High-Temperature Potential of Uncooled Radial Turbines

1978 ◽  
Vol 100 (2) ◽  
pp. 294-302 ◽  
Author(s):  
D. J. Arnold ◽  
O. E. Balje
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Experimental Investigations ◽  
Inlet Temperature ◽  
High Reaction ◽  
Temperature Potential ◽  
Axial Turbines ◽  
Radial Turbines

Radial turbines are used predominantly for turbo-charges where the geometry is frequently compromised to favor low fabrications costs. Theoretical as well as experimental investigations have shown that the efficiency potential of radial turbines is as high as the efficiency potential of high reaction axial turbines. Structural and heat transfer studies on radial turbines show that the highest stresses in “deep scalloped” radial rotors occur at locations where the metal temperature is considerably lower than at rotor inlet. Thus the maximum allowable gas inlet temperature for radial turbines is several hundred degrees higher than for high-reaction axial turbines. This difference tends to increase with increasing expansion ratios, at least up to expansion ratios of 10:1. Since the thermal efficiency of typical gas turbine cycles increases with increasing gas temperatures and increasing expansion ratios, it results that the application of uncooled radial turbines will yield cycle efficiencies which are not obtainable with uncooled axial turbines.

Comparative Study of Barrier Coatings on Turbine Blade Cooling

2021 ◽  
Author(s):  
Kishan A. Singh ◽  
Zozimus D. Labana
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Thermal Efficiency ◽  
Considerable Effect ◽  
Inlet Temperature ◽  
Cooling Effectiveness ◽  
Continuous Growth ◽  
Barrier Coatings

Abstract There is a continuous growth in various sectors of engineering and technology resulting in high demand for modern and innovative steps into providing solutions to overcome all barriers. With the increase in demand of modern age technology growing rapidly, the requirement of the advanced system has to keep up with this demand. The power required to drive such technology has one of its sources from the gas turbine propulsion system, which is capable to provide thrust and power to major components. In modern gas turbine applications, high power and thermal efficiency are of essential requirement. The two parameters that play a vital role in increasing the thermal efficiency of the gas turbine are its compression ratio and high turbine inlet temperature. The advanced gas turbine has inlet temperature, which exceeds the material thermal limitation of the blade. This high temperature has an impact on the performance and life of the blade employed for energy extraction in the turbines. The current study analyzes the methods dealing with increasing the cooling effectiveness of the turbine blade, which are working under very high-temperature hot gases that exit from the combustion chamber. This gas expands into the turbine region by which power is extracted. These high-temperature gases can have a considerable effect on the stresses developed that can lead to failure under the cyclic loading of these hot gases. Cooling effectiveness can increase the system working temperature from 800K up to 1000K inlet. The current research compares the means of reducing the heat transfer and improve cooling effectiveness with the help of the latest improved material coatings such as thermal barrier coatings (TBCs) and environmental barrier coatings (EBCs). The study focuses on the effect of these TBCs and EBCs employed on the surface of the blade. Analysis of results obtained from this conjugate heat transfer (CHT) study has shown good agreement with the experimental data. The comparison revealed the use of the SST k-ω model which was efficient and predicted similar trends as that of the experimental for pressure were as with 3% of deviation for temperature.

Conceptual Design and Cooling Blade Development of 1700°C Class High-Temperature Gas Turbine

2005 ◽  
Vol 127 (2) ◽  
pp. 358-368 ◽  
Author(s):  
Shoko Ito ◽  
Hiroshi Saeki ◽  
Asako Inomata ◽  
Fumio Ootomo ◽  
Katsuya Yamashita ◽  
...  
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Gas Turbine ◽  
Conceptual Design ◽  
Thermal Efficiency ◽  
Internal Cooling ◽  
Closed Cycle ◽  
Steam Consumption ◽  
Flow Phenomena ◽  
High Temperature Gas

In this paper we describe the conceptual design and cooling blade development of a 1700°C-class high-temperature gas turbine in the ACRO-GT-2000 (Advanced Carbon Dioxide Recovery System of Closed-Cycle Gas Turbine Aiming 2000 K) project. In the ACRO-GT closed cycle power plant system, the thermal efficiency aimed at is more than 60% of the higher heating value of fuel (HHV). Because of the high thermal efficiency requirement, the 1700°C-class high-temperature gas turbine must be designed with the minimum amount of cooling and seal steam consumption. The hybrid cooling scheme, which is a combination of closed loop internal cooling and film ejection cooling, was chosen from among several cooling schemes. The elemental experiments and numerical studies, such as those on blade surface heat transfer, internal cooling channel heat transfer, and pressure loss and rotor coolant passage distribution flow phenomena, were conducted and the results were applied to the conceptual design advancement. As a result, the cooling steam consumption in the first stage nozzle and blade was reduced by about 40% compared with the previous design that was performed in the WE-NET (World Energy Network) Phase-I.

