2750 Deg F Engine Test of a Transpiration Air-Cooled Turbine

1971 ◽  
Vol 93 (2) ◽  
pp. 238-248 ◽  
Author(s):  
S. L. Moskowitz ◽  
S. Lombardo
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Effective Means ◽  
Inlet Temperature ◽  
Test Results ◽  
Gas Temperature ◽  
Supersonic Aircraft ◽  
Turbine Inlet ◽  
Marine Applications ◽  
Turbine Blading

The development of gas turbine engines for advanced subsonic and supersonic aircraft as well as for potential utilization of these high performance engines for stationary and marine applications requires, as a key element, the ability to operate at turbine inlet temperatures above the actual melting temperatures of the turbine materials. A limit on gas temperature levels is imposed by the fact that current alloys available for use in turbines, exhibit inadequate strength and oxidation characteristics above 1600–1800 deg F. However, the performance gains offered by operating engines at a high turbine inlet temperature may be realized through the application of an efficient method of cooling the highly stressed turbine components. As a step toward demonstrating that transpiration cooling of turbine blading is an effective means for achieving reliable and efficient gas turbine operation in a high gas temperature environment, a full-scale engine was tested at average gas temperatures of 2750–2800 deg F with a transpiration cooled turbine fabricated from normally used turbine alloys which are limited to metal temperatures of 1600–1800 deg F. The authors discuss the design of the transpiration air-cooled turbine, the technique used in fabricating the porous turbine blading, and the experimental test results obtained from operating the high-temperature engine. Furthermore, correlation of the test results on blade cooling with analytical predictions is presented.

Rolls Royce/Allison 501-K Gas Turbine Anti-Fouling Compressor Coatings Evaluation

2002 ◽  
Author(s):  
Daniel E. Caguiat
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbines ◽  
Performance Degradation ◽  
Specific Fuel Consumption ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Compressor Performance ◽  
Compressor Efficiency

The Naval Surface Warfare Center, Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 was tasked by NSWCCD Shipboard Energy Office Code 859 to research and evaluate fouling resistant compressor coatings for Rolls Royce Allison 501-K Series gas turbines. The objective of these tests was to investigate the feasibility of reducing the rate of compressor fouling degradation and associated rate of specific fuel consumption (SFC) increase through the application of anti-fouling coatings. Code 9334 conducted a market investigation and selected coatings that best fit the test objective. The coatings selected were Sermalon for compressor stages 1 and 2 and Sermaflow S4000 for the remaining 12 compressor stages. Both coatings are manufactured by Sermatech International, are intended to substantially decrease blade surface roughness, have inert top layers, and contain an anti-corrosive aluminum-ceramic base coat. Sermalon contains a Polytetrafluoroethylene (PTFE) topcoat, a substance similar to Teflon, for added fouling resistance. Tests were conducted at the Philadelphia Land Based Engineering Site (LBES). Testing was first performed on the existing LBES 501-K17 gas turbine, which had a non-coated compressor. The compressor was then replaced by a coated compressor and the test was repeated. The test plan consisted of injecting a known amount of salt solution into the gas turbine inlet while gathering compressor performance degradation and fuel economy data for 0, 500, 1000, and 1250 KW generator load levels. This method facilitated a direct comparison of compressor degradation trends for the coated and non-coated compressors operating with the same turbine section, thereby reducing the number of variables involved. The collected data for turbine inlet, temperature, compressor efficiency, and fuel consumption were plotted as a percentage of the baseline conditions for each compressor. The results of each plot show a decrease in the rates of compressor degradation and SFC increase for the coated compressor compared to the non-coated compressor. Overall test results show that it is feasible to utilize anti-fouling compressor coatings to reduce the rate of specific fuel consumption increase associated with compressor performance degradation.

