Development of the Advanced Closed-Cycle Gas Turbine System

Turbine Blade Cooling ◽

This aims to put the fruits of the R&D; “The Hydrogen Combustion Turbine” in WE-NET Phase I Program(1993-1998) to practical use at an early stage. The topping regenerating cycle was selected as the optimum cycle, with energy efficiency expected to be more than 60%(HHV) under the conditions of the turbine inlet temperature of 1973K(1700°C) and the pressure of 4.8MPa,in it. • As the turbine inlet temperature and pressure increase, issues to be resolved include the amount of NOx emissions and the durability of super alloys for turbine blades under such thermal conditions. In this respect, the development of the highly efficient methane-oxygen combustion technology, the turbine blade cooling technology, and the ultrahigh-temperature materials including thermal barrier coatings is being carried out. • In 1999, the results made it clear that there are little error among the three analytic programs used to verify the system efficiency, it was verified that the burning rate was going to arrive at over 98% from the methane-oxygen combustion test (under the atmospheric pressure). And the type of vane “Film cooling plus recycle type with internal cooling system” was selected as the most suitable vane.

Cooling Process of Gas Turbine Blade: A Comparison Study

Al-Qadisiyah Journal for Engineering Sciences ◽

10.30772/qjes.v13i3.661 ◽

2020 ◽

Vol 13 (3) ◽

pp. 215-222

Author(s):

Akram Luaibi Ballaoot ◽

Naseer Hamza

Keyword(s):

Gas Turbine ◽

Turbine Blade ◽

Power Output ◽

Film Cooling ◽

Aviation Industry ◽

Inlet Temperature ◽

Internal Cooling ◽

Gas Turbine Blade ◽

The gas turbine engines are occupied an important sector in the energy production and aviation industry and this important increase day after day for their features. One of the most important parameters that limit the gas turbine engine power output is the turbine inlet temperature. The higher is the turbine inlet temperature, the higher is the power output or thrust but this increases of risks of blade thermal failure due to metallurgical limits. Thus the need for a good and efficient process of blade cooling can lead to the best compromise between a powerful engine and safe operation. There are two major methods: film or external cooling and internal cooling inside the blade itself. . In the past number of years there has been considerable progress in turbine cooling research and this paper is limited to review a few selected publications to reflect recent development in turbine blade film cooling. The maximum drop in the surface temperature of the gas turbine blade and associated thermal stress – due to incorporating cooling systems- were 735 ˚C, 1217 N/mm2 respectively.

Comparative Thermodynamic Analysis of Gas Turbine Systems with Turbine Blade Film Cooling

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.505.539 ◽

2012 ◽

Vol 505 ◽

pp. 539-543

Author(s):

Kyoung Hoon Kim ◽

Kyoung Jin Kim ◽

Chul Ho Han

Keyword(s):

Gas Turbine ◽

Turbine Blade ◽

Thermodynamic Analysis ◽

Film Cooling ◽

Pressure Ratio ◽

Turbine Blades ◽

Inlet Temperature ◽

Blade Cooling ◽

Since the gas turbine systems require active cooling to maintain high operating temperature while avoiding a reduction in the system operating life, turbine blade cooling is very important and essential but it may cause the performance losses in gas turbine. This paper deals with the comparative thermodynamic analysis of gas turbine system with and without regeneration by using the recently developed blade-cooling model when the turbine blades are cooled by the method of film cooling. Special attention is paid to investigating the effects of system parameters such as pressure ratio and turbine inlet temperature on the thermodynamic performance of the systems. In both systems the thermal efficiency increases with turbine inlet temperature, but its effect is less sensitive in simpler system

Comprehensive Review on Leading Edge Turbine Blade Cooling Technologies

International Journal of Heat and Technology ◽

10.18280/ijht.390209 ◽

2021 ◽

Vol 39 (2) ◽

pp. 403-416

Author(s):

Chirag Sharma ◽

Siddhant Kumar ◽

Aanya Singh ◽

Kartik R. Bhat Hire ◽

Vedant Karnatak ◽

...

Keyword(s):

Turbine Blade ◽

Turbine Blades ◽

Leading Edge ◽

Inlet Temperature ◽

Entire Surface ◽

Turbine Blade Cooling ◽

Blade Cooling ◽

Advantages And Disadvantages ◽

Developments in the gas turbine technology have caused widespread usage of the Turbomachines for power generation. With increase in the power demand and a drop in the availability of fuel, usage of turbines with higher efficiencies has become imperative. This is only possible with an increase in the turbine inlet temperature (TIT) of the gas. However, the higher limit of TIT is governed by the metallurgical boundary conditions set by the material used to manufacture the turbine blades. Hence, turbine blade cooling helps in drastically controlling the blade temperature of the turbine and allows a higher turbine inlet temperature. The blade could be cooled from the leading edge, from the entire surface of the blade or from the trailing edge. The various methods of blade cooling from leading edge and its comparative study were reviewed and summarized along with their advantages and disadvantages.

