Design and Development of a Convective Air-Cooled Turbine and Test Facility

1961 ◽  
Vol 83 (1) ◽  
pp. 9-17
Author(s):  
W. F. Weatherwax
Keyword(s):  
Axial Flow ◽  
Weight Ratio ◽  
Fold Increase ◽  
Test Facility ◽  
Inlet Temperature ◽  
Air Cooling ◽  
Turbine Inlet Temperature ◽  
Jet Engine ◽  
Engine Thrust ◽  
Turbine Inlet

Demands for higher jet engine thrust-to-weight ratios to satisfy the needs for high Mach number and vertical take-off aircraft are continually increasing. Since World War II, the three-fold increase in thrust-to-weight ratio can be attributed almost entirely to the development of lightweight construction and the axial-flow compressor, and little credit can be given to the meager 200-F increase in turbine-inlet temperature. Increasing turbine-inlet temperature, beyond present-day material limits of 1600-1700 F, by convective air cooling, will increase the jet-engine thrust-to-weight ratio and will markedly improve the performance of the turboprop and bypass engines. The partial results of a program undertaken by the author’s company to develop a fully cooled, flight-type, turbine and test facility are reported. The design heat-transfer considerations are discussed, the test facility described, and performance results to date are given.

Long-Life Base Load Service at 1600 F Turbine Inlet Temperature

1967 ◽  
Vol 89 (1) ◽  
pp. 41-46 ◽  
Author(s):  
N. E. Starkey
Keyword(s):  
Inlet Temperature ◽  
Air Cooling ◽  
Turbine Inlet Temperature ◽  
Fuel Distribution ◽  
Design Considerations ◽  
Turbine Inlet ◽  
Accurate Temperature ◽  
Long Life ◽  
Accurate Temperature Control ◽  
Base Load

Design considerations required for base load long-life service at turbine inlet temperature above 1600 F are discussed. These include control of combustion profile, air cooling of the first-stage nozzle, long-shank turbine buckets, accurate air and fuel distribution, and accurate temperature control.

Micro Gas Turbine With Ceramic Nozzles and Rotor: Part 2

2006 ◽  
Author(s):  
Norihiko Iki ◽  
Takahiro Inoue ◽  
Takayuki Matsunuma ◽  
Hiro Yoshida ◽  
Satoshi Sodeoka ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Efficiency ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Metal Combustion ◽  
Jet Engine ◽  
Rotating Speed ◽  
Micro Gas Turbine ◽  
Turbine Inlet

In order to develop a micro gas turbine with high turbine inlet temperature and thermal efficiency, a series of running tests has been carried out. J-850 jet engine (Sophia Precision Co., Ltd.) was chosen as a baseline machine. The turbine nozzle and the rotor are replaced by type SN-01 (Otsuka Ceramics Co., Ltd.) and type SN-235 (Kyocera Corporation) ceramic elements, respectively. By using type 3a engine, we succeeded one-hour running test of the engine without cooling and severe damages. The turbine inlet temperature was higher than 1000 °C. The rotating speed was about 120,000 rpm. Performances of the type 3a engine (with ceramic nozzle and rotor) and the type 1 (with Inconel alloy nozzle and ceramic rotor) were compared as follows: At the same rotation speed, turbine inlet temperature of the type 3a became higher than that of the type 1. Simultaneously, fuel consumption of type 3a was larger than that of the type 1. Thrust of the type 3a was slightly larger than that of the type 1. Those results imply that the thermal efficiency of type 3a is slightly, 2%, lower than that of the type 1. The present sealing configurations between ceramic nozzle-vanes and their holder plate and ceramic rotor-housing and metal combustion chamber were found to work well.