Development and Evaluation of Ceramic Components for Gas Turbine

2002 ◽  
Author(s):  
Takero Fukudome ◽  
Sazo Tsuruzono ◽  
Wataru Karasawa ◽  
Yoshihiro Ichikawa
Keyword(s):  
High Temperature ◽  
Silicon Nitride ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Technology Development ◽  
Inlet Temperature ◽  
Combustion Gas ◽  
Development Organization ◽  
Nitride Material ◽  
Ceramic Components

An 8000 kW class Hybrid Gas Turbine (HGT) project, administered by the New Energy and Industrial Technology Development Organization (NEDO), has been ongoing since July of 1999 in Japan. Targets of this project are improvement in thermal efficiency and output power by using ceramic components, and early commercialization of the gas turbine system. The ceramic components are used for stationary parts subjected to high temperature, such as combustor liners, transition ducts, and first stage turbine nozzles. Development of the gas turbine is conducted by Kawasaki Heavy Industries, Ltd. (KHI), to achieve the Turbine Inlet Temperature (TIT) of 1250°C, thermal efficiency of 34%, NOx emission less than standard regulation values, and 4,000 h engine durability. Kyocera is in charge of the development and evaluation of the ceramic components. Recently, recession of the Si based ceramic materials under the combustion gas is the focus of attention to improve the reliability of ceramic components for gas turbine. For the HGT project, the silicon nitride material (SN282 : silicon nitride material produced by Kyocera Corporation) is used for the components subjected to high temperature. The SN282 was evaluated under the combustion gas, and clear recession was observed. Our technology of the Environmental Barrier Coating (EBC) is under development to obtain reliable heat resistive SN282 components, against the recession by combustion gas. Reliability of the SN282 with EBC has been evaluated by exposure and hydrothermal corrosion test. Ceramic components made of SN282 with EBC will be also evaluated by a proof engine test of 4,000 h, which starts in the spring of 2002.

Thermodynamic and Energy Study of a Regenerator in Gas Turbine Cycle and Optimization of Performances

2016 ◽  
Vol 5 (2) ◽  
pp. 25-44
Author(s):  
Saria Abed ◽  
Taher Khir ◽  
Ammar Ben Brahim
Keyword(s):  
Heat Transfer ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Parametric Study ◽  
Pressure Ratio ◽  
Operating Conditions ◽  
Inlet Temperature ◽  
Compressor Pressure Ratio ◽  
Compressor Inlet ◽  
Gas Turbine Cycle

In this paper, thermodynamic study of simple and regenerative gas turbine cycles is exhibited. Firstly, thermodynamic models for both cycles are defined; thermal efficiencies of both cycles are determined, the overall heat transfer coefficient through the heat exchanger is calculated in order to determinate its performances and parametric study is carried out to investigate the effects of compressor inlet temperature, turbine inlet temperature and compressor pressure ratio on the parameters that measure cycles' performance. Subsequently, numerical optimization is established through EES software to determinate operating conditions. The results of parametric study have shown a significant impact of operating parameters on the performance of the cycle. According to this study, the regeneration technique improves the thermal efficiency by 10%. The studied regenerator has an important effectiveness (˜ 82%) which improves the heat transfer exchange; also a high compressor pressure ratio and an important combustion temperature can increase thermal efficiency.

