Lycoming T-53 Gas Turbine Engine Modification for Industrial Application

2007 ◽  
Author(s):  
Vladimir Lupandin ◽  
Martyn Hexter ◽  
Alexander Nikolayev
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Alternative Fuels ◽  
Phase 1 ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Combustion System ◽  
Original Design ◽  
High Hydrogen ◽  
Turbine Engine

This paper describes a development program active at Magellan Aerospace Corporation since 2003, whereby specific modifications are incorporated into an Avco Lycoming T-53 helicopter gas turbine engine to enable it to function as a ground based Industrial unit for distributed power generation. The Lycoming T-53 is a very well proven and reliable two shaft gas turbine engine whose design can be traced back to the 1950s and the fact of its continued service to the present day is a tribute to the original design/development team. Phase 1 of the Program introduces abradable rotor path linings, blade coatings and changes to seal and blade tip clearances. Magellan has built a test cell to run the power generation units to full speed and full power in compliance with ISO 2314. In co-operation with Zorya-Mashproekt, Ukraine, the exhaust emissions of the existing combustion system for natural gas was reduced by 30%. New nozzles for low heat value fuels and for high hydrogen content fuels (up to 60% H2) have been developed. The T-53 gas turbine engine exhaust gas temperature is typically around 620 deg C, which makes it a very good candidate for co-generation and recuperated applications. As per Phase 2 of the program, the existing helicopter integral gearbox and separate industrial step-down gearbox will be replaced with single integral gearbox that will use the same lubrication oil system as the gas turbine engine. The engine power output will increase to 1200 kW at the generator terminals with an improvement to 25% efficiency ISO. Phase 3 of the Program will see the introduction of a new silo type combustion system, developed in order to utilize alternative fuels such as bio-diesel, biofuel (product of wood pyrolysis), land fill gases, syn gases etc. Phase 4 of the Program in cooperation with ORMA, Russia will introduce a recuperator into the package and is expected to realize a boost in overall efficiency to 37%. The results of testing the first two T-53 industrial gas turbine engines modified per Phase 1 will be presented.

Test results of the OGT2500 Gas Turbine Engine Running on Alternative Fuels: BioOil, Ethanol, BioDiesel and Crude Oil

2005 ◽  
Author(s):  
Vladimir Lupandin ◽  
Raj Thamburaj ◽  
Alexander Nikolayev
Keyword(s):  
Crude Oil ◽  
Gas Turbine ◽  
Alternative Fuels ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Engine Operation ◽  
Technical Feasibility ◽  
Turbine Engine ◽  
Full Speed ◽  
Under Construction

This paper describes the results of an on going development program aimed at determining the technical feasibility of utilizing alternative fuels such as bio-mass derived BioOil, Ethanol, Bio-Diesel and bituminous Crude Oil in a 2.5 MW GT2500 industrial Gas Turbine Engine. This gas turbine engine was designed and manufactured by “Zorya-Mashproekt” in the Ukraine and further modified for the alternative fuels application through a join development program between “Zorya-Mashproekt” and Orenda Aerospace Corporation in Canada. The modification of the GT2500 Gas Turbine Engine hot section and combustion system to operate on liquid alternative fuels are described. Also described is an engine hot section online cleaning system and features of the fuel-handling module, which carries out fuel preheating and preprocessing. A test rig equipped with a load bank was designed and built to test the modified GT2500 Gas turbine Engine on different alternative fuels (full speed/full power). Results of the modified GT2500 gas turbine engine operation along with the emissions data are presented. The tests proved the technical feasibility of operating this gas turbine engine on the alternative fuels mentioned above. Based on these results a power generation package with the engine and fuel handling module have been accepted for commercial operation in a pilot plant under construction in West Lorne, Ontario, Canada.

scholarly journals 2MW Class High Efficiency Gas Turbine IM270 for Co-Generation Plants

1996 ◽  
Author(s):  
Hideo Kobayashi ◽  
Shogo Tsugumi ◽  
Yoshio Yonezawa ◽  
Riuzou Imamura
Keyword(s):  
Gas Turbine ◽  
High Efficiency ◽  
Mechanical Design ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Maintenance Cost ◽  
Turbine Engine ◽  
Generation Plant ◽  
Emission Regulation ◽  
Heavy Duty Gas Turbine

