Closure to “Discussions of ‘Long-Life Base Load Service at 1600 F Turbine Inlet Temperature’” (1967, ASME J. Eng. Power, 89, pp. 46–48)

1967 ◽  
Vol 89 (1) ◽  
pp. 48-48
Author(s):  
N. E. Starkey
Keyword(s):  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Turbine Inlet ◽  
Long Life ◽  
Base Load

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.

Experimental Results of a Transpiration-Cooled Turbine Operated in an Engine for 150 Hours at 2500 F Turbine Inlet Temperature

1967 ◽  
Author(s):  
S. Lombardo ◽  
S. L. Moskowitz ◽  
S. A. Schnure
Keyword(s):  
Effective Means ◽  
Turbine Blades ◽  
Strength Properties ◽  
Inlet Temperature ◽  
High Melting Point ◽  
Turbine Inlet Temperature ◽  
Supersonic Aircraft ◽  
Melting Temperatures ◽  
Turbine Inlet ◽  
Long Life

A key element in the development of gas turbine powerplants for advanced subsonic and supersonic aircraft is the ability to operate at turbine inlet temperatures significantly above the 1600–1800 F limit of today. This limit is imposed by the fact that current materials available for use in turbines exhibit inadequate strength and oxidation characteristics above 1600–1800 F. Certain metals such as molybdenum, chromium, tungsten and other high-melting-point alloys show good strength properties at temperatures far above which conventional super alloys are useful in turbines. However, these materials lack either the ductility or oxidation resistance necessary for turbine components. A means of realizing the gains possible by operating turbines at high turbine inlet temperatures is through cooling of the highly stressed turbine components. The necessity of reliable and efficient turbine operation for periods of long life in an environment of gas temperatures above the actual melting temperatures of the materials requires that effective means of cooling the blades be developed. The authors discuss the design of transpiration air cooled turbines as a means of operating engines at gas temperatures of 2500 F and higher, utilizing available turbine materials which are limited to metal temperatures between 1600 and 1800 F. The technique utilized in fabricating transpiration air cooled turbine blades is discussed. The results of operating a full-scale J65 engine, modified to incorporate a single-stage turbine fitted with transpiration air cooled blades, for 150 hr at 2500 F turbine inlet temperature are presented.

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.

Influence of Turbine Inlet Temperature on the Efficiency of Externally Fired Gas Turbines

2014 ◽  
pp. 79-95 ◽  
Author(s):  
Paulo Eduardo Batista de Mello ◽  
Sérgio Scuotto ◽  
Fernando dos Santos Ortega ◽  
Gustavo Henrique Bolognesi Donato
Keyword(s):  
Gas Turbines ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Turbine Inlet

Expanding Fuel Flexibility in MHPS’ Dry Low NOx Combustor

2018 ◽  
Author(s):  
Katsuyoshi Tada ◽  
Kei Inoue ◽  
Tomo Kawakami ◽  
Keijiro Saitoh ◽  
Satoshi Tanimura
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Environmental Conservation ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Turbine Inlet Temperature ◽  
Social Perspectives ◽  
Turbine Inlet ◽  
Fuel Flexibility

Gas-turbine combined-cycle (GTCC) power generation is clean and efficient, and its demand will increase in the future from economic and social perspectives. Raising turbine inlet temperature is an effective way to increase combined cycle efficiency and contributes to global environmental conservation by reducing CO2 emissions and preventing global warming. However, increasing turbine inlet temperature can lead to the increase of NOx emissions, depletion of the ozone layer and generation of photochemical smog. To deal with this issue, MHPS (MITSUBISHI HITACHI POWER SYSTEMS) and MHI (MITSUBISHI HEAVY INDUSTRIES) have developed Dry Low NOx (DLN) combustion techniques for high temperature gas turbines. In addition, fuel flexibility is one of the most important features for DLN combustors to meet the requirement of the gas turbine market. MHPS and MHI have demonstrated DLN combustor fuel flexibility with natural gas (NG) fuels that have a large Wobbe Index variation, a Hydrogen-NG mixture, and crude oils.

Development of the Advanced Closed-Cycle Gas Turbine System

2001 ◽  
Author(s):  
Miki Koyama ◽  
Toshio Mimaki
Keyword(s):  
Film Cooling ◽  
Cooling System ◽  
Early Stage ◽  
Turbine Blades ◽  
Thermal Conditions ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Turbine Inlet Temperature ◽  
Turbine Blade Cooling ◽  
Turbine Inlet

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.

Proposal of Innovative Gas Turbine Combined Cycle Power Generation System

2004 ◽  
Author(s):  
Hideto Moritsuka
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Thermal Efficiency ◽  
Pressure Ratio ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Generation System ◽  
Turbine Inlet Temperature ◽  
Turbine Inlet ◽  
Power Generation System

In order to estimate the possibility to improve thermal efficiency of power generation use gas turbine combined cycle power generation system, benefits of employing the advanced gas turbine technologies proposed here have been made clear based on the recently developed 1500C-class steam cooling gas turbine and 1300C-class reheat cycle gas turbine combined cycle power generation systems. In addition, methane reforming cooling method and NO reducing catalytic reheater are proposed. Based on these findings, the Maximized efficiency Optimized Reheat cycle Innovative Gas Turbine Combined cycle (MORITC) Power Generation System with the most effective combination of advanced technologies and the new devices have been proposed. In case of the proposed reheat cycle gas turbine with pressure ratio being 55, the high pressure turbine inlet temperature being 1700C, the low pressure turbine inlet temperature being 800C, combined with the ultra super critical pressure, double reheat type heat recovery Rankine cycle, the thermal efficiency of combined cycle are expected approximately 66.7% (LHV, generator end).

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