Analysis of Integrated Cooling Systems for Gas Turbine Power Plants

2017 ◽  
Author(s):  
Waleed El-Damaty ◽  
Mohamed Gadalla
Keyword(s):  
Gas Turbine ◽  
Power Plants ◽  
Turbine Blades ◽  
Operating Conditions ◽  
Inlet Temperature ◽  
Air Cooling ◽  
Turbine Inlet Temperature ◽  
Current Increase ◽  
Turbine Inlet ◽  
Compact Size

With the current increase in electricity consumption and energy demand, most of the research focus is shifted towards the means of increasing the power plants efficiency in order to produce more electricity by using as less fuel as possible. Gas turbine power plants specifically have been under the study in the recent years due to its feasibility, low capital cost, simple design, compact size and higher efficiency compared to steam turbine power plants. There are a lot of operating conditions that affect the performance of the gas turbine which includes the inlet air climatic conditions, mass flow rate and the turbine inlet temperature. Many improvements and enhancements became applicable through the advancement in the material and cooling technologies. Cooling techniques could be used to cool the inlet air entering the compressor by utilizing evaporative coolers and mechanical chillers, and to cool the turbine blades in order to avoid a decline in the life of turbine blades due to unwanted exposure to thermal stresses and oxidation. Internal convection cooling, film cooling and transpiration cooling are the three main techniques that can be used in the process of turbine blades cooling. The main objective of this proposal is to improve the durability and performance of gas turbine power plants by proposing the usage of integrated system of solid desiccant with Maisotsenko cooler in the turbine blade cooling and inlet air cooling processes. Four configurations were presented and the results were an increase in the efficiency of the gas turbine cycle for all the cases specially the two stage Maisotsenko desiccant cooling system where the efficiency increased from 33.33% to 34.17% as well as maintaining the turbine inlet temperature at a desired level of 1500°K.

Introduction of Intercooling in a High Bypass Jet Engine

2000 ◽  
Author(s):  
Tilemachos Papadopoulos ◽  
Pericles Pilidis
Keyword(s):  
Heat Pipe ◽  
Pressure Ratio ◽  
Preliminary Investigation ◽  
Propulsion System ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Jet Engine ◽  
Turbine Inlet ◽  
Weight Penalty ◽  
Bypass Ratio

In this paper an exercise to introduce intercooling in a high bypass civil turbofan is outlined. The engine selected as the basic propulsion system is a three spool high bypass turbofan with a bypass ratio 6.4. The air leaving the IP compressor is cooled in the bypass duct prior to entering the HP compressor. This preliminary investigation appears to indicate that the main benefit to be gained is an increase in the net thrust from the engine without increasing the turbine inlet temperature. To keep engine diameter constant, the bypass ratio has not been changed. This results in a requirement to significantly increase the pressure ratio to reduce the SFC levels to an acceptable value. A sizing exercise has been carried out to understand the weight and volume penalties imposed by heat pipe intercooling hardware. The preliminary sizing exercise indicates that the weight penalty is very large. The performance of the aircraft using the intercooled engines is also investigated and some improvements in performance are predicted. Overall this investigation is considered to be positive so that further investigations should be considered. It appears that an intercooled engine can produce a somewhat higher thrust at a given turbine entry temperature at similar SFC levels of current engines, or, if a small increase in SFC is acceptable, the increase in thrust is quite important.

Experimental Investigation of an Inverted Brayton Cycle for Exhaust Gas Energy Recovery

2018 ◽  
Vol 141 (3) ◽  
Author(s):  
Ian Kennedy ◽  
Zhihang Chen ◽  
Bob Ceen ◽  
Simon Jones ◽  
Colin D. Copeland
Keyword(s):  
Experimental Investigation ◽  
Pressure Drop ◽  
Test Facility ◽  
Inlet Temperature ◽  
Specific Work ◽  
Brayton Cycle ◽  
Turbine Inlet Temperature ◽  
Exhaust Gases ◽  
Turbine Inlet ◽  
System Pressure