Cooling and Sealing Air System in Industrial Gas Turbine Engines

Volume 1: Turbomachinery ◽

10.1115/96-gt-256 ◽

1996 ◽

Cited By ~ 2

Author(s):

A. W. Reichert ◽

M. Janssen

Keyword(s):

Gas Turbine ◽

Film Cooling ◽

Gas Turbines ◽

State Of The Art ◽

Cooling System ◽

Inlet Temperature ◽

Turbine Inlet ◽

Air System ◽

Calculation System ◽

Cooling Air

Siemens heavy duty Gas Turbines have been well known for their high power output combined with high efficiency and reliability for more than 3 decades. Offering state of the art technology at all times, the requirements concerning the cooling and sealing air system have increased with technological development over the years. In particular the increase of the turbine inlet temperature and reduced NOx requirements demand a highly efficient cooling and sealing air system. The new Vx4.3A family of Siemens gas turbines with ISO turbine inlet temperatures of 1190°C in the power range of 70 to 240 MW uses an effective film cooling technique for the turbine stages 1 and 2 to ensure the minimum cooling air requirement possible. In addition, the application of film cooling enables the cooling system to be simplified. For example, in the new gas turbine family no intercooler and no cooling air booster for the first turbine vane are needed. This paper deals with the internal air system of Siemens gas turbines which supplies cooling and sealing air. A general overview is given and some problems and their technical solutions are discussed. Furthermore a state of the art calculation system for the prediction of the thermodynamic states of the cooling and sealing air is introduced. The calculation system is based on the flow calculation package Flowmaster (Flowmaster International Ltd.), which has been modified for the requirements of the internal air system. The comparison of computational results with measurements give a good impression of the high accuracy of the calculation method used.

Reduction in Flow Parameter Resulting From Volcanic Ash Deposition in Engine Representative Cooling Passages

Journal of Turbomachinery ◽

10.1115/1.4034939 ◽

2016 ◽

Vol 139 (3) ◽

Cited By ~ 9

Author(s):

Sebastien Wylie ◽

Alexander Bucknell ◽

Peter Forsyth ◽

Matthew McGilvray ◽

David R. H. Gillespie

Keyword(s):

Film Cooling ◽

Volcanic Ash ◽

Flow Parameter ◽

Cooling System ◽

Pressure Ratio ◽

Turbine Blades ◽

Metal Temperature ◽

Internal Cooling ◽

Cooling Hole ◽

Cooling Passage

Internal cooling passages of turbine blades have long been at risk to blockage through the deposition of sand and dust during fleet service life. The ingestion of high volumes of volcanic ash (VA) therefore poses a real risk to engine operability. An additional difficulty is that the cooling system is frequently impossible to inspect in order to assess the level of deposition. This paper reports results from experiments carried out at typical high pressure (HP) turbine blade metal temperatures (1163 K to 1293 K) and coolant inlet temperatures (800 K to 900 K) in engine scale models of a turbine cooling passage with film-cooling offtakes. Volcanic ash samples from the 2010 Eyjafjallajökull eruption were used for the majority of the experiments conducted. A further ash sample from the Chaiten eruption allowed the effect of changing ash chemical composition to be investigated. The experimental rig allows the metered delivery of volcanic ash through the coolant system at the start of a test. The key metric indicating blockage is the flow parameter (FP), which can be determined over a range of pressure ratios (1.01–1.06) before and after each experiment, with visual inspection used to determine the deposition location. Results from the experiments have determined the threshold metal temperature at which blockage occurs for the ash samples available, and characterize the reduction of flow parameter with changing particle size distribution, blade metal temperature, ash sample composition, film-cooling hole configuration and pressure ratio across the holes. There is qualitative evidence that hole geometry can be manipulated to decrease the likelihood of blockage. A discrete phase computational fluid dynamics (CFD) model implemented in Fluent has allowed the trajectory of the ash particles within the coolant passages to be modeled, and these results are used to help explain the behavior observed.