IHI is developing a new heavy duty gas turbine engine for 2MW class co-generation plants, which is called IM270. This engine is a simple cycle and single-spool gas turbine engine. Target thermal efficiency is the higher level in the same class engines. A dry low NOx combustion system has been developed to clear the strictest emission regulation in Japan. All parts of the IM270 are designed with long life for low maintenance cost. It is planned that the IM270 will be applied to a dual fluid system, emergency generation plant, machine drive engine and so on, as shown in Fig.1. The development program of IM270 for the co-generation plant is progress. The first prototype engine test has been started. It has been confirmed that the mechanical design and the dry low NOx system are practical. The component tuning test is being executed. On the other hand, the component test is concurrently in progress. The first production engine is being manufactured to execute the endurance test using a co-generation plant at the IHI Kure factory. This paper provides the conceptual design and status of the IM270 basic engine development program.

Development of Small-sized Gas Turbine Engine Control System for Power Generation

2011 ◽  
Vol 14 (4) ◽  
pp. 52-56
Author(s):  
Seong-Jin Hong ◽  
Seung-Min Kim ◽  
Sim-Kyun Yook ◽  
Sam-Sik Nam
Keyword(s):  
Power Generation ◽  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Engine Control System

Exploration of Compact Combustors for Reheat Cycle Aero Engine Applications

2006 ◽  
Author(s):  
J. Zelina ◽  
D. T. Shouse ◽  
J. S. Stutrud ◽  
G. J. Sturgess ◽  
W. M. Roquemore
Keyword(s):  
Gas Turbine ◽  
Temperature Rise ◽  
Gas Turbines ◽  
Gas Turbine Engine ◽  
Operating Conditions ◽  
Combustion System ◽  
Turbine Engine ◽  
Lean Blowout ◽  
Power Extraction ◽  
Wide Range

An aero gas turbine engine has been proposed that uses a near-constant-temperature (NCT) cycle and an Inter-Turbine Burner (ITB) to provide large amounts of power extraction from the low-pressure turbine. This level of energy is achieved with a modest temperature rise across the ITB. The additional energy can be used to power a large geared fan for an ultra-high bypass ratio transport aircraft, or to drive an alternator for large amounts of electrical power extraction. Conventional gas turbines engines cannot drive ultra-large diameter fans without causing excessively high turbine temperatures, and cannot meet high power extraction demands without a loss of engine thrust. Reducing the size of the combustion system is key to make use of a NCT gas turbine cycle. Ultra-compact combustor (UCC) concepts are being explored experimentally. These systems use high swirl in a circumferential cavity about the engine centerline to enhance reaction rates via high cavity g-loading on the order of 3000 g’s. Any increase in reaction rate can be exploited to reduce combustor volume. The UCC design integrates compressor and turbine features which will enable a shorter and potentially less complex gas turbine engine. This paper will present experimental data of the Ultra-Compact Combustor (UCC) performance in vitiated flow. Vitiation levels were varied from 12–20% oxygen levels to simulate exhaust from the high pressure turbine (HPT). Experimental results from the ITB at atmospheric pressure indicate that the combustion system operates at 97–99% combustion efficiency over a wide range of operating conditions burning JP-8 +100 fuel. Flame lengths were extremely short, at about 50% of those seen in conventional systems. A wide range of operation is possible with lean blowout fuel-air ratio limits at 25–50% below the value of current systems. These results are significant because the ITB only requires a small (300°F) temperature rise for optimal power extraction, leading to operation of the ITB at near-lean-blowout limits of conventional combustor designs. This data lays the foundation for the design space required for future engine designs.