Exhaust gases from an internal combustion engine (ICE) contain approximately 30% of the total energy released from combustion of the fuel. In order to improve fuel economy and reduce emissions, there are a number of technologies available to recover some of the otherwise wasted energy. The inverted Brayton cycle (IBC) is one such technology. The purpose of this study is to conduct a parametric experimental investigation of the IBC. The hot air from a turbocharger test facility is used. The system is sized to operate using the exhaust gases produced by a 2 l turbocharged engine at motorway cruise conditions. A number of parameters are investigated that impact the performance of the system such as turbine inlet temperature, system pressure drop, and compressor inlet temperature. The results confirm that the output power is strongly affected by the turbine inlet temperature and system pressure drop. The study also highlights the packaging and performance advantages of using an additively manufactured heat exchanger to reject the excess heat. Due to rotordynamic issues, the speed of the system was limited to 80,000 rpm rather than the target 120,000 rpm. However, the results show that the system can generate a specific work of up to 17 kJ/kg at 80,000 rpm. At full speed, it is estimated that the system can develop approximately 47 kJ/kg, which represents a thermal efficiency of approximately 5%.

Status of the Development of the CGT301, a 300 KW Class Ceramic Gas Turbine

1996 ◽  
Author(s):  
Takao Mikami ◽  
Shinya Tanaka ◽  
Masashi Tatsuzawa ◽  
Takeshi Sakida
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Blades ◽  
Axial Flow ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Turbine Inlet ◽  
All Ceramic ◽  
Ceramic Components ◽  
Primary Type

The CGT301 ceramic gas turbine is being developed under a contract from NEDO as a part of the New Sunshine Program of MTTI to improve the performance of gas turbines for cogeneration through the replacement of hot section components with ceramic parts. The project is conducted in three phases. The project currently in Phase 2 focuses on the development of the “primary type” ceramic gas turbine (turbine inlet temperature: 1,200°C). CGT301 is a recuperated, single-shaft, ceramic gas turbine. The turbine is a two-stage axial flow type. The major effort has been on the development of the turbine which consists of metallic disks and inserted ceramic blades (“hybrid rotor”). Prior to engine tests, component tests were performed on the hybrid rotor to prove the validity of the design concepts and their mechanical integrity. The engine equipped with all ceramic components except the second stage turbine blades was tested and evaluated. The engine was operated successfully for a total of 23 hours without failure at the rated engine speed of 56,000 rpm with the turbine inlet temperature of 1,200 °C. Further, the engine equipped with all ceramic components was successfully tested for one hour under the same conditions. Engine testing of the “primary type” ceramic gas turbine is continuing to improve the performance and the reliability of the system for the purpose of moving forward to the development of the “pilot” ceramic gas turbine (turbine inlet temperature: 1,350 °C) as the final target of this project. This paper summarizes the progress in the development of the CGT301 with the emphasis on the test results of the hybrid rotor.

scholarly journals Experimental Investigation of an Inverted Brayton Cycle for Exhaust Gas Energy Recovery

2018 ◽  
Author(s):  
Ian Kennedy ◽  
Zhihang Chen ◽  
Bob Ceen ◽  
Simon Jones ◽  
Colin D. Copeland
Keyword(s):  
Experimental Investigation ◽  
Pressure Drop ◽  
Test Facility ◽  
Inlet Temperature ◽  
Specific Work ◽  
Brayton Cycle ◽  
Turbine Inlet Temperature ◽  
Exhaust Gases ◽  
Turbine Inlet ◽  
System Pressure

Exhaust gases from an internal combustion engine (ICE) contain approximately 30% of the total energy released from combustion of the fuel. In order to improve fuel economy and reduce emissions, there are a number of technologies available to recover some of the otherwise wasted energy. The inverted Brayton cycle (IBC) is one such technology. The purpose of the study is to conduct a parametric experimental investigation of the IBC. Hot air from a turbocharger test facility is used. The system is sized to operate using the exhaust gases produced by a 2 litre turbocharged engine at motorway cruise conditions. A number of parameters are investigated that impact the performance of the system such as turbine inlet temperature, system pressure drop and compressor inlet temperature. The results confirm that the output power is strongly affected by the turbine inlet temperature and system pressure drop. The study also highlights the packaging and performance advantages of using a 3D printed heat exchanger to reject the excess heat. Due to rotordynamic issues, the speed of the system was limited to 80,000 rpm rather than the target 120,000 rpm. However, the results show that the system can generate a specific work of up to 17 kJ/kg at 80,000 rpm. At full speed it is estimated that the system can develop approximately 47 kJ/kg, which represents a thermal efficiency of approximately 5%.