Recent Advances of Internal Cooling Techniques for Gas Turbine Airfoils

Journal of Thermal Science and Engineering Applications ◽

10.1115/1.4023829 ◽

2013 ◽

Vol 5 (2) ◽

Cited By ~ 24

Author(s):

Minking K. Chyu ◽

Sin Chien Siw

Keyword(s):

Gas Turbine ◽

Gas Turbines ◽

Energy Demand ◽

Major Elements ◽

Inlet Temperature ◽

Internal Cooling ◽

Performance Goal ◽

Air Breathing ◽

The performance goal of modern gas turbine engines, both land-base and air-breathing engines, can be achieved by increasing the turbine inlet temperature (TIT). The level of TIT in the near future can reach as high as 1700 °C for utility turbines and over 1900 °C for advanced military engines. Advanced and innovative cooling techniques become one of the crucial major elements supporting the development of modern gas turbines, both land-based and air-breathing engines with continual increment of turbine inlet temperature (TIT) in order to meet higher energy demand and efficiency. This paper discusses state-of-the-art airfoil cooling techniques that are mainly applicable in the mainbody and trailing edge section of turbine airfoil. Potential internal cooling designs for near-term applications based on current manufacturing capabilities are identified. A literature survey focusing primarily on the past four to five years has also been performed.

A Selective Assembly Method to Reduce the Impact of Blade Flow Variability on Turbine Life

Volume 5: Turbo Expo 2004, Parts A and B ◽

10.1115/gt2004-53930 ◽

2004 ◽

Cited By ~ 2

Author(s):

Vince Sidwell ◽

David Darmofal

Keyword(s):

Turbine Blades ◽

High Flow ◽

Metal Temperature ◽

Low Flow ◽

Inlet Temperature ◽

Selective Assembly ◽

Assembly Method ◽

Turbine Inlet ◽

The Impact

A selective assembly method is proposed that decreases the impact of blade passage manufacturing variability on the life of a row of cooled turbine blades. The method classifies turbine blades into groups based on the effective flow areas of the blade passages, then a row of blades is assembled exclusively from blades of a single group. A simplified classification is considered in which blades are divided into low-flow, nominal-flow, and high-flow groups. For rows assembled from the low-flow class, the blade plenum pressure will tend to rise and the individual blade flows will be closer to the design intent than for a single low-flow blade in a randomly-assembled row. Since the blade metal temperature is strongly dependent on the blade flow, selective assembly can lower the metal temperature of the lowest-flowing blades and increase the life of a turbine row beyond what is possible from a randomly-assembled row. Furthermore, the life of a nominal-flow or high-flow row will be significantly increased (relative to a randomly-assembled row) since the life-limiting low-flow blades would not be included in these higher-flowing rows. The impact of selective assembly is estimated using a model of the first turbine rotor of an existing high-bypass turbofan. The oxidation lives of the nominal-flow and high-flow blade rows are estimated to increase approximately 50% and 100% compared to randomly-assembled rows, while the life of the low-flow rows are the same as the randomly-assembled rows. Alternatively, selective assembly can be used to increase turbine inlet temperature while maintaining the maximum blade metal temperatures at random-assembly levels. For the nominal-flow and high-flow classes, turbine inlet temperature increases are estimated to be equivalent to the turbine inlet temperature increases observed over several years of gas turbine technology development.

Reduction in Flow Parameter Resulting From Volcanic Ash Deposition in Engine Representative Cooling Passages

Volume 5B: Heat Transfer ◽

10.1115/gt2016-57296 ◽

2016 ◽

Cited By ~ 1

Author(s):

Sebastien Wylie ◽

Alexander Bucknell ◽

Peter Forsyth ◽

Matthew McGilvray ◽

David R. H. Gillespie

Keyword(s):

Film Cooling ◽

Volcanic Ash ◽

Flow Parameter ◽

Cooling System ◽

Pressure Ratio ◽

Turbine Blades ◽

Metal Temperature ◽

Internal Cooling ◽

Cooling Hole ◽

Cooling Passage

Internal cooling passages of turbine blades have long been at risk to blockage through the deposition of sand and dust during fleet service life. The ingestion of high volumes of volcanic ash therefore poses a real risk to engine operability. An additional difficulty is that the cooling system is frequently impossible to inspect in order to assess the level of deposition. This paper reports results from experiments carried out at typical HP turbine blade metal temperatures (1163K to 1293K) and coolant inlet temperatures (800K to 900K) in engine scale models of a turbine cooling passage with film-cooling offtakes. Volcanic ash samples from the 2010 Eyjafjallajökull eruption were used for the majority of the experiments conducted. A further ash sample from the Chaiten eruption allowed the effect of changing ash chemical composition to be investigated. The experimental rig allows the metered delivery of volcanic ash through the coolant system at the start of a test. The key metric indicating blockage is the flow parameter which can be determined over a range of pressure ratios (1.01–1.06) before and after each experiment, with visual inspection used to determine the deposition location. Results from the experiments have determined the threshold metal temperature at which blockage occurs for the ash samples available, and characterise the reduction of flow parameter with changing particle size distribution, blade metal temperature, ash sample composition, film-cooling hole configuration and pressure ratio across the holes. There is qualitative evidence that hole geometry can be manipulated to decrease the likelihood of blockage. A discrete phase CFD model implemented in Fluent has allowed the trajectory of the ash particles within the coolant passages to be modelled, and these results are used to help explain the behaviour observed.

