiency and other important operating parameters for the cases of a simple cycle and HAT cycle with and without utilization of LNG cold energy. Compared with simple cycle, HAT cycle got 48% increase in total work, 16% increase in efficiency and HAT-LNG cycle got each 54%, 17% increases at 10 pressure ratio. An analysis shows that a reasonable matching exists between the amount of LNG as fuel and the energy required to control inlet air temperature. It should be also admitted that use of a high cost liquified natural gas is inevitable for transportation of fuel from production site to consumer.

Design and Off-Design Characteristics of the Alternative Recuperated Gas Turbine Cycle With Divided Turbine Expansion

2006 ◽  
Author(s):  
Sung Hoon Hwang ◽  
Soo Hyung Yoon ◽  
Tong Seop Kim
Keyword(s):  
Mechanical Design ◽  
Pressure Ratio ◽  
Variable Speed ◽  
Part Load ◽  
Turbine Expansion ◽  
Compressor Pressure Ratio ◽  
Design Characteristics ◽  
Inlet Conditions ◽  
Design Analyses ◽  
Gas Turbine Cycle

In order to fully address the characteristics of the alternative recuperated cycle with divided turbine expansion, both the design and off-design analyses have been performed. Two types of mechanical design are assumed: two-shaft and single-shaft. In particular, optimal pressure ratio division between the high and low pressure turbines is evaluated for the single shaft configuration. It is predicted that the alternative recuperated cycle hardly exhibits sensible design efficiency advantage over the conventional recuperated cycle for moderate turbine inlet conditions and with usual component performances. An advantage of the alternative cycle with single shaft design is that thermal efficiency is less sensitive to compressor pressure ratio compared with other configurations and we can also have flexibility in the turbine division without much efficiency loss. The part load analyses have been carried out with the aid of realistic component maps and models for off-design operation. In addition to the general fuel only control, a variable speed control is assumed as the part load operating strategy of the single shaft configuration. Obvious advantage with the alternative cycle is observed in the variable speed operation of the single shaft design. With this strategy, the part load efficiency of the alternative cycle is far superior to the conventional cycle. Almost constant efficiency is predicted for a wide power range.

A New High-Efficiency Heavy-Duty Combustion Turbine 701F

1994 ◽  
Vol 116 (2) ◽  
pp. 389-394 ◽  
Author(s):  
I. Fukue ◽  
S. Aoki ◽  
K. Aoyama ◽  
S. Umemura ◽  
A. Merola ◽  
...  
Keyword(s):  
High Efficiency ◽  
Pressure Ratio ◽  
Heavy Duty ◽  
Test Program ◽  
Testing Program ◽  
Industrial Grade ◽  
Design Changes ◽  
Compressor Pressure Ratio ◽  
Verification Test ◽  
Reliability Verification

The 701F is a high-temperature 50 Hz industrial grade 220 MW size engine based on a scaling of the 501F 150 MW class 60 Hz machine, and incorporates a higher compressor pressure ratio to increase the thermal efficiency. The prototype engine is under a two-year performance and reliability verification testing program at MHI’s Yokohama Plant and was initially fired in June of 1992. This paper describes the 701F design features design changes made from 501F. The associated performance and reliability verification test program will also be presented.

Impact of Inlet Fogging on the Performance of Steam Injected Cooled Gas Turbine Based Combined Cycle Power Plant

2017 ◽  
Author(s):  
Anoop Kumar Shukla ◽  
Onkar Singh
Keyword(s):  
Power Plant ◽  
Gas Turbine ◽  
Film Cooling ◽  
Pressure Ratio ◽  
Steam Injection ◽  
Combined Cycle ◽  
Specific Power ◽  
Temperature Cycle ◽  
Inlet Temperature ◽  
Combined Cycle Power Plant

Gas/steam combined cycle power plants are extensively used for power generation across the world. Today’s power plant operators are persistently requesting enhancement in performance. As a result, the rigour of thermodynamic design and optimization has grown tremendously. To enhance the gas turbine thermal efficiency and specific power output, the research and development work has centered on improving firing temperature, cycle pressure ratio, adopting improved component design, cooling and combustion technologies, and advanced materials and employing integrated system (e.g. combined cycles, intercooling, recuperation, reheat, chemical recuperation). In this paper a study is conducted for combining three systems namely inlet fogging, steam injection in combustor, and film cooling of gas turbine blade for performance enhancement of gas/steam combined cycle power plant. The evaluation of the integrated effect of inlet fogging, steam injection and film cooling on the gas turbine cycle performance is undertaken here. Study involves thermodynamic modeling of gas/steam combined cycle system based on the first law of thermodynamics. The results obtained based on modeling have been presented and analyzed through graphical depiction of variations in efficiency, specific work output, cycle pressure ratio, inlet air temperature & density variation, turbine inlet temperature, specific fuel consumption etc.

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