Combined First and Second-Law Analysis of Gas Turbine Cogeneration System With Inlet Air Cooling and Evaporative Aftercooling of the Compressor Discharge

2007 ◽  
Vol 129 (4) ◽  
pp. 1004-1011 ◽  
Author(s):  
A. Khaliq ◽  
K. Choudhary
Keyword(s):  
Relative Humidity ◽  
Gas Turbine ◽  
Pressure Ratio ◽  
Second Law ◽  
Inlet Temperature ◽  
Air Cooling ◽  
Exergy Destruction ◽  
Turbine Inlet Temperature ◽  
Ambient Relative Humidity ◽  
Turbine Inlet

A conceptual gas turbine based cogeneration cycle with compressor inlet air cooling and evaporative aftercooling of the compressor discharge is proposed to increase the cycle performance significantly and render it practically insensitive to seasonal temperature fluctuations. Combined first and second-law approach is applied for a cogeneration system having intercooled reheat regeneration in a gas turbine as well as inlet air cooling and evaporative aftercooling of the compressor discharge. Computational analysis is performed to investigate the effects of the overall pressure ratio rp, turbine inlet temperature (TIT), and ambient relative humidity φ on the exergy destruction in each component, first-law efficiency, power-to-heat ratio, and second-law efficiency of the cycle. Thermodynamic analysis indicates that exergy destruction in various components of the cogeneration cycle is significantly affected by overall pressure ratio and turbine inlet temperature, and not at all affected by the ambient relative humidity. It also indicates that the maximum exergy is destroyed during the combustion process, which represents over 60% of the total exergy destruction in the overall system. The first-law efficiency, power-to-heat ratio, and second-law efficiency of the cycle significantly vary with the change in the overall pressure ratio and turbine inlet temperature, but the change in relative humidity shows small variations in these parameters. Results clearly show that performance evaluation based on first-law analysis alone is not adequate, and hence, more meaningful evaluation must include second-law analysis. Decision makers should find the methodology contained in this paper useful in the comparison and selection of advanced combined heat and power systems.

Field and Laboratory Evaluations of Commercial and Next-Generation Alumina-Forming Austenitic Foil for Advanced Recuperators

2016 ◽  
Vol 138 (12) ◽  
Author(s):  
Bruce A. Pint ◽  
Sebastien Dryepondt ◽  
Michael P. Brady ◽  
Yukinori Yamamoto ◽  
Bo Ruan ◽  
...  
Keyword(s):  
Field Trials ◽  
Austenitic Steels ◽  
Inlet Temperature ◽  
Next Generation ◽  
Turbine Inlet Temperature ◽  
New Class ◽  
Turbine Inlet ◽  
Higher Temperature ◽  
Oxidation Testing

Alumina-forming austenitic (AFA) steels represent a new class of corrosion- and creep-resistant austenitic steels designed to enable higher temperature recuperators. Field trials are in progress for commercially rolled foil with widths over 39 cm. The first trial completed 3000 hrs in a microturbine recuperator with an elevated turbine inlet temperature and showed limited degradation. A longer microturbine trial is in progress. A third exposure in a larger turbine has passed 16,000 hrs. To reduce alloy cost and address foil fabrication issues with the initial AFA composition, several new AFA compositions are being evaluated in creep and laboratory oxidation testing at 650–800 °C and the results compared to commercially fabricated AFA foil and conventional recuperator foil performance.

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