Numerical Evaluation of Influence of Internal Ribs on Heat Transfer in Flat Plate Film Cooling

Volume 3B: Heat Transfer ◽

10.1115/gt2013-95450 ◽

2013 ◽

Cited By ~ 1

Author(s):

Yukiko Agata ◽

Toshihiko Takahashi ◽

Eiji Sakai ◽

Koichi Nishino

Keyword(s):

Heat Transfer ◽

Heat Transfer Coefficient ◽

Transfer Coefficient ◽

Film Cooling ◽

Inlet Temperature ◽

Cooling Effectiveness ◽

Cooling Performance ◽

Film Cooling Effectiveness ◽

To augment the thermal efficiency of combined power generation plants, the turbine inlet temperature of an industrial gas turbine has been increased. Cooling technology plays a vital role in the durability of gas turbine blades in situations in which the turbine inlet temperature exceeds the allowable temperature of the blade material. Cooling air is also directly associated with the reduction in thermal efficiency because bleed air from the compressor is used for turbine cooling. Thus, improvement in cooling performance has a marked impact on the further augmentation of thermal efficiency by increasing turbine inlet temperature. To evaluate film cooling performance on the basis of heat flux reduction, it is necessary to accurately estimate both heat transfer coefficient and adiabatic film cooling effectiveness. Most studies of film cooling, however, have focused on improving adiabatic film cooling effectiveness. In contrast, there are few studies focusing on heat transfer coefficient. One of the reasons for this is that adiabatic film cooling effectiveness is a performance parameter unique to film cooling. To preliminarily estimate the heat flux through a blade, heat transfer coefficient without film cooling can still be used as substitute. Moreover, the accurate CFD prediction of heat transfer coefficient with film cooling is difficult, compared with the evaluation of adiabatic film cooling effectiveness. Therefore, in this study, we addressed the CFD prediction of heat transfer coefficient with film cooling on a flat plate, and discussed its feasibility. Recent gas turbine blades operated at a turbine inlet temperature of over 1300 degree Celsius employ internal convection cooling with ribbed passages and external film cooling. These cooling technologies have been studied extensively, particularly regarding their individual effects. On the other hand, there are few investigations on the interaction between internal convection cooling and the film cooling. Although most of such film-cooling studies employed stagnant plenums to bleed cooling air, some researchers including the present authors have shown the marked impact of the conditions for supplying coolant air on film cooling performance. In this study, we focus particularly on the influence of internal rib orientation on external film cooling performance along the blade outer surface. CFD analysis is used to resolve the flow fields of the flat plate film cooling and to clarify the influence of rib orientation on heat-transfer.

Proceedings of the Institution of Mechanical Engineers Part A Journal of Power and Energy ◽

Estimation of cooling flow rate for conceptual design stage of a gas turbine engine

10.1177/09576509211014981 ◽

2021 ◽

pp. 095765092110149

Author(s):

EP Filinov ◽

VS Kuz’michev ◽

A Yu Tkachenko ◽

YaA Ostapyuk ◽

IN Krupenich

Keyword(s):

Gas Turbine ◽

Cooling System ◽

Numerical Models ◽

Turbine Blades ◽

Gas Turbine Engine ◽

Design Stage ◽

Inlet Temperature ◽

Turbine Engine ◽

Turbine Cooling ◽

Development of a gas turbine engine starts with optimization of the working process parameters. Turbine inlet temperature is among the most influential parameters that largely determine performance of an engine. As typical turbine inlet temperatures substantially exceed the point where metal turbine blades maintain reasonable thermal strength, proper modeling of the turbine cooling system becomes crucial for optimization of the engine’s parameters. Currently available numerical models are based on empirical data and thus must be updated regularly. This paper reviews the published information on turbine cooling requirements, and provides an approximation curve that generalizes data on all types of blade/vane cooling and is suitable for computer-based optimization.