Radiative Effectiveness on the Aero- and Thermodynamics in a Highly Thermally Loaded Film Cooling System

2011 ◽  
Author(s):  
Wenping Wang ◽  
Peng Sun ◽  
Jing Ren ◽  
Hongde Jiang
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Gas Turbine ◽  
Film Cooling ◽  
Cooling System ◽  
Numerical Study ◽  
Discrete Ordinates ◽  
Spanwise Direction ◽  
Inlet Temperature ◽  
Gas Channel

With the increasing of the gas turbine inlet temperature, the radiative heat transfer plays a more important role in the total heat transfer. In this paper, a high temperature test rig has been built to research the radiative effect in high temperature film cooling. The test section is made up of a high temperature hot gas channel and a middle temperature coolant air channel which are separated by a flat plate with a row of film cooling holes. The goal is to analyze the effects of radiation and its interaction between conduction and convection in the internal and film cooling which consider the heat transfer in both gas and solid. Meanwhile, the numerical study on the test cases are also carried out by combining conjugate heat transfer with radiative models. The fluid and solid regions were solved simultaneously. The Discrete Ordinates (DO) model and the Weighted Sum of Gray Gases Model (WSGGM) has been used to solve the radiative transfer equation for the radiation modeling. The results show that the temperature of the plate increase greatly when the radiation is taken into account and the temperature gradient through the plate becomes much larger. The temperature distribution has been changed and become smoother in spanwise direction. The results also indicate that the internal emissivity of the inlet has an influence mainly on the whole temperature of the plate, which suggests that the control of inlet emissivity is a good way for prevent over-high temperature on the first stage gas turbine vane.

Conceptual Design and Cooling Blade Development of 1700 °C-Class High-Temperature Gas Turbine

2003 ◽  
Author(s):  
Shoko Ito ◽  
Hiroshi Saeki ◽  
Asako Inomata ◽  
Fumio Ootomo ◽  
Katsuya Yamashita ◽  
...  
Keyword(s):  
Heat Transfer ◽  
High Temperature ◽  
Gas Turbine ◽  
Conceptual Design ◽  
Thermal Efficiency ◽  
Internal Cooling ◽  
Closed Cycle ◽  
Steam Consumption ◽  
Flow Phenomena ◽  
High Temperature Gas

This paper describes the conceptual design and cooling blade development of a 1700 °C-class high-temperature gas turbine in the ACRO-GT-2000 (Advanced Carbon Dioxide Recovery System of Closed-Cycle Gas Turbine Aiming 2000K) project. In the ACRO-GT closed cycle power plant system, the thermal efficiency aimed at is more than 60% of higher heating value of fuel (HHV). Because of the high thermal efficiency requirement, the 1700 °C-class high-temperature gas turbine must be designed with the minimum amount of cooling and seal steam consumption. The hybrid cooling scheme, which is a combination of closed loop internal cooling and film ejection cooling, was chosen from among several cooling schemes. The elemental experiments and numerical studies, such as those on blade surface heat transfer, internal cooling channel heat transfer and pressure loss and rotor coolant passage distribution flow phenomena, were conducted and the results were applied to the conceptual design advancement. As a result, the cooling steam consumption in the first stage nozzle and blade was reduced by about 40% compared with the previous design that was performed in the WE-NET (World Energy Network) Phase-I.

Development and Fabrication of Silicon Nitride Components for Ceramic Gas Turbine

1997 ◽  
Author(s):  
Keisuke Makino ◽  
Ken-Ichi Mizuno ◽  
Toru Shimamori
Keyword(s):  
High Temperature ◽  
Silicon Nitride ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
High Strength ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Spark Plug ◽  
Power Turbine

NGK Spark Plug Co., Ltd. has been developing various silicon nitride materials, and the technology for fabricating components for ceramic gas turbines (CGT) using theses materials. We are supplying silicon nitride material components for the project to develop 300 kW class CGT for co-generation in Japan. EC-152 was developed for components that require high strength at high temperature, such as turbine blades and turbine nozzles. In order to adapt the increasing of the turbine inlet temperature (TIT) up to 1,350 °C in accordance with the project goals, we developed two silicon nitride materials with further unproved properties: ST-1 and ST-2. ST-1 has a higher strength than EC-152 and is suitable for first stage turbine blades and power turbine blades. ST-2 has higher oxidation resistance than EC-152 and is suitable for power turbine nozzles. In this paper, we report on the properties of these materials, and present the results of evaluations of these materials when they are actually used for CGT components such as first stage turbine blades and power turbine nozzles.