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.

scholarly journals Shock-Expansion Wave Engines — New Directions for Power Production

1986 ◽  
Author(s):  
H. E. Weber
Keyword(s):  
High Pressure ◽  
High Performance ◽  
High Pressures ◽  
High Efficiency ◽  
Power Production ◽  
Inlet Temperature ◽  
Gas Temperature ◽  
Turbine Inlet ◽  
Discharge Temperature ◽  
Cycle Efficiency

For decades large amounts of money and effort have been spent on conventional turbomachinery development. Initially improvements in performance were rapid. However, in the last two decades better performance of these machines has slowed considerably. Compressor efficiencies have been near their present limits of 88% to 92% for many years. High pressure ratios required of high performance engines are not efficiently produced in the conventional turbomachines. High pressure ratios for high cycle efficiency require many stages of conventional compression. Compressors, especially in small turbomachines, decrease in efficiency as the number of stages increase due to the large amounts of surface area and relatively large leakage passages in the higher pressure stages. The requirement for many stages of conventional compression also results in heavy machines. If high compressor pressure cannot be attained the turbine exhaust gas temperature may be considerably above the compressor discharge temperature; a regenerator or recuperator is then required for acceptable cycle efficiency. This results in considerable complication and high engine weight. Maximum turbine inlet temperatures in conventional machines have also been near their limit for many years. High temperatures and high pressures required for light weight, high efficiency machines are inconsistent with the requirements for high strength materials. To increase permissable turbine inlet temperatures compressor discharge air is used for blade cooling. Use of this air soon reaches its limit because the high pressure cooling air is then not available for power production. Engine power and cycle efficiency begins to decrease and a limit on turbine inlet temperature results. Consequently, new concepts in power and thrust production are required. One class of machines which may alleviate many of the above described problems are the wave rotors or engines (1 thru 15). These operate with time dependent flow in the moving rotor blade passages and steady flow in the stator parts.

Rolls Royce/Allison 501-K Gas Turbine Antifouling Compressor Coatings Evaluation

2003 ◽  
Vol 125 (3) ◽  
pp. 482-488 ◽  
Author(s):  
Daniel E. Caguiat
Keyword(s):  
Gas Turbine ◽  
Fuel Consumption ◽  
Gas Turbines ◽  
Performance Degradation ◽  
Specific Fuel Consumption ◽  
Inlet Temperature ◽  
Test Results ◽  
Turbine Inlet ◽  
Compressor Performance ◽  
Compressor Efficiency

The Naval Surface Warfare Center, Carderock Division (NSWCCD) Gas Turbine Emerging Technologies Code 9334 was tasked by NSWCCD Shipboard Energy Office Code 859 to research and evaluate fouling resistant compressor coatings for Rolls Royce Allison 501-K Series gas turbines. The objective of these tests was to investigate the feasibility of reducing the rate of compressor fouling degradation and associated rate of specific fuel consumption (SFC) increase through the application of anti-fouling coatings. Code 9334 conducted a market investigation and selected coatings that best fit the test objective. The coatings selected were Sermalon for compressor stages 1 and 2 and Sermaflow S4000 for the inlet guide vanes and remaining 12 compressor stages. Both coatings are manufactured by Sermatech International, are intended to substantially decrease blade surface roughness, have inert top layers, and contain an anti-corrosive aluminum-ceramic base coat. Sermalon contains a Polytetrafluoroethylene (PTFE) topcoat, a substance similar to Teflon, for added fouling resistance. Tests were conducted at the Philadelphia Land Based Engineering Site (LBES). Testing was first performed on the existing LBES 501-K17 gas turbine, which had an uncoated compressor. The compressor was then replaced by a coated compressor and the test was repeated. The test plan consisted of injecting a known amount of salt solution into the gas turbine inlet while gathering compressor performance degradation and fuel economy data for 0, 500, 1000, and 1250 KW generator load levels. This method facilitated a direct comparison of compressor degradation trends for the coated and uncoated compressors operating with the same turbine section, thereby reducing the number of variables involved. The collected data for turbine inlet, temperature, compressor efficiency, and fuel consumption were plotted as a percentage of the baseline conditions for each compressor. The results of each plot show a decrease in the rates of compressor degradation and SFC increase for the coated compressor compared to the uncoated compressor. Overall test results show that it is feasible to utilize antifouling compressor coatings to reduce the rate of specific fuel consumption increase associated with compressor performance degradation.

