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.

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.

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.

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.

ABS NVR Type Approval of the Rolls-Royce Naval Marine Model MT5S Gas Turbine Engine and the RR4500 Generator Set

2014 ◽  
Author(s):  
Peter Lahm ◽  
Jack Halsey
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Lessons Learned ◽  
Test Results ◽  
Approval Process ◽  
Naval Vessel ◽  
Design Assessment ◽  
Turbine Engine ◽  
Type Approval ◽  
Type Approval Testing

This treatise examines the activities required to Type Approve the MT5S gas turbine engine and RR4500 generator set to the American Bureau of Shipping Naval Vessel Rules (ABS NVR). Detailed accounts of the various phases of the approval process and challenges encountered therein are presented. The methods utilized to achieve ABS design assessment and the process of Type Approval testing is presented. Design assessment and Type Approval test results are summarized. A discourse containing lessons learned and corrective measures for future Type Approval efforts is included.

scholarly journals Development of the AGT101 Regenerator Seals

1987 ◽  
Author(s):  
C. A. Fucinari ◽  
J. K. Vallance ◽  
C. J. Rahnke
Keyword(s):  
Gas Turbine ◽  
Pressure Ratio ◽  
Dynamic Test ◽  
Development Program ◽  
Analytical Techniques ◽  
Gas Turbine Engine ◽  
Inlet Temperature ◽  
Gas Temperature ◽  
Turbine Engine ◽  
Seal Design

The design and development of the regenerator seals used in the AGT101 gas turbine engine are described in this paper. The all ceramic AGT101 gas turbine engine was designed for 100 hp at 5:1 pressure ratio with 2500F (1371C) turbine inlet temperature. Six distinct phases of seal design were investigated experimentally and analytically to develop the final design. Static and dynamic test rig results obtained during the seal development program are presented. In addition, analytical techniques are described. The program objectives of reduced seal leakage, without additional diaphragm cooling, to 3.6% of total engine airflow and higher seal operating temperature resulting from the 2000F (1093C) inlet exhaust gas temperature were met.

Enhanced TF40B Gas Turbine Engine Development Program

2002 ◽  
Author(s):  
Roger Yee ◽  
Lee Myers ◽  
Ken Braccio ◽  
Mike Dvornak
Keyword(s):  
Gas Turbine ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Life Extension ◽  
Engine Control ◽  
Turbine Engine ◽  
Analog Control ◽  
Service Life Extension ◽  
Land Systems ◽  
Engine Development

The Navy Landing Craft Air Cushion (LCAC) Service Life Extension Program (SLEP) upgrades the current TF40B gas turbine engine and analog control system on the LCAC to an Enhanced TF40B (ETF40B) gas turbine with a Full Authority Digital Engine Control (FADEC) system. This upgrade and enhancement will provide additional engine horsepower, increased engine reliability, and modern digital engine control equipment to the LCAC. The success of the ETF40B engine development program has been an ongoing effort between the Navy, the LCAC craft builder Textron Marine & Land Systems (TM&LS), and the engine manufacturer Honeywell Engine and Systems. This paper will document and outline the differences between the TF40B and ETF40B and the efforts of the ETF40B 150 hour endurance qualification test.

A New 10,000-Hp Gas Turbine Engine for Industrial Service

1977 ◽  
Author(s):  
P. W. Pichel
Keyword(s):  
Gas Turbine ◽  
High Performance ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Simple Cycle ◽  
Turbine Engine ◽  
Design Philosophy ◽  
Industrial Service ◽  
Engine Development ◽  
Future Plans

This paper summarizes the scope and results to date of a program initiated in 1974 to develop a high-performance, simple-cycle, 10,000-hp engine for application in gas compressor, mechanical drive, and generator set packages. Design philosophy, a detailed description, and component and engine development testing are covered. Future plans for the development program up to the point of production availability in 1978 are also outlined.

Development of a Centrifugal Compressor for a Small Gas-Turbine Engine

1956 ◽  
Author(s):  
N. R. Balling ◽  
V. W. van Ornum
Keyword(s):  
Research And Development ◽  
Gas Turbine ◽  
Fuel Consumption ◽  
Centrifugal Compressor ◽  
Pressure Ratio ◽  
Development Program ◽  
Gas Turbine Engine ◽  
Specific Fuel Consumption ◽  
General Description ◽  
Turbine Engine

The objective of the research and development program reported by this paper was to decrease the specific fuel consumption of a small gas-turbine engine by means of an increase in pressure ratio alone. Development of a centrifugal compressor is presented, with a general description of equipment, methods, and special problems met during the tests. Results showed the required decrease in specific fuel consumption and pointed up the advantages of a straightforward development program.

Integration of the ETF40B Gas Turbine Engine and FADEC System Into the Landing Craft Air Cushion Vehicle

2000 ◽  
Author(s):  
Howard Harris ◽  
Phil Schneider ◽  
John Richards ◽  
Mike Dvornak
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Field Testing ◽  
Gas Turbine Engine ◽  
Design Development ◽  
Turbine Engine ◽  
Analog Control ◽  
The Us ◽  
Land Systems ◽  
Air Cushion

The US Navy along with Textron Marine & Land Systems (TM&LS) is qualifying and field testing the ETF40B gas turbine engine along with Full Authority Digital Engine Control (FADEC) system as possible upgrades to the current TF40B engine and analog control system currently installed on the Landing Craft Air Cushion (LCAC). The ETF40B engine and FADEC control system are of interest due to: increased power, proposed increase in Mean Time Between Overhauls (MTBO), and proposed increase in engine reliability. The primary topics presented in this paper are: 1. The design, development, and qualification of the ETF40B engine and FADEC control system 2. Integration of the ETF40B engine and FADEC into the LCAC 3. Field test data from two LCACs, follow-up testing and implementation

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