Comparison of 3D Unsteady Transient Conjugate Heat Transfer Analysis on a High Pressure Cooled Turbine Stage With Experimental Data

2017 ◽  
Author(s):  
Jong-Shang Liu ◽  
Mark C. Morris ◽  
Malak F. Malak ◽  
Randall M. Mathison ◽  
Michael G. Dunn
Keyword(s):  
Heat Transfer ◽  
Experimental Data ◽  
Heat Flux ◽  
High Pressure ◽  
High Temperature ◽  
Gas Turbine ◽  
Conjugate Heat Transfer ◽  
Turbine Rotor ◽  
Turbine Stage ◽  
Cooling Flow

In order to have higher power to weight ratio and higher efficiency gas turbine engines, turbine inlet temperatures continue to rise. State-of-the-art turbine inlet temperatures now exceed the turbine rotor material capability. Accordingly, one of the best methods to protect turbine airfoil surfaces is to use film cooling on the airfoil external surfaces. In general, sizable amounts of expensive cooling flow delivered from the core compressor are used to cool the high temperature surfaces. That sizable cooling flow, on the order of 20% of the compressor core flow, adversely impacts the overall engine performance and hence the engine power density. With better understanding of the cooling flow and accurate prediction of the heat transfer distribution on airfoil surfaces, heat transfer designers can have a more efficient design to reduce the cooling flow needed for high temperature components and improve turbine efficiency. This in turn lowers the overall specific fuel consumption (SFC) for the engine. Accurate prediction of rotor metal temperature is also critical for calculations of cyclic thermal stress, oxidation, and component life. The utilization of three-dimensional computational fluid dynamics (3D CFD) codes for turbomachinery aerodynamic design and analysis is now a routine practice in the gas turbine industry. The accurate heat-transfer and metal-temperature prediction capability of any CFD code, however, remains challenging. This difficulty is primarily due to the complex flow environment of the high-pressure turbine, which features high speed rotating flow, coupling of internal and external unsteady flows, and film-cooled, heat transfer enhancement schemes. In this study, conjugate heat transfer (CHT) simulations are performed on a high-pressure cooled turbine stage, and the heat flux results at mid span are compared to experimental data obtained at The Ohio State University Gas Turbine Laboratory (OSUGTL). Due to the large difference in time scales between fluid and solid, the fluid domain is simulated as steady state while the solid domain is simulated as transient in CHT simulation. This paper compares the unsteady and transient results of the heat flux on a high-pressure cooled turbine rotor with measurements obtained at OSUGTL.

scholarly journals Current Status of Ceramic Gas Turbine (CGT302)

1998 ◽  
Author(s):  
Hirotake Kobayashi ◽  
Tetsuo Tatsumi ◽  
Takashi Nakashima ◽  
Isashi Takehara ◽  
Yoshihiro Ichikawa
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Technology Development ◽  
Development Program ◽  
Point Of View ◽  
Current Status ◽  
Fiscal Year ◽  
Inlet Temperature ◽  
Development Organization ◽  
New Energy

In Japan, from the point of view of energy saving and environmental protection, a 300kW Ceramic Gas Turbine (CGT) Research and Development program started in 1988 and is still continuing as a part of “the New Sunshine Project” promoted by the Ministry of International Trade and Industry (MITT). The final target of the program is to achieve 42% thermal efficiency at 1350°C of turbine inlet temperature (TIT) and to keep NOx emissions below present national regulations. Under contract to the New Energy and Industrial Technology Development Organization (NEDO), Kawasaki Heavy Industries, Ltd. (KHI) has been developing the CGT302 with Kyocera Corporation and Sumitomo Precision Products Co., Ltd. By the end of the fiscal year 1996, the CGT302 achieved 37.0% thermal efficiency at 1280°C of TIT. In 1997, TIT reached 1350°C and a durability operation for 20 hours at 1350°C was conducted successfully. Also fairly low NOx was proved at 1300°C of TIT. In January 1998, the CGT302 has achieved 37.4% thermal efficiency at 1250°C TIT. In this paper, we will describe our approaches to the target performance of the CGT302 and current status.

scholarly journals High-Temperature Turbine Technology Readiness

1982 ◽  
Author(s):  
M. W. Horner ◽  
A. Caruvana
Keyword(s):  
High Temperature ◽  
Gas Turbine ◽  
Phase Ii ◽  
Combined Cycle ◽  
Technology Readiness ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Combined Cycle Plant ◽  
Gas Fuel

Final component and technology verification tests have been completed for application to a 2600°F rotor inlet temperature gas turbine. These tests have proven the capability of combustor, turbine hot section, and IGCC fuel systems and controls to operate in a combined cycle plant burning a coal-derived gas fuel at elevated gas turbine inlet temperatures (2600–3000°F). This paper presents recent test results and summarizes the overall progress made during the DOE-HTTT Phase II program.

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