scholarly journals Ceramic Small Gas Turbine Technology Demonstrator

1990 ◽  
Author(s):  
Tibor Bornemisza
Keyword(s):  
Power Systems ◽  
Gas Turbine ◽  
High Performance ◽  
Weight Ratio ◽  
High Strength ◽  
Ceramic Materials ◽  
Inlet Temperature ◽  
Development Effort ◽  
Turbine Wheel ◽  
Turbine Inlet

Requirements for increased power density, improved fuel economy, and rapid start demand higher turbine inlet temperatures and turbine wheel tip speeds, resulting in the need for materials with high strength to weight ratio at temperatures in excess of 2000°F. High performance ceramics appear to be the most promising substitutes for the current cobalt-nickel based superalloys. The numerous advantages of ceramics are coupled with several unfavorable properties, such as the brittleness, the low reliability of the ceramic pans, and the lack of established design, manufacturing and inspection techniques. The development of reliable components requires a close cooperation between the user and the manufacturer of the high performance ceramics. Sundstrand Power Systems has been involved with the development of ceramic gas turbine components since 1972. The current Research and Development effort involves the demonstration of ceramic turbine components operating at 2200°F turbine inlet temperature. Silicon nitride turbine wheel and stationary components were designed and subjected to a series of tests in the Gemini small gas turbine modified for this purpose. Engine start to full speed in 2.5 seconds and continuous operation at 2300°F was demonstrated. The successful testing of the ceramic turbine components demonstrated the feasibility of the currently available structural ceramic materials for non-flight-critical and unmanned turbine applications.

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.

scholarly journals Conjugated heat transfer analysis of gas turbine vanes using MacCormack's technique

2008 ◽  
Vol 12 (3) ◽  
pp. 65-73 ◽  
Author(s):  
Micha Kumar ◽  
N. Alagumurthi ◽  
K. Palaniradja
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Turbine Blades ◽  
Heat Transfer Analysis ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Material Development ◽  
Turbine Vanes

It is well known that turbine engine efficiency can be improved by increasing the turbine inlet gas temperature. This causes an increase of heat load to the turbine components. Current inlet temperature level in advanced gas turbine is far above the melting point of the vane material. Therefore, along with high temperature material development, sophisticated cooling scheme must be developed for continuous safe operation of gas turbine with high performance. Gas turbine blades are cooled internally and externally. Internal cooling is achieved by passing the coolant through passages inside the blade and extracting the heat from outside of the blade. This paper focuses on turbine vanes internal cooling. The effect of arrangement of rib and parabolic fin turbulator in the internal cooling channel and numerical investigation of temperature distribution along the vane material has been presented. The formulations for the internal cooling for the turbine vane have been done and these formulated equations are solved by MacCormack's technique.

scholarly journals Gas Turbine Performance Enhancement for Naval Ship Propulsion using Wave Rotors

2019 ◽  
Author(s):  
A Fatsis ◽  
A S N Al Balushi
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
High Speed ◽  
High Performance ◽  
Performance Enhancement ◽  
Waste Heat ◽  
Specific Power ◽  
Inlet Temperature ◽  
Wave Rotor ◽  
Turbine Inlet