Conversion of the AE 1107C From the V-22 Osprey Application to Marine Service

2013 ◽  
Author(s):  
Zechariah D. Green ◽  
Sean Padfield ◽  
Andrew F. Barrett ◽  
Paul G. Jones
Keyword(s):  
Gas Turbine ◽  
System Integration ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Naval Vessel ◽  
Turbine Engine ◽  
The Us ◽  
Technical Risk ◽  
Turbine Design ◽  
System Designs

This paper presents a study on the conversion of the Rolls-Royce AE 1107C V-22 Osprey gas turbine engine into the MT7 Ship-to-Shore Connector (SSC) marine gas turbine engine. The US Navy led SSC design requires a propulsion and lift gas turbine rated at 5,230 shaft horsepower, which the AE 1107C variant MT7 is capable of providing with margin on power and specific fuel consumption. The MT7 leverages the AE family of engines to provide a propulsion and lift engine solution for the SSC craft. Extensive testing and analysis completed during the AE 1107C development program aided in the robust gas turbine design required to meet the needs of the SSC program. Requirements not met by the AE 1107C configuration were achieved with designs based on the AE family of engines and marine grade sub-system designs. Despite the fact that system integration and testing remain as key activities for integrating the MT7 with the SSC craft, conversion of the AE 1107C FAA certified engine into an American Bureau of Shipping Naval Vessel Rules Type Approved MT7 engine provides a low technical risk alternative for the demanding requirements of the SSC application.

WR21 Water Wash Development Approach for the Intercooled Recuperated (ICR) Gas Turbine Engine

1997 ◽  
Author(s):  
Jay T. Janton ◽  
Kevin Widdows
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Test Site ◽  
Gas Turbine Engine ◽  
Test Program ◽  
Turbine Engine ◽  
Baseline Design ◽  
Development Approach ◽  
Pressure Compressor ◽  
Wash Test

The WR21 Intercooled Recuperated (ICR) Gas Turbine Engine is being developed as the prime power plant for future US and Foreign Navy ship applications. The development test program started in July 1994 and is still ongoing. One of the many challenges of the ICR design is the development of the compressors and intercooler (IC) wash system. The integration of the IC between the intermediate pressure compressor (IPC) and high pressure compressor (HPC) is unique to current US Navy applications and has introduced new design considerations from traditional wash development programs that must be addressed. Significant increase in wetted surface area of the heat exchanger (HX) matrix and the radial flow are two design aspects unique to the WR21. This paper reviews the design of the WR21 engine and the challenges it offers to developing both crank and on-line compressor/IC wash systems. The baseline design of the water wash systems are discussed, in addition to the water wash test program and its integration into the overall WR2I development program. Details are also given of the off-engine wash delivery system and salt injection systems in place at the test site. Crank wash test results to date are also presented.

Development of the 5MW Power Generation Gas Turbine Engine

2011 ◽  
Author(s):  
Sooyong Kim ◽  
Sungryong Lee ◽  
Jewook Ryu ◽  
V. E. Spitsyn
Keyword(s):  
Power Generation ◽  
Gas Turbine ◽  
Nuclear Power ◽  
Peak Load ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
Load Power ◽  
The Future ◽  
Lng Fuel ◽  
Base Load

Gas turbine engine has been applied to the aircraft and ship propulsion with its advantages of compactness and comparatively short starting time. With a significant improvement in gas turbine efficiency with development of super alloy materials and advancement in cooling technologies in the second half of 1990s, its importance as a source of base load as well as peak load power generation has been increasing. However, with increased demand in nuclear power and renewable energy in the 21st century, there seems to be speculations among the power generation industries that gas turbine will take more or less a buffering role supplementing the irregular inflow of electricity to the grid rather than acting as a base load power source. With the shift in the role of gas turbine from base to supplementary, CHP application based on small powered gas turbine utilizing biogas or syngas as its fuel is expected to increase in the future. In this context, this paper describes the development result of 5MW gas turbine engine for CHP application. It can be operated with LNG or syngas of low LHV fuel. Originally, the engine was designed for LNG as its primary fuel, but since the importance of syngas power generation market will be increasing in the future, a complementary work for modification of combustor part has been carried out and has been tested. However, this paper deals with the parts developed with the use of LNG fuel. The test result of emission characteristics meets the standards required in Korea. The development has been made through the cooperation of Doosan Heavy Industry (DHI, Korea) and Zory-Mashproekt (Ukraine).

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