The propulsion demands of high speed naval vessels often rely on gas turbines fitted in small engine rooms, producing significant amounts of power achieving thus high performance requirements. Gas turbines can be used either to provide purely mechanical propulsion, or alternatively to generate electricity, which is subsequently used by electric drives to propel the ship. However, the thermal efficiencies of gas turbines are lower than those of Diesel engines of similar power, in addition to the fact that all gas turbines are less efficient as the ambient temperature rises, particularly for aero-derivative engines. In the context of improving the performance of existing marine gas turbines with minimum modifications to their baseline configuration, this article is proposing engine’s performance enhancement by integrating a pressure wave supercharger (or wave rotor), while keeping the compressor, combustion chamber and turbine entry temperature of the baseline engine unchanged. Thermodynamic cycle analysis for two-shaft gas turbine engines configurations with and without heat exchanger to recuperate the waste heat from the exhaust gases, typical for marine propulsion is performed for the baseline engines, as well as for the topped with four-port wave rotor engines, at design point conditions and their performances are compared accordingly. Important benefits are obtained for four-port wave rotor-topped engines in comparison to the self-standing baseline engines for the whole range of engine’s operation. It is found that the higher the turbine inlet temperature is, the more the benefit gain of the wave rotor topped engine is attained in terms of efficiency and specific power. It is also concluded that the integration of wave rotor particularly favours engines operating at low compressor pressure ratios and high turbine inlet temperatures. The effect of variation of the most important parameters on performance of the topped engine is investigated. It is concluded that wave rotor topping of marine gas turbines can lead to fuel savings and power increase.

scholarly journals Cooled Radial In-Flow Turbines for Advanced Gas Turbine Engines

1981 ◽  
Author(s):  
J. M. Lane
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Turbine Engines ◽  
Inlet Temperature ◽  
Internal Cooling ◽  
Gas Turbine Engines ◽  
Radial Turbine ◽  
Internally Cooled ◽  
Subsequent Discussion ◽  
Near Term

While the radial in-flow turbine has consistently demonstrated its capability as a high-performance component for small gas turbine engines, its use has been relegated to lower turbine-inlet-temperature cycles due to insurmountable problems with respect to the manufacturing of radial turbine rotors with internal cooling passages. These cycle temperature limitations are not consistent with modern trends toward higher-performance, fuel-conservative engines. This paper presents the results of several Army-sponsored programs, the first of which addresses the performance potential for the high-temperature radial turbine. The subsequent discussion presents the results of two successful programs dedicated to developing fabrication techniques for internally cooled radial turbines, including mechanical integrity testing. Finally, future near-term capabilities are projected.

Application of Ultra-Low NOx Combustor to the MHPS Existing Gas Turbine

2021 ◽  
Author(s):  
Takashi Nishiumi ◽  
Hirofumi Ohara ◽  
Kotaro Miyauchi ◽  
Sosuke Nakamura ◽  
Toshishige Ai ◽  
...  
Keyword(s):  
High Pressure ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Combined Cycle ◽  
Inlet Temperature ◽  
Operational Experience ◽  
Emission Rates ◽  
Gas Temperature ◽  
Design Development ◽  
And Control

Abstract In recent years, MHPS achieved a NET M501J gas turbine combined cycle (GTCC) efficiency in excess of 62% operating at 1,600°C, while maintaining NOx under 25ppm. Taking advantage of our gas turbine combustion design, development and operational experience, retrofits of earlier generation gas turbines have been successfully applied and will be described in this paper. One example of the latest J-Series technologies, a conventional pilot nozzle was changed to a premix type pilot nozzle for low emission. The technology was retrofitted to the existing F-Series gas turbines, which resulted in emission rates of lower than 9ppm NOx(15%O2) while maintaining the same Turbine Inlet Temperature (TIT: Average Gas Temperature at the exit of the transition piece). After performing retrofitting design, high pressure rig tests, the field test prior to commercial operation was conducted on January 2019. This paper describes the Ultra-Low NOx combustor design features, retrofit design, high pressure rig test and verification test results of the upgraded M501F gas turbine. In addition, it describes another upgrade of turbine to improve efficiency and of combustion control system to achieve low emissions. Furthermore it describes the trouble-free upgrade of seven (7) units, which was completed by utilizing MHPS integration capabilities, including handling all the design, construction and service work of the main equipment, plant